Skip to main content

Full text of "Demodulation System for Fiber Optic Bragg Grating Dynamic Pressure Sensing"

See other formats


NASA/TM— 2001-210895 




Demodulation System for Fiber Optic Bragg 
Grating Dynamic Pressure Sensing 



John D. Lekki and Grigory Adamovsky 
Glenn Research Center, Cleveland, Ohio 

Bertram Floyd 

Akima, Inc., Brook Park, Ohio 



Prepared for the 

Eighth Annual International Symposium on Smart Structures and Materials 
sponsored by The International Society for Optical Engineering 
Newport Beach, California, March 4-8, 2001 



National Aeronautics and 
Space Administration 

Glenn Research Center 



August 2001 



Available from 



NASA Center for Aerospace Information 
7121 Standard Drive 
Hanover, MD 21076 



National Technical Information Service 
5285 Port Royal Road 
Springfield, VA 22100 



Available electronically at http: / /gltrs.grc.nasa.gov /GLTRS 



Demodulation System for Fiber Optic Bragg Grating Dynamic Pressure Sensing 

John D. Lekki and Grigory Adamovsky 

National Aeronautics and Space Administration 

Glenn Research Center 

Cleveland, Ohio 44 135 

Bertram Floyd 

Akima, Inc. 

Brook Park, Ohio 44142 

Abstract 

Fiber optic Bragg gratings have been used for years to measure quasi-static phenomena. In aircraft engine applications there 
is a need to measure dynamic signals such as variable pressures. In order to monitor these pressures a detection system with 
broad dynamic range is needed. This paper describes an interferometric demodulator that was developed and optimized for 
this particular application. The signal to noise ratio was maximized through temporal coherence analysis. The demodulator 
was incorporated in a laboratory svstem that simulates conditions to be measured. Several pressure sensor configurations 
incorporating a fiber optic Bragg grating were also explored. The results of the experiments are reported in this paper. 

Keywords: Fiber, Sensor, Interferometer, Bragg Grating 

1. Introduction 

Fiber optic sensors are believed to have a significant role to play in future "smart" aerospace vehicles. The benefits of using 
fiber optic sensors become evident when a large number of sensors are required and size and weight of these sensors are 
significant issues. In airplanes or launch vehicles the number of sensors desired is increasing and, as always, the size and 
weight are to be minimized. Low weight is of extreme importance for launch vehicles as the cost for launching each pound 
into orbit is on the order of several thousand dollars per pound. 

An aircraft engine is an excellent candidate for incorporating "smart" capabilities. There are many parameters within an 
aircraft engine that, if monitored and compensated for, could produce marked improvement in efficiency and reliability. 
Some examples are liners that detect blade rub damage and compressor blades that detect cracks. The area that is of initial 
interest for using dynamic pressure measurement is the detection of engine stall or surge conditions. The sensors and sensor 
demodulation method have been examined with this particular application as the target application. 

A sensor capable of detecting stall or surge preconditions could have a significant impact in improving the efficiency of 
turbomachinery. Presently, turbomachinery is operated at conditions that are outside of a certain margin from stall 
conditions. In some circumstances operating within this margin, closer to conditions that may induce stall or surge, can 
increase engine efficiency. Smart aircraft engines capable of detecting stall or surge preconditions, and able to react to cut 
off such, is proposed as a way to realize these efficiency increases by allowing safe operation with a smaller stall margin 
[1.2]. 

It has been shown that stall conditions in turbomachinery are preceded by anomalous pressure fluctuations [3]. In the 
referenced case for example, the nominal pressure fluctuation in the diffuser due to the passage of compressor blades is 
approximately 13.8 KPa (2 psi). The stall precursors start at 0.1 seconds before the surge and have peak-to-peak amplitude 
of approximately ~>1 6 KPa (4 psi). These numbers are only characteristic of this particular machine. For other machines the 
location where stall begins and magnitude of precursors would be different. The pressure of the compressor blade wake from 
this particular machine served as the target pressure sensitivity requirement for the sensor system. The frequencies of blade 
passage and the frequencies of the stall precursors motivated the target sample frequency. While this application is the 
preferred objective, sensor configurations were examined that might not be practical for this application but are of interest for 
dynamic pressure sensing in general. 



N AS A/TM— 200 1-21 0895 



The multiplexing capability of the fiber optic Bragg grating and the fact that strain linearly modulates the reflected 
wavelength are why this sensor type was chosen for this application. The target frequency response was 500 Hz. This 
narrowed the choices of possible demodulation techniques. As a result, the scanning Fabry-Perot or other scanning 
demodulation methods were not considered due to their low frequency response. 

