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Satellite Services system 

Servicing Equipment Catalog 

New Initiatives Office 

Advanced Projects Definition Office 



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NASA 

National Aeronautics and 
Space Administration 

Lyndon B.Johnson Space Center 

Houston, Texas 



Z 3 

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JSC-22796 

PREFACE 

The purpose of this document is to identify existing and planned equipment 
items that could be used for on-orbit satellite servicing. 

The Servicing Equipment Catalog was composed and complied by the JSC 
Satellite Services System Working Group which consisted of NASA, DOD, 
Industry, and International participants. Special thanks are given to the 
following individuals from Lockheed Engineering and Management Services 
Company, Inc., and Omni pi an Corporation. 

LEMSCO Herbert G. Patterson 

Lisa B. Sloan 
Lana R. Arnold 

Omniplan David A. Krenek 

Sally L. Harrison 

Information contained herein should not be construed as being official NASA 
Policy, nor does it represent any commitment or obligation on the part of 
NASA. 

This document was funded by the NASA Headquarters Office of Space Flight 
(OSF) Satellite Servicing Branch, Code MD. 






L-L- fcfc 



Gordon Rysavy, Chairman 

Satellite Services System Working Group 

NASA/JSC 

Code IB 



Approved by: 

William Milligan, Jr. fl 

Manager, Advanced Projects Definition Office 

NASA/JSC 

Code IB 



111 , * 






TABLE OF CONTENTS 



Equipment Title 



Adaptive Payload Carrier 

Aft Flight Deck 

Airlock 

Antenna Bridge Structure 

Apogee Kick Motor Capture 

Device 
Automatic Umbilical 

Connector 
Auxiliary Grapple Fixture 
Bridge Payload Carrier 
Cargo Bay Envelope 
Closed Circuit Television 
Command and Monitor Panel 
Containerless Support 

Assembly 
Delta Keel "Payload Carrier 
Developemental Flight 

Instrumentation Carrier 
Electrical Connectors, G&H 

Family of Connectors 
Electrical Connectors, G&H 

Model 882 Family 
EMU Helmet Mounted Display 
Explorer Platform 
Extravehicular Mobility Unit 
Flight Support System 
Flight Support System Latch 
Flight Support System/ 

Servicing Aid Tool 
Fluid Connector, EVA 
Getaway Special Beam 
Handrail, EVA 
Hydrazine Detector 
Increased Capability 

Adaptive Payload Carrier 
Inerti al Upper Stage Air- 
borne Support Equipment 
Jettison Handle 
Jumper Cable 



STS Flight 
Qualified 



All 
Flights 



X 
X 



Specific 
Flights 



X 
X 



X 
X 



X 
X 
X 



X 
X 



X 
X 
X 
X 



X 
X 
X 



Prototype 



Concept 



Page 



11 
13 
15 
17 
19 
21 

23 
25 

27 

29 

31 
33 
35 
37 
39 
41 

43 
45 
47 
49 
51 

53 

55 
57 
59 



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TABLE OF CONTENTS 





STS Flight 








Equipment Title 


Qualified 
















All 
Flights 


Specific 
Flights 


Prototype 


Concept 


Page 


Laser Docking System 






X 




61 


Lightweight Grapple Fixture 




X 






63 


Lightweight Module Servicing 












Tool 






X 




65 


Linear Remotely Operated 












Electrical Umbilical 








X 


67 


Linear Remotely Operated 












Electrical/Fluid Umbilical 








X 


69 


Longeron and Keel Latches 




X 






71 


Magnetic End Effector 






X 




73 


Manipulator Foot Restraint 




X 






75 


Manned Maneuvering Unit 




X 






77 


Middeck 


X 








79 


Mission Peculiar Equipment 












Support Structure 




X 






81 


Modular Power Subsystem 




X 






83 


Module Servicing Tool 




X 






85 


Orbital Maneuvering Vehicle 








X 


87 


Orbital Spacecraft Consum- 












ables Resupply System 








X 


89 


Orb iter Cargo Bay Floodlight 












System 


X 








93 


Payload Active Cooling/- 












Heating System 








X 


95 


Payload Bay Standard Active 












Cooling Kit 




X 






97 


Payload Berthing System 








X 


99 


Payload Interface Mechanism 




X 






101 


Payload Retention Systems 


X 








103 


Portable Electron Beam 












Welder 






X 




105 


Portable EVA Light 




X 






107 


Portable Foot Restraint 




X 






109 


Portable Foot Restraint 












Socket 




X 






111 


PFR Socket (HST) 




X 






113 


Power Package, EVA 




X 






115 


Power Ratchet Tool 






X 




117 



VI 



TABLE OF CONTENTS 



Equipment Title 



Remote Electrical Umbilical 

Remote Manipulator System 

Remote Manipulator System 
Module Servicing Tool 

Remotely Operated Electrical 
Umbilical 

Retractable Tether 

RMS-Based Handling and 
Positioning Aid 

Robocon 

Rotary Shut-Off Fluid 
Connector 

Safety Tether, 35-Foot 

SAMSIN Master-Slave Servo 
Manipulator 

Satellite Checkout Equipment 

Satellite Workshop 

Softride Container 

Spacelab Pallet 

Spin-Nut Hold Down Mechanism 

Spin Table 

Stabilized Payload Deploy- 
ment System 

Standard End Effector 

Standard Umbilical Retrac- 
tion-Retention System 

Standard Umbilical Retrac- 
tion Vent System 

Strap-On Attitude Control 
System 

Sun Shield 

Trunnion Pin Attachment 
Device 

Universal Service Tool 

Video Tape Recorder 

Waist Tether 

Zero Prebreathe EMU 

Appendix A Acronym List 



STS Flight 
Qualified 








All 
Flights 


Specific 
Flights 


Prototype 


Concept 


Page 


X 


X 


X 




119 
121 

123 


X 


X 


X 
X 

X 




125 
127 

129 
131 

133 
135 




X 
X 


X 
X 


X 
X 
X 


137 
139 
141 
143 
145 
147 
149 


X 


X 


X 




151 
153 

155 




X 




X 


157 
159 




X 






161 


X 


X 
X 


X 
X 




163 
165 
167 
169 
171 

173 



VII 



Adaptive Payload Carrier 




OVERVIEW 

The Adaptive Payload Carrier (APC) was originally designed to mount a 
Standard Interface Panel (SIP), the APC evolved into a carrier for 
lightweight payloads that can be mounted in available locations along the 
sides of the payload bay. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

Mounts in 23 positions on each side of the payload bay. Unique port and 
starboard APC's, which excludes bay 1 and aft section of bay 2. 

300 pound load carrying capability, at J> inch offset, evenly distributed. 



STATUS 

Successfully flown on a number of STS missions, 
fabricated. (8 port, 8 starboard). 



16 APC's have been 



CONTACTS 

Source: Rockwell International, 12214 Lakewood Blvd., Downey, CA 90241 
Operational: C. W. Anderson, (213)922-5095 
R. L. Gasteiger, (213)922-5339 



ADAPTIVE PAYLOAD CARRIER 



Technical Information 


Weight 


26 lbs. 


Power Req 


N/A 


Temp Range 


N/A 


Cooling 


N/A 


Material 


Aluminum 


Status 


Flight qualified 



Interface Details 


Electrical 


N/A 


Mechanical 


Attaches to Orbiter main 
frame, stub frame, and 
longeron sill 


Data Rate 


N/A 


Documentation 


Design Requirements Document 
STS 81-0302 




Possible Coolant Pump and Cold Plate 
Installation on APC or ICAPC 




Aft Flight Deck 








S83-37177 



OVERVIEW 



The Aft Flight Deck (AFD) is the station in the rear of the Orbiter crew 
compartment from which all pay load-related activities are controlled. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

Payload display and control panels and equipment are installed in Orbiter- 
provided removable consoles at the mission station (left) and payload 
station (right). Panel area for payload display and control is provided 
near the windows at the on-orbit station (center). Accommodations to 
install and remove panels in the consoles and in the panel areas are 
provided as required. 

STATUS 

The Aft Flight Deck is an integral part of the Shuttle Orbiter. 

CONTACTS 

Source: Rockwell International, 12214 Lakewood Blvd., Downey CA 90241 
Operational: Ronald Zaguli, NASA/JSC/DF, (713)483-0887 



REFERENCES 

Shuttle Orbiter/Cargo Standard Interfaces. ICD2-1900. 



AFT FLIGHT DECK 



Mission 
Station 



Locker assembly 
survival kit 



RMS Rotational 
hand controller 

Panel A8/A1 




Temporary 
stowage bag 



Location 

decal kit 

RMS translational 
hand controller 

Standard switch/ 
deployment pointing 
panel kit 



Payload 
Station 

AFD Removable container 
Access panel 



Locker assembly 
70/35mm camera 



7047.ART;1 



Airlock 




Airlock (Exterior View) 




Airlock Inside 
Crew Model 




Airlock in 
Payload Bay 



OVERVIEW 

The primary purpose of the Airlock is to eliminate the need for cabin 
decompression for extravehicular activity and to provide a means for 
transferring between the crew module and the Space lab or Payload Bay. It 
may also be used to provide additional volume in the Orbiter Cabin. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

In addition to being a compartment which can be depressurized and 
repressurized to accommodate EVA access to the payload bay, the airlock 
supports EVA preparation and post EVA activities by providing: 

• Handholds and restraints for crewmember translation and position 
maintenance in zero '6'. 

• Interfaces between the EVA Life Support Systems and the Orbiter 
Environmental Control and Life Support Systems, and, 

• Displays and controls to control all Airlock functions. 



STATUS 



Flight Qualified. 



AIRLOCK 



Technical Information 


Inside Diameter 


63 in . 


Length 


83 in. 


Two D-Shaped Hatches 


40 in. in diameter each 


Corded side of Hatches 


36 in. 



Light 




Foot restraint - airlock in-cabin 
configuration (relocatable for 
airlock out of cabin configuration) 



Handhold 



Airlock D&C panel — j£~i 

Handhold - airlock ^> - 
in-cabin configuration 
(relocatable for 
airlock out of cabin 
configuration) 

Airlock (Interior View) 



Handhold 



Light 
Air recirculation duct 



Antenna Bridge Structure 




S84-39126 



OVERVIEW 

The Antenna Bridge Structure (ABS) was designed to create a framework which 
distributes remote manipulator system (RMS)-induced forces on a Hughes 
satellite (HS376). The structure with brackets is approximately 100 inches 
by 32 inches by 28 inches. The surface of the structure is coated with 
Chemglaze A276 white paint. It has an RMS grapple fixture and EVA 
handholds. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The ABS was used on the HS376 retrieval mission. It was designed to be 
connected to a common bracket and a bumper bracket, which are attached to 
the satellite first. Velcro holds the ABS in position while connecting it 
to the brackets. After the ABS is secured, the RMS can maneuver the 
satellite. The ABS is a payload-unique device and is not normally 
manifested. It has mounting locations for the antenna cutter and a cut 
omnidirectional antenna. 



STATUS 



Flight qualified. Flown on specific STS flights. 



CONTACTS 

Source: R. C. Trevino, NASA/DG4, (713)483-2597 
Operational: C. S. Anton, NASA/EC2, (713)483-9152 



ANTENNA BRIDGE STRUCTURE 



Technical Information 


Part Numbers 


SEO 39117098 


Weight 


116.5 lb 


Material/ 
Construction 


Aluminum, Chemglaze A276 white paint, 
EVA handholds, RMS grapple fixture 


Temperature Range 


-130" to 150° F 



Dimensional Data 


A 


97 in. 


B 


26.5 in. 


C 


36 in. 





Apogee Kick Motor Capture Device 




S84-42909 
OVERVIEW 

The Apogee Kick Motor Capture Device (ACD) is a mechanical interface between 
the Manned Maneuvering Unit (MMU) and the Apogee Kick Motor (AKM) of a 
Hughes HS 376 satellite. The ACD includes a grapple fixture for use with 
the Remote Manipulator System (RMS). Two pip pins attach the ACD to the 
arms of the ACD to the satellite. 



OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The ACD must first be attached to the MMU before the MMU can position the 
ACD for capture of the satellite. The MMU is used to insert the toggle 
assembly at the tip of the ACD into the AKM of the satellite. Lines marked 
on the ACD indicate depth of insertion. Spring-loaded toggle fingers are 
then released inside the AKM to secure the satellite. 

The RMS attaches to the grapple fixture on the ACD and holds the satellite 
while an Antenna Bridge Structure (ABS) is attached to it. The ACD and MMU 
are then used to hold the satellite while the RMS moves to the grapple 
fixture of the ABS. The ACD is then released from the satellite and 
restowed, using the MMU. 

STATUS 

Flight qualified. Flown on specific STS flights. 

CONTACTS 

Source: R. C. Trevino, NASA/DG4, (713)483-2597 
Operational: C. E. Whitsett, NASA/EC5, (713)483-9111 



APOGEE KICK MOTOR CAPTURE DEVICE 



Part Numbers 



Weight 



Material 



Major Components 



Design Tempera- 
ture Range 



Quantity Flown 



Stowage 



Technical Information 



SEO 39117132 



128 lb 



Stainless steel, aluminum alloy 



Toggle assembly, control box and 
retractor, separation ring struts and 
structure, RMS grapple fixture (trunnion 
pin attachment device unit) 



-130° to 150* F 



Two for STS-51A 



Spacelab pallet 



Dimensional Data 


A 


14.25 in. 


B 


23.89 in. 


C 


11.5 in. 





27 in. 


E 


44. 18 in . 


F 


0.50 in. 


G 


6.0 in. 


H 


41.04 




G 




H- 



10 



Automatic Umbilical Connector 




OVERVIEW 

The Moog Automatic Umbilical Connector (AUC), Model 50E559, is a self- 
contained, fully automatic system capable of making multi-line umbilical 
connections for spacecraft consumable resupply. The AUC requires only 
electrical power and input control commands for engage and disengage ' . 
operations. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The electromechanical actuator is a leadscrew/cam mechanism driven by a 200V 
line-to-line, 3-phase, 400 Hz electric gear motor. Two Moog rotary shut off 
disconnects are rigidly attached to the mounting plate. Both disconnects 
are protected by a rotary circular cover to seal them against contamination 
when disengaged. 



STATUS 

The prototype AUC has been built and tested. 

CONTACTS 

Source: MOOG Space Products Divison 

East Aurora, NY 14052 
Operational: Joseph M. Cardin, MOOG, (716)667-4417 



11 



AUTOMATIC UMBILICAL CONNECTOR 



Spec if ications 



Flow Capacity analogous to 0.50 inch tubing 



Three seals against external leakage when connected 



One seal against external leakage when disconnected 



Seal verification and purge ports 



Plug compatible with like units 



Cycl e Life 



Wetted Materials 



Compatib 1 1 1 ty 



Misalignment Envelope 



1,000 connects/ 
disconnects minimum 



CRES, Teflon, EPR 



H2O. GN2 . Hydraz'ne 



Pitch & Yaw ± 5.0° 
Roll ± 1.0° 
X + 0. 125 in. 
Y, Z ± 0. 125 in. 




12 



Auxiliary Grapple Fixture 




Standard 
EVA release 
mechanism 



$ 

^ 



I 



Grapple fixture adaptor plate (payload mounted) 



-Grapple fixture 
latch (ref. 3) 



Front elevation 



Side elevation 



NASA ICD 

standard 

10" PCD 

6 bolt mounting 




Latching receptacle 
{6 position 
grapple fixture 
interface option} 



Roll load pin 
location 
(6 position 
grapple fixture 
interface option) 



OVERVIEW 

The Auxilliary Grapple Fixture (AGF) offers a means to attach a Grapple Fixture 
to a payload on-orbit and thereby permit the Shuttle Remote Manipulator System 
to handle the payload. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

To provide the means to attach the AGF on-orbit a small, low weight adapter 
plate is installed onto the payload prior to flight via the standard grapple 
fixture bolted interface. On-orbit EVA attachment of an AGF is achieved by 
rotating three cams on the rear face of the AGF which engage with cut-outs on 
the adapter plate. 

The cams are rotated into the locked position by rotating the End Effector 
location cams on the front face of the grapple fixture. The adapter plate has 
six cut-outs for cam engagement which allow the AGF to be attached in any of 
six angular orientations. 

The AGF is manufactured using the same lightweight construction approch used 
for the Lightweight Grapple Fixture. The adapter plate permanently attached to 
the payload provides an extremly small weight and envelope penalty to a payload 
which may require a Grapple Fixture for contingency operations. 

EVA release has been designed as a standard feature and an electrical interface 
option between the AGF and the End Effector may be accommodated. 



STATUS 

Conceptual design, patent applied for. 
consideration for future use by NSTS. 



Under development and a possible 



CONTACTS 

Source: Spar Aerospace Limited, 1700 Ormont Dr. 
Operational: B. Hill Spar/(416)745-9680 



Weston, Ontario Canada MGL-2W7 



13 



(THIS PAGE INTENTIONALLY LEFT BlANK) 



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Bridge Payload Carrier 




A870625-A-2C 
OVERVIEW 

The Bridge Payload Carrier (BPC), commonly known as the GAS bridge, was 
originally designed to carry multiple Getaway Special (GAS) canisters. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

Mounts in bays 2 through 8, unique BPC for 14 locations (7 port and 7 
starboard). 

800 pound load carrying capability 

STATUS 

Successfully flown on most STS missions. 

Units fabricated 10 - (5 Port, 5 Starboard) 

10 - for Starboard, bays 2, 3 & 4 only 
1 - Bay 12, starboard (special build) 

CONTACTS 

Source: Rockwell International, 12214 Lakewood Blvd., Downey, CA 90241 
Operational: C. W. Anderson, (213)922-5095 
R. L. Gasteiger, (213)922-5339 



**aUdL 



PRECEDING PAGE BLANK NOT F1LM1D 



BRIDGE PAYLOAD CARRIER 



Technical Information 




Weight 


155 lbs. 


Power Req 


N/A 




Temp Range 


N/A 


Cool ing 


N/A 


Material 


Aluminum and Inconel 


Status 


Fl ight qual if ied 


' 



Interface Details 


Electrical 


N/A 


Mechanical 


Attaches to two main 
frames and longeron sill 
See ICD - 2 - 19001 and 
ICD - A - 14021 


Data Rate 


N/A 


Documentation 


Design Requirements 
Document STS79-0695A 




Inconnell steel slider blocks and 
rear faceplate for load resistance 

Aluminum body and front faceplate 
for lighter weight (right- and left-hand) 

Three end fittings for versatility fits in 
orbiter bays 2 through 8 (right and 
left-hand) 



• Payload mounts directly to front faceplate 

or 

• Mounts to assembly mounting frame 




Payload bay locations 



16 



Cargo Bay Envelope 



.7 -. 









ORIGINAL PAGE Iff 
OF POOR QUALITY 




I S83-35804 



OVERVIEW 



The Cargo Bay of the Space Shuttle Orbiter consists of an envelope which is 
15 ft. in diameter and 60 ft. in length; it is designed to accommodate a 
variety of different payloads. Because it houses the payloads, it is also 
called the Payload Bay. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The Cargo Bay envelope is the designated volume within which all payloads, 
payload protrusions, and payload deflections must be contained. Payloads or 
payload protrusions outside of this volume may interfere with Cargo Bay door 
operation and Cargo Bay vision requirements. The Cargo Bay payload attach 
points are outside of the envelope and payload attach fittings may .extend 
outward to reach these points. Umbilicals required to interface the payload 
with the Orbiter may also penetrate the envelope. The user must make 
allowances for, and surrender volume to, Orbiter-related hardware which 
protrudes into the envelope. A minimum clearance of 3 in. is required 
between cargo elements and the Orbiter-related hardware. 



STATUS 

The Cargo Bay is an integral part of the Shuttle Orbiter. 



CONTACTS 

Source: Rockwell International, 12214 Lakewood Blvd., Downey, CA 90241 
Operational: Robert Adams, NASA/JSC/DF, (713)483-2567 



REFERENCES 

Level II Program Definition and Requirements, Vol. 14, Space Shuttle System 
Payload Accommodations, Rev. G, Attachment 1. JSC-07700, ICD-2-19001, 
May 1983. 



17 



CARGO BAY ENVELOPE 



Specifications 


Length 


60 ft. 


Diameter 


15 ft. 


Volume 


-10.600 ft 3 



X 1302 



Center line 
of cargo bay 



Z 400 




Z = 



Cargo bay doors 



18 



Closed Circuit Television 



OVERVIEW 

The Closed Circuit Television (CCTV) 
system is used primarily to support on- 
orbit activities which require visual 
feedback to the crew. The CCTV system 
also provides the capability to document 
on-orbit activities and configurations 
for permanent record or for real-time 
transmission to the ground. The CCTV 
system can be controlled both onboard 
and remotely by uplink commands. 

OPERATIONAL COMMENTS AND 
INTERFACE PROVISIONS 

The CCTV system is a standard monochrome 
(black and white) system which utilizes 
a color filter wheel to provide color 
capability. Color scenes are not 
available on the onboard monitoring 
because of hardware restrictions; they 
are available, however, on recorded and 
downlinked video. 




S82-27664 



Video inputs to the CCTV system are 

available from Cargo Bay bulkhead and 

keel cameras, Remote Manipulator System cameras, pallet-mounted cameras, and 

crew cabin cameras. Video outputs can be assigned to onboard TV monitors, 

to the onboard video tape recorder, or to any payloads with TV capability; 

output can also be downlinked to the ground. 

The CCTV system is typically used to monitor and record mission activities 
such as Cargo Bay door operations, Remote Manipulator System camera output, 
experiment operations, rendezvous and stationkeeping operations, and onboard 
crew activities. Inspection of the Orbiter Cargo Bay and the Orbiter 
exterior, along with inspection of other on-orbit vehicles, constitutes 
another important use of the CCTV system. 

