WO1998036243A1 - Optical signal noise reduction for fiber optic gyroscopes - Google Patents

Optical signal noise reduction for fiber optic gyroscopes Download PDF

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Publication number
WO1998036243A1
WO1998036243A1 PCT/US1998/003096 US9803096W WO9836243A1 WO 1998036243 A1 WO1998036243 A1 WO 1998036243A1 US 9803096 W US9803096 W US 9803096W WO 9836243 A1 WO9836243 A1 WO 9836243A1
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Prior art keywords
beams
polarization
output
light
fiber optic
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French (fr)
Inventor
Sidney X. Huang
Naveen Sarma
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Honeywell International Inc
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AlliedSignal Inc
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Priority to AT98908580T priority patent/ATE207608T1/en
Priority to EP98908580A priority patent/EP0960319B1/en
Publication of WO1998036243A1 publication Critical patent/WO1998036243A1/en
Anticipated expiration legal-status Critical
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
    • G01C19/00—Gyroscopes; Turn-sensitive devices using vibrating masses; Turn-sensitive devices without moving masses; Measuring angular rate using gyroscopic effects
    • G01C19/58—Turn-sensitive devices without moving masses
    • G01C19/64—Gyrometers using the Sagnac effect, i.e. rotation-induced shifts between counter-rotating electromagnetic beams
    • G01C19/72—Gyrometers using the Sagnac effect, i.e. rotation-induced shifts between counter-rotating electromagnetic beams with counter-rotating light beams in a passive ring, e.g. fibre laser gyrometers
    • G01C19/726—Phase nulling gyrometers, i.e. compensating the Sagnac phase shift in a closed loop system

Definitions

  • This invention relates generally to fiber optic gyroscopes of ie kind discussed at length in U.S. Patent No. 5,278,631, issued January 1 1, 1994, to Hollmger et al.. for a Closed Loop Fiber Optic Gyroscope with Signal Processing Arrangement for Improved Performance, U S Patent No. 5,280,339 issued January
  • the sensitivity of an lnterferomet ⁇ c fiber optic gyroscope can be expressed as a function of the random walk coefficient of noise.
  • a significant component of the random walk coefficient is the relative intensity noise (RIN) Noise in general
  • Equation 1 yields the fluctuations within one phase space cell whose volume in configuration space is A c C ⁇ c , where c is the speed of light.
  • the first term, ⁇ n > in the ⁇ ghthand side of Eq. 1, is the shot-noise and the second term, ⁇ n> , is the excess photon noise due to the beating of various
  • the broadband radiauon is unpolarized and is observed over a detector area A during the time ⁇ , it will occupy a volume of Ac ⁇ . It follows then that there will be m phase space cells contained in this volume, such that
  • Variable p in Equation 2 takes into account the lack of correlation between photons with different polarization states. Typically, m is much greater than one. since ⁇ is much greater than ⁇ c and A is greater than A c . Since the fluctuations in noise among
  • ⁇ n 2 > m[ ⁇ n>/m + ( ⁇ n> /m) : ] (3) and, therefore,
  • ⁇ n 2 > ⁇ n> + A c t,. ⁇ n> 2 /(pA ⁇ ) (5)
  • the optical bandwidth B] and the observation time ⁇ is inversely proportional to the
  • ⁇ I> is the mean detected photocurrent
  • e is the electron charge
  • P( ⁇ ) is the power-spectral-dens lty of the light source.
  • the relative intensity noise (RIN) can be expresse ⁇ as the ratio of the photocurrent fluctuation to the product of the mean square of the D.C. current, ⁇ I > 2 , and the detector bandwidth &,.
  • the gyroscopes previously noted above utilize linearly polarized light for sensing rotational rate and therefore exhibit the RIN characteristics attendant with a system using a single polarization. It would be desirable to reduce the random walk coefficient of noise in fiber optic gyroscopes without sacrificing their accuracy.
  • Figure 1 is a schematic block diagram of a gyroscope with reduced relative intensity noise and random walk error
  • Figure 2 is a schematic block diagram of an alternative gyroscope with reduced relative intensity noise
  • Figure 3 is a schematic block diagram ot another alternative gyroscope with reduced relative intensity noise.