2. Theory of Operation 

The demodulation method chosen for the fiber optic Bragg grating sensor is an interferometer, either Michelson or Mach- 
Zehnder. The chief advantage in a Michelson or Mach-Zehnder interferometer, implemented in a fiber optic or an integrated 
optic device, is that there is very little optical power lost. An interferometer also has the benefit of having continuous 
responsivity to wavelength shifts. One disadvantage of an interferometer is the drift in sensitivity due to thermal affects. 
However, using a feedback loop to keep the output of the interferometer in quadrature can minimize this effect of drift. The 
techniques to accomplish the compensation can be found elsewhere [4,5]. 

The output signal from a classical interferometer is a function of a phase difference generated by a difference in optical paths. 
This phase difference <p is a product of the optical path difference (OPD) nAI and wavenumber k and can be expressed as 



= k flA/ . 



:d 



If OPD is kept constant, then the variation in the wavelength would lead to changes in the phase: 

d<p = dk nAI . (2) 

Interference of two optical signals with limited coherence length results in a pattern that is influenced not only by the phase 
difference but also by fringe visibility [5,6,7]. The visibility function, V, limits the maximum interferometer response to 
wavelength shift because the increase in OPD decreases the coherence between the interferometer paths. The visibility 
function is: 



V = exp 



nAI Ak 



4Vln(2) y 



(3) 



where Ak is the full width half maximum power of the optical spectrum reflected from the Bragg grating, in wavenumbers. 
This phase shift and fringe visibility has been used to evaluate optical signals reflected back from fiber optic Bragg gratings 
[4,5,6]. The current from the photo detector can be expressed as: 



i = p PV d<p. 



(4) 



where p is photo detector sensitivity, 

P is the optical power reflected from the Bragg grating. 



Substituting Equations (2 ) and (3) into Equation (4) gives an equation for the current response as a function of wavelength 
shift: 



i = p P nAI dk exp 



nAI Ak 



(5) 



It may be seen from Equation (5) that in order to maximize the sensitivity to wavelength changes, the signal degradation due 
to coherence loss from an increased nAI must be balanced with the effect of the increased nAI on the phase shift. 



NASA/TM— 2001-210895 



The interferometer output vs. wavelength shift is significantly influenced by the bandwidth of the reflected light from the 
fiber optic Bragg grating [6]. The full width half maximum (FWHM) power of the optical spectrum for the grating used was 
experimentally measured to be 0.2 nm using an optical spectrum analyzer with a resolution of 0. 1 nm. The error band of the 
spectrum analyzer gives a range of FWHM from 0. 15 to 0.25 in the measurement of bandwidth. Equation (5) was used to 
compute the sensitivity to wavelength shift for three different values of FWHM in this range. Results are shown in Figure 1 . 
From the resultant graphs, the optical path difference that will produce an interferometer with maximum sensitivity ranges 
from 2.5 mm to 4.2 mm. 



>O.I5<OPD) 

.1? i 02 (OPDl 

c 

| i o:5 (OPD) 





Normalized Interferometer Sensitivities 


1 


I 


i i 




/.•■ / 


\ N ^v 




/// 


\ \ 


(IS 


" /'/ 


\ \ - 




V 


\ 




\ v 




/ 
f i 


X 



2000 



4000 



6000 



OPD 

OPD (microns) 



FWHM 



0.15 nm 
0.2 nm 
0.25 nm 



OPD of Max. Sensitivity 



4.2 mm 
3.2 mm 
2.5 mm 



Figure 1: Comparison of normalized sensitivities for fiber optic Bragg grating reflected signals with 
FWHM of 0.15 nm, 0.2 nm and 0.25 nm. 



3. Experiment 



3.1 Determination of Interferometer Sensitivity 



Figure 2 shows the configuration in which the sensitivity of the interferometer to wavelength shift vs. optical path length 
difference was determined. The fiber Bragg grating was attached to a rectangular piezoelectric element (PZT) made of Lead 
Zirconate Titanate that had dimensions of: length 50.8mm, width 4.69 mm, and thickness 3.43 mm. The fiber was attached 
parallel to the long dimension. The material used was Navy II type of PZT with d.„ constant of 185x10" " Volts/m. The 
applied voltage had a DC component and a time periodic component. The voltage was applied in the direction of thickness. 
Thus the strain generated in the fiber by the expansion and contraction of the PZT element was mainly along the optical axis 
of the fiber. 