The CCTV system consists of the following major components: 

(1) Video control unit - An interleave capability exists with audio 
channels A and B; multiplex capability is available for split screen. 
Remote command control of the camera lens and the pan/tilt functions, 
by both the crewman and the ground, is available. Eleven video inputs 
and five outputs are available for independent selection. 

(2) Television cameras - A choice of lens assembly provides selection of 
either color or black and white. The Cargo Bay camera pan and tilt 
capability is ±170° at the rate of 1.2°/sec or 12°/sec. Zoom 
capability is either 30° to 80°, horizontal field of view, or 

6.5° to 39°. 



19 



CLOSEO CIRCUIT TELEVISION 

(3) Video Tape Recorder - Record capability is 30 min (increased to 12 min 
on later missions); monochrome or National Television Standards 
Committee (NTSC) color is available. 

(4) Television monitors - Two black-and-white 8-in. -diagonal displays are 
provided. 

STATUS 

Flight qualified. Flown on specific STS flights. 

CONTACTS 

Source: RCA, NASA/JSC 

Operational: David R. Brooks, NASA/JSC/DF, (713)483-2565 

REFERENCES 

Close Circuit Television 



20 



ORIGINAL PAOE; IS 
OF POOR QUALrTY 



Command and Monitor Panel 




OVERVIEW 

The Command and Monitor Panel was designed to provide a man/machine 
interface to monitor and control payloads from the aft flight deck of the 
Orbiter. However, it could also be used as a standard monitor and control 
device for satellites while they are being serviced by the Orbiter. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The Command and Monitor Panel consists of a computer, CRT display, two 
joysticks, keyboard, hardline toggle switches, and interface connections. 
Functional capabilities include monitoring, command, control, telemetry 
link, and other satellite-unique features as required. It is equipped with 
a Command and Telemetry Interface Unit which can input/output a variety of 
both analog and digital data. 

STATUS 

The Command and Monitor Panel was developed by the Lockheed Missiles and 
Space Company (LMSC). A flight-qualified version has flown on the Shuttle. 



CONTACTS 

Source: LMSC, 1111 Lockheed Way, Sunnyvale, CA 
Operational: LMSC, Jack Wohl, (408)743-1690 



94089-3504 



21 



COMMAND AND MONITOR PANEL 



Technical Information 


We ight 


70 lb 


Power Req. 


180 Watts 


Temperature 
Range 


+30" to +125' C 


Cool ing 


Orbiter air duct 
fitting 


Material 


Structure -aluminum 


Status 


Fl ight qual if ied 



Interface Details 


Electrical 


Standard mixed 
cargo Harness 


Mechanical 


Uses 1/2 Orbiter 
payload console 


Data Rate 


Multiple formats 
256 kbps 


Documentation 


Interface control 
document Available 



Dimensional Data 


A 


10 in. 


B 


19 in. 


C 


16 in. 


D 


5.4 m. 


E 


7.2 in. 



■B- 




22 



Containerless Support Assembly 



V51 4-340300 




Z 388.15 



OVERVIEW 

The Containerless Support Assembly (CSA) is designed to carry the cargo bay 
storage assembly used for storage in the payload bay. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

CSA for bay 1 port or starboard. 

400 lb. load carrying capability at 11 inch offset. 

CSA for bay 2 through 6 (port and starboard assemblies) 

400 lb. load carrying capability at 11 inch offset. 

STATUS 

Flown on a number of STS missions 

Four (4) units fabricated for Bay 1 

Four (4) units (2 Port, 2 Starboard) fabricated for Bays 2-6 

CONTACTS 

Source: Rockwell International, 12214 Lakewood Blvd., Downey, CA 90241 
Operational: C. W. Anderson, RI, (213)922-5095 
R. L. Gasteiger, RI, (213)922-5339 



23 



CONTAINERLESS SUPPORT ASSEMBLY 



Technical Information 


Weight 


CSA (bay 1) 45 lbs, CSA (bay 2-6) 


75 lbs. 


Power Req 


N/A 


Temp Range 


N/A 


Cooling 


N/A 


Material 


Aluminum 


Status 


Flight qualified 



Interface Details 


Electrical 


N/A 


Mechanical 


Attaches to two orbiter main frames and 
longeron sill 


Data Rate 


N/A 



"Boss" area on 
multiple bay 
beam design 



Boss area on 
single bay 
beam design ■ 



Beam to mid body 
sill longeron bay 2 
attachment location 



Midbody 
main frame 




Midbody sill longeron 
(Z 410) 



Beam bays 
2 through 6 



Midbody 
main frame 



Payload liner 

attachment 

retainer 



Longeron 

attachment 

bolt 



y— Slider block 

*- ^^^^T\^~" Midbody main frame 

\t Vx attachment bolt 

>- Payload liner 
attachment retainer 



24 



Delta Keel Payload Carrier 




OVERVIEW 

The Delta Keel Payload Carrier (DKPC) was conceived to "Fill the Gap" in the 
Orb iter payload carrying capability wh en th e side loaded pay loads (i.e., 
Adaptive Payload Carrier - APC, Bridge Payload Carrier - BPC, or the 
Extended APC - EAPC) are installed, leaving the center part of the cargo bay 
open for payload use. 



OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

• Attaches to Keel Bridge Locations & Orbiter Scar Attach Points 

• Uses Orbiter Keel Bridge Attach Hardware 

• Single Design Fits All Bays 

• Isogrid Structure Provides Many Potential Payload Attach Points 

STATUS 

Concept 

CONTACTS 

Source: STS Users Center, Rockwell International, Space Business, 

12214 Lakewood Boulevard, Downey, CA 90241, (213)922-3344 
Operational: R. L. Gasteiger, (213)922-5339 



25 



DELTA KEEL PAYLOAD CARRIER 



Technical Information 
Design Goal 


Weight 


<150 lbs. 


Load Design 


2000 lbs. 


Size 


24" % 40" 


Load Carrying 
Capability by Bay 

Bay 1 

Bay 2 

Bays 3 & 4 

Bays 5.6,7 & 12 

Bays 8.9.10 & 11 


250 lbs. 
550 lbs. 
1000 lbs. 
1500 lbs 
2000 lbs. 




26 



Developmental Flight Instrumentation Carrier 




OVERVIEW 



S80-42417 



The Developmental Flight Instrumentation (DFI) Carrier is a reusable 
equipment support structure which can be mounted in any one of several 
places within the Orbiter Cargo Bay. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The DFI Carrier structure is T-shaped, with trunnions at the ends of the 
upper structure and a keel fitting at the lower end. Payload elements are 
attached to the structure by means of several clevis-type fittings arrayed 
to carry components along the front and rear faces of the carrier. In 
addition, a shelf is fitted to the top surface to accommodate additional 
elements. The passive trunnion and keel fittings are unique to the carrier 
structure. 



STATUS 

Four developmental units were flight qualified through STS-8. 



CONTACTS 

Source: Rockwell International 

Operational: Larry P. Ratcliff, JSC/ES6, (713)483-8943 



REFERENCES 

DFI Container Tech Order. M 072-340034. 



21 



DEVELOPMENTAL FLIGHT INSTRUMENTATION CARRIER 



Technical Information 


Dimensions 


See drawing 


Weight 


1.700 lb 

Maximum attachable weight: 6.000 lb 



Measurements in inches 




12.0 



28 



Electrical Connectors, G&H Family of Connectors 



Large 





Small 
Medium 



ffc# 





G&H Model 870 Cryogenic Electrical Family 




Positive Mate Monitor Family of Connectors 



ltf*M 





• 



«9 




Breech-Lok® MIL-C-38999 Family of Connectors 

29 



Electrical Connectors, G&H Family of Connectors 




Breech-Lok® MIL-CX-38999 with Fiber Optic Termini 



OVERVIEW 



The above G&H family of electrical connectors are available either as a 
complete family or as components of any given family. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

G&H family of connectors provides for various interconnect functions such as: 

1. Electrical circuits (contact size) 

(a) 22 gage, 20 gage, 16 gage, 8 gage, RG 122/U, RG 142, RG 393, as well 
as Size 8 coax, triax and data bus contacts. Litz Power Cable 
contacts are also included. 

2. Fiber Optic 

(a) Equivalent contact sizes are 16 gage-Fiber Size 125-625 micron 

STATUS 

Many of the G&H Family of Connectors have been designed to NASA specifications 
and have flown on various space vehicles. 



CONTACTS 

Source: G&H Technology, Inc., 1649 17th Street, Santa Monica, CA 90404 
Operational: Earl Cooper, G&H, (213)450-0561 



30 



Electrical Connectors, G&H Model 882 Family 




OVERVIEW 

The G&H Model 882 Family of Electrical Connectors are designed to be used by 
astronauts in EVA, in a shirt sleeve environment and eventually by remote 
manipulators. Therefore, these connectors are designed for operational 
ease. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The design characteristics of the Model 882 Family of Connectors consist of 
the following elements: 

(1) Self Aligning 

Engage without visual aid. Referred to as Blind Mate Capability. 

(2) Scoop Proof 

The Circuit components (Electrical contacts, valves, etc.) must be 
protected from damage during the self aligning (Blind mate) portion of 
the connector engagement sequence. 

(3) Low Force 

The force required to complete the connector engagement and 
disengagement sequence must be as low as possible. 

(4) Full Connector Engagement Position Maintenance 

Maintained by means of a self locking, easy to release self contained 
mechanism. 



31 



ELECTRICAL CONNECTORS, G&H MODEL 882 FAMILY 

(5) Antibind Rolloff 

Prevents connector plug shell to receptacle shell binding when the 
connector is subjected to side or moment loading during the engage or 
disengage motion. 

(6) Full Mate Feedback 

Electrical or mechanical indication that the connector is fully mated. 

STATUS 

Flight qualified. A Model 882 connector was returned to earth from the 

Solar Max Recovery Mission. 

CONTACTS 

Source: G&H Technology, Inc., 1649 17th Street, Santa Monica, CA 90404 

Operational: Earl Cooper, G&H, (213)450-0561 



Specifications 



Blind Mate-Self Aligning 



EMI/EMP Protection 



Low Outgassing 



Insulation Resistance 



Dielectric Withstanding 
Voltage 



Vibration 



Physical Shock 



Temperature Range 



Thermal Shock 



Salt Spray 



Moisture Resistance 



Durabil ity 




Engagement accomplished with angular misalignment 

of up to ±10° and lateral misalignment of up to +12". 



Better than 60db attenuation from 15KHz to 1,000MHz and 
decreasing linearly from 1,000MHz to 40db @ 10GHz. 



Less than 1% TML and <0.U CVCM. 



1,000 Megohms contact to contact or contact to shell . 



1.500 VOC contact to contact or contact to shell 



20G's from 10HZ to 2Khz. 



Per MIL-STD-202, method 213, condition G 



-55°F to +250°F operating range. 



Per MI1-ST0-202, method 102, condition C. 



Per MI1-STD-202. method 101, condition B. 



Per MI1-ST0-202. method 106. 



250 mate and unmate cycles. 



-7.10- 
-2.90- 



4V 




32 



ORIGINAL PAGE 
BLACK AND WHITE PHOTOGRAPH 



EMU Helmet Mounted Display 




OVERVIEW 

The Helmet Mounted Display (HMD) is 
an electro-optical system designed 
to provide text, graphics, and video 
of selected data for viewing within 
the Helmet of an extravehicular 
crewmember. 

OPERATIONAL COMMENTS AND 
INTERFACE PROVISIONS 

HMD imagery is provided on a virtual, 
see-through display located conven- 
iently above the user's horizontal 
line of sight. The HMD is attached 
to the extravehicular mobility unit's 
(EMU) visor assembly located external 
to the pressure Helmet. 

S87-41829 

- The Wright-Patterson HMD demonstrator consists of twin high-resolution 
(525-line), miniature CRTs (1" diameter x 3" length) that project a 
binocular image via an optical train/toroidal combiner to the user 
providing a 24-degree by 45-degree image (1/3 center overlap). The HMD 
may be interfaced to a speech recognizer to provide a totally "hands- 
free" environment. 

- The Hamilton Standard HMD provides a fully-overlapped, binocular image 
from backlit, dense (320 x 220 pixel) transmissive LCDs and a projection 
optics train. The HMD may be interfaced to a speech recognizer to 
provide a totally "hands-free" environment. 

STATUS 

The Wright-Patterson HMD demonstrator was delivered to NASA on May 12, 1987, 
and is currently under evaluation. A Votan 6050 voice recognizer has been 
interfaced with the HMD and an EVA simulation program has been written for 
demonstration purposes. 

The Hamilton Standard HMD demonstrator is scheduled for delivery to NASA in 
May 1988. 



CONTACTS 
Operational: 



Jose A. Marmolejo, NASA/JSC/EC3, (713)483-9233 
Hai Nguyen, NASA/JSC/EC3, (713)483-9240, Crew and 
Thermal Systems Division, Crew System Branch 



33 



EMU HELMET MOUNTED DISPLAY 



Technical Information 
Wright-Patterson HMD 


Part Number 


N/A 


Weight 


<10 lbs. 


Power 


3 Watts/CRT. 
40-Watt Driver 


Status 


Oemonstrator 
Hardware 


Material 


Glass. 

Polycarbonate. 

Aluminum 


Temperature Range 


Room Temperature 


Interface Details 


110 Vac (60 Hz) 
RS-170 Video 
Input 



Technical Information 
Hamilton Standard HMD 


Part Number 


N/A 


Weight 


<10 lbs. 


Power 


TBD 


Material 


Glass, 
Polycarbonate, 

Aluminum 


Temperature Range 


Room Temperature 


Interface Details 


110 Vac (60 Hz) 
RS-170 Video 
Input 



34 



Explorer Platform 




OVERVIEW 

The Explorer Platform (EP) is based on the Multi-mission Modular Spacecraft 
(MMS), which has successfully been implemented on a variety of satellites 
and proven its effectiveness by being repaired on-orbit. EP can support a 
variety of remote-sensing, low earth orbiting missions requiring solar, 
stellar or earth pointing. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The EP presents a standardized telemetry and command interface for 
integration, test and on-orbit operations with the Tracking and Data Relay 
Satellite System (TDRSS), using the Deep Space Network (DSN) as backup. EP 
provides multi-mission versatility by accommodating instrument payload 
replacement and combining the baseline configuration with mission options 
and mission-unique equipment to meet specific user requirements. 

The design goal of EP is to provide an economical space based platform from 
which Explorer class instruments can be remotely exchanged. The MMS 
structure supports the Platform Equipment Deck (PED), which serves as the EP 
interface to the payload. A payload module is mounted on the PED, and 
mission-unique equipment can be placed within removable PED modules. When 
EP is integrated with its payload module, it becomes a mission-unique 
explorer satellite. Instruments and equipment can be exchanged during 
Shuttle-based servicing missions. 

STATUS 

Presently in the technology development stage. 



35 



EXPLORER PLATFORM 



CONTACTS 

Source: Fairchild Space Company 

Operational: Frank J. Cepollina, GSFC, (301)286-1359 



Technical Information 


Mission Requirements Summary 


£P Capabil ities 


Mission Lifetime 


2 yrs. w/o servicing 
10 yrs with servicing 


Orb,: Altitude 


300 to 550 km 


Orbit Inclination 


28.5 degrees 


Telemetry Rates 


32 kbps 

256 kbps direct line 

512 kbps direct line 


Payload Weight 


4000 lbs delta launch 
10000 lbs STS launch 


Payload Power 


300 waits 


ACS Type (Attitude) 


3 axis stabilized 


Maneuvers 


2 deg/sec 


Pointing Knowledge (3o) 


104.5 sec ACS 
CO al ig only 
37.5 sec ACS/INSTR 
CO alig 


Pointing Control (3o) 


105.6 sec ACS 
CO alig only 
40.4 sec ACS/INSTR 
CO alig 



36 



Extravehicular Mobility Unit 



OVERVIEW 

The Extravehicular Mobility Unit (EMU) is an 
independent anthropomorphic system that provides 
crewmembers with environmental protection, life 
support, mobility, communications, and visibility 
while performing various EVA's. The EMU has an 
on-orbit recharge capability and can provide 
multiple EVA periods during a single flight. 



OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

Two EMU's are included in each Orbiter mission 
without a planned EVA. Three EMU's are flown for 
a planned EVA mission. Consumables are provided 
for two two-man, 6-hour EVA's, one of which is for 
payload use (mission success) and the other 
reserved for an unscheduled Orbiter safety- 
critical EVA. For missions with a planned EVA, 
consumables are provided to support all planned 
EVA's and an Orbiter contingency EVA. The EMU 




S82-40857 



primary life support system is designed for 7 hours of independent life 
support, of which only 6 hours are available for nominal EVA's. The EMU 
also has a backup life support system which can provide 30 minutes of oxygen 
under reduced suit pressure. Instrumentation and a microprocessor provide 
the capability to monitor the status of the EMU and expendables and to alert 
the crewmember of any abnormal system function. 

Standard interface attachments are provided for the manned maneuvering unit, 
the mini work station, tool caddies, EMU television system, EMU lights, and 
the wrist and waist tethers. 



STATUS 

Flight qualified. Flown on all STS flights. 



CONTACTS 

Source: Hamilton Standard 

Operational: C. H. Armstrong, NASA/DG4, (713)483-2588 



37 



EXTRAVEHICULAR MOBILITY UNIT 



Technical Information 



Part Number 



Weight 



Wrist Tether Loop 
Breaking Force 



SEO 13101492-307 



257 LB (mm) 300 lb (max) 



30 lb 



Dimensional Data 




95% Male 


5% Female 


A 


28.4 in. 


26.0 in. 


B 


7 in. 


7 in. 


C 


32 in. 


32 in. 


D 


23 in. 


23 in. 


E 


29.4 in. 


- 


F 


75.5 in. 


67.5 in. 






38 



ORIGINAL' PAGE 
BLACK AND WHITE PHOTOGRAPH 



Flight Support System 




OVERVIEW 

The Flight Support System (FSS) is 
a reusable equipment system that 
provides the structural, 
mechanical, thermal, and 
electrical interfaces between 
various spacecraft and the space 
shuttle for LAUNCH, RETRIEVAL, and 
ON-ORBIT servicing missions. The 
FSS was developed as the primary 
interface between the multimission 
modular spacecraft and the Shuttle 
Orbiter for launch, deployment, 
servicing and landing operations. 
The FSS configuration consists of 
three structural cradles, 
mechanisms for spacecraft 
retention and positioning, and S84-30360 

avionics. The configuration for on-orbit servicing consists of one cradle 
with the berthing and positioning system, mechanisms, and avionics. The on- 
orbit servicing configuration in most cass does not include the structural 
capability to support the spacecraft for launch or landing. 



OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The FSS consists of five major hardware elements: 

Cradle A - 16 in. deep cradle with a latch beam which can be used for both 
servicing and deployment missions. 

Cradle B - A 52 In. deep cradle with capability for Shuttle attachment 
through four Longeron trunnions and one keel trunnion. 

Cradle A'- A cradle dimensionally the same as Cradle A with removable 
cradle extenders. 

Berthing and Positioning System (BAPS) - 

A movable platform with spacecraft latches and umbilical 
connectors that provides an on-orbit spacecraft positioning 
capability for apendage extension or retraction, inspection, 
pre-deployment testing, deployment, servicing or retrieval 
berthing. 

Lightweight Cradle - A 16 in. deep cradle^ with two Longeron trunnions and 
one keel trunnion. 

The FSS avionics provide for the electrical operation of the Berthing and 
Positioning System mechanisms and the electrical support services to the FSS 
and spacecraft while on the ground and on-orbit. These services include 



39 



FLIGHT SUPPORT SYSTEM 

operating power, externally applied heater power, and serial commands and 
telemetry relay to the user's Payload Operations Control Center (POCC) via 
Orbiter avionics. Control and monitor of hardline digital and analog 
signals by the Orbiter crew are accommodated at the Aft Flight Deck (AFD) 
using standard Orbiter equipment. These signals can be relayed to the 
user's POCC. These services on the ground are provided by the Ground 
Support Equipment (GSE) via the Orbiter's T-0 umbilical. When the 
FSS/spacecraft is not installed in the Orbiter, the electrical GSE interface 
is accomplished by directly connecting to the Orbiter Standard Interface 
Panel (SIP) connectors. 

STATUS 

Flight Tested. FSS was first used on-orbit during the solar maximum repair 
mission in 1984. 

CONTACTS 

Source: Fairchild Space Company 

Operational: E. Falkenhayn, GSFC/Code 48, Greenbelt, MD 20771 (301)286-4144 



Technical Information 



Power 



Provides 28 volts D.C. 
115 volts 400 Hertz (Hz) 



Umbilical 
connector (2) 

Berthing platform 

Positioning platform 
retention latch 

S/C retention 
latch (3) 



Latch beam 



Pivoting 
mechanism 



Berthing latch (3) 



Adapter (2) 
1 Extender 




Longeron 
trunnions (4) 



Cradle A 



Keel Trunnion 



40 



Flight Support System Latch 




OVERVIEW 

Designed as a part of the Flight Support System (FSS) to provide latching of 
payload to the FSS. Subsequently, the latch has been incorporated on a 
number of payloads as a standard berthing/docking latch. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

Design for berthing pin diameter of 1.5 in., the latch accommodates 
misalignments of ±2.0 and ±1.0° half cone angle. 

Latch has redundancy from motor up to drive shaft with EVA backup 
capability. 



STATUS 

Successfully flown on a number of missions including Solar Max repair. 