  • Figure 4 is a schematic block diagram of an alternative gyroscope with reduced relative intensity noise having an oDtical power balancing capability
  • the gyroscope illustrated in Figure 1 has a oroadband light source 10 which can be a laser diode, a light emitting diode (LED), a superluminescent ⁇ iode ⁇ SLD) or a superfluorescent fiber source (SFS)
  • Tne light source 10 is normallv unpolarized, producing light waves having two independent polarization states defined as the -state and the j-state (orthogonal to the p-state). and operates at some specified mean wavelengm which dictates tne operating wavelength of the oth ⁇ r components in the fiber optic gyroscope.
  • the light source 10 preferably generates
  • the output of the light source 10 provides unpolarized light to port 1 of a
  • the bidirectional coupler 20 can be a 2x2
  • the light appearing at port 3 of the coupler 20 is provided to a
  • splitter/modulator 30 which can be incorporated in an optional integrated optics
  • the splitter/modulator 30 splits the j-state polarization component light
  • splitter/modulator 30 and travel back through the coupler 20, entering at port 3 and
  • port 1 will travel back to the light source 10 and can be ignored.
  • the output of port 2 of the coupler 20 is one-half of the input to port 3, i.e..
  • This unpolarized light energy in turn is provided to a
  • a semiconductor device such as an avalanche-type or p-i-n diode
  • the output of the photodetector 60 is provided to the photodetector 60.
  • the gyroscope electronics 70 that generates an output signal, closing the loop of the
  • the feedback signal is also indicative of angular rate.
  • a closed-loop interferometric fiber optic gyroscope that accomplishes a 3 db
  • die gyroscope has an unpolarized light source 100 generating light having
  • the output of d e light source 100 provides unpolarized light to port 1 ot a
  • the bidirectional coupler 110 can be a 2x2
  • the light energy from the bidirectional coupler 110 is provided to port 1 ot A
  • polarization splitter 120 four-port polarization splitter 120, a 2x2 polarization-dependent coupler/splitter
  • One polarization component e.g., the state, is coupled from port 1 to
  • port 4 and from po ⁇ 3 to port 2 while the other component, the j-polarization state, is coupled from port 1 to po ⁇ 3 and from port 4 to port 2. If the light source 100 provides an unpolarized output, fifty percent of the light, the j-pola ⁇ zation state, will travel to port 3 and fifty percent, the -pola ⁇ zation state, will be provided to port 4.
  • the J-state polarization component appearing at port 3 of the polarization splitter 120 is provided to a splitter/modulator 130 which can be incorporated in an optional integrated optics chip, which splits the light energy into two beams and provides them to a fiber optic sensing coil 140. After travelling through the fiber
  • optic sense coil 140 the two beams recombme in me splitter/modulator 130 and travel back through the polarization splitter 120, entering at port 3 and leaving through po ⁇ 1, to po ⁇ 3 of the bidirectional coupler 110.
  • the 7-state polarization component appearing at po ⁇ 4 of me polarization splitter 120 is coupled through an optical isolator 150 and a variable optical attenuator 160, such as a Mach-Zehnder interferometer, to po ⁇ 4 of the bidirectional coupler 110.