The PZT was driven by a 1 KHz sinusoidal signal with constant amplitude and a zero bias. The translation mirror was used 
to change the optical path difference nAl in 400 micron increments and a spectrum analyzer measured the (Volt)" Root Mean 
Squared signal. A fine adjustment of 11 Al (±1 micron) was made to find the local maximum. The maximum response 
corresponds to the quadrature point. It is this maximum signal that was recorded every 400 microns. This was repeated two 
times over a range of 8000 microns. The interferometer was taken apart between measurements in order to have two 
independent measurements. The results from both measurement sets, their average values, as well as a curve calculated from 
Equation 5 using a bandwidth of 0.2 nm are shown in Figure 3. The data sets in Figure 3 have been normalized so that the 
maximum value of optical power reaches unity. This results in a dimensionless normalized intensity response curve as a 
function of the optical path difference. Despite the fact that only two independent measurement sets were made, the results 
showed a good correlation between the two sets. 

The measured average sensitivity curve in Figure 3(b) shows good agreement to that predicted by Equation (5). The 
measured average has a peak that does fall within the range (2.5mm - 4.2 mm) predicted from the bandwidth measured. This 
peak corresponds to the one predicted for a Bragg grating reflection with a 0.16 nm bandwidth. There is enough difference 



N AS A/TM— 200 1 -2 1 0895 



between the measured average and the curve predicted from a 0.2 nm bandwidth to indicate the importance of measuring an 
interferometer's responsivity to wavelength shifts. From Figure 3(b), the measured average curve shows a peak at 4 mm and 
the calculated peak is at 3.2 mm. If an interferometer were built using the 3.2 mm nAl then there would be a 14% reduction 
in sensitivity as is shown in the comparison of the measured average to the calculated curve. 



Source 



Spectrum 
Analyzer 




1 3 1 nm Bragg Grating 



Piezoelectric 
Element 



■d— 



Translation 
mirror 







Figure 2: The experimental setup used to determine interferometer sensitivity 



1.2 



* Meas. 1 



— ■■ — Meas. 2 




2000 4000 6000 

Optical Path Difference (microns) 



1.2 




■Meas. Avg. 

■ Predicted 
0.2 nm 
Bandwidth 



2000 4000 6000 8000 
Optical Path Difference (microns) 



a) 



b) 



Figure 3: Normalized signals from interferometer as a function of the optical path difference nAl: 

a) Experimentally obtained data from two sets of measurements and their average values 

b) Comparison of the measured average response and the predicted one for optical signal with 0.2 nm bandwidth. 

The importance of measuring an interferometer to confirm a particular requirement is made apparent from the differences in 
the predicted curve and measured average curve in Figure 3(b). The measured average peak and the predicted peak have an 
n Al that is separated by 0.8 mm. The predicted curve in Figure 3 has a value of 0.9 or more over a range of approximately 
2000 microns. The range at which the measured average responsivity remains over 0.9 nm is approximately 900 microns: a 
range that is less than half that for the predicted curve. At 6000 microns nAl , both measured and predicted responsivities 
were 0.5 1 . The largest discrepancies between the measured average and predicted curve are observed at lower nAl . For 
instance, at nAl = 2000 urn the normalized measured response was 0.52 and the predicted value was 0.85. 



N AS A/TM— 200 1 -2 1 0895 



It was thought that the differences in the predicted curve and the measured average curve might be due to power variability 
caused from moving the translation mirror away from the beam splitter as shown in Figure 2. It was decided to measure the 
power from just the translation mirror path and use this information to compensate the data. The results from measuring this 
power are shown in Figure 4(a). The optical power does drop off by almost 20% as the translation mirror is moved away 
from the beam splitter and so this is a systematic error that should be compensated for. The method to compensate the data 
comes from the relation of the optical power in the two paths of a Michelson interferometer to the output. The Michelson 
interferometer's total power can be expressed in terms of the power from the fixed mirror path, /„ and the power from the 
translation mirror path, /„ by 



/ 



l f +I,+ 



2 Vf^ Y tf C ° S ^' 



(6) 



where y, f is the complex degree of coherence and $ is the phase difference of the light from the fixed path and the translation 
path [4]. 