CONTACTS 

Source: Rockwell International, 12214 Lakewood Blvd., Downey, CA 90241 
Operational: C. w. Anderson, (213)922-5095 
R. L. Gasteiger, (213)922-5339 



41 



FLIGHT SUPPORT SYSTEM LATCH 



Technical Information 


Weight 


63 lbs. 


Power Req. 


Three phase 115 V, 400 Hz. 


Temp Range 


N/A 


Cool ing 


N/A 


Material 




Status 


Fl ight qual if ied 



Interface Details 


Electrical 


N/A 


Mechanical 




Data Rate 


N/A 


Documentation 





Latch pin 




Latch pin 




Latch pin 
retention jaws 



End-of-travel assy 



Closed 



Open 



42 



Flight Support System/Servicing Aid Tool 



NSTS 

Aft Flight Deck 




RMS 


!-♦" 


j 




ALT '-■* 

Interfaces 


FSS/SAT 






- -^ 


FSS 





OVERVIEW 

The Flight Support System/Servicing Aid Tool is a remotely-operated 
bilateral force-reflecting manipulator system. It will enhance the 
capability of the NSTS Mission Specialists to perform IVA and EVA Free-Flyer 
Spacecraft servicing in the Space Shuttle Cargo Bay from the Aft Flight 
Deck. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The system, which mounts to the FSS by a versatile electro-mechanical 
interface, can be repositioned by use of the remote manipulator system. The 
FSS/SAT will have provision to pickup and restow tools from a tool storage 
locker mounted on the FSS. The FSS/SAT will either be stowed in a storage 
rack or will be secured to the FSS during launch and landing operations. 
The system is designed to operate from the Space Shuttle onboard utilities. 



STATUS 

The development of this system, which may be used during a new SMM Servicing 
Mission and during the Explorer Platform Interchange of Payloads, is in a 
competitive procurement cycle. Phase I calls for a graphics feasibility 
simulation, commercial model demonstration, and prototype model design. 
Phase II calls for production of the system, its flight qualification, 1-g 
ground demonstration in the GSFC Space Shuttle simulator, and delivery 
within a two-year period. 



CONTACTS 

Source: GSFC, Fairchild Space Company, (301)286-2000 
Operational: R. E. Davis, NASA/GSFC SSP/CODE 408.0, (301)286-2260 



43 



FLIGHT SUPPORT SYSTEM/SERVICING AID TOOL 



Technical Information 


Part Number 


TBS 


Weight 


Approx. TBD Ib./Manip. 


Power 


External 28 VDC Shuttle 
power at TBD watts/manip. 


Status 


Phase C/D design and 
hardware development 


Materials 


Structure - aluminum 


Temperature 
Range 


-50 to +100 deg F; 

degr, -100 to +250 deg. F 


Pressure 


Min. 10~ 10 Torr 


Operations 


Intermittant over 4 yrs 
with minor servicing 



Interface Details 


Interface 
Device 


RMS IT-WT FLT releasable 
electrical grapple fixture 
and versatile electro- 
mechanical end-effector 


Precapture 
Misal ignment 
Limits 


RMS: 4" pitch/yaw radius. 
4" axial , +/-15 Deg all AT 
and electro-mech EE: TBD 


Electrical 
Connectors 


RMS 51-contact modified 
connector and TBD for 
FSS/SAT E-M end effector 


Cable Type 


Interconnections via 
existing RMS and FSS wiring 
to AFT f 1 lght deck 


Type OPNS 


Mission specialist contrs 
RMS and FSS/SAT from Aft 
Fit deck controllers/panels 


Contacts 
Assignment 


RMS per JSC ICO 2-06001 and 
FSS/SAT TBD 



44 



ORIGINAL PAGE ' 
3LACK AND WHITE PHOTOGRAPH 



Fluid Connector, EVA 




OVERVIEW 



FCSC 109-3-85-574 



The EVA Fluid Connector is a coupling device designed for transferring 
fluids and low pressure gases. The Fluid Connector has three manual valves 
with positive pressure indicators 1n each coupling and a pressure transducer 
to check valve integrity. Triply redundant interface seals between coupling 
halves have pressure ports to check seal integrity. Interlocks prevent 
valve opening while a coupling is disengaged and prevent coupling 
disengagement with a valve open. . . 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The Fluid Connector is connected by first aligning the tanker coupling 
(male) and the spacecraft coupling (female) halves and then engaging. By 
means of the handle grips, the tank coupling is rotated clockwise 
approximately 40° until the handles are horizontal. The locking pin is then 
rotated clockwise. The seal integrity is checked, and the safety lever is 
pulled forward and down exposing the Tlow control valves. The valves are 
opened in the following order: T-3, 1-2, S-3, S-2, allowing fluid transfer. 
The operations, from rotating the locking pin through opening the valves, 
are clearly numbered 1 through 7 on the face of the tool. These steps are 
reversed (7 to 1) to close the valve and remove the tool. Designed to be 
used to refuel the Gamma Ray Observatory (6R0). 

STATUS 

The EVA Fluid Connector is undergoing flight qualification testing. 

CONTACTS 

Source: Fairchild Control System Company 
Operational: R. C. Trevino, NASA/DL4, (713)483-2597 



45 



FLUID CONNECTOR, EVA 



Technical Information 


Part Number 


Not available 


Weight 


13.0 lb 


Material 


Stainless steel 


Operating 
Pressure 


500 psig nominal, 600 psig maximum 


Operating 
Temperature 


40* F minimum, 70° F nominal, 120" F maximum 


Flow rate 


10 gpm nominal, 20 gpm maximum 



Dimensional Data 


A 


7.82 in. 


B 


2.330 1n. 


C 


3.16 in. 


D 


2.34 in. 


E 


6.82 in. 


F 


1 in. 


G 


1.6 in. 


H 


1.5 in. 


I 


7.5 in. 


J 


3.7 in. 


K 


4.8 in. 




20«6600M. lfl',2 



46 



ORIGINAL" PAGE 
SLACK AND WHITE PHOTOGRAPH 



Getaway Special Beam 










S83-33534 



OVERVIEW 



The Getaway Special Beam (GAS) Beam is a structural frame to which small 
pay loads can be attached. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The GAS Beam, which connects to the longerons on either side of the Cargo 
Bay can be attached at any of 30 sites, and a total of 30 GAS Beams may be 
carried on a Shuttle mission. The GAS Beam does notcontain any interface 
provisions for electrical power, control, or monitoring. 



STATUS 

Flight qualified and has flown on several Shuttle missions. 



CONTACTS 

Source: Rockwell International 
Operational: Bill Ponce, RI, (213)922-4036 



47 



GETAWAY SPECIAL BEAM 



REFERENCES 

Fitting Assembly - Adapter Beam Bridge Getaway Special. 

Drawing no. V724-340001, Rockwell. 

Space Shuttle Interface Control Document. ICD-A-14021, November 1979. 

STS and Getaway Special (GAS) Payload Integration Plan, Rev. B, JSC- 14021, 

March 1983. 



Technical Information 


Beam Length 


52.3 in. 


Beam Width 


6.0 in. 


Beam Height 


22.4 in. 


Maximum weight 


of payload at a 6.0--in. moment arm: 


300 lb 



Payload attach 
points (32) 



Fixed flange 



Payload mounting surface 




Frame flange in 
three lengths, 
depending on 
bay location 



48 



ORIGINAL PAGE 
BLACK AND WHITE PHOTOGRAPH 



Handrail, EVA 




S88-32969 



OVERVIEW 



The EVA HANDRAIL provides a mobility aide for EVA crews during planned work 
in the payload area. The handrail consists of standoffs with integral 
tether attachment points and a standard cross section rail for gloved 
handgrip. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

EVA Handrails are provided on the bulkhead at each end of the payload bay 

and at strategic points along the length of the payload compartment. The 

handrail is designed such that standoffs and the rail can be replaced as 
separate components. 

STATUS 

Design is complete and the handrail system is being used on the Hubble Space 
Telescope EVA tool box. Numerous designs for EVA handrails exist and are in 
varying stages of development. 



CONTACTS 

Source: ILS Space Systems Divison 

Operational: R. Fullerton, NASA/JSC/DF 421, (713)483-2789 



49 



HANDRAIL, EVA 



Material 



Length 



Forces 



Technical Information 



6061 - T6 aluminum tubing (minimum griplength of 
handholds/handrails for EVA) 



5.81 in. { 14.75 cm.) 



187 lb (841. 5N) in any direction (Handrail tube) 

547 lb (2450. 56N) in any direction (Handrail standoff) 



Handholds and handrails shall be fabricated from metals. Other rigid, semirigid, or 
nonmetallic materials also may be used but must not be susceptible to brittle fracture. 



DIMENSIONS (INCHES) 


A 


0.75 ± 0.06 (19mm) 


B 


1.38 t 0.06 (33 mm) 


C 


2,25 (57.2mm) minimum 





5.81 (147.5mm) minimum 


E 


36.0 (914.4mm) maximum 




24.0 (610.0mm) preferred 



& 



i 



T 

A 



2 L 



bk 




□ ( 



50 



ORIGINAL PAGE 
BLACK AND WHITE PHOTOGRAPH 



Hydrazine Detector 




S84-41548 



OVERVIEW 



The hydrazine detector is intended to be only a qualitative sampler of 
hydrazine contamination. The detector kit consists of two parts, the air 
sampler and the detector tube. The air sampler consists of an airlock 
depress valve cap, a tube holder, and coiled Teflon tubing. The detector 
tubes are covered with Teflon shrink tubing and are packaged in standard 
foil -mylar vacuum packaging. 

Detection is based upon the chemical reaction of hydrazine with a 
crystal ine-line mixture of yellow acetic acid and bromophenol blue. 
Reaction occurs as the airlock atmosphere is drawn through the reactants. 
The crystals change color from yellow to blue upon contact with hydrazine. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The system is stowed in the airlock's EVA bag prior to depress and is 
assembled by the EVA crew for use after airlock repress to cabin pressure. 
Operation ind contamination detection involves a 20- to 30-second depress of 
the airlock with visual observation of a color change in the detector. If 
hydrazine is detected, the EVA crew will return to vacuum to sublimate any 
combination. This system is known as the Draeger tube in crew procedures. 



STATUS 



Flight qualified. Flown on specific STS missions. 



CONTACTS 

Source: R. K. Fullerton, NASA/DG4, (713)483-2589 
Operational: R. J. Marak, NASA/EC5, (713)483-9144 



51 



HYDRAZINE DETECTOR 



Technical Information 


Part Numbers 


SED 39116311-301 (air sampler) 
SED 39117159-301 (Draeger tube) 


Weight 


1.3 lb 


Material 


Package - foil-mylar 

Tubing - Teflon 

Tube holder - anodized aluminum 

Valve cap - anodized aluminum 

Draeger tube - glass covered by Teflon 

shrink tubing 


Force/Torque 


Attach cap to depress valve - hand-tight 


Design Tempera- 
ture Range 


50* to 122° F 


Accuracy 


Qualitative only 



t =MHOB- 











■* l_ 




(~ 




\ 


1 


■ 




•^ '• 






1 t 




t , t „. 








) 


■ 



Dimensional Data 


A 


9.75 in. 


B 


1.5 in. 


C 


5.25 in. 


D 


3.125 in. 


E 


6.875 in. 


F 


4.25 in. 




52 



Increased Capability Adaptive Payload Carrier 




OVERVIEW 



The Increased Capability Adaptive Payload Carrier (ICAPC) is design-based 
upon APC. Provides increased weight carrying capability for payload bay 
sidewall mounted payloads. 



OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

Mounts in 23 positions on each side of the payload bay. Unique port and 
starboard ICAPC's, which excludes bay 1 and aft section of bay 2. 

500 lb. load carrying capability. 

STATUS 

Four (4) Port and four (4) Starboard units fabricated. 

CONTACTS 

Source: Rockwell International, 12214 Lakewood Blvd., Downey, CA 90241 
Operational: C. W. Anderson, (213)922-5095 
R. L. Gasteiger, (213)922-5339 



53 



INCREASED CAPABILITY ADAPTIVE PAYLOAD CARRIER 



Technical Information 


Weight 


53 lbs. 


Power Req 


N/A 


Temp Range 


N/A 


Cooling 


N/A 


Material 


Aluminum 


Status 


Flight qualified. 



Interface Details 


Electrical 


N/A 


Mechanical 


Attacnes to crbiter mam frame, 
stub frame, and longeron sill. 


Data Rate 


N/A 


Documentation 


Design Requirements Document 
STS 85-0162 




54 



Inertial Upper Stage Airborne Support Equipment 



Non-deployable latches (6) 



Standard mix cable harness 
(SMCH) panel (both sides) 

Deployable latches (2) 



Longeron 




X =645 
Power panel 



X =576 
Bulkhead 



Keel bridge fitting (1) 
Purge duct 



To umbilical 
(both sides) 

Longeron 

bridge 

fitting 



SMCH (both sides) 



7O05.ART;1 



L-Aft flight deck 



r- Aft frame 



Low response 
mechanism 



Deployable payload 
attachment fitting (2) 

Load leveler 
Forward frame 




OVERVIEW 



Tilt actuator (2) 



Low response 
spreader beam (2) 



Hydraulic 
viscous damper 



The Inertial Upper Stage Airborne Support Equipment (IUS/ASE) is an adjust- 
able platform which provides the proper orientation for IUS stowing and 
deployment. 



55 



INERTIAL UPPER STAGE AIRBORNE SUPPORT EQUIPMENT 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The IUS/ASE consists of two structural frames rigidly mounted in the Orbiter 
Carqo Bay. The aft frame is a structural ring which supports the aft end of 
the IUS and pivots to erect the IUS and spacecraft out of the Cargo Bay for 
deployment. The aft frame is attached to the aft ring of the IUS first- 
stage solid-rocket motor with a spring-loaded separation system. The 
forward frame provides rigid support for the forward ring of the IUS. The 
IUS separates from the forward frame during the aft frame pivot prior to 
deployment. The ASE power subsystem, which is self-contained, provides the 
distribution and switching of power between the IUS/spacecraft combination 
and the Orbiter. The ASE electrical systems are monitored from the Aft 
Flight Deck of the Orbiter by means of a display and control panel. 

STATUS 

The IUS/ASE is flight qualified. Flown on specific STS flights. 

CONTACTS 

Source: Boeing 

Operational: William J. Hungerford, NASA/JSC/IB, (713)282-1960 

REFERENCES 

Inertia! Upper Stage Orbital Operation Handbook. Boeing, D290-10554-1. 
Shuttle Orbiter/Inertial Upper Stage Cargo Element Interfaces. ICD-D-E0001. 



56 



ORIGINAL PAGE 
SLACK AND WHITE PHOTOGRAPH 



Jettison Handle 




Jvl *£ 


J 








3^ 


. 5 


*s% 


* _' -+ 

l 5 jffi 1« 


-Sin 


. fs& S88-32952 



OVERVIEW 

The jettison handle is a contingency tool designed for the space telescope. 
If the space telescope must be returned to the payload bay, all appendages 
must be folded back into their original positions. If, for some reason, an 
appendage is unable to be returned to its original position, either auto- 
matically or manually, the EVA crewmember must then jettison the appendage 
using the jettison handle. The solar arrays and aperture door have a 
mounted socket which mates with the jettison handle. 



OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The jettison handle connects into a socket located on the failed appendage 
near the center of gravity of the appendage and provides a means of holding 
the appendage structure for easy movement away from the space telescope. 



STATUS 

Flight hardware, flight ready and will be manifested on STS-31. 

CONTACTS 

Source: LMSC, HST Contracts Office, (408)742-5505 
Operational: R. C. Trevino, NASA/JSC/DF 42, (713)483-2597 



57 



JETTISON HANDLE 



Technical Information 


Part Number 


4175850 


Weight 


2.95 lb 


Material 


Aluminum alloy 








il 



I 








3EHHE 



Dimensional Data 


A 


0.980 in. 


B 


1.50 in. 


C 


2.250 in. 





12.72 in. 


E 


13.54 in. 


F 


5.65 in. 


G 


6.50 in. 




20466BB8B.AfiT,l 



58 



ORIGINAL FA3E i.n 
Of PCOR QUALITY 



Jumper Cable 




X r-» S84-28131 



OVERVIEW 



The jumper cable is an 11-foot electrical cable with a female electrical 
connector on one end and a male electrical connector on the other. Each end 
has two captive bolts used in mating the jumper cable to the desired 
interface. A tether ring is provided on both sides of the male connector. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The jumper cable was designed to provide an electrical interface during the 
servicing of the Solar Maximum satellite (Solar Max). The jumper cable is 
manually mated to the Solar Max connector. The two bolts on the jumper 
cable connector are tightened by rotating approximately seven full turns 
clockwise with a tool having a 7/16-inch hex socket. This procedure is then 
repeated with the other end of the jumper cable at the Flight Support System 
(FSS) umbilical connector actuator position. 



STATUS 



Flight qualified. Flown on STS-41B. 



CONTACTS 

Source: K. Rosette, NASA/GSFC, (301)344-7201 
Operational: K. A. Havens, NASA/JSC/DF, (713)483-2569 



59 



JUMPER CABLE 



Technical Information 


Part Number 


9390000808 


Weight 


17 lb 


Material 


Cable - black Teflon webbing 

Connector housing - Irradiated aluminum 


Temperature Range 


-94» to +158»F 



Retaining ring 
(typical) 



Length: 11 ft 



Solar Max end 



Captive bolts 




60 



Laser Docking System 



OVERVIEW 



CCTV 

control 

panel 




The Laser Docking System (LDS) consists of passive docking aids (reflectors) 
placed on the target vehicle in a known location and orientation. These 
reflectors are acquired and tracked by means of a modulated laser beam 
located on the interceptor vehicle. The LDS enables the interceptor vehicle 
to analyze the return (reflected) signal in order to determine both relative 
position and relative attitude of the target vehicle during stationkeeping 
and docking. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

Space operations require soft docking and/or maintenance of a fixed relative 
attitude while stationkeeping. In either case, a versatile, lightweight 
stationkeeping and docking system is needed to augment or replace visual 
tracking of the target vehicle. Massive or flexible spacecraft requires 
greater sensor system accuracy to minimize contact forces and moments, 
docking mechanism mass and complexity, vehicle dispersions, and fuel 
expenditures. In addition, a docking/stationkeeping system permits long- 
term stationkeeping to be performed in an automatic mode to relieve the crew 
of the workload and tedium of monitoring relative positions and applying 
corrective maneuvers. Eventually, this system capability will enable 
automatic rendezvous and docking. 

Laser ranging experiments have been accomplished at NASA, and from these 
experiments have evolved laser docking concepts. The concepts include angle 
and attitude measurements which are capable of providing all of the 
information needed for automatic docking control by the interceptor vehicle. 
Several designs are being compared. Plans include the development and 
testing of, first, a breadboard model; then an engineering model; and 
finally, qualification and flight systems. 



61 



LASER DOCKING SYSTEM 



Well in advance of operational stationkeeping and docking, a standard 
configuration for payload-mounted passive tracking aids needs to be 
established. This will enable payloads which are launched in the near 
future to be configured before launch for future on-orbit servicing. The 
LDS will function effectively within a range of approximately 1 km for 
close-range stationkeeping and for docking and tracking. 



STATUS 

The LDS concept described above is currently being evaluated at the Johnson 
Space Center. 



CONTACTS 

Source: NASA/JSC 

Operational: Harry Erwin, NASA/JSC/IC, (713)282-1822 



REFERENCES 

Satellite Services Workshop, Vol. 1, JSC-18201. NASA/JSC, June 1982. 



62 



Light-Weight Grapple Fixture 




OVERVIEW 

The Light-Weight Grapple Fixture (LWGF) provides a low weight, reduced abutment 
plate diameter alternative to the Standard Grapple Fixture. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The LWGF serves the same functional requirements as the Flight Releasable 
Grapple Fixture by providing the mechanical interface between the Shuttle 
Remote Manipulator System End Effector and a payload The LWGF offers the 
added advantage of low weight providing a reduced abutment plate dl f ^ter and 
satisfies all other major Grapple Fixtures characteristics such as load earring 
capability. 

The LWGF is a development from the original Grapple Fixture design and can at 
the completion of formal qualification testing replace the oj"^ 1 ^ 1 /"^ 6 ^ 
design. The design includes EVA release provisions and may be adapted to pro- 
vide electrical interface with the End Effector. 

STATUS 

Hardware built and tested to qualification levels. 

CONTACTS 

Source- Spar Aerospace Limited, 1700 Ormont Dr. Weston, Ontario Canada MGL-2W7 
Operational: B. Hill, Spar, (416)745-9680 



63 



LIGHT-WEIGHT GRAPPLE FIXTURE 



Technical Information 


Weight 


12 lbs. maximum 


Abutment Plate 


14.25 in. diameter 


EVA releasable 


Electrical connector option 



64 



Light-Weight Module Servicing Tool 




OVERVIEW 

The Light-Weight Module Service Tool (LW/MST) is a device to permit remote 
on-orbit exchange of Orbital Replacement Units (ORUs) when coupled to an 
automated servicer system. It is being redesigned for use with the Orbit 
Maneuvering Vehicle, Flight Support System/Servicing Aid Tool, Remote 
Manipulator System, other manipulator and robotic servicers. This tool will 
permit on-orbit exchange of spacecraft modules, payloads, and instrument 
orbital replacement units for the Explorer Platform, Orbit Maneuvering 
Vehicle, Solar Maximum Mission, Upper Atmosphere Research Satellite, and 
other missions. Remote computer or manipulator control is retained to 
permit the servicing operations to be performed from the Shuttle aft flight 
deck. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The LW/MST receives external 28 VDC to power its latch and bolt motors with 
torque selectable up to 220 ft-lbs. Remote control can be performed by 
either manual or automated modes. The current end-effector accommodates the 
integrated orbital servicer system, but special adaptations can be made for 
other requirements. The electrical umbilical accommodates command, 
telemetry, bolt and latch motor functions. 