  • the isolator 150 prevents light energy from die light source 100 leaving po ⁇ 4 of the bidirectional coupler 1 10 from entering the polarization splitter
  • the s- and -state polarization components combine in the bidirectional coupler 110 and emerge at po ⁇ 2 (and po ⁇ 1) of the coupler 1 10
  • the combined light energy is then provided to a photodetector 170
  • the photodetector 17 1"1 can be a semiconductor device such as an avalancne type or p-i-n diode The ou ⁇ ut
  • the gyroscope of Figure 3 uses a second bidirectional coupler
  • a light source 200 provides unpolarized light to po ⁇ 1 ot a first bidirectional coupler 210
  • Light energy exits the coupler 210 via port 3 and enters po ⁇ 1 of a polarization splitter 220 to provide one polarization component e.g., the s-state polarization component at po ⁇ 3 and the odier component e g , the
  • the 5-state polarization component is routed to a splitter/modulator 230 and a fiber optic sensing coil 240. On me return, die two beams recombine and travel back through the polarization splitter 220 and through the first bidirectional coupler 210. One-half of this j-state component, exiting through po ⁇ 2 of the coupler 210
  • die odier half exiting through po ⁇ I of the first bidirectional coupler 210) and the estate component appearing at po ⁇ 4 of die polarization splitter 220 are provided to
  • the s- and -state polarization components combine in the bidirectional coupler 250; the combined components emerge at po ⁇ 4 (and po ⁇ 3) and are provided to a photodetector 260
  • the ou ⁇ ut ot die photodetector 260 is provided to the gyroscope electronics 270 to generate an ou ⁇ ut signal and close the loop or the
  • gyroscope by providing a feedback signal 272 to die splitter/modulator 230.
  • the unused ou ⁇ ut at port 4 of the first bidirectional coupler 210 can be provided to a
  • the common-mode noise detector 280 receives the ou ⁇ ut generated by the common-mode noise detector 280 and provides the gyroscope electronics 270 ⁇
  • variable optical attenuator 290 can be placed in the line between po ⁇ 4 of the polarization splitter 220 and po ⁇ 2 ot the second bidirectional coupler 250 to balance the levels of the optical energy provided to the inputs to the coupler 250.
  • Polarization Adjustment - Figure 4 The arrangement of the gyroscope shown in Figure 4 permits optical Dower balancing of me two polarization components.
  • a light source 300 provides unpolarized light to po ⁇ 1 of a first bidirectional coupler 310.
  • Light energy exits the coupler 310 via po ⁇ 3 and enters po ⁇ I of a polarization splitter 320 to separate the light energy into an 5-state polarization component at po ⁇ 3 for example and a p-
  • the j-state polarization component is routed to a splitter/modulator 330 and after having been split into two beams, a fiber optic sensing coil 340 On the return the two beams recombine and travel back through the polarization splitter 320 to port 3 of the first bidirectional coupler 310.
  • the -state polarization component appearing at po ⁇ 4 of the polarization splitter 320 is coupled through an isolator 350, a variable optical attenuator 360.
  • the isolator 350 prevents light energy from the light source 300 leaving po ⁇ 4 of the first bidirectional coupler 310 from entering the polarization splitter 320.
  • Tlie combined light energy is then provided to a photodetector 380.
  • Tlie ou ⁇ ut of the photodetector 380 is provided to the gyroscope electronics 390 to generate an ou ⁇ ut signal and close the loop of the gyroscope by providing a feedback signal 392 to the splitter/modulator 330.
  • a polarization adjustment detector 400 receiving the p-state polarization component appearing at po ⁇ 2 of the second bidirectional coupler 370, enables the gyroscope to balance the s- and p-state polarization components.
  • polarization adjustment detector 400 and die gyroscope photodetector 380 are provided to a polarization signal processor 410 which compares die relative levels ot the two components and generates an error signal 412 that controls die variable optical attenuator 360.
  • a polarization signal processor 410 which compares die relative levels ot the two components and generates an error signal 412 that controls die variable optical attenuator 360.
  • common mode noise reduction can be provided
  • the unused optical ou ⁇ ut at po ⁇ 4 of the second bidirectional coupler 370 can be provided to a common-mode noise detector 420.
  • the ou ⁇ ut generated b ⁇ the common-mode noise detector 420 is in turn provided to the gyroscope electronics

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Power Engineering (AREA)
  • Optics & Photonics (AREA)
  • Electromagnetism (AREA)
  • General Physics & Mathematics (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Gyroscopes (AREA)

Abstract

The RIN (random intensity noise) component of the random walk error of a fiber optic gyroscope can be reduced by utilizing an unpolarized light signal during processing. By depolarizing the light wave modulated by the fiber optic sensing coil or combining it with the unmodulated light wave of orthogonal polarization, a 3 db reduction in RIN can be achieved.