The complex degree of coherence, y, f , decreases from one as the paths become imbalanced, so for all points other than zero, 
the third term of Equation (6) cannot be as large as the first two. The first two terms of Equation (6) represent the DC level 
upon which the power due to phase modulation oscillates. Since only the dynamic component is important only the third 
term needs to be considered. In a normalized response the intensity is compensated for by 



/ C U) = 2^7 f 7,(.v) y rf cos(0) 



/ r (.v) 



(7) 



where I, max is the maximum optical power from the translation mirror, 
and I,(x) is the optical power measured at each translation point. 

In Figure 4 (b) each of the measured data points has been corrected for power variations by multiplying the measured 
sensitivity by a correction factor equal to the square root of the maximum power measured from the translation mirror 
divided by the measured power value of each position. The correction in general only amounted to one percentage point 
correction, and did not change the location of the measured average peak sensitivity. 



I 0.8 

Q- 

-a 



o 
Z 



0.6 

0.4 

0.2 





f*>**-»-»-»3 



i v 



2000 4000 



6000 



8000 



Position (microns) 




'Meas. Avg. 

" Corrected 

Avg- 



8000 



Position (microns) 



a) b) 

Figure 4: Compensation for loss of reflected power in translation mirror path: 

a) The optical power from the translation mirror path of the interferometer as a function of position. 

b) The responsivity data corrected for translation mirror power variance. 

3.2 Sensor Operation with imposed strain 

In Figure 5 the output from the fiber optic sensor system is shown with a 5 Hz ramp function applied to the PZT. The 
dynamic voltage was 38 v p . p and there was also a 100 V DC offset applied to the PZT. A straight thin line has been added for 



N AS A/TM— 200 1 -2 1 0895 



comparison of linearity. The slightly nonlinear response is believed to be a second order effect, which becomes significant 
with large amplitude strain. This should not be a problem for pressure sensing as the strains in the fiber are expected to be of 
a low magnitude. 




50 100 150 200 250 300 

Time, msec 



350 



400 



Figure 5: The Michelson demodulated signal from piezoelectric strain. A thin straight line is added as a reference. 
3.3 Tests of the Sensor with flow imposed strain 

Since future possible applications are as an element of a pressure sensor the Bragg grating was tested in three configurations 
that are shown in Figure 6. In each configuration the strain was imposed by airflow from a pressurized nozzle that was 
chopped with a frequency of 10 Hz by an optical chopper wheel. To monitor the total pressure from the jet a pressure 
transducer was placed directly behind the fiber. In the first configuration, Figure 6(a), the fiber optic Bragg grating is held in 
tension within the flow field. The second configuration, Figure 6(b), is similar to the first, the fiber was held at tension 
within the flow but the distance between the anchor points was decreased. In the third configuration. Figure 6(c), the fiber is 
attached to a flexible membrane but in all other respects is the same as in the second configuration. This membrane offers a 
larger area exposed to the flow so the fiber is strained more from the chopped flow. 



(a) 



(b) 



Flexible 
(c) / Membrane 



x Srfl l 



V zhW 



Nozzle 



u 



Chopper Wheel 



Nozzle 



I I Chopper Wheel 



Nozzle 



D 



Chopper Wheel 



Pressurized 
Air Supply 



Pressurized 
Air Supply 



Pressurized 
Air Supply 



Figure 6: Three sensor configurations tested: 

a) Fiber held at tension between two holders with pressurized air causing pressure variations, 

b) Fiber held at tension between two holders with shorter distance between anchor points. 

c) Fiber attached to back of cylinder with flexible membrane. 



NASA/TM— 2001-210895 



In all three configurations the fiber was subjected to periodic flow variations. The oscillator)' component of total pressure 
was about 1 .75 KPa and the frequency 10Hz. Figure 7 demonstrates the pressure variations detected by the pressure 
transducer installed behind the Bragg grating. 



3 1 

$ 2 - 5 



0> 

£ 0.5 



mi fhj\ rvJ 



w! 



[jMifl 



***w^ 



rtiu 



mM 



Lvy * 



Uw 



JffcC 



50 



100 



150 200 250 300 

Time (msec) 



350 



400 



450 



500 



Figure 7: Typical signal from the pressure transducer. 



In these experiments signals from the interferometer were processed by a signal processing unit which replaced the spectrum 
analyzer in the setup described in Figure 2. The signal processing involves ratioing of a reference signal by the filtered signal 
from the interferometer. This makes the resultant signal less sensitive to intensity variations that occur in connecting optical 
cables. These processed signals are dimensionless. Figure 8 contains displays of the processed signals obtained from the 
three fiber configurations in Figure 6. 