STATUS 

Electrical and mechanical design modifications for the 1-g engineering model 
light-weight module service tool are underway to permit on-orbit operations. 
A companion holster, for mounting of the tool on the MMS Flight Support 
System or other structural cradles is also undergoing development. 



65 



LIGHT-WEIGHT MODULE SERVICING TOOL 



CONTACTS 

Source: R. E. Davis, NASA/GSFC SSP/Code 408.0, (301)286-2260 
Operational: R. E. Davis, NASA/GSFC SSP/Code 408.0, (301)286-2260 



Technical Information 


Part Number 


TBS 


Weight 


Approx. 30 lbs. 


Power 


External 28 VDC opera- 
tion for motors, TLM, 
and CMO 


Status 


Phase B design with 
phase C/D hardware FO 


Materials 


Structure - aluminum 


Temperature 
Range 


-50 to +100 deg. F; 
degr -100 to +250 deg. F 


Pressure 


Min. 10" 10 Torr 


Operations 


Intermittent over 4 yrs 
with minor servicing 



Interface Details 


Interface 
Device 


Integrated orbital servicer 
system end effector or 
optional RMS Lt-Wt EGF 


Precapture 
Misal ignment 
Limi ts 


TBD" pitch/yaw radius 

0.5" axial 

+/- TBD deg all attitudes 


Electrical 
Connector 


XX-contact modified 
subminiature "D" Connector 


Cable Type 


Interconnections via RMS/ 
manipulator/robotic system 


Type OPNS 


Mission specialist contrs 
RMS and MST from Aft Fit 
deck controllers/panels 


Bolt Torque 


Selectable to MAX 220 Ft-Lbs 



Top cover 

Left side latch motor. 
Leftside plate - 



End effector 
attach fitting - 



Motor mounting plate 



Back plate assy. 

Drive motor/ 
transmission assy. 




Bearing spindle assy. 
Latch 

Bolt drive 



Right side plate 
Bottom plate 



Controller and 
power supply 



\ 



66 



Linear Remotely Operated Electrical Umbilical 




The Linear Remotely Operated Electrical Umbilical (LROEU) is an electrical 
umbilical concept to accommodate pay loads which do not exhibit large 
orbiter/payload misalignments in X and Y . The LROEU incorporates the 
Flight Support System umbilical proven concept and the Remotely Operated 
Electrical Umbilical (ROEU) alignment features. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS ' > 

Compact disconnect system may be mounted in a variety of orbiter locations 
to accommodate payloads with restricted access to umbilical connectors. 
Normal mounting is on Port or Starboard bridge rail. Provides self 
alignment of orbiter/payload portions of disconnect. 



STATUS 



Concept 



CONTACTS 

Source: Rockwell International, 12214 Lakewood Blvd., Downey, CA 
Operational: C. U. Anderson, (213)922-5095 
R. L. Gasteiger, (213)922-5339 



90241 



67 



LROEU - LONGERON MOUNTING 



Technical Information 


Weight 


<25 lbs. 


Power Req 


TBO 


Temp Range 


TBD 


Cooling 


N/A 


Material 


Aluminum 


Status 


Concept 



Interface Details 


Electrical 


28 V dc 


Mechanical 


TBO 


Data Rate 


N/A 


Documentation 


TBD 




68 



Linear Remotely Operated Electrical/Fluid Umbilical 




OVERVIEW 

The Linear Remotely Operated Electrical/Fluid Umbilical (LROEFU) is an 
electrical/fluid umbilical concept to accommodate payloads which do not 
exhibit large orbiter/payload misalignments in Xo and Y . The LROEFU 
incorporates the Flight Support System umbilical proven concept and the 
Remotely Operated Electrical Umbilical (ROEU) alignment features. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

Compact disconnect system may be mounted in a variety of orbiter locations 
to accommodate payloads with restricted access to umbilical connectors. 
Normal mounting is on Port or Starboard bridge rail. Provides self 
alignment of orbiter/payload portions of disconnect. 



STATUS 



Concept 



CONTACTS 

Source: Rockwell International, 12214 Lakewood Blvd., Downey, CA 90241 
Operational: C. W. Anderson, (213)922-5095 
R. L. Gasteiger, (213)922-5339 



69 



LROEFU - LONGERON MOUNTING 



Technical Information 


Weight 


<25 lbs. 


Power Req 


TBO 


Temp Range 


TBD 


Cooling 


N/A 


Material 


Aluminum 


Status 


Concept 


Connector Insert 


Accommodates approx 130 
pins and selection of 
qualified fluid disconnects 
of various sizes. 


Misal ignment 


± 0.5 inches 


Conical Displacement 


5° 


Length of Stroke 


9.15 inches 



Interface Details 


Electrical 


28 V dc 


Mechanical 


TBD 


Data Rate 


N/A 


Documentation 


TBO 



70 



Longeron and Keel Latches 






OVERVIEW 

The longeron and keel latches presented herein have been fabricated and are 
currently in the STS inventory and available to payload users. Character- 
istics and operational data are presented in both summary and unique 
formats. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 
See attached data. 

STATUS 

Each of the latches described are flight qualified and have flown on most 
STS missions. 

CONTACTS 

Source: Rockwell International, 12214 Lakewood Blvd., Downey, CA 90241 
Operational: C. w. Anderson, (213)922-5095 
R. L. Gasteiger, (213)922-5339 



71 



LONGERON AND KEEL LATCHES 



PAYLOAD RETENTION LATCHES MAJOR 


CHARACTERISTICS 


LATCH DESIGNATION 


LIMIT LOAD (POUNDS) 
(NOT SIMULTANEOUSLY) 


WEIGHT 
(POUNDS) 


DRAWDOWN CAPABILITY 


STANDARD WEIGHT 
LONGERON LATCH 


X = 121,000 
Y = 12,100 
Z = 121,000 


113 


15,000 POUNDS MAX. 


MIDDLE WEIGHT 
LONGERON LATCH 


X = 64,000 
Y = 6,400 
Z = 64,000 


55 


12,000 POUNDS MAX. 


MODIFIED MIDDLE 
WEIGHT LATCH 


X = 64,000 
Y = 6,400 
Z = 64,000 


44 


12,000 POUNDS MAX. 


LIGHT WEIGHT 
LONGERON LATCH 


X = 48,400 
Y = 4,840 
Z = 48,000 


44 


12,000 POUNDS MAX. 


PASSIVE LONGERON 
LATCH 


X = 121,000 
Y = 12,100 
Z = 121,000 


28 


N/A 


STANDARD WEIGHT 
KEEL LATCH 


X = 6,800 
Y = 73,690 
Z = 7,370 


80 


1,000 POUNDS 

» 


LIGHT WEIGHT 
KEEL LATCH 


X = 2,500 
Y = 25,000 
Z = 2,500 


44 


1,000 POUNDS 



72 



Magnetic End Effector 



OVERVIEW 

The Magnetic End Effector (MEE) 
with force feedback is a pro- 
posed attachment for the Remote 
Manipulator System (RMS) which 
improves dexterity. 



■Remote Manipulator System (RMS) 
wrist element 



Standard End Effector (SEE) 




Force torque Sensor (FTS) 

Magnetic End Effector (MEE) 



OPERATIONAL COMMENTS AND 
INTERFACE PROVISIONS 

The MEE with force feedback is 
designed to be attached to the 
end of the RMS using an Electri- 
cal Flight Grapple Fixture (EFGF). 
The hardware consists of a force- 
torque sensor sandwiched between 
the EFGF and the MEE. The force 
torque sensor detects forces and 

moments being exerted at the end of the RMS and sends data to a computer and 
video graphics generator on the Aft Flight Deck. The RMS operator can monitor 
these forces on a CRT display. The Magnetic End Effector is designed to 
grapple objects which have a simple, flat strike plate of ferrous material. In 
addition, the MEE will have the capability to transfer data across the 
interface by means of an optical data link and to transfer power. The MEE is 
equipped with both a centerline TV camera and a camera oriented 90 degrees from 
the centerline camera. The MEE will be particularly useful in handling items 
which must be stacked flat and which cannot accomodate the standard grapple 
fixture. An example of such items are the heatpipes to be used on the Space 
Station and to be flown as part of the SRAD experiment. Other examples would 
be various tools and construction materials. The MEE and force-torque sensor 
will be stowed on their own carrier mounted shelf, using a unique latching 
mechanism. 



STATUS 

The concept and hardware/software described above were a joint development of 
JPL and JSC. A training version of the MEE and the force-torque sensor has 
been delivered to the Manipulator Development Facility at JSC. The hardware/- 
software has been checked out and used to demonstrate increased dexterity of 
the MDF arm under several conditions. One of the demonstrations involved 
inserting a two foot long probe, with a hex head socket attached, into a guide 
tube and applying a specified amount of torque to a bolt at the bottom of the 
tube. 



73 



MAGNETIC END EFFECTOR 

The current effort includes additional tests/demonstrations using the MDF unit 
and the preliminary design of a flight version. Funding has not been identi- 
fied to support a:tual development of the flight version. 

CONTACTS 

Source: JPL and JSC ,_ 

Operational: L. Monford, NASA JSC/IC, (713)282-1809 



74 



Manipulator Foot Restraint 



ORIGINAL PAGE 
BLACK AND WHITE PHOTOGRAPH 




S84-27021 



OVERVIEW 

The Manipulator Foot Restraint (MFR) is a crewmember restraint device and 
work station which is grappled by the Remote Manipulator System (RMS). It 
consists of a lower base with a standard RMS grapple fixture and a latch and 
roller assembly for attaching the MFR to the Adaptive Payload Carrier (APC). 
On top of the lower base is the MFR base, supporting the foot restraint 
platform and vertical stanchion. The upper portion of the stanchion, the 
work station, includes handholds, space for two removable tool boards, and 
the Payload Interface Mechanism (PIM). A safety tether is attached to the 
foot restraint platform for crewmember use. Several parts of the mi-k rotate 
to provide a wide range of crewmember motion. 

OPERATIONAL COMMENTS AN " TNTFRFACE PROVISIONS 

The MFR provides for EVA crewmember translation, positioning, and restraint 
in cargo bay worksites within reach of the RMS. Positioning of the MFR is 
by voice link with the RMS operator in the cabin. 



STATUS 

Flight qualified. Flown on specific flights. 

CONTACTS 

Source: T. W. Anderson, NASA/ES6, (713)483-8959 
Operational: R. C. Trevino, NASA/DF4, (713)483-2597 



75 



MANIPULATOR FOOT RESTRAINT 



Part Number 



Weight 



Material 



Rotation of MFR 
base including 
vertical stanchion 



Tilt of stanchion 
away from crewmember 



Rotation of work 
station about 
vertical stanchion 
axis 



Rotation of foot 
platform inde- 
pendent of base 



Stowage 



Technical Information 



SED33103150-305 



102 lb 



Primarily aluminum 



±180" with locking in 45° increments 



27° forward with locking in 9" increments 



+180° with locking in 45* increments 



Continuous 360° with locking in 30° 

increments 



Cargo bay. attached to APC 



Dimensional Data 


A 


25 in. 


B 


61.5 in. 


C 


14 in. 


D 


20.56 in. 


E 


14.5 in. 


F 


8 in. 


G 


52.5 in. 






76 



ORIGINAL PAGE 
BLACK AND WHITE PHOTOGRAPH 



Manned Maneuvering Unit 



OVERVIEW 

The Manned Maneuvering Unit (MMU) is a 
modular self-supporting backpack, 
containing its own electrical power, 
propulsion system, and controls. It 
readily attaches to the Extravehicular 
Mobility Unit (EMU) and can be donned, 
doffed, and serviced by one EVA 
crewmember for use as required during 
a nominal 6-hour EVA. It has complete 
si x-degree-of -freedom control 
authority and automatic attitude hold 
capability. It provides attachment 
points for the use of ancillary 
equipment such as satellite docking 
mechanisms, tools, portable lights, 
cameras, and instrument sensors. Th e 
propellant is gaseous nitrogen, which 
1n noncontaminating. 

OPERATIONAL COMMENTS AND 
INTERFACE PROVISIONS 

The MMU is used to increase the EVA 
crewmember' s mobility by extending the 

range of activities from the cargo bay S82-26984 

to other portions of the spacecraft, 

to appendages of pay loads protruding from the cargo bay, or to other space- 
craft. It can be used to carry cargo of moderate size, to stabilize 
satellites, to retrieve small free-flying payloads, and to provide remote 
photography/television of Shuttle operations. 

Two MMU's are normally manifested. On past missions, the MMU has been used 
with the Apogee Kick Motor Capture Device (ACD), the trunnion pin attachment 
device (TPAD), and MMU camera provisions. The MMU is stowed in the forward 
cargo bay (1) on the flight support station (FSS) designed specifically for 
that purpose. 




STATUS 

Flight qualified. Flown on specific flights. 

CONTACTS 

Source: L. J. Rogers, Martin Marietta, Denver, CO, (303)977-3669 
Operational: C. E. Whitsett, NASA/JSC/EC, (713)483-9111 



77 



MANNED MANEUVERING UNIT 



Technical Information 


Part Number 


852MUOO00O0 


Weight 


338 lb 


Material 


Aluminum 


Control 


Three modes of operation - manual, automatic 
attitude hold, and satellite stabilization 
Left hand controller - 300F translation 
Right hand controller - 3D0F rotation 
Acceleration - approximately 0.2 to 

0.4 ft/sec z 
Redundant logic 


Maximum Range 


Early flights - approximately 300 ft 
Potential - approximately 3000 ft 


Electrical Power 


Two batteries: total power - 852 W-hr 


Propellant 


Gaseous nitrogen 

ReservicTng in Tess than 10 min 


Stowage 


Forward cargo bay on FSS 



Dimensional Data 


A 


50.0 in. 


B 


33.3 in. 


C 


27.0in. 





48.0 in. 





) 








•TTT 










% 









V 




n 




? 


c 


Jul 





o 






^s^ J I [ r I-— P i It t \^ 


^ 


•^PSSJ- 




B s 











o 



B 




78 



Modular 
lockers 



CO2 Absorber 
use location 



Airlock 



Fire 
extinguisher 



Modular 
lockers 



Volume G 
(MD80R) 



Middeck 



Optional 
4-tier bunk 
sleep stations 




Airlock hatch 



Modular 
lockers 



Avionics bay 3A 



Middeck (Forward) 



Waste management 
compartment 



Side hatch 



Window 

shades/filters 

bag 




Volume H 
(MD23R) 



Volume F 
(wet trash) 



Volume E 
OFK/PPK's) 



Volume D 
(MD52C) 



Middeck (Aft) 



79 



MIDDECK 

OVERVIEW 

The Orbiter Middeck contains D&C panels for Orbiter systems control, siowage 
provisions for most of the crew equipment on a flight, a waste management 
system compartment, the airlock, and middeck floor stowage compartments. 
Beneath the middeck, the lower equipment bay contains Environmental Control 
and Life Support System (ECLSS) hardware. Access to equipment in the lower 
equipment bay is through Middeck floor panels which are marked with Middeck 
codes. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The Middeck has provisions for up to 42 modular lockers each containing such 
items as experiments, food, and nominal and contingency equipment. In 
addition, provisions exist for the waste management system, galley and sleep 
stations. The ECLSS is contained beneath the Middeck and equipment bay. 
Contingency access to the ECLSS is provided by means of removable floor 
panels. LiOH canisters and the wet trash compartment are also located 
there. 

STATUS 

The Middeck is an integral part of the Shuttle Orbiter. 



80 



ORIGINAL PAGE 13 
OF POOR QUALITY 



x. 



Mission Peculiar Equipment Support Structure 




108-KSC-385C-1 367/2 



OVERVIEW 

The Mission Peculiar Equipment Support Structure (MPESS) provides support 
for experiments and/or instruments in the Orbiter Cargo Bay during Space 
Shuttle flights. 



OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The MPESS is connected to the Cargo Bay by means of trunnion fittings on 
each end and a keel fitting at the bottom. There are no preintegrated 
electrical, environmental, or command and data management subsystems. The 
structural arrangement provides reasonable access for experiment 
installation and removal. 



STATUS 

The MPESS is flight qualified for STS operations. 

CONTACTS 

Source: George C. Marshall Space Flight Center, (205)453-2121 
Operational: Jim Turner/NASA MSFC/PS-01, (205)544-0617 

REFERENCES 

Design and Performance Specification CE Part 1 MPE Support Structure 
CE #F 4300 1A 



81 



MISSION PECULIAR EQUIPMENT SUPPORT STRUCTURE 



Technical Information 


Weight 


1,185 lb 


Material 


2219-T85 and 6061-T6 
Aluminum Alloy 



Dimensions 


Length 


173.5 in. 


Width 


27.5 in. 


Height 


109.0 in. 



Trunnion fittings 




Trunnion fittings 



Keel fitting 



82 



Modular Power Subsystem 




Remote 
Interface 
Unit A 

Signal 

Conditioning 

Assembly 

Bus 

Protection 

Assembly 



Nickel | 
Cadmium , 
Storage 
Batter ies(3) 



OVERVIEW 

The Modular Power Subsystem provides a compact, cost-effective, modular 
power management system which conditions, stores, and distributes electrical 
power to onboard satellite systems. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The six major internal components of the MPS (shown in the photograph) 
perform separate but equally important tasks. The power regulator unit 
draws energy from solar arrays and conditions it for satellite use. The 
power control unit directs the energy flow to the nickel cadmium storage 
batteries (for use during portions of the orbit when sunlight is not 
available) and directly to the satellite's equipment or experiments. The 
signal conditioning assembly handles the command and telemetry signals that 
control and monitor the functions of the MPS. The two remote interface 
units channel these signals to and from the spacecraft's computer. The bus 
protection assembly provides fuse protection for loads within the MPS. 

STATUS 

The MPS is being used on the Solar Maximum Mission Satellite, launched in 
1980, and Landsats 4 and 5, launched in 1982 and 1984. Two more MPS modules 
will provide power conditioning on NASA's new Gamma Ray Observatory 
spacecraft. 



CONTACTS 

Source: McDonnell Douglas, St. Louis Division, (314)232-0232 
Operational: Michael Mackowski, (314)233-2364 



83 



MODULAR POWER SUBSYSTEM 



Technical Information 



Size 



4 * 4 x 1.5 foot 

Aluminum honeycomb housing 



Self-contained module 



84 



ORIGINAL PAGE IS 
OF POOR QUALITY 



Module Servicing Tool 




OVERVIEW 



84-A-0139 



84-A-0137 



The Module Servicing Tool (MST) is a self-contained power tool used to 
install and remove standard Multimission Modular Spacecraft (MMS) subsystem 
modules. It is intended to simplify and reduce the time required for 
extravehicular, on-orbit maintenance and repair operations. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The MST is an Extravehicular Mobility Unit (EMU) battery-powered, extra- 
vehicular activity (EVA) tool. It is designed to loosen and tighten the MMS 
module retention bolts to predetermined torques of up to 160 ft-lbs. 
Controls for manual operation of the MST are located on the rear panel and 
left and right grip assemblies. A torque limit switch is available to 
select the desired torque for bolt tightening and loosening. In addition, 
the MST has a bolt drive counter which provides the operator with a visual 
indication of bolt drive rotation direction and bolt tightening completion. 
A separate control circuit provides power to two resistance heaters which 
thermostatically maintain the minimum battery temperature. Separate 
external heaters are required to maintin MST battery temperatures prior to 
EVA use. The MST is battery-powered and manually operated, and therefore, 
does not have any Space Transportation System power or signal interfaces. 
Two MST's were flown on STS-41C and were used during the successful exchange 
of the attitude control system module of the Solar Maximum satellite. 



STATUS 

Flight units: Two flight qualified units are available 

Engineering unit: Available for one gravity dry-land and KC-135 aircraft 

training and demonstration 

Underwater training unit: Available for training and demonstration 



85 



MODULE SERVICING TOOL 



CONTACTS 

Source: GSFC, Fairchild Space Company, (301)286-2000 
Operational: R. Lewis or K. Rosette, NASA/GSFC, Code 408, 
(301)286-2060, (301)286-7201 



Technical Information 



Part Number 



Weight 



Material 



Torque Range 



Temperature Range 



Power Requirements 



GSFC 93972000002 



70.5 lb 



Housing - not available 
Surface - Chemglaze blue 



Settings for 25. 75, 100, 125, and 
160 ft-lbs. 



-lCF to 104°F 



16.5 V EMU battery 



Dimensions (Inches) 


A 


14.75 in. 


B 


14.32 in. 


C 


35.20 in. 



I TO PI 



■IL, 

«fclL. 



^ 



LT 






86 



ORIGJN^- AGE IS 
OF PCQR QUAL'TY 



Orbital Maneuvering Vehicle 



X 



\ 




OVERVIEW 

The Orbital Maneuvering Vehicle 
(OMV) provides for the extension 
of payload services and 
capabilities out of the Orbiter 
and the Space Station, these 
services include spacecraft 
delivery and retrieval to and from 
higher orbits, reboost or deboost, 
payload viewing and satellite 
support. The OMV will also be ^_ 
capable of supporting advanced 
mission kits for remote servicing, 
refueling, and debris retrieval. 