Description

UNITED STATES PATENT APPLICATION FOR: OPTICAL SIGNAL NOISE REDUCTION FOR FIBER OPTIC GYROSCOPES
Background of the Invention
This invention relates generally to fiber optic gyroscopes of ie kind discussed at length in U.S. Patent No. 5,278,631, issued January 1 1, 1994, to Hollmger et al.. for a Closed Loop Fiber Optic Gyroscope with Signal Processing Arrangement for Improved Performance, U S Patent No. 5,280,339 issued January
18, 1994, to. Hollmger et al., for a Closed Loop Fiber Optic Gyroscope with Fine Angle Resolution: U.S. Patent No. 5,309,220, issued May 3, 1994, to Hollmger et
al., for a Closed Loop Fiber Optic Gyroscope wim Reduced Sensitivity to Electronic Drift; and U.S. Patent No. 5,504,580 issued April 2, 1996, to Hollmger et al , for a Tuned Integrated Optic Modulator on a Fiber Opϋc Gyroscope; all of which are incorporated herem by reference. More particularly, it relates to a scheme for
increasing the sensitivity of an mterferometric fiber optic gyroscope.
The sensitivity of an lnterferometπc fiber optic gyroscope can be expressed as a function of the random walk coefficient of noise. A significant component of the random walk coefficient is the relative intensity noise (RIN) Noise in general
can be described as the mean square fluctuations < Δn" > in the number ot photo-
electrons n emitted from a photodetector illuminated over an area .\ during an observation time τ. In the case of emission caused by polarized broadband light incident upon the photodetector,
< Δn2 > = < n > + < n> 2 (1)
This equation holds true where the illumination area A is less than the coherence area A,, of the source and the observation time τ is less than the coherence time τc cf
the source. For A = Ac and τ = τc. Equation 1 yields the fluctuations within one phase space cell whose volume in configuration space is AcCτc, where c is the speed of light.
The first term, < n > , in the πghthand side of Eq. 1, is the shot-noise and the second term, < n> , is the excess photon noise due to the beating of various
Fourier components within the broadband spectrum of the light source. Since the light source power at the photodetector is normally greater than 1.0 μw, the largest contributor to RIN will be the excess noise term, < n>2.
If the broadband radiauon is unpolarized and is observed over a detector area A during the time τ, it will occupy a volume of Acτ. It follows then that there will be m phase space cells contained in this volume, such that
m = pAτ/ AcXc) ( 2 ) where p is the number of polarization states (p = 2 for unpolarized light; p = 1 for polarized light).
Variable p in Equation 2 takes into account the lack of correlation between photons with different polarization states. Typically, m is much greater than one. since τ is much greater than τc and A is greater than Ac. Since the fluctuations in noise among
the m phase space cells are uncorrelated and < n > /m electrons are emitted from each cell, the total mean square fluctuations are defined by
<Δn2> =m[<n>/m + (<n> /m):] (3) and, therefore,
<Δn > = <n> + <n>7m (4)
Substituting for m using Equation 2,
<Δn2> = <n> + Act,. <n>2/(pAτ) (5)
Since the coherence time of the light source τc is inversely proportional to
the optical bandwidth B] and the observation time τ is inversely proportional to the
detector bandwidth B2, the ratio of Bj to Bi can be substituted for the ratio of τ to tc in Equation 2:
Figure imgf000005_0001
and <Δn2> = <n> + A^ <n>2/(pAB,) (') where λ A. « 1 for a Gaussian beam. Substituting the photocurrent I of the photodetector for the number n or electrons emitted, the photocurrent fluctuation is defined by
<ΔI2> = 2eB, <1> + 2B: <I>2/(pΔυ)
where <I> is the mean detected photocurrent, e is the electron charge, Δυ is the optical newidth defined by Δυ = [{P(υ)dυ]2 /[}P2(υ)dυ] (9)
and P(υ) is the power-spectral-dens lty of the light source.