8.06 1 




•3 8.055 - 


1 1 1 J i . i 


5> 8.05 " 


Aiiiilju klUjiAitlUrUiljimiiMj 


™ 8.045 


\wvmy\W"wflnwi 


1 8.04 


r 1 I W f 


8 8.035 - 


¥ 1 " 1 


g 8.03 " 


T T ' 


&• 8.025 - 


i 



100 



200 300 
Time (msec) 



400 500 




c 

60 



on 

-o 




100 200 300 400 500 
Time (msec) 



Figure 8: 



c) 
Processed signals obtained under pressure variations from Figure 7 for the three sensor configurations: 



N AS A/TM— 200 1 -2 1 0895 



a) Data for sensor configuration described in Figure 6(a); 

b) Data for sensor configuration described in Figure 6(b); 

c) Data for sensor configuration described in Figure 6(c). 

Analysis of the data obtained has shown that all three sensor configurations may be able to detect the total pressure 
fluctuations necessary. The second and third configurations of the sensor possess the best response to pressure pulses as is 
shown in Figure 8(b.c). The frequency response in both configurations was nominally the same as that of the pressure 
transducer. 

Higher frequency total pressure pulses have also been applied in order to examine the capability to sense higher frequencies. 
A fiber set up in the second configuration has been preliminarily tested at frequencies up to 200 hundred Hertz with a 
different nozzle geometry. Results are shown in Figure 9. 








0.02 



0.04 



0.06 0.08 

Time (sec) 



0.1 



0.12 



0.14 



Figure 9. Processed signal from interferometer detecting 200 Hz pressure variations. 

DISCUSSION 

The Michelson and Mach-Zehnder interferometers have known capabilities for fiber optic sensor demodulation. Their 
sensitivity to wavelength shift has been previously shown to be a function of the optical path length difference nAl. 
However, these interferometers are difficult to design for this application without first measuring their responsivity curve. 
This is because the error in the measurement of the fiber Bragg grating's spectral bandwidth places the nAl in a range of 
values where the responsivity will vary as much as 14%. 

The interferometer has been shown capable of demodulating slight wavelength shifts caused from pressure fluctuations 
straining a fiber within a flow field. The high sensitivity coupled with the ability to detect frequencies of the order of few 
hundred Hertz would permit detection of pressure waves associated with stall precursors in the referenced turbomachinery. 
The problem of how to configure the sensor inside a turbomachine does remain. The first and second configuration of the 
fiber in Figure 6(a,b) would be the least intrusive but may not survive for long if there is contamination within the airflow, 
such as sand that is sucked into an aircraft engine. The third configuration. Figure 6(c) simulates a configuration where the 
fiber is built into a sensor housing that would be installed within an engine. However a sensing device based on this principle 
would be a bulky one that would be more difficult to install and may have an adverse effect on the airflow within the engine. 
If the problem of how to install a fiber within a turbomachine can be solved, it appears that an interferometer would have the 
sensitivity necessary to demodulate the Bragg grating wavelength shifts. To achieve the goal of using fiber optic Bragg 
gratings to detect stall precursors, future development will be focused on sensor configurations including the use of Bragg 
gratings with axially selective sensitivity and sensor housings to secure these gratings. 

REFERENCES 

1 . 1. J. Day. "'Active Suppression of Rotating Stall and Surge in Axial Compressors," Journal of Turbomachinery, 115, pp. 

40-47. 1993. 
2. A. H. Epstein, J. E. Ffowcs Williams, and E. M. Greitzer, "Active Suppression of Aerodynamic Instabilities in 

Turbomachines", AIAA Journal of Propulsion and Power, 5, pp. 204-21 1, 1986. 



NASA/TM— 2001-210895 



3. M. Wernet and M. Bright, "Dissection of Surge in a High Speed Centrifugal Compressor using Digital PIV", 37 th AIAA 
Aerospace Sciences Meeting, Reno. 1999. 

4. M. Song, S. Yin, and P. Ruffin, "Fiber Bragg grating strain sensor demodulation with quadrature sampling ot a Mach- 
Zehnder interferometer," Applied Optics. 39. pp. 1 106- 1 1 1 1 (2000). 