OPERATIONAL COMMENTS AND INTERFACE 
PROVISIONS 

The OMV will have the capability 
of performing delivery, retrieval, 
reboost, deboost and viewing 
missions from both the Orbiter and 
Space Station. On-orbit opera- 
tions mav be controlled either ... 

from the ground or the Space Station. Space Station operations typical y 
will be controlled by the Space Station operator when the OMV s operating 
in close ?rox?mity of the station: In either case, final Peking maneuvers 
are performed by remote piloted modes. Cold gas propulsion will be utilized 
for final docking and proximity operation maneuvers near contamination 
sensitive payloads. The OMV will be capable of a nine month storage period 
?n the event the orbiter has to return to the ground prior to OMV return to 
the orbiter. The OMV will be designed to accommodate on-orbit maintenance 
and will have a design life of 10 years with ground ref urbishme nt. OMV 
payload accommodations are available in the form of structura support 
power, data and command. Electrical power will be available up to 5 kw at a 
peak of 1 kw. 

STATUS 

Presently in the fabrication stage. 

CONTACTS 

Source: TRW Space and Technology Group , M „.,~> ,„„ 
Operational: James R. Turner, NASA/MSFC, (205)453-2817 



87 



ORBITAL MANEUVERING VEHICLE 



ORU 3A, 
Communications 



ORU 4A, GN&C, 



ORU 2, Battery /j 

ORU 1A, Electrical 
power control ( 



< 

ORU 7, Data ) 
management i 



RMS Grapple 
docking mechanism 



Propulsion 
module 




ORU 5, 
Battery 



^J/ ORU 1B, Electrical 
power control 



sORU 6, GN&C 



ORU 4B, GN&C, l 
Data management 



ORU 3B, 
Communications 



88 



Orbital Spacecraft Consumables Resupply System 



Docking 

mechanism 

(PRLA) 




MLI Blanket 



Tanks 



Motorized 

thermal 

shade 



Pressurant bottle 



OVERVIEW 



The Orbital Spacecraft Consumables Resupply System (OSCRS) is designed to be 
flexible in order to service a wide range of satellites and be adaptable to 
support Space Station. OSCRS will also provide adequate data and control to 
permit independent crew operation/trouble shooting/work-around without 
ground coverage. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

Preliminary fluid quantities include Monopropellant and Bipropellant 
(conceptual design). 

A. Monopropellant OSCRS Requirements 

• Basic System 

Resupply up to 2910 lb. of Hydrazine 

Standard Orbiter interfaces 

Operational after one failure 

Safe after two failures 

Design for a life of 80 flights 

Manual connection to the satellite being serviced 

Emergency separation of satellite without EVA 

Vent propel lant and/or gas from OSCRS and the satellite 



89 



ORBITAL SPACECRAFT CONSUMABLES RESUPPLY SYSTEM 

• Basic Growth System 

Resupply up to 4850 lb. of Hydrazine 

Resupply high pressure gas (up to 3000 psi) 250 lb. of GN2 or 36 lb. 
of GHe 

• Future Growth System 

Resupply high pressure gas (3000 to 5000 psi) 

Operate more than one fluid resupply system from the AFD on a single 
mission 

Automatic mating/demating of fluid and electrical disconnects 
Resupply spacecraft from an OSCRS attached to OMV or space station 

B. Bipropellant OSCRS Requirements 

• Basic System 

Resupply up to 7695 lb. of MMH and NTO 
Resupply up to 270 lb. of GN2 at up to 4500 psi 
Other - Same as Monopropellant 

• Basic Growth System 

Resupply up to 11542 lb. of MMH and NTO 
Resupply up to 630 lb. of GN2 at up to 4500 psi 

• Future Growth System 

Operate more than one fluid resupply system from the AFD on a single 
mission 

Automatic mating/demating of fluid and electrical disconnects 
Resupply spacecraft from an OSCRS attached to OMV or space station 

STATUS 

Presently in the technology development stage. 

CONTACTS 

Source: Rockwell International 

Martin Marietta Corporation 
Fairchild Space Company 
Operational: R. Gasteiger, RI, (213)922-5339 

Ralph Eberhardt, MMC, (303)977-4183 
I. M. Leiy, Fairchild, (301)428-6951 



90 



ORBITAL SPACECRAFT CONSUMABLES RESUPPLY SYSTEM 



Technical Information 


Item 


Monopropel lant 


Bipropel lant 


Design reference mission 


GRO resupply 


OMV resupply 


Fuel quantity for mission 


3000 LBM 


7000 LBM 


Tanks & quantity 


3 TDRS 


4 L-SAT 
+2 catch tanks 


Tank volume 


16.3 Ft 3 each 


27.0 Ft 3 each 


Gas bottles 


2 


4 


Structure 


2219-T87 
machined truss 


2219-T87 
machined truss 


Service life 


80 missions 


80 missions 


Attachment to orbiter 


3 point 


5 point 


Docking mechanism 


PRLA or 

3 FSS latches 


PRLAA or 

3 FSS latches 


Mass fraction 


.60 


.70 



91 



(THIS PAGE INTENTIONALLY LEFT BLANK) 



ORIGINAL PAGE 
BLACK AND WHITE PHOTOGRAPH 



Orbiter Cargo Bay Floodlight System 




S83-46316 



OVERVIEW 

Seven floodlights are provided in the Cargo Bay to aid extravehicular crew 
members in the performance of Cargo Bay door contingency operations; the 
lights are also integral to the launch, retrieval, and repair of various 
space systems. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

Seven metal halide type lights provide a minimum of 7 ft-c of illumination 
at the Cargo Bay centerline; the forward bulkhead light provides the same 
level at 30 ft. There are some restrictions to activity near these lights 
because of the generated heat. In addition, some lighting may be blocked by 
payloads. 



STATUS 

Used on each flight since STS-1. Flight qualified. 

CONTACTS 

Source: Rockwell /ILC Technology 

Operational: C. D. Wheelwright/SP34, (713)483-3725 



REFERENCES 

Space Transportation System: 
Rev. A, JSC-10615 



EVA Description and design criteria, 



PRECEDING PAGE BLANK NOT FILMK) 



93 




Uia&JZ'-Ad^-tt 



■mmm* &&$ 



ORBITER CARGO BAY FLOODLIGHT SYSTEM 



I 






/ fwd| i w 




X-576 



W 



Y = 56 



X = 750 



"7 Electrical wire tray 



Cargo bay floodlight 



Z - 325.2 




Y = -48 



lY- -918 



X»979 



I Y- 918 



Iy-56 
I X- 1140.67 

■ Y - -56 



Electrical wire trav ' 



IZ-320 



_JB 2 .° 3 2 6 ^ 1 — 
Electrical wire tray 

Wk Z - 324.0 



Z - 325.2 



94 



Payload Active Cooling/Heating System 




OVERVIEW 

The Payload Active Cooling/Heating System (PACS) is a self contained thermal 
control system mounted in the cargo bay on a sidewall carrier. The PACS is 
designed to accommodate small payloads or payload components with heat loads 
up to 8500 watts. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

PACS modular design utilizing a lightweight structure, radiator panel, pump 
package, thermal plates and instrumentation may be used in an autonomous 
mode or with the payload orb iter cooling system. 



STATUS 
Concept 

CONTACTS 

Source: Rockwell International, 12214 Lakewood Blvd., Downey, CA 90241 
Operational: C. W. Anderson, (213)922-5095 
R. L. Gasteiger, (213)922-5339 



95 



PAYLOAD ACTIVE COOLING/HEATING SYSTEM (PACS) 



Technical Information 


Weight 


<185 lbs 


Power Req 


28V dc. 80-500W depending 
upon pump speed and 
heater power 


Temp Range 


-250° to 250" F 


Cool ing 


Coldplate maintained at 

70" ± 4" F 


Power 


2BVDC, 80-500 W 


Material 


TBD 


Status 


Concept 



Interface Details 


Electrical 


28V dc 


Mechanical 


Sidewall Mounted 


Data Rate 


N/A 


Documentation 


TBD 



Dimensional Data 


Coldplate 


A 


40 in . 


B 


20 in. 


C 


1.4 in. 


Radiator 


A 


50 in. 


B 


36 in. 




Autonomous Cooling 



Orbiter Dependent Cooling 



Radiator/Heater module 



Coldplates 




Add-on 



96 



Payload Bay Standard Active Cooling Kit 




Standard Interface Panel (SIP) 



QD Support 



Longeron 
Z 372 



OVERVIEW 

The Payload Bay Standard Active Cooling Kit (SACK) provides cooling 
provisions to the lead payload in the orbiter. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 
Elements of kit hardware include: 

• Quick disconnects for coolant supply and return at SIP interface 

• Brackets and supports for fluid lines 

• Fluid line segments 

• Insulation blankets 

This model establishes a standard interface for water or freon cooling 
systems at a SMCH-SIP panel (Model MV0725A). 

STATUS 

First used on STS-26. 

CONTACTS 

Source: Rockwell International, 12214 Lakewood Boulevard, Downey, CA 90241 
Operational: R. Gasteiger, RI, (213)922-5339 



97 



(THIS PAGE INTENTIONALLY LEFT BLANK) 



Payload Berthing System 




A861010-V-4C 



OVERVIEW 



The Payload Berthing System (PBS) provides on-orbit docking/berthing of 
payloads for servicing, repair or temporary holding. The PBS is sidewall 
mounted at the primary attachment locations of bay 3 through 12. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The PBS utilizes the standard Flight Support System (FSS) interfaces, 
latches and umbilicals, and provides docking/berthing out of the confines of 
the cargo bay. The rotating berthing ring provides capability to access all 
side of a docked payload. The PBS may be deployed from the payload bay by 
EVA, RMS or motor. The PBS design provides the capability to support a 
40,000 pound payload. 

STATUS 

Concept. Several design studies have been performed. 

CONTACTS 

Source: Rockwell International, 12214 Lakewood Blvd., Downey, CA 90241 
Operational: C. W. Anderson, (213)922-5095 
R. L. Gasteiger, (213)922-5339 



PRECEDING PAGE BLANK NOT FILMED 



99 



Bfl^^XJMHNUONAfcW BIAN< 



PAYLOAD BERTHING SYSTEM 



Technical Informatio 


Weight 


< 1000 pounds 


Power Req 


TBD 


Temp Range 


TBO 


Cool ing 


TBD 




Material 


Aluminum 


Status 


Concept 



Interface Details 


Electrical 


"BD 


Mechanical 


Sidewall mounted 


Data Rate 


K/A 


Documentation 


U'jsign study report 



Berthing ring 

Tilt mechanism 

Support structure 

Sidewall carrier 




100 



Payload Interface Mechanism 




S83-37182 

OVERVIEW 

The Payload Interface Mechanism (PIM) mounts on top of the Manipulator Foot 
Restraint (MFR) stanchion. It is a tethering device for attaching a payload 
to the MFR and consists of three main parts: a payload fitting, a pyramid 
fitting, and a pyramid housing. The pyramid fitting and the pyramid housing 
are connected by a retractable tether. Tether attachment rings are provided 
on the ends of the pyramid fitting's handles and on the payload fitting. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The PIM was designed for temporary stowage and transfer of the MST. The 
pyramid fitting attaches to the payload fitting mounted on the MST.- Then 
the pyramid fitting and the MST are pulled over to the MFR and latched onto 
the pyramid housing. The MST is released from the PIM by turning the lock- 
unlock lever on the pyramid fitting and depressing the release levers on the 
payload fitting handles. The pyramid fitting is released from the pyramid 
housing by pushing the lock-unlock bar on the pyramid housing to the unlock 
position and depressing the housing latch handle. 

STATUS 

Flight qualified. Flown on specific STS flights. 

CONTACTS 

Source: S. Abraham, Grumman Aerospace Corp., (516)575-9553 
Operational: R. C. Trevino, NASA/JSC/DF, (713)483-2597 



101 



PAYLOAD INTERFACE MECHANISM SOCKET 



Technical Information 



Part Number 



Weight 



Material 



Tether Length 



Quantity Flown 



C95-105 



5.5 lb 



Aluminum 



6 ft 



One with the MFR 



Dimensional Data 


A 


4.06 in. 


B 


5.56 in. 


C 


20.875 in. 



D 

W 















ml- 


. B ■ 



o 




o 



102 



Payload Retention Systems 



Five-point Retention System 
Used by Most Payloads 



Primary Payload 
Retention Latch 
Actuators (PRLA's): 
react longitudinal 
and vertical loads 
(F x and F z ) 



Stabilizing PRLA's: 
react vertical load (F z ) 




Lower Centerline Active 
Keel Actuator: reacts 
side load (F y ) 



OVERVIEW 



The Orbiter Payload Retention Systems provide structural attachments for 
each payload by using four or five attachment points to secure the payload 
within the Orbiter Cargo Bay during all phases of the Orbiter mission. 



OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 



The Shuttle Orbiter prov 
a carrier or a payload a 
payloads are retained by 
are secured by motor-dri 
1n the Orbiter Cargo Bay 
are equipped with their 
able to function under e 
or deberthing on-orbit i 
System. 



ides structural support attachment points for either 
long the length of the Cargo Bay. Nondeployable 

passive retention devices, and deployable payloads 
ven, active retention devices. Payloads are secured 

by means of the Payload Retention System, or they 
own unique retention systems. The mechanisms are 
ither one-g or zero-g conditions. Payload berthing 
s accomplished by utilizing the Remote Manipulator 



At the present time paylod retention mechanisms that are capable of 
supporting a payload of up to 65,000 lb through all phases of flight have 
been designed, developed, and certified. For weight-saving purposes and 
handling enhancement, a lightweight latch system is now being designed to 
accommodate lighter payloads. Intermediate capability latching mechanisms 
are in the proposal stage. Unique latching systems may be developed by 
using system components which have already been developed and certified. 

STATUS 

Structural support attachment points are an integral part of the STS. 
Latches are flight qualified. 



103 



PAYLOAD RETENTION SYSTEMS 



CONTACTS 

Source: Rockwell International 

Operational: D. C. Wade, NASA/JSC/ES, (713)483-2876 



REFERENCES 
Hardee, J. H.: 



The Space Shuttle Orbiter Payload Retention System. 
Rockwell International 



Technical Information 


Size 


Longeron latch 


Keel latch 


Approximately 
18 in. by 12 in. 


Approximately 
19 in. by 14 in. 


Weight 
Standard 
Lightweight 


113 lb 
46 lb 


77 lb 
31 lb 


Ultimate load 
in X-Z plane 
Standard 
Lightweight 


169.400 lb (radius) 
67.600 lb (radius) 


114.200 lb 
57.600 lb 



PRLA Payload Installation Sec j-:- nee 



1 With latch open, the 
payload trunnion is 
guided toward the 
spherical bearing 
by the guides 

2. Trunnion sensed by 
ready-to-latcn 

switches 

3. Claw is driven closed 
to latch payload 

Payload 
trunnion 



Guide for 
payload trunnion 




- Ready-to-latch 
switch and 
trunnion eject 
arm 



Orbiter 
bridge 
fitting 



Spring link 



Active Keel Actuator 

- Ball screw assembly 




Dynamic latch - 

Static latch- 



104 



ORIGINAL PAGE 
SLACK AND WHITE PHOTOGRAPH 



Portable Electron Beam Welder 





Early Engineering Mock-up 



Conceptual EVA OPS 



OVERVIEW 



Portable Electron Beam Welder (PEBW) forms high-integrity, spatterfree butt 
or lap weld of (dis)similar metals, bending the beam and focusing it onto 
the target seam via a computer-controlled electromagnetic deflection field. 
Uses electrical power from battery pack (no umbilical) only, no other con- 
sumables. Leakproof welded seams (99.995% success rate) replace heavy, 
clumsy QD's (in tubes) and adhesives (in flat plate patches) for infinite 
life. Patented process uses a higher-voltage, lower-current secondary 
e-beam to scatter x-rays inside welded tubes (collected by CCD's) to 
digitally inspect welds immediately after formation. Welder highly reliable 
due to total lack of critical moving parts. Gravity-independence, use with rough 
seams and zero surface preparation make PEBW ideal for leakproof on-orbit 
joining/inspection. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

Packaged PEBW for tubes (above) affixes to tube ends via a clamshell; second 
tube inserted; welder automatically snugs butt seam; settings chosen 
(manually or remotely preprogrammed) for depth, power, tube size, beam 
duration; expert system tracks seam as tubes welded and inspected; 'Weld OK 1 
or 'Defect' annunciated; clamshell opened and welder moved to new position. 
Anticipate hands-off weld/inspect in 1-5 minutes (exclude tube positioning). 
I/F with EVA crew or robot. 

STATUS 

Computer-controlled beam bending, focusing, secondary x-ray inspection 
technique patented/tested by The Welding Institute. PEBW hard mockup built 
by WI/Babcock. Prelim. Space Station applications/ops study, interfaces, 
software & controllers under study by ARRI. Funding required to develop 
prototype, miniaturize power supply, and test (on-orbit if required, vacuum 
chamber at least - zero-g does not affect the weld). 



105 



PORTABLE ELECTRON BEAM WELDER 

CONTACTS 

Source: Mr. Martin Peters, Babcock Energy Ltd., Marketing Division., 

165 Great Dover Street, London, England SE1 4YA 011-44-1-232-4907 
Dr. Alan Sanderson, The Welding Institute, Abington Hall, 
Cambridge, London, England CB16AL 011-44-223-891162 

Operational: Mr. Michael L. Drews, Automation & Robotics Research Inst., 
7300 Jack Newell Blvd. S., Forth Worth, TX 76118 
(817)284-6101 



Technical Information 


Part Number 


TBD - Proposed 


Weight 


<5 kg { 12 lbs. ) approx . 


Power 


TBD: dependent on materials list 


Status 


Eng . mockup. computer models, and 
prelim, feasibility study complete. 
X-ray testing in planning stage 


Material 


Structure - Al pkg . 1 mm Pb 
foil coils - Specs TBD 
Beam Gun - TBD 


Temp. Range 


TBD: dep. on transistor selection 


Cool ing 


Radiative from structure 



Interface Details 


Electrical 


Power to recnargeaole batteries 


Mechanical 


In Use: Hinged clamshell attaches 
to tubes; Stowed: TBD 


Fluid 


None 


Electronics 


Self-contained microprocessors 


Controls 


On/Off switch. Status lights, 
settings panel 


Software 


Seam tracking, welding, X-ray 
inspection, reporting to SS S/W 


Communicat ions 


None if manual: TBD if robotic 


Data Rate 


TBD :f reqd. 


Documentation 


TBS upon request 



CCD's for 

Detecting 

rays 




Target Seam 





Dimensional 


Data 




A 


27.9 cm. 


(11 


n.) 


B 


15.2 cm. 


(6.0 


in.) 


C 


7.6 cm. 


(3.0 


in , ) 


D 


20.3 cm. 


(3.0 


in.) 


E 


1.3 cm. 


(0.5 


in.) 


F 




7.6 cm. 


(3.0 


in.) 



I 



■B- 



C 

L 




1 mm Lead Shielding 



ORIGINAL PAGE 
BLACK AND WHITE PHOTOGRAPH 

Portable EVA Light 




HSTL87-11-09PG 132 



OVERVIEW 



The HST Portable Floodlight provides portable lighting during extravehicular 
activity. It provides a minimum of 30 foot candles at a distance of 10 feet 
and has an electronic intensity control which can be preset at assembly. It 
can also be operated by EVA astronauts. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

Requires 50 watts at 28 volts D.C. Has 8 foot power cord. Handle clamping 
ranges from 0.250 to 0.375 inches. Seal beam life of 400 hours. 



STATUS 

Ready for STS flight use. 

CONTACTS 

Source: Marshall Space Flight Center, Huntsville, AL 35812 
Operational: J. R. Turner, NASA/MSFC PS-01, (205)544-0617 



107 



PORTABLE EVA LIGHT (HST) 



Technical Information 



Part Number 



Weight 



Power 



Temperature Range 



16101-10061-01 



6.5 lbs. 



47.3 



-67* F to 257° F 



Interface Details 


Electrical 


28 V DC, external via 
power cord 


Plug Part 


# 860547765-8P (GFE) 





0.25 in. 



3.75 in. 



108 



Portable Foot Restraint 




S84-42686 



OVERVIEW 



The Portable Foot Restraint (PFR) is a working platform which restrains the 
crewmember during the performance of EVA tasks. The platform consists of a 
system of toe guides and heel clips which interface with the EMU boots. A 
two-axis (roll and pitch) gimbal system with lock knobs is provided for 
adjustment and positioning. A probe enables the PFR assembly to interface 
with the worksite at the PFR socket, where yaw adjustment is available. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The PFR was originally designed to provide Space Shuttle EVA crewmembers 
with a contingency restraint system for performing EVA work tasks and door 
latch repairs on or about the forward and aft bulkhead and along the center- 
line door latches of the payload bay. As EVA operations increased in fre- 
quency, new applications for its use were identified and improvements were 
made in the design to minimize set-up and adjustment times as well as to 
increase the operational work load limits from 25 to 100 pounds. Several 
configurations of the PFR exist, varying in mounting socket design and probe 
lengths and are capable of attachment to a variety of work surfaces. 
Spring-loaded lock knobs have also been incorporated into the later configu- 
rations to prevent inadvertent unlocking of the gimbal system. One PFR 
platform is part of the normally manifested STS equipment. 



STATUS 

Flight qualified. Flown on specific STS flights. 

CONTACTS 

Source: M. Withey, ILC Space Systems, (713)488-9080 
Operational: R. C. Trevino, NASA/JSC/DF, (713)483-2597 



109 



PORTABLE FOOT RESTRAINT 



Technical Information 


Part Number 


10159-10034-01. -02 


Weight 


8.4 lb 


Material 


Aluminum alloy 


Input Load 


10176 configuration - 100 lb. any direction 
10155 configuration - 25 lb, any direction 


Quantity Flown 


One 


Stowage 


Orbiter forward bulkhead 



Dimensional Data 


A 


15.94 in. 