The relative intensity noise (RIN) can be expresseα as the ratio of the photocurrent fluctuation to the product of the mean square of the D.C. current, < I > 2, and the detector bandwidth &,. Thus
RIN = < ΔI2 > /( < I > 2 B2) = 2/(pΔυ) ( 10)
From Eq. 10, it can be seen that the RIN of polarized light, where p = 1 , is twice that of unpolarized light (p = 2). Similarly, the contribution of RIN to the random walk coefficient is dependent on whether the detected light is polarized. There tore. the random walk coefficient will be significandy reduced when the light is not polarized.
The gyroscopes previously noted above utilize linearly polarized light for sensing rotational rate and therefore exhibit the RIN characteristics attendant with a system using a single polarization. It would be desirable to reduce the random walk coefficient of noise in fiber optic gyroscopes without sacrificing their accuracy.
Brief Description of Drawings
A more complete understanding of the present invention, as well as other objects and advantages thereof not enumerated herein, will become apparent upon consideration of the following detailed description and the accompanying drawings. wherein: Figure 1 is a schematic block diagram of a gyroscope with reduced relative intensity noise and random walk error;
Figure 2 is a schematic block diagram of an alternative gyroscope with reduced relative intensity noise;
Figure 3 is a schematic block diagram ot another alternative gyroscope with reduced relative intensity noise; and
Figure 4 is a schematic block diagram of an alternative gyroscope with reduced relative intensity noise having an oDtical power balancing capability
Description of the Invention
By depolarizing the light energy output of the fiber optic sensing coil ot the fiber optic gyroscope or by combining this energy with the unmodulated light energy of the orthogonal polarization, a 3 db reduction in RIN can be achieved. A closed- loop interferometric fiber optic gyroscope that accomplishes this by depolarizing e
output of the coil is shown in Figure 1 Tne curved interconnecting lines αenote
optical interconnections.
The gyroscope illustrated in Figure 1 has a oroadband light source 10 which can be a laser diode, a light emitting diode (LED), a superluminescent αiode <SLD) or a superfluorescent fiber source (SFS) Tne light source 10 is normallv unpolarized, producing light waves having two independent polarization states defined as the -state and the j-state (orthogonal to the p-state). and operates at some specified mean wavelengm which dictates tne operating wavelength of the othεr components in the fiber optic gyroscope. The light source 10 preferably generates
sufficient optical power so that the largest component of random walk error is the
excess or RIN-dominated noise to afford a significant, reduction of gyroscope noise.
The output of the light source 10 provides unpolarized light to port 1 of a
four-port bidirectional coupler 20. The bidirectional coupler 20 can be a 2x2
polarization-maintaining (PM), single-mode (SM) coupler with an internal coupling
ratio of approximately 50/50. Light energy entering port 1 exits the bidirectional
coupler 20 via ports 3 and 4 in approximately equal amplitudes. Similarly, light
energy entering the coupler at port 3 would exit the coupler at ports 1 and 2, again
in approximately equal amplitudes.
The light appearing at port 3 of the coupler 20 is provided to a
splitter/modulator 30 which can be incorporated in an optional integrated optics
chip, which accepts one polarization component, e.g., the s-state polarization
component, and discards the other component, e.g., the p-s ∑&e polarization
component. The splitter/modulator 30 splits the j-state polarization component light
energy into two beams and provides them to a fiber optic sensing coil 40. After
travelling through the fiber optic sense coil 40, the two beams recombine in the
splitter/modulator 30 and travel back through the coupler 20, entering at port 3 and
leaving through ports 1 and 2 of the bidirectional coupler 20. The energy leaving
port 1 will travel back to the light source 10 and can be ignored.
The output of port 2 of the coupler 20 is one-half of the input to port 3, i.e..
one-half of the reconstructed -state polarization component. It passes through a depolarizer 50, which produces an unpolarized ouφut with two uncorrelated
polarization states. This unpolarized light energy in turn is provided to a
photodetector 60. A semiconductor device, such as an avalanche-type or p-i-n diode
can serve as the photodetector 60. The output of the photodetector 60 is provided to
the gyroscope electronics 70 that generates an output signal, closing the loop of the
gyroscope by providing a feedback signal 72 to the splitter/modulator 30. It should
be understood that although the gyroscope electronics 70 produces an angular rate-
indicative output, the feedback signal is also indicative of angular rate.