5. A. D. Kersey, T. A. Berkoff. and W. W. Morey, "High-Resolution Fibre-Grating Based Strain Sensor with Interferometnc 
Wavelength-Shift Detection," Electronics Letters. 28, pp. 236-238 (1992). 

6. R. S. Weis, A. D. Kersey, and T. A. Berkoff. "A Four-Element Fiber Grating Sensor Array with Phase-Sensitive 
Detection," IEEE Photonics Letters, 6, pp. 1469-1472 (1994). 

7 M Born and E. Wolf. Principles of Optics. Ch. 10, Pergamon Press. Oxford. 1980. 

8 J R Dunphy. G. Meltz. and W. W. Morey. "Optical Fiber Bragg Gratin Sensors: A Candidate for Smart Structure 
Applications." Fiber Optic Smart Structures. Eric Udd. pp. 271-286. Wiley-Interscience. New York, 1995. 



NAS A/TM— 200 1 -2 1 0895 



REPORT DOCUMENTATION PAGE 



Form Approved 
OMBNo. 0704-0188 



Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources 
gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this 
collection of information, including suggestions for reducing this burden, to Washington Headquarters Services, Directorate for Information Operations and Reports 1215 Jefferson 
Davis Highway, Suite 1204. Arlington, VA 22202-4302, and to the Office of Management and Budget, Paperwork Reduction Project (0704-0188) Washington DC 20503 



1. AGENCY USE ONLY {Leave blank) 



4. TITLE AND SUBTITLE 



2. REPORT DATE 

August 200 1 



REPORT TYPE AND DATES COVERED 

Technical Memorandum 



Demodulation System for Fiber Optic Bragg Grating Dynamic Pressure Sensing 



6. AUTHOR(S) 

John D. Lekki, Grigory Adamovsky. and Bertram Floyd 



7. PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) 

National Aeronautics and Space Administration 
John H. Glenn Research Center at Lewis Field 
Cleveland. Ohio 44 1 35 - 3 1 9 1 



9. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES) 

National Aeronautics and Space Administration 
Washington. DC 20546-0001 



5. FUNDING NUMBERS 



WU-704-30-53-00 



8. PERFORMING ORGANIZATION 
REPORT NUMBER 



E- 12772 



11. SUPPLEMENTARY NOTES 



10. SPONSORING/MONITORING 
AGENCY REPORT NUMBER 



NASA TM— 200 1 -2 1 0895 



Prepared for the Eighth Annual International Symposium on Smart Structures and Materials sponsored by The 
International Society for Optical Engineering, Newport Beach, California, March 4-8, 2001. John D. Lekki and 
Grigory Adamovsky, NASA Glenn Research Center; and Bertram Floyd, Akima. Inc.. 2001 Aerospace Parkway, 
Brook Park. Ohio 44142. Responsible person. John Lekki. organization code 5520, 216-433-5650. 



12a. DISTRIBUTION/AVAILABILITY STATEMENT 

Unclassified - Unlimited 

Subject Categories: 06, 19. and 35 



Distribution: Nonstandard 



Available electronically at http://gltrs.grc.nasa.gov/GLTRS 

This publication is available from the NASA Center for AeroSpace Information. 301-62 1-0390. 
13. ABSTRACT (Maximum 200 words) 



12b. DISTRIBUTION CODE 



Fiber optic Bragg gratings have been used for years to measure quasi-static phenomena. In aircraft engine applications 
there is a need to measure dynamic signals such as variable pressures. In order to monitor these pressures a detection 
system with broad dynamic range is needed. This paper describes an interferometric demodulator that was developed 
and optimized for this particular application. The signal to noise ratio was maximized through temporal coherence 
analysis. The demodulator was incorporated in a laboratory system that simulates conditions to be measured. Several 
pressure sensor configurations incorporating a fiber optic Bragg grating were also explored. The results of the experi- 
ments are reported in this paper. 



14. SUBJECT TERMS 

Sensors; Optical sensors; Fiber optic Bragg gratings; Fiber; Interferometer 



17. SECURITY CLASSIFICATION 
OF REPORT 

Unclassified 



18. SECURITY CLASSIFICATION 
OF THIS PAGE 

Unclassified 



19. SECURITY CLASSIFICATION 
OF ABSTRACT 

Unclassified 



NSN 7540-01-280-5500 



15. NUMBER OF PAGES 

15 



16. PRICE CODE 



20. LIMITATION OF ABSTRACT 



Standard Form 298 (Rev. 2-89) 

Prescribed by ANSI Std. Z39-18 
298-102