B 


20.5 in. 




110 



ORIGINAL PAGE 
BLACK AND WHITE PHOTOGRAPH 



\ 



Portable Foot Restraint Socket 




S84-25783 
OVERVIEW 

The Portable Foot Restraint (PFR) Socket, also called the 12-point socket, 
secures the PFR extension arm to a stationary location. There are three 
types of PFR sockets. Two types have only one socket position; the third 
has separate socket positions for stowage and use. Each type has a 12-point 
polygon-shaped receptacle into which the hex-shaped probe of a PFR is 
inserted and secured by self-tethering quick-release pins. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The PFR socket used on the Solar Maximum satellite (Solar Max) repair 
mission (10172-20433) is made of stainless steel and has only one PFR 
receptacle. The PFR socket 10174-20019, made of aluminum, has two PFR 
receptacles in which the PFR extension arm may be secured: one for launch, 
the other for use. The PFR socket 10176-20648 is similar to the Solar Max 
socket except that is is made of aluminum and has a thicker base to with- 
stand greater loads. The PFR can be mounted to the socket for launch and 
EVA use. A tether pip pin is incorporated to lock the socket to the PFR. 

STATUS 

Flight qualified. Flown on specific STS flights. 

CONTACTS 

Source: M. Withey, ILC Space Systems, (713)488-9080 
Operational: R. C. Trevino, NASA/JSC/DF, (713)483-2597 



111 



PORTABLE FOOT RESTRAINT SOCKET 



Part Number 



Material/Weight 



Technical Information 



10172-20433 
10174-20019 
10176-20648 



10172-20433 
S0174-20019 
10176-20648 



stainless steel/6 lb 
al ufninum/2 .813 lb 
al uminum/2 .0 lb 



Dimensional Data 


A 


4.000 in. 


B 


3.0 in. 


C 


2.88 in. 


D 


4.000 in. 


E 


5.88 in. 


F 


2.88 in. 




1J 




10172-20433 
10176-20648 



-*■ 



10174-20019 



@A 



204660109. ART) 3 



112 



PFR Socket (HST) 




OVERVIEW 

The Hubble Space Telescope (HST) Portable Foot Restraint (PFR) socket is a 
12-point receptacle which mates with the HST PFR. It provides a stable foot 
restraint for an EVA crewmember performing space telescope maintenance or 
repair. The PFR socket receptacles are located at various work stations 
along the shell of the space telescope. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The PFR socket is equipped with a pip pin hole. When the HST PFR is 
inserted into the socket, a pip pin attached to the PFR is inserted to 
prevent the PFR from coming out of the socket. The PFR socket structure has 
four mounting holes 0.287 inch in diameter for mounting. Because of the 
large number of PFR sockets on the HST, each socket does not have an 
attached pip pin but relies on a pip pin from the PFR. 



STATUS 

Flight qualified. Will be flown on the STS/HST flights. 

CONTACTS 

Source: LMSC, HST Contracts Office, (408)742-5505 
Operational: K. A. Havens, NASA/JSC/DF, (713)483-2569 



113 



PFR SOCKET (HST) 



Part Number 



Weight 



Material 



Construction 



Technical Information 



4173704 



0.78 lb 



Aluminum alloy 



Mounting holes - 0.287-in. dia 
Pip pin - 0.375-in. dia 



Dimensional Data 


A 


0.375 in. 


B 


1.250 in. 


C 


2.00 in. 


D 


0.544 in. 


E 


2.50 in. 


F 


1.625 in. 


G 


1.0055 in. 


H 


1.250 in. 


I 


3.62 in. 



A x 

PIP Pin hole-v. \^- 


. B ► 




ii 
C 

" 


f w 


, ^ 




9 


t 

D 








. — 






„ E ► 






114 



ORIGINAL" PAGE 
BLACK AND WHITE PHOTOGRAPH 



Power Package, EVA 




S85-31369 
OVERVIEW 

The EVA Power Package (EPP) is a portable general purpose power supply. It 
1s currently configured as a contingency power source for payload assist 
module D (PAM-D) sunshield operations in the event of an Orbiter power 
failure. 



OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The EPP can provide up to 10 amp-hours, using an EMU battery, with controls 
for four independent circuits, main power, and self test to confirm 
operation of the system under load. One or any combination of the four 
circuits provides 6.0 amps of continuous power, 8.0 amps surge capability at 
28.0 ± 2.0 volts dc, and 10-amp circuit- interrupt protection. 

Controls include a system on/off switch and four output control switches. 
There are four 19-pin output/monitoring connectors and five lift-to-lock, 
three-position toggle switches. Control circuit labels can be replaced for 
different mission applications. The EPP has a handle grip and two adjust- 
able tethers and passive thermal protection for a 6-hour EVA. 

STATUS 

Flight qualified. Flown on specific STS flights. 

CONTACTS 

Source: M. Withey, ILC Space Systems, (713)488-9080 
Operational: R. C. Trevino, NASA/JSC/OF, (713)483-2597 



115 



POWER PACKAGE, EVA 



Technical Information 


Part Number 


10175-10075 


Weight 


37 lb 


Continuous Out- 
put Capacity 


6 A 


Capacity 


10 A-hr 


Voltage 


28 ± 2 V dc 


Interrupt 
settings 


3.5, 4.5, 7.5 A 


Max Battery Temp 
for 12 min 


115' F 


Max Temp for 1 hr 
10 min Operation 


160" F 


Thermal 
Protection 
Garment Material 


Ortho. Teflon fabrics, aluminized maylar, 
and polyester scrim 


Quantity Flown 


One for STS-51I 


Stowage 


Middeck locker without battery 



Dimensional Data 


A 


6.3 in . 


B 


9.4 in . 


C 


13.0 in. 




116 



ORIGINAL PAGE 
BLACK AND WHITE PHOTOGRAPH 

Power Ratchet Tool 






87-D-0265 



OVERVIEW 



The Power Ratchet Tool (PRT) is a self-contained, power-driven, 3/8 inch 
drive ratchet tool for extravehicular use. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The PRT is battery powered and is controlled by a dedicated electronic 
controller, which is designed to be carried on the crewmember ' s mini- 
workstation. Fourteen discrete combinations of torque, turn, and speed may 
be programmed prior to the mission. The crewmember controls these 
parameters of the tool by a switch mounted on the controller. A trigger, 
located on the handle, is the start/stop control for the tool (not shown in 
above picture). The tool may also be used in a manual mode similar to a 
non-powered ratchet wrench. The direction of the ratcheting action may be 
changed by the crewmember using an external switching ring surrounding the 
gearhead/ratchet assembly. The silver-zinc battery module is replaceable 
during an extravehicular activity (EVA). 



STATUS 

A. Flight unit: 

• First version - undergoing integration 

• Second version - undergoing development 

B. Prototype unit: 

• Available for one-gravity dry-land and KC-135 aircraft training and 
demonstration 

C. Underwater training unit: 

• Undergoing development 

117 



POWER RATCHET TOOL 



CONTACTS 

Source: R. Lewis or K. Rosette, NASA/GSFC, Code 408, 

(301)286-2060 or (301)286-7201 
Operational: Capt. B. McCandless II, NASA/CB, (713)483-2421 



Technical Information 


Part Number 


Not available 


Weight 
Ratchet Assembly 
Controller 
Battery Module 


8.5 lbs 
4.0 lbs 
3.0 lbs 


Operating Torque 
Maximum Manual 


75 ft-lb 


Programmable Parameters 
Torque 
Turns 
Speed 


Integer value from 1 to 25 ft-lb 
Zero to Continuous 
10 rpm to 50 rpm 


Power Input 


28 V dc; silver-zinc, 
EVA exchangeable 



Dimensional Data 


Wrench portion (as shown) 


A 


0.75 in. 


B 


15.9 in. 


C 


5 . 45 in . 


D 


25.0 in. 


Controller {not Shown) 


Length 


9.65 in. 


Width 


8.20 in. 


Height 


2.97 in. 



A 

_L 



r ® 



■B- 



o o 




WA 



118 



Remote Electrical Umbilical 



Payload 




Connector holder 
moving interface 



Umbilical 
cable 



Payload 
umbilical 



Drive unit 



OVERVIEW 

The Remote Electrical Umbilical (REU) was initially designed for use on the 
NASA/GSFC Flight Support System (FSS) as an umbilical between the FSb and 
spacecraft. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

Provides a 4 inch stroke with 400 pounds force utilizing dual redundant 
motors. Mechanism is locked against backdrive when power is removed and is 
redundant from the motor to output shaft. EVA backup is provided for 
mate/de-mate. 

Utilizes G&H Model 882-series connector with engagement angles of ± 10° with 
±0.12 inch misalignment. 



STATUS 

Has been flown on a number of STS missions, 
delivered to NASA/GSFC 



Six umbilicals fabricated and 



CONTACTS 

Source: Rockwell International, 12214 Lakewood Blvd., Downey, CA 90241 
Operational: C. W. Anderson, RI, (213)922-5095 
R. L. Gasteiger, (213)922-5339 



119 



REMOTELY ELECTRICAL UMBILICAL 



Technical Information 


Weight 


20 pounds 


Power Req 


115V ac, 400 Hz. 3 phase 


Temp Range 


N/A 


Cool ing 


N/A 


Status 


FT ight Qualified 



Interface Details 



Electrical 



Mechanical 



See below 



N/A 



Electrical Interface Details 


Contact Type 


Quantity 


ARRNG. #1 


ARRNG. #2 


Size 8 


8 


26 


Size 16 


50 min 
60 max 


80 


Coax (RG-393/U) 


6 





Coax (RG-142B/U) 


6 


2 



120 



ORIGINAL PAGE 
BLACK AND WHITE PHOTOGRAPH 



Remote Manipulator System 




OVERVIEW 



S84-28541 



The Remote Manipulator System (RMS) is a mechanical arm which augments the 
Shuttle systems in performing the deployment and/or retrieval of a payload. 
In addition, the RMS may be used to perform other tasks in support of 
satellite servicing or to assist in extravehicular activities. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The manipulator arm consists of four joints connected by structural members 
to a payload-capturing device called an end effector. The movement of the 
arm is controlled by an operator using a display and control panel and two 
three-degree-of -freedom hand controllers. The operator also has visual 
access through the windows in the Aft Flight Deck. The manipulator arm is 
anthropomorphic by design, comprising shoulder pitch, shoulder yaw, and 
elbow pitch joints (mainly providing end-point translation) plus wrist 
pitch, yaw, and roll joints (providing rotation of the end effector). The 
RMS is stowed outside of the Cargo Bay envelope on the port longeron and is 
charged to Orbiter weight. 



STATUS 

The RMS is an integral part of the STS. 

CONTACTS 

Source: SPAR, Canada (416)745-9680 Telex: 065-27360 
Operational: R. Zaguli, NASA/JSC/DF441, (713)483-0887 



121 



REMOTE MANIPULATOR SYSTEM 



REFERENCES 

Level II Program Definition and Requirements, Vol. 14, Space Shuttle System 
Payload Accommodations, Rev. G, Attachment 1. JSC-07700, ICD-2-19001, 

May 1983^ 
RMS Design Definition Report, Issue E. SPAR-R.776. 
Shuttle Orbiter/Cargo Standard Interfaces. ICD-2-19001. 



Technical Information 



Length 



Weight 



Positioning Accuracy 
(within reach envelope) 



Payload Release 



Design Limit Load 



Payload Characteristics 



50 ft 



905 lb (add 28 lb for elbow camera) 



± 2 in. + 1' 



± 5° attitude 

<0.015° per sec relative delta v 

Approx 0, 1 to 1.0 ft/sec delta v 



Torsional moment about longitudinal axis 

of end effector: 750 ft-lb 

Bending moment to end effector: 

1200 ft-lb 

Shear force associated with bending 

moment: 50 lb 



Maximum size: 15 ft diameter by 60 ft 

long cyl inder 

Maximum nominal payload weight: 

32.000 lb 

Maximum contingent payload weight: 

65.000 lb 




1. Shoulder yaw |oint 

2. Shoulder pitch 

3. Shoulder elect, comp 

4. Upper arm boom 

5. Elbow elect, comp 



Components 

6. Elbow joint 

7. Lower arm boom 

8. Wrist fwd elect, comp 

9. Wrist pitch joint 

10. Wrist yaw joint 



qjBrtjjx] 



8— | — 9— ]-1 0-f-11-|—12— f-13-] 



11. Wrist aft elect, comp 

12. Wrist roH 

13. Standard end effector 

14. CCTV Camera and viewing light - wrist location 

15. CCTV Camera with pan/tilt unit - elbow location 



(Figure shows shoulder pitch joint rotated through 90" from stowed position) 



122 



Remote Manipulator System Module Servicing Tool 




OVERVIEW 

The Remote Manipulator System Module Servicing Tool (RMS MST) is a device to 
permit remote on-orbit exchange of Orbital Replacement Units (ORUs) when it 
is coupled to the RMS. It develops high torques, up to 160 ft-lbs, with 
provision for torque takeout and transporting of multimission modular 
spacecraft (MMS) and other compatible ORUs. The tool is controlled and 
operated from the Space Shuttle Aft Flight Deck. The RMS MST is modelled 
from an extravehicular activity (EVA) astronaut operable tool used for the 
same purpose (see "Module Servicing Tool"). 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The RMS MST retains an internal MMU battery to power its bolt and latch 
motors. Remote control can be performed either by manual or automated 
modes. Pickup and restowing of the tool is performed by use of the RMS 
grapple to an electrical grapple fixture at the rear of the tool. The 
electrical umbilical accommodates command and telemetry functions. 

STATUS 

Electrical and mechanical design modifications to a prototype EVA MST are 
underway which will permit remote control of the tool. Johnson Space Center 
is defining the interface control document and developing a flight- 
releasable electrical grapple fixture for general applications. A companion 
holster, to be used for mounting the RMS MST on the MMS Flight Support 
System or other structural cradle, is also undergoing development. 



CONTACTS 

Source: R. E. Davis, NASA/GSFC SSP/Code 408.0, (301)286-2260 
Operational: R. E. Davis, NASA/GSFC SSP/Code 408.0, (301)286-2260 



123 



REMOTE MANIPULATOR SYSTEM MODULE SERVICING TOOL 



Technical Infor ition 



Part Number 



Weight 



Power 



Status 



Materials 



Temperature 
Range 



Pressure 



Operations 



TBS 



Approx. 90 lbs. 



Integral 17 VDC MMU 
battery/28 VDC contr/TML 



Phase B design MODS and 
phase D EVA MST hardware 



Structure - aluminum 



-50 to +100 deg. F; 
degr -100 to +250 deg. F 



Min. 10" 10 Torr 



Intermittant over 4 yrs 
with minor servicing 



Interface Details 


Interface 
Device 


RMS Lt-Wt Fit releasable 
electrical grapple fixture 


Precapture 
Misal ignment 
L lmi ts 


4" pitch/yaw radius 

4" axial 

+/- 15 deg all attitudes 


Electrical 
Connector 


51-contact modified sub- 
miniature "D" connector 


Cable Type 


Interconnections via RMS 
wiring to Aft Fit Oeck 


Type OPNS 


Mission specialist contrs RMS 
and MST from Aft Fit deck 
controllers /pane Is 


Contacts 
Assignment 


Per JSC document TBS 



Grapple 
fixture 



-Target 



Adapter plate 



Adapter plate 
bracket assemblies 




G&H 
Connector 



Existing MST 
less handles 



Adapter 

plate 

stiffeners 



Controller and 
trickle charge 
electronics 



124 



Remotely Operated Electrical Umbilical 




OVERVIEW 



The Remotely Operated Electrical Umbilical (ROEU) provides a remateable 
electrical disconnect that can accommodate a full 1/4 SMCH (R.F, ML, HO and 
Power). 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

Mounts on port or starboard bridge rail with a maximum 1.5 inch intrusion 
into the 180 inch payload envelope. Provides self alignment of orbiter and 
payload portions of the disconnect and accommodates orbiter/payloadv relative 
motions. Essentially zero load imparted to payload during mate/de-mate 
operations. 

Two units (1 port and 1 starboard) to be fabricated, flight qualified and 
delivered to NASA. 

STATUS 

Flight units to be delivered in 1988. 

CONTACTS 

Source: Rockwell International, 12214 Lakewood Blvd., Downey, CA 90241 
Operational: C. W. Anderson, RI, (213)922-5095 
R. L. Gasteiger, (213)922-5339 



125 



REMOTELY OPERATED ELECTRICAL UMBILICAL 



Technical Information 


Weight 


65 pounds 


Power Req 


28V dc 


Temp Range 


100° F to ♦ 250° F 


Cool ing 


N/A 


Material 


Aluminum 


Status 


In final manufacture 6/87 



Interface Details 


Electrical 


See Design Requirements 
Doc. STS-85-0121 


Mechanical 


See Design Requirements 
Doc. STS-85-0121 


Data Rate 


N/A 


Documentation 


Design Requirements Doc. 
STS-85-0121 



EVA Access Cover release 




Drive rod 



— Hook drive 
bellcrank 



-Hook (unlatched position) 
-Alignment guides 



EVA Access cover 
(latch drive)' 



-Orbiter disconnect mech 



Elec wire 
support 

Arm drive assembly 
(positioning mech) 



Force 

control 

bungee 



Arm drive 
actuator 



Elec connector 
support panel 




Actuator link 
arm drive 



126 



ORIGINAL PAGE 
BLACK AND WHITE PHOTOGRAPH 



Retractable Tether 




S85-39485 



OVERVIEW- 



Retractable tethers are used to restrain tools and small equipment stowed on 
tool boards and tool caddies for use during EVA. Tethers consist of a take- 
up reel enclosed in a housing, a 3-foot or 6-foot Kevlar tether line, and a 
swivel hook or hooks to secure tools and equipment. The 6-foot tether 
design incorporates a velocity limiting feature. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The retractable tether extends and retracts smoothly, with no more than 0.6 
pounds of retracting force. A French hook is sometimes fixed to the swivel 
hook to permit release of a tool from the retractable tether. 

STATUS 

Flight qualified. Flown on all STS flights. 

CONTACTS 

Source: M. Withey, ILC Space Systems, (713)488-9080 
Operational: R. C. Trevino, NASA/JSC/DF, (713)483-2597 



127 



RETRACTABLE TETHER 



Part Number 



Weight 



Material 



Retracting Force 



Cord Breaking 
Strength 



Quantity Flown 



Stowage 



Technical Information 



10153-20004-01 Vespel case 
10153-20004-02 aluminum case 
10156-20027-02 aluminum case 



0.14 lb 



Case-01 - aluminum allow 

Case-02 - Vespel 

Tether - 400 Denier Kevlar cord 



0.6 lb 



100 lb 



Varies, used on tool caddies or tool boards 



Assembly dependent 



Dimensional Data 


A 


0.79 in. 


B 


1.24 in. 


C 


2.31 in. 




128 



RMS - Based Handling and Positioning Aid 




X = 679.50 



X = 937.06 



OVERVIEW 

The RMS-Based Handling and Positioning Aid (RMS/HPA) is a mechanical arm 
which provides a wide range of adjusable work stations both inboard and 
outboard of the Orbiter Cargo Bay. It is derived from Remote Manipulator 
System (RMS) technology. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The RMS/HPA is a mechanical arm attached to the Orbiter starboard -longeron 
which will support, maneuver, and position payloads to permit inspection, 
servicing, construction, and repair. The design is modular and may be 
developed with up to six degrees of freedom; the four- joint version is shown 
above. It will be fitted with the RMS Standard End Effector or Special 
Purpose End Effector as a payload interface. 

The shoulder yaw and shoulder pitch joints will be connected to the wrist 
pitch joint by a carbon composite boom. The RMS/HPA will be approximately 
22 ft long to maintain the existing Manipulator Positioning Mechanism 
(MPM)/Manipulator Retention Latch (MRL) support equivalent to the Remote 
Manipulator System. 

The RMS/HPA will be mounted on the starboard side of the Orbiter in the 
position designated for the starboard side RMS. It will be maneuvered on a 
joint-by- joint basis with brakes applied when a joint is not commanded to 
move. The single- joint, direct-drive, and back-up modes will be controlled 
from the RMS display and control panel. 



STATUS 

The RMS/HPA is a concept that was developed through critical design review. 
The system utilizes existing flight qualified hardware. 



129 



RMS - BASED HANDLING AND POSITIONING AID 



CONTACTS 



Source: Spar Aerospace Limited, Remote Manipulator Systems Division, 
1700 Ormont Drive, Weston, Ontario, Canada M/L 2W7 

Operational: B. Fuller, Spar, (416)745-9680 Telex: 065-27360 
J. Lindemenn, MP, (713)483-5202. 



REFERENCES 

HPA Requirements Definition Document. SPAR, HPA-SG70L 
HPA Contract End Item Specification. SPAR, HPA-SG739. 



130 



Robocon 

OVERVIEW 

This series of subminiature connectors has been designed for robotic/ 
manipulator, hand, EVA glove, and blind-mate modes of operation for 
serviceable spacecraft, payloads, and instrumentation applications. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The connector incorporates the scoop-proof, EMI, backshell, and other 
features of the MMS S-700-42 blind-mate connector technology and includes 
the use of long-lasting, low-insertion/low-withdrawal force, low-resistance 
contacts. For the manipulator, hand, ani EVA glove modes, the connectors 
are equipped with an automatic latching mechanism which retains the mated 
connector until the release mechanism is pressed permitting easy release of 
the mated pairs. For blind-mate applications, one of the connectors halves 
is firmly mounted with the opposite half float mounted to provide a plus or 
minus ten degree and plus or minus 0.12 inch translational error without 
bending contacts. There are plans for 30, 60, & 90 contact versions as well 
as provision for coaxial, twinaxial, triaxial, and optical couplers. Models 
have been made of a larger version for space station power distribution use 
employing a flat ribbon form of interconnection. 