A First Alternative Arrangement - Figure 2
A closed-loop interferometric fiber optic gyroscope that accomplishes a 3 db
reduction in RIN by combining the output of die fiber optic coil with the
unmodulated light energy of the orthogonal polarization is shown in Figure 2.
Again, die gyroscope has an unpolarized light source 100 generating light having
two independent polarization states.
The output of d e light source 100 provides unpolarized light to port 1 ot a
four-port bidirectional coupler 110. The bidirectional coupler 110 can be a 2x2
polarization-maintaining (PM), single-mode (SM) coupler with an internal coupling
ratio of approximately 50/50. Light energy exits the bidirectional coupler 1 10 \ ιa
ports 3 and 4.
The light energy from the bidirectional coupler 110 is provided to port 1 ot A
four-port polarization splitter 120, a 2x2 polarization-dependent coupler/splitter One polarization component, e.g., the
Figure imgf000010_0001
state, is coupled from port 1 to
port 4 and from poπ 3 to port 2, while the other component, the j-polarization state, is coupled from port 1 to poπ 3 and from port 4 to port 2. If the light source 100 provides an unpolarized output, fifty percent of the light, the j-polaπzation state, will travel to port 3 and fifty percent, the -polaπzation state, will be provided to port 4.
The J-state polarization component appearing at port 3 of the polarization splitter 120 is provided to a splitter/modulator 130 which can be incorporated in an optional integrated optics chip, which splits the light energy into two beams and provides them to a fiber optic sensing coil 140. After travelling through the fiber
optic sense coil 140, the two beams recombme in me splitter/modulator 130 and travel back through the polarization splitter 120, entering at port 3 and leaving through poπ 1, to poπ 3 of the bidirectional coupler 110.
The 7-state polarization component appearing at poπ 4 of me polarization splitter 120 is coupled through an optical isolator 150 and a variable optical attenuator 160, such as a Mach-Zehnder interferometer, to poπ 4 of the bidirectional coupler 110. The isolator 150 prevents light energy from die light source 100 leaving poπ 4 of the bidirectional coupler 1 10 from entering the polarization splitter
120. The s- and -state polarization components combine in the bidirectional coupler 110 and emerge at poπ 2 (and poπ 1) of the coupler 1 10 The combined light energy is then provided to a photodetector 170 Again, the photodetector 171"1 can be a semiconductor device such as an avalancne type or p-i-n diode The ouφut
of the photodetector 170 is provided to die
Figure imgf000011_0001
electronics 180 to generate an ouφut signal, closing the loop of the gyroscope by providing a feedback signal 182 to the splitter/modulator 130. Another Alternative Aπangement - Figure 3
The gyroscope of Figure 3 uses a second bidirectional coupler In the gyroscope of Figure 3, a light source 200 provides unpolarized light to poπ 1 ot a first bidirectional coupler 210 Light energy exits the coupler 210 via port 3 and enters poπ 1 of a polarization splitter 220 to provide one polarization component e.g., the s-state polarization component at poπ 3 and the odier component e g , the
/7-state polarization component, at poπ 4
The 5-state polarization component is routed to a splitter/modulator 230 and a fiber optic sensing coil 240. On me return, die two beams recombine and travel back through the polarization splitter 220 and through the first bidirectional coupler 210. One-half of this j-state component, exiting through poπ 2 of the coupler 210
(die odier half exiting through poπ I of the first bidirectional coupler 210) and the estate component appearing at poπ 4 of die polarization splitter 220 are provided to
ports 1 and 2, respectively, of a second bidirectional coupler 250
The s- and -state polarization components combine in the bidirectional coupler 250; the combined components emerge at poπ 4 (and poπ 3) and are provided to a photodetector 260 The ouφut ot die photodetector 260 is provided to the gyroscope electronics 270 to generate an ouφut signal and close the loop or the
gyroscope by providing a feedback signal 272 to die splitter/modulator 230.
If desired, common mode noise reduction can be provided. The unused ouφut at port 4 of the first bidirectional coupler 210 can be provided to a
common-mode noise detector 280. The ouφut generated by the common-mode noise detector 280 is in turn provided to the gyroscope electronics 270 Λ
commercially-available module matched to the photodetector 260 can be emploved as the common-mode noise detector 280.
As a further refinement, a variable optical attenuator 290 can be placed in the line between poπ 4 of the polarization splitter 220 and poπ 2 ot the second bidirectional coupler 250 to balance the levels of the optical energy provided to the inputs to the coupler 250.
Polarization Adjustment - Figure 4 The arrangement of the gyroscope shown in Figure 4 permits optical Dower balancing of me two polarization components. A light source 300 provides unpolarized light to poπ 1 of a first bidirectional coupler 310. Light energy exits the coupler 310 via poπ 3 and enters poπ I of a polarization splitter 320 to separate the light energy into an 5-state polarization component at poπ 3 for example and a p-
state polarization component at the odier poπ, poπ 4.
The j-state polarization component is routed to a splitter/modulator 330 and after having been split into two beams, a fiber optic sensing coil 340 On the return the two beams recombine and travel back through the polarization splitter 320 to port 3 of the first bidirectional coupler 310.
The -state polarization component appearing at poπ 4 of the polarization splitter 320 is coupled through an isolator 350, a variable optical attenuator 360. and
a second bidirectional coupler 370 to poπ 4 of the first bidirectional coupler 310.
The isolator 350 prevents light energy from the light source 300 leaving poπ 4 of the first bidirectional coupler 310 from entering the polarization splitter 320.
The s- and -state polarization components combine in the first bidirectional coupler 310 and emerge at port 2 (and poπ 1). Tlie combined light energy is then provided to a photodetector 380. Tlie ouφut of the photodetector 380 is provided to the gyroscope electronics 390 to generate an ouφut signal and close the loop of the gyroscope by providing a feedback signal 392 to the splitter/modulator 330.
A polarization adjustment detector 400, receiving the p-state polarization component appearing at poπ 2 of the second bidirectional coupler 370, enables the gyroscope to balance the s- and p-state polarization components. The ouφut ot the
polarization adjustment detector 400 and die gyroscope photodetector 380 are provided to a polarization signal processor 410 which compares die relative levels ot the two components and generates an error signal 412 that controls die variable optical attenuator 360. Again, if desired, common mode noise reduction can be provided The unused optical ouφut at poπ 4 of the second bidirectional coupler 370 can be provided to a common-mode noise detector 420. The ouφut generated b\ the common-mode noise detector 420 is in turn provided to the gyroscope electronics
390.
While there has been described what is believed to be the preferred embodiment of the invention, those skilled in the an will recognize that other and
further modifications may be made thereto without depaπing from the spirit of the invention, and it is intended to claim all such embodiments diat fall within the true scope of the invention.

Claims

What is claimed is:
1. An apparatus, comprising: a broadband light source for generating an unpolarized light wave output; polarization-splitting means for splitting at least a portion of the light wave output into first and second polarization components, one orthogonally oriented with respect to the other; means for modulating one polarization component of the light wave output; and means for combining the modulated polarization component with the other polarization of the light wave output.
2. An apparatus as set forth in claim 1, where die means for modulating comprises a sensing coil and splitter/modulator means for splitting one of die polarization components of me light wave ouφut into two beams, and for providing the two beams to me sensing coil and receiving the beams from the sensing coil, modulating one of me beams, and recombining the two beams.
3. A fiber optic gyroscope for sensing angular rate, die gyroscope having a fiber optic sensing coil for carrying light beams in opposing directions, comprising: a broadband light source for generating a light output; polarization splitting means for splitting at least a portion of the light output into first and second components, one orthogonally oriented with respect to the other; splitter/modulator means for splitting one of the components of the light output into two beams, providing the two beams to the sensing coil and receiving the beams from the sensing coil, modulating one of the beams, and recombining the two beams to provide an output; coupler means for combining the output of the splitter/modulator means and the other of the components of the light output; detection means, responsive to the coupler means, for detecting the recombined beams and providing an output proportional