STATUS 

Concept models of the subminiature and power type of Robocons have been 
designed and produced by the contractor and given preliminary tests. 

CONTACTS 

Source: NASA/GSFC SSP/CODE 408.0 
Operational: R. E. Davis (301)286-2260 or 
D. R. Manges (301)286-2431 



131 



(THIS PAGE INTENTIONALLY LEFT BLANK) 



ORIGINAL PAGE 
BLACK AND WHITE PHOTOGRAPH 



Rotary Shut-Off Fluid Connector 




OVERVIEW 

The MOOG Rotary Shut-Off (RSO) design provides a fluid coupling that has 
minimal pressure loss across the unit and minimal leakage during 
connection/disconnection operations. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

Some of the features of the MOOG RSO Fluid Connector are as follows: 

Zero leakage during connection/disconnection if the purge option is 
utilized. 

Disconnect valving elements automatically open or close during act of 
connection or disconnection. 

Triple redundant o-rings seal the unit against external leakage when 
connected . _H 

Valving element seals can be checked for leakage (verified) before the 
unit is disconnected. 

Unobstructed flow path has a minimal pressure drop. 

Actuation can be accomplished by a suited astronaut with standard tools, 
by a remote manipulator arm or remotely via an optional motor. 

Once fully engaged, the disconnect forms a rigid structural as well as 
hydraulic connection. 

STATUS 

The RSO Coupler is being manufactured and tested. 

CONTACTS 

Source: MOOG Space Products Division 

East Aurora, NY 14052 
Operational: Joseph M. Cardin, MOOG, (716)667-4417 



133 



PRECEDING PAGE BLANK NOT FILMHJ 



ROTARY SHUT-OFF FLUID CONNECTOR 



Spec i f ications 



Less than 50 in. lb. force required to engage/disengage under 
full system pressure of 620 psi 



External Leakage 



Spillage 



Pressure Drop 



Cycle Life 



Engagement Torque 



Capture Force 



Stroke 



We i g h t 



Material 



1.0 x 10"8 SCCS GHe at 620 psi 



0.07 cm 1 



0.75 psid at 5.0 gpm HgO 



1000 connect/disconnect 



40 m. lbf. 



20 lbf. 



1.8 in. including capture mechanism 



1000 grams 



Aluminum 







c 

Disengage Configuration 




Engage Configuration 



134 



Safety Tether, 35-Foot 




OVERVIEW 

The 35-foot safety tether connects the 
crewmember to a slide wire along the 
cargo bay sill longeron during EVA. The 
tether consists of a reel case with an 
integral D-ring, a take-up reel, a 35- 
foot cable, and a locking hook. A 
selector on the reel case can be set to 
lock the take-up reel or to unlock it to 
allow the tether to reel out and retract. 

The locking hook on the tether 
incorporates a lock-lock feature to 
prevent accidental opening. 

OPERATIONAL COMMENTS AND 
INTERFACE PROVISIONS 

For launch and entry, the port and ^ - ^ v cc m 

starboard safety tethers are stowed in a S82-35970 

cloth-covered stowage container which is secured to the bulkhead above the 
airlock in the cargo bay. While still in the airlock, after opening the 
airlock hatch, a crewmember attaches a waist tether to the D-ring of the 
safety tether. (The other end of the waist tether is hooked to a ring on 
the EMU waist bearing.) 

A series of straps, clips, and a small capstan secures the 35-foot tether 
between the slide wire and airlock d uring launch and entry. The tether is 
secured near handrails to allow the crewmember to unstow it while moving to 
the work area and to restow it while returning to the airlock after 
finishing the EV task. 

STATUS 

Flight qualified. Flown on all STS flights. 

CONTACTS 

Source: M. Witney, ILC Space Systems, (713)488-9080 
Operational: R. C. Trevino, NASA/JSC/DF, (713)483-2597 



05 



SAFETY TETHER, 35-FOOT 



Part Number 



Weight 



Material 



Load Limit 



Retracting Force 



Takeup Force 



Quantity Flown 
Stowage 



Technical Information 



10 153-20004-01 Vespel case 
10153-20004-02 aluminum case 
10156-20027-02 aluminum case 



0.14 lb 



Housing - alumrnum, stainless steel 

Tether - stainless steel cord. 3/32-in. dia. 



Cable - 920 lb 



1.5 lb 



0.5 lb 



Two 



Payload bay X - 576 bulkhead 



Dimensional Data 


A 


8.360 in. 


B 


2.086 in. 


C 


4.490 in. 


D 


1.5 in. 


E 


5 in . 


F 


1.75 in. 




136 



SAMSIN Master-Slave Servo Manipulator 



Slave Work Station 



Master Work Station 



J 1 



Slave Motor Package 






Slave arm assembly 




Master Motor Package 
rTU— 



Master arm assembly 



Slave power and 
control cable 



Master power and 
control cable 



Slave 
control 
system 



Master-Slave 

communications ' 

cable 




OVERVIEW 

SAMSIN (Servo-Actuated Manipulator System With Intelligence Networks) is a 
bilateral force reflecting master-slave servo manipulator. SAMSIN is a 
general purpose electrical-mechanical device. (SAMSIN is a registered trade 
mark.) 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

SAMSIN is used to extend the hand and arm manipulative capacity into a 
"remote hostile" environment. A mas ter- slave manipulator is an extension of 
the human hand. The remote hand may be used as a tool, but can be used more 
effectively as the hand that holds and guides a tool. SAMSIN has seven 
degrees-of-freedom and is bilateral and force reflecting in all degrees-of- 
freedom. 

STATUS 

SAMSIN units are available on a production basis for use as engineering 
development test beds, for use in irradiation testing facility operations 
and are being specified by contractors for the DOE fuel rod consolidation 
program. On going development including/B demonstrations. 

CONTACTS 

Source: Central Research Laboratories, P. 0. Box 75, Redwing, MN 55066 
Operational: R. Adams, CRL, (612)388-3565 



137 



SAMSIN MASTER-SLAVE SERVO MANIPULATOR 



Weight 



Power Req 



Temperature 



Remote Handling Capacity 



Master Force Reflection 
Capacity 



No-Load Slewing Rate 



Technical Information 



Master arm assembly 65 lbs." 

Master motor package 170 lbs. 

Slave arm assembly 90 lbs.' 

Slave Motor Package 180 lbs. 

•includes counterbalance weights 



Master arm system 
Slave arm system 



1000 watts 
1000 watts 



0° to 55* C 



15, 20. or 50 lbs. 



15 lbs. 



40 in/sec. 



Electronics 



Electrical 



Tool 



Slave Work Station 
Mounting Interfaces 



Interface Details 



RS-232. Multibus I or II VME, or Q bus, or PC bus 



120 VAC, single phase or 
240 VAC, three phase 60 Hz. 



Remotely interchangeable tong jaws for alternate end 
effectors or tools 

Universal mounting plate attachment provided 
on motor pkg. 



Master Arm Assembly 
(Arm Fully Retracted) 



20 

DIA 
16 1/2 
DIA 

J. 



_!_ 



4r 



-11 V4 — 

— Ml/!- 



¥ 



m 



5 ■• 



Miller Motor Package 




Slave Arm Assembly 
(Arm Fully Retracted) 



so 

DIA 



16 1/J 
OIA 

± 



O- 1 



"b 



Dimension Value (inche*) 



«^L 



Sieve Motor Package 



¥ 



138 



Satellite Checkout Equipment 



OVERVIEW 




The Satellite Checkout Equipment provides checkout/diagnostic capability for 
payloads prior to launch, on-orbit deployment or during maintenance/repair. 
Operates independent of orbiter systems except for power and uplink, if 



Operates 
required 



OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

Payload bay mounted main computer with orbiter cabin displays and controls 
utilizes standard interfaces with payload. 

Utilizes orbiter data links to accommodate customer ground compiled test 
sequences to be executed on-orbit. 



STATUS 
Concept 

CONTACTS 

Source: Rockwell International, 12214 Lakewood Blvd., Downey, CA 90241 
Operational: C. W. Anderson, (213)922-5095 
R. L. Gasteiger, (213)922-5339 



139 



SATELLITE CHECKOUT EQUIPMENT 



Technical Information 




Weight 


TBO 


Power Req 


TBD 


Temp Range 


TBD 


Cool ing 


TBD 


Material 


TBD 


Status 


Concept 



Interface Details 


Electrical 


TBD 


Mechanical 


TBD 


Data Rate 


TBD 


Documentation 


TBD 



Satellite or ORU 




Customer 
site 



140 



Satellite Workshop 



Supplies 
Spares 




Folded to allow 
viewing out of 
cabin windows 



• Tools 

• Stowage 

• Checkout equipment 



Floodlights 



Isogrid 
folded floor 



OVERVIEW 

The Satellite Workshop is an expandable structure, covered with 
environmental resistant fabric surface, provides an EVA enclosure with 
environmental protection for personnel and equipment located outside the 
orbiter cargo bay during satellite servicing. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

Stowed configuration utilizes about 8 ft of cargo bay length and expands to 
approximately 26 ft x 26 ft x 26 ft on orbit. Structure contains work area 
with constant lighting, storage for tools/equipment and payload attachment 
facilities. 

EVA crew thermal/micrometeoroid garment (space suit) requirements can be 
reduced thus providing crewman increased flexibility /mobility. 



STATUS 
Concept 



CONTACTS 

Source: Rockwell International, 12214 Lakewood Blvd., Downey, CA 
Operational: C. W. Anderson, (213)922-5095 
R. L. Gasteiger, (213)922-5339 



90241 



141 



SATELLITE WORKSHOP 



Technical Information 


Weight 


TBO 


Power Req 


TBO 


Temp Range 


TBO 


Cooling 


TBD 


Material 


Aluminum/Fabric 


Status 


Concept 



Interface Details 


Electrical 


TBD 


Mechanical 


TBD 


Data Rate 


N/A 


Documentation 


TBD 




13'R 



142 



Softride Container 



Primary structure 




Trunnion 



Interface panel 



Shock & vibration control 



Container 



OVERVIEW 

The Softride Container mounted in the Orbiter cargo bay provides capability 
to carry sensitive payloads (un-ruggedized) into orbit by isolating shock 
and vibration levels to 1G. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

Container utilizes an interface panel which provides electrical/fluid 
connections to payload. Container may be environmentally controlled thus 
providing capability to install payload at the "factory" and monitor/control 
payload until it reaches orbit without the need to open container. 



STATUS 



Concept 



CONTACTS 

Source: Rockwell International, 12214 Lakewood Blvd., Downey, CA 90241 
Operational: C. W. Anderson, (213)922-5095 
R. L. Gasteiger, (213)922-5339 



143 



SOFTRIDER CONTAINER 



Technical Information 


Weight 


TBD 


Power Req 


TBD 


Temp Range 


TBD 


Cool ing 


TBD 


Material 


Aluminum 


Status 


Concept 



Interface Details 


Electrical 


TBD 


Mechanical 


TBD 


Data Rate 


N/A 


Documentation 


TBD 



■180 in. Dia Cargo bay 

■15 in. Excursion clearance 



Y&ZAxis 
Shock struts 



X Axis Shock strut 




■150 in. Dia 
Container 



15 in. Excursion clearance 
L - optional 



144 



Spacelab Pallet 



OVERVIEW 

The Orbital Flight Test (OFT) 
Pallet, called the Spacelab 
Pallet, is a specialized payload- 
carrying platform which provides 
mechanical, electrical, thermal, 
and control support to the 
attached pay load. 



OPERATIONAL COMMENTS AND 
INTERFACE PROVISIONS 

The OFT Pallet is U-shaped and 

provides hard points for mounting 

heavy experiments and a large 

panel surface area to accommodate 

lighter payload elements. The s-19-41-064 

carrier system contains a power 

distribution unit, a flex multiplexer/demultiplexer, a timing buffer system, 

a coolant pump, cold plates, necessary system plumbing and cabling, and a 

software interface to the Orbiter general purpose computer. Pallet segments 

are 3 meters in length and 4 meters in width, and they may be flown 

separately or in combination. Pallet configurations may consist of one to 

five pallet segments, and as many as three interconnected pallets can be 

supported by one set of Orbiter attachment settings. Pallets are controlled 

from the Orbiter Aft Flight Deck. 




STATUS 



Flight Qualified. 



CONTACTS 

Source: Marshall Space Flight Center 
Operational: W. Johnson, MSFC, (205)453-2121 



REFERENCES : 

OFT Pallet System Carrier, Payload Integration Plan, Rev. B, JSC-14017, 

July 1980. 
Shuttle Orbiter/Oft Pallet, ICD A-14017. 
Spacelab Payload Accommodation Handbook, Rev. 2, SLP/2104, July 1979. 



145 



SPACELAB PALLET 



Longeron 
fittings (4) 




Outer 
panel 



OFT Pallet Segment 



146 



ORIGINAL PAGE 
BLACK AND WHITE PHOTOGRAPH 



Spin-Nut Hold Down Mechanism 



OVERVIEW 

The Spin-Nut Hold Down Mechanism, 
an electric motor-driven hold and 
release, self aligning mechanism 
was developed for in-orbit 
servicing and construction. The 
mechanism, designed for use on 
spacecraft or orbiting platforms, 
comprises a motor driven, free- 
floating, nut assembly that can be 
aligned with a threaded bolt 
protruding from the mating part. 
It is ideally suited for in-orbit 
repairs and replacements that 
require secure hold down of large 
equipment modules. 



OPERATIONAL COMMENTS AND 
INTERFACE PROVISIONS 

The Spin-Nut Hold Down Mechanism 
has design advantages Including: 

• Angular, axial and lateral self-alignment during mating operation. 

• Completely remote operation to align, capture, hold and release a 
threaded protrusion on any space component. 

• Appendage can be released remotely without loss of reattachment 
capability. 

• Spar hold down equipment is available in various nut sizes and hold down 
torques, and can be supplied with either one of two drive motors that can 
be mounted to suit client configuration. 

• The mechanism also features capture/release sensors and an anti-backdrive 
interlock. 




STATUS 

Engineering model undergoing performance testing, 
flight program. 



Under consideration for 



CONTACTS 

Source: Spar Aerospace Limited, 1700 Ormont Drive, Weston, 

Ontario, Canada M9L 2W7 
Operational: B. Fuller, Spar/Business Development, 
(416)745-9680, Telex: 065-27360 



147 



SPIN-NUT HOLD DOWN MECHANISM 







Technical 


Information 




Axial 
Draw Bar 
Rating 


Mass 

(Less 

Motors) 


Motor/Nut 
Ratio 


Screw 
Size 


Nut 
Torque 


Radial 
Float 


3000 lb 

6000 lb 

20000 lb 


1.3 lb 
1.5 lb 
2.5 lb 


90:1 

255:1 

1023:1 


.500 in 
.500 in 
.750 in 


296 lb. in. 

600 lb. in. 

2680 lb. in. 


.025 in 
.024 in 
.036 in 




148 



ORIGINAL P^z 
BLACK AND WHITE PHOlutiRAPH 



Spin Table 




S83-44606 



OVERVIEW 

The Spin Table provides the capability to 
deployment from the Orbiter Cargo Bay. 



"spin-up" 



a satellite prior to 



OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The Spin Table is powered by redundant electric drive motors. Prior to 
deployment from the Orbiter, the satellite to be spun is held to the top of 
the Spin Table system by a clamp band. The clamp band is released by 
redundant bolt cutters, and separat ion spr ings on the Spin Table provide the 
initial separation impulse. In the^vent of an aborted mission after spin- 
up has been initiated, the drive motors will stop the rotation and the 
system will be returned to its original position. 

STATUS 

Flight qualified and has flown on several Shuttle missions. 

CONTACTS 

Source: McDonnell Douglas Corporation 
Operational: George Wells, MDC, (713)483-5485 

REFERENCES 

PAM-D/PAM-D11 User Requirements Document. McDonnell Douglas, MDCG6626E. 



149 



SPIN TABLE 



Technical Information 


Initial Impulse Rate 


2.5 ft/sec (minimum) 


Nominal Rotation 
Velocity 


50 rpm 


Time to Nominal 
Rotation Velocity 


80 to 80 sec 



Restraint 
fittings 



Expendable 
vehicle 



ASE 
Avionics 




Payload attach fitting 



Solid rocket motor 



Spin table and 

separation 

system 



Orbiter 
longeron 
fittings (4). 



Airborne 
support 
equipment 
(ASE) 




Orbiter kee 
fitting 



Cradle 
assembly 



150 



Stabilized Payload Deployment System 




OVERVIEW 

The Stabilized Payload Deployment 
System (SPDS) is a dual redundant 
motorized system designed to 
deploy RMS type payloads up to 
50,000 pounds that are typically 
secured in the bay with "Port" 
side and starboard Payload 
Retention Latch Assemblies 
(PRLA's) and Active Keel Assem- 
blies (AKA's). SPDS has been 
designed to operate from either 
port or starboard side of the pay- 
load bay. SPDS consists of a 
primary and a secondary pedestal 
attached to the Orbiter bridge 
fitting immediately behind each 
PRLA on the part side. Each 
pedestal consists of a payload 
interface plate, a rotary drive 
actuator, Z springs, a Y positi- 
oning mechanism, and a pyro dis- 
connect assembly. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The payload interface plate attaches to both the separable portion of the 
disconnect assembly and the payload trunnion, providing the structural 
interface between SPDS and the payload. The SPDS is controlled and acti- 
vated from the aft flight deck. There are no data or electrical connections 
between SPDS and the payload. 

The deployment sequence is: open active keel assemblies (AKA's); open port 
PRLA's (Z springs extend 2 inches); drive Y positioning mechanism to 
outboard; open starboard PRLA's; and rotate payload 114° at 1/16 RPM. 

Payload release is accomplished by firing 4 initiators attached to 3 pin 
pullers on each pedestal head assembly. Only one pin puller on each head is 
required to release the payload. Expulsion springs sized for specific pay- 
load mass and center of gravity are built into the pedestal heads. The 
springs provide a 1 inch per second expulsion rate. 

STATUS 

Flight hardware is scheduled to be available September, 1989. 

CONTACTS 

Source: Rockwell International 

Operational: R. L. Farris, NASA/JSC/DF441, (713)483-0881 



151 



STABILIZED PAYLOAD DEPLOYMENT SYSTEM 



Technical Information 



Weight 



Two peoestals, the Y drive 
wiring and panel 180 lbs. 



Secondary pedestal 



Payload interface plate 




Drive mechanism 
torque shaft 



-Yq Drive mechanism 



Payload rotary 
drive actuator - 



Yq Positioning 
bungee & linkage 



Orbiter 

disconnect 

assembly 




Primary pedestal 



152 



ORIGINAL PAGE 
SLACK AND WHITE PHOTOGRAPH 



Standard End Effector 




OVERVIEW 

The Standard End Effector (SEE) Is 
the terminal device on the Remote 
Manipulator System (RMS) arm, and 
its prime function is to capture, 
hold, and release payloads. 



OPERATIONAL COMMENTS AND 
INTERFACE PROVISIONS 

The SEE is a hollow, light-gauge 
aluminum cylinder which contains a 
remotely controlled motor drive 
assembly and three wire snares. 
The SEE drive system provides the 

abilities both to capture and 

release and to rigidize a S81-35420 

payload. The capture/release function is achieved by rotating rings at the 
end of the unit which open or close the wire snares around the payload- 
mounted grapple fixture. The captured payload is rigidized when the same 
assembly is withdrawn into the end effector, pulling the payload into full 
contact with it. The SEE is controlle d from the RMS control panel in the 
Aft Flight Deck of the Orbiter. 



STATUS 

The Standard End Effector is an integral part of the RMS. 

CONTACTS 

Source: SPAR, Canada 

Operational: Ronald Zaguli, NASA/JSC/DF, (713)483-0887 



REFERENCES 

Level II Program Definition and Requirements, Vol. 14, Space Shuttle System 
Payload Accommodations, Rev. G, Attachment 1. JSC-07700, ICD-2-19001, 
May 1983. 

RMS Design Definition Report. SPAR-R.776, Issue E. 



153 



STANDARD END EFFECTOR 



Specifications 


Length 


21.5 in. 


Diameter 


13.6 in. 


For other specifications, see RMS. 





TV/Viewing light 
envelope- 

Wrist AFT 
electronics 
compartment- 
Wrist yaw joint 



Standard 

grapple 

fixture- 



Wrist pitch joint 




End 

effector 

envelope 

Wrist roll 
joint 



Retention 

fitting 

striker 



■Retention fitting 



End Effector 



154 



Standard Umbilical Retraction-Retention System 



Swivel lnboard arm 

mounting 

bracket 



Outboard arm 



Receptacle 

swivel 

mount 




OVERVIEW 

The Standard Umbilical Retraction-Retention System (SURS) is designed to 
provide a separation system for the SPAS power and command-data electrical 
interfaces. Basic design was to provide separation capability only, 
however, remate may be accomplished by EVA. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

Mounts on port or starboard bridge rail. After separation from the payload, 
the inboard arm retracts into the outboard arm, which is then stowed and 
does not penetrate the payload envelope. 

Orb iter to payload relative motion is accommodated by a payload mounted 
monoball, the arm elbow joint, shoulder joint and rotating base. 

Command/data disconnect - 128 pins (R.F., ML and HO) 
Power disconnect - 18 pins (6 sets of 12 AWG) 

STATUS 

Successfully flown on a number of STS missions. 
5 units fabricated - 2 command/data 

2 power 



CONTACTS 

Source: Rockwell International, 12214 Lakewood Blvd., Downey, CA 90241 
Operational: C. w. Anderson, (213)922-5095 
R. L. Gasteiger, (213)922-5339 



155 



STANDARD UMBILICAL RETRACTION-RETENTION SYSTEM 



Te 


chnical Information 




Weight 


20 lbs. 


Power Req. 


N/A 


Temp Range 


75* F to + 200- F 
to + 100° F prior 
during disconnect 
operations) 


(-40° F 
to and 


Cooling 


N/A 


Material 


Aluminum 


Status 


Flight qualified 



Interface Details 


Electrical 


See ICD-A-14024 and 
ICO-2-19001 


Mechanical 


See ICD-A-14024 and 
ICD-2-19001 


Data Rate 


N/A 


Documentation 


Design Requirements Doc. 
STS81-0055 



156 



Standard Umbilical Retraction Vent System 



Solenoids 



SURVS arm 




-Vent 

disconnect 
receptacle 



Orbiter attachment 
(bridge mount) 



OVERVIEW 

The Standard Umbilical Retraction Vent System (SURVS) is an orbital vent 
disconnect system, based upon the SURS electrical disconnect system, with 
electrical plug and receptacle inserts and cabling replaced with vent 
inserts and plumbing. 

Basic design provided for separation capability only, however, remate may be 
accomplished by EVA. . • 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

Mounts on port or starboard bridge rail. After separation from the payload, 
the inboard arm retracts into the outboard arm, which is then stowed and 
does not penetrate the payload envelope. 

Orbiter to payload relative motion is accommodated by a payload mounted 
monoball, the arm elbow joint, shoulder joint and rotating base. 

Utilizes a 3/4 in. vent disconnect with a vent insert seal capable of 
maintaining a leak rate less than 10-4 standard cubic centimeters per second 
at an operating pressure (vacuum) of 0.5 PSI. 

STATUS 

One unit fabricated for the COBE program. 

CONTACTS 

Source: Rockwell International, 12214 Lakewood Blvd., Downey, CA 90241 
Operational: C. w. Anderson, (213)922-5095 
R. L. Gasteiger, (213)922-5339 



157 



STANDARD UMBILICAL RETRACTION VENT SYSTEM 



Technical Information 


Weight 


17 pounds 


Power Req 


N/A 


Temp Range 


-70° F to +200° F (-40° F to 
+100" F prior to and during 
disconnect operations) 


Cooling 


16101-10061-01 


Material 


6.5 lbs. 


Status 


6.5 lbs. 



Interface Details 


Electrical 


28 V DC. external via 
power cord 


Plug Part 


# 860547765-8P (GFE) 



158 



Strap - On Attitude Control System 







OVERVIEW 

The Strap-On Attitude Control System (SACS) provides three-axis control and 
stabilization. Capable of being attached to payload by RMS or EVA, in low 
earth orbit, or by OMV, in high/low earth orbit. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

"STRAP - ON" capability provides variety of applications: 

- Stabilize disabled satellites until repaired 

- Provides "Parking Capability" for payloads 

- Hold any object as a target 

- Holds payloads during assembly or subassembly build-up on-orbit 

STATUS 
Concept 

CONTACTS 

Source: Rockwell International, 12214 Lakewood Blvd., Downey, CA 90241 
Operational: C. W. Anderson, (213)922-5095 
R. L. Gasteiger, (213)922-5339 



159 



STRAP-ON ATTITUDE CONTROL SYSTEM 



Technical Information 


Weight 


<12C0 lb 


Power Req 


TBD 


Temp Range 


TBD 


Cool ing 


TBD 


Material 


TBD 


Status 


Concept 



Interface Details 


Electrical 


<1200 16 


Mechan ical 


Transported in Cargo 
Bay util izing 
Trunnion/Keel fittings 


Data Rate 


N/A 


Documentation 


TBD 




Modular Construction Concept 



160 



Sun Shield 




PAM 

Sunshield 
(open position) 



Thermal 

control 

system 



OVERVIEW 

The Sun Shield provides protection to sun-sensitive payloads. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The Sun Shield provides sun-impingement protection to a payload with the 
Cargo Bay doors open. The shield is retracted whenever the Cargo Bay doors 
are closed. As the Cargo Bay doors open, the shield closes automatically to 
envelop the payload as illustrated above. 

As presently conceived, the large area surface of the Sun Shield is composed 
of thin-film insulation and can be modularly adaptable to accommodate 
payloads of varying lengths. The deploy-on-orbit approach minimizes the 
weight of the unit by eliminating the need for the shield to accommodate 
structural/vibration loadings during launch. 

STATUS 

Flight qualified. Flown on specific STS flights. 



CONTACTS 

Source: MDAC, Huntington Beach, CA 

Operational: Wayne Wedlake, NASA/JSC/DF42, (713)483-2568 



REFERENCES 

Shuttle Orbiter PAM-D Class Cargo Element Interfaces. ICD-A-14005. 



161 



(THIS PAGE INTENTIONALLY LEFT BLANK) 



Trunnion Pin Attachment Device 




S84-27030 
OVERVIEW 

The Trunnion Pin Attachment Device (TPAD), mounted on the Manned Maneuvering 
Unit (MMU), is used to capture and stabilize a multimission modular space- 
craft (MMS) -type satellite. It can also be used to attach a grapple fixture 
to a satellite for connection to the Remote Manipulator System (RMS). 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The TPAD consists of three parts: the control assembly, the Primary 
assembly, and the secondary assembly. All are attached to the MMU by two 
brackets held by pip pins. The control assembly provides jaw action and 
locking control and allows the primary assembly to be detached from the 
control assembly. The primary assembly attaches the crewmember and MMU to 
the TPAD satellite for stabilization. A secondary TPAD assembly may be 
rotated up to take the place of the primary TPAD assembly in case of a 
primary TPAD failure. 



STATUS 

Flight qualified. Flown on specific STS flights. 

CONTACTS 

Source: M. Withey, ILC Space Systems, (713)488-9080 
Operational: R. C. Trevino, NASA/JSC/DF, (713)483-2597 



PRECEDING PAGE BLANK NOT FILMED 



163 




NU08AOS U\Ht 



TRUNNION PIN ATTACHMENT DEVICE 



Part Number 



Weight 



Quantity Flown 



Stowage 



Technical Information 



10169-10069 



106.5 lb 



One for STS-41B and 41C 



Flight support system locker and special 
equipment stowage assembly 



Dimensional Data 


A 


27.22 in. 


B 


23.48 in. 


C 


20.78 in. 





164 



ORIGINAL PAGE ' 
BLACK AND WHITE PHOTOGRAPH 



Universal Service Tool 



OVERVIEW 

The UST is a Spar concept for a flight 
power tool that allows changeout of the 
tool attachments on orbit. 

Designed to anchor itself to a payload, 
spacecraft module, or orbiter, the UST 
can be used to remove or tighten bolts, 
and operate latches and fasteners w hile 
reacting the resulting torque to the 
anchor points. The UST comprises a 
control module, a drive module, and 
interchangeable tool elements. 



OPERATIONAL COMMENTS AND 
INTERFACE PROVISIONS 

The UST can be operated manually by an 
astronaut (as a NASA GSFC version was 
used on the Solar Maximum Mission - 
SMM), or operated remotely when attached 
to a manipulator arm. With anchor 
latches engaged, the tool can be used to 
maneuver, position and replace modules. 



; *r f. 




— 


- -Kdp""-'-. 1 


.; 


»-v-T* 4S&T- . ] 




^^H "-- 1 







% SSslle* «.* n*3"^ »•*? "= 



The range of replaceable tool elements available with the UST provides an 
astronaut with the operational flexibility to perform a variety of module 
changeouts and repair tasks in space. EVA handgrips can be attached to the 
UST for manual operation. For remote operations the UST is attached to the 
end effector of a remote manipulator arm. 

Attached to the end effector of a remote manipulator arm, the UST has 
demonstrated, on test, its capability to carry out orbital replacement unit 
changeouts on OMV. By reacting the resulting torque to the anchor points, 
the UST can be used to remove or tighten bolts, operate latches and 
fasteners, and cut, drill and impact-chisel materials. Other design 
advantages include: 

All functions have full manual override 

Tool elements are easily exchanged 

Torque values and speeds are monitored 

Full latching/del atching verification 

Latching torque can be limited to specific value, allowing greater 
available torque capacity for del atching 

High starting torque latch-drive motor 

Independent latch-drive motors provide redundancy 



165 



UNIVERSAL SERVICE TOOL 



STATUS 

Engineer model undergoing extensive performance testing, 
qualified at this time. 



Not flight 



CONTACTS 

Source: Spar Aerospace Limited, 1700 Ormont Drive, Weston, 

Ontario, Canada M9L 2W7 
Operational: B. Fuller, Spar/Business Development, 
(416)745-9680, Telex: 065-27360 



Technical Information 


Screw Drive Motor 


riSVac induction, 400 Hz. 2 phase 
Stall Torque - 2000 lb. in. 
Running Torque - 60 lb. in. 
Running Speed - 35RPM 


Latch Drive Motor 


28Vdc - Perm. Mag. 
Stall Torque - 490 oz. in. 
Running Torque - 99 oz . in. 
Running Speed - 90RPM 


Unit Length 


26 in. 



166 



ORIGINAL PAGE IS 
OF POC? QUALITY 



Video Tape Recorder 




OVERVIEW 

The Video Tape Recorder (VTR) is used to record video signals from the 
Closed Circuit Television (CCTV) system because continuous downlink 
transmission is not presently possible. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

The VTR is an off-the-shelf recorder that has been modified for spaceflight. 
The VTR is rack mounted in the pay load equipment modules of the Aft Fli g{j^ 
Deck and is safe for crew operation in a closed-cabin environment. The VTR 
is mounted so that it can be exchanged during flight with a spare. The VTR 
has the capability to record and play back black-and-white and National 
Television Standards Committee (NTSC) color video signals. The VTR is a 
cassette type recorder for easy operation. 

STATUS 

The VTR is flight qualified. Flown on specific STS missions. 

CONTACTS 

Source: Lockheed-EMSCO, 2400 NASA RD. 1, Houston, TX 77058 
Operational: Curtis Hyman, EE2, (713)483-0188 

REFERENCES 

Space Shuttle Program Operational Video Cassette Recorder, Ground Support 
Equipment Program Requirement Document. JSC- 18690. 



167 



VIDEO TAPE RECORDER 



Technical Information 


General 


Video Recording System 


Rotary, 2 heads, helical scan system, frequency 
modulation (FM) recording 


Video Signal System 


Electrical Industries Association (EIA) black-and- white 
or NTSC color 


Power Source 


28 t 4 Vdc unregulated 


Power Consumption 


50 W (maximum) 


Weight 


50 lb 


Operating Temperature 


-10° to +55° C 


Operating Humidity 


to 80 percent relative humidity 



Video Signals 


Input 


1 VP-p, negative sync, 75 ohms balanced 


Output 


1 VP-p, negative sync, 75 ohms balanced, tip of sync 
direct current restored to Vdc 


Signal-to-Noise Ratio 


>43 dB 


Bandwidth 


-8 dB, relative to 1 MHz, at 4.2 MHz 



Audio Signals 


Input 


-9 to +13 dBm, dBm nominal 600 ohms balanced 


Output 


+27 dBm maximum, dBm nominal, 600 ohms balanced 


Frequency Response 


200 H z to 10 kH z , ±3 dB 


Signal-to-Noise Ratio 


>40 dB 



Tape Transport 


Tape Speed 


95.3 mm/sec (3-3/4 in. /sec) 


Time base Stability 


10 \is relative to a field period 


Recording Time 


30 min continuous time with KCS-30S video cassette "S" 
tape 



168 



Waist Tether 




S83-35198 
OVERVIEW 

The waist tether consists of a strip of Nomex webbing material with an 
aluminum EVA hook on each end (one hook is larger than the other). The 
fully extended tether is approximately 44 inches long including the hooks. 
The tether incorporates a load-limiting feature which allows no more than 75 
pounds to be imparted to the extravehicular mobility unit (EMU) until full 
extension of the tether occurs. If this load is exceeded, the tether will 
break, and the shock will be absorbed by the additional segment of webbing 
which allows the tether to accept loads of up to 585 pounds. 

OPERATIONAL COMMENTS AND INTERFACE PROVISIONS 

Waist tethers are used to attach the crewmember to a worksite or to tether 
an otherwise unrestrained tool to t he cre wmember. The large hook is 
attached to handrails, and the small hook is attached to an EMU waist tether 
ring. Opening of an EVA hook requires that push-to-open buttons on each 
side be depressed simultaneously while the hook is squeezed. The hook will 
spring-close as soon as it is released. The small hook opens 0.75 inch, and 
the large hook opens 1 inch. Two waist tethers are normally attached to 
each EMU. 



STATUS 

Flight qualified. Flown on all STS flights. 

CONTACTS 

Source: M. Withey, ILC Space Systems, (713)488-9080 
Operational: C. H. Armstrong, NASA/JSC/DG, (713)483-6226 



169 



WAIST TETHER 



Part Number 



Weight 



Material 



Webbing Breaking 
Strength 



Load Limit 
Before Extension 



Operational Load 
Limit 



Quantity Flown 



Technical Information 



10151-20040-04 



0.93 lb 



Nomex, webbing strap, aluminum hooks 



1400 lb 



75 lb 



585 lb 



Two for each EMU 



Dimensional Data 


A 


5.00 in. 


B 


normal - 
24.0 in. 
break-away 
50.0 in. 


C 


7.25 in. 


D 


4.00 in. 


E 


5.25 in. 


F 


1.3 in. 


G 


0.75 in. 


H 


0.7 in. 


I 


1.5 in. 


J 


2.3 in. 




r-^-iw // 




want Twmm 



MMJWTO 



170 



Zero Prebreathe EMU 






'£ ' -v 



OVERVIEW 

The Zero Prebreathe EMU is an advanced- 
development, higher-operating-pressure 
space suit system which enables crew 
members to accomplish extravehicular 
operations on a routine basis without 
the need for prebreathing. 

OPERATIONAL COMMENTS AND INTERFACE 
PROVISIONS 

Current Shuttle Extravehicular Mobility 
Unit (EMU) operation requires a minimum 
of 3.5 hours of prebreathing pure oxygen 
before extravehicular activity (EVA). 
This prebreathing denitrogenates the 
blood and prevents the crew members from 
getting the 'bends' during EVA. 

The Zero Prebreathe EMU operates at a 
suit pressure of 8 lbs per square inch 
(psi). compared to the 4.3 psi opera- 
tional pressure of the Shuttle EMU. 
Modular in construction, it consists of 
a separate hard upper torso, a hard/ 
flexible element lower torso assembly, 
and interchangeable shoulder, elbow, 
wrist, and glove assemblies. The construction features of the upper and 
lower torso assemblies vary, making use of rolling convolute, multibearing, 
and fabric joint mobility systems. Mechanical attachment of joints to 
fabric is used to increase suit integrity. Modularity allows quick and 
easy breakdown of parts for cleaning, resizing, inspection, and stowing. 
The suit provides three-axis movement for the shoulder, wrist, and hip 
joints; two-axis movement for ankle joints; and single-axis movement for the 
waist and for elbow and knee joints. 




S88-30185 



STATUS 



Presently in the technology development stage. Presently planned for flight 
by mld-1990's and will be used for on-orbit space station activities. 

CONTACTS 

Source: Hamilton Standard 

Operational: Joseph J. Kosmo, NASA/JSC/EC, (713)483-9235 



171 



(THIS PAGE INTENTIONALLY LEFT BLANK) 



APPENDIX A 
ACRONYMS AND ABBREVIATIONS 



ABS 
ACD 
ACS 
AFD 
AGF 
AKA 
AKM 
APC 
ASE 
AUC 
AWG 

BAPS 
BPC 

CCD 

CCTV 

CMD 

COBE 

CRL 

CRT 

CSA 

DFI 
DOD 
DOE 
DPC 
DSN 

EAPC 

ECLSS 

EFGF 

EGF 

EIA 

EMI 

EMP 

EMU 

EP 

EPP 

ATR 

EVA 

FM 

FSS 

FSS/SAT 

FTS 

FWD 



Antenna Bridge Structure 

Apogee Kick Motor Capture Device 

Attitude Control System 

AFT Flight Deck 

Auxill iary Grapple Fixture 

Active Keel Assembly 

Apogee Kick Motor 

Adaptive Payload Carrier 

Airborne Support Equipment 

Automatic Umbilical Connector 

American Wire Gauge 

Berthing and Positioning System 
Bridge Payload Carrier 

Charged Coupling Device 
Closed Circuit Television 

Command 

Cosmic Background Explorer 
Central Research Laboratory 
Cathode-Ray Tube 
Containerless Support Assembly 

Developmental Flight Instrumentation Carrier 
Department of Defense 
Department of Energy 
Delta Payload Ca rrier 
Deep Space Network 

Extended Adaptive Payload Carrier 
Environment Control and Life Support System 
Electrical Flight Grapple Fixture 
Electrical Grapple Fixture 
Electrical Industries Association 
Electromagnetic Interference 
Electromagnetic Pulse 
Extravehicular Mobility Unit 
Explorer Platform 
EVA Power Package 
Eastern Test Range 
Extravehicular Activity 

Frequency Modulation 

Flight Support System 

Flight Support System/Servicing Aid Tool 

Force Torque Sensor 

Forward 



PRECEDING PAGE BLANK NOT FILMID 



173 




ufiM^i-MHHWMAtt mm 



GAS Getaway Special 

GFE Government Furnished Equipment 

GN&C Guidance, Navigation and Control 

GRO Gamma Ray Observatory 

GSE Ground Support Equipment 

GSFC Goddard Spaceflight Center 

HMD Helmet Mounted Display 

HST Hubble Space Telescope 

ICAPC Increased Capability Adaptive Payload Carrier 

ICD Interface Control Document 

ILC International Latex Corporation 

IUS Inertial Upper Stage 

IVA Intravehicular Activity 

JPL Jet Propulsion Laboratory 

JSC Johnson Space Center 

LDS Laser Docking System 

LEMSCO Lockheed Engineering and Management Services Company 

LMSC Lockheed Missiles and Space Company 

LROEFU Linear Remotely Operated Electrical/Fluid Umbiliical 

LROEU Linear Remotely Operated Electrical/Umbiliical 

LWGF Lightweight Grapple Fixture 

MDAC McDonnell Douglas Astronautics Company 

MDF Manipulator Development Facility 

MEE Magnetic End Effector 

MFR Manipulator Foot Restraint 

MIL GSFC Spaceflight Tracking and Data Network Station (KSC) 

Merritt Island, Fla. (STDN Site) 

MIL Military 

ML Middeck Left 

MMH Monomethyl hydrazine 

MMS Multi-Mission Modular Spacecraft 

MMU Manned Maneuvering Unit 

MPM Manipulator Positioning Mechanism 

MPS Modular Power Subsystem 

MRL Manipulator Retention Latch 

MSFC George C. Marshall Space Flight Center 

MST Module Servicing Tool 

NASA National Aeronautics and Space Administration 

NSTS National Space Transportation System 

NTO Nitrogen Tetroxide 

NTSC National Television Standards Committee 

OFK Official Flight Kit 

OFT Orbital Flight Test 

OMV Orbital Maneuvering Vehicle 

OMV Oxygen Manual Valve 

ORU Orb iter Replacement Unit 



174 



OSCRS 
OSF 

PACS 

PAN! 

PAM-D 

PAM-D 

PBS 

PCD 

PEBW 

PED 

PFR 

PIM 

POCC 

PRLA 

PRT 

psi 

QD 

RCA 

RCS 

REU 

RI 

RMS 

RMS/HPA 

ROEU 

RSO 

SACS 
SAMS IN * 

sees 

SCE 

SEE 

SIP 

SIP 

SMCH 

SMCH 

SMM 

SPDS 

SRAD 

SSP 

STS 

SURS 

SURVS 

TBS 
TDRSS 
TLM 
TPAD 

UST 



Orbital Spacecraft Consumables Resupply System 
Office of Space Flight 

Payload active Cooling/Heating System 
Payload Assist Module 
PAM, Delta Class Spacecraft 
Payload Assist Module 
Payload Berthing System 
Procurement Control Document 
Partable Electron Beam Welder 
Platform Equipment Deck 
Portable Foot Restraint 
Payload Interface Mechanism 
Payload Operations Control Center 
Payload Retention Latch Actuators 
Power Ratchet Tool 
Pounds per Square Inch 

Quick Disconnect 

Radio Corporation of America 
Reaction Control System (Subsystem) 
Remote Electrical Umbilical 
Rockwell International 
Remote Manipulator System 
RMS-Based Handling and Positioning Aid 
Remotely Operated Electrical Umbilical 
Rotary Shut-Off 

Strap-On Attitude Control System 

Servo-Actuated Manipulator System with Intelligence Networks 

Standard Cubic Centemeters per Second 

Satellite Checkout Equipment 

Standard End Effector 

Scientific Instrument Package 

Standard Interface Panel 

Standard Mix Cable Harness 

Standard Mixed Cargo Harness 

Solar Maximum Mission 

Stabilized Payload Deployment System 

Shuttle Radiator Assembly' Demonstration 

Space Shuttle Program 

Space Transportation System 

Standard Umbilical Retraction-Retention System 

Standard Umbilical Retraction Vent System 

To Be Specified 

Tracking and Data Relay Satellite System 

Telemetry 

Trunnion Pin Attachment Device 

Universal Service Tool 



175 



VTR Video Tape Recorder 

WTR Western Test Range 

* - TRADEMARK 



176 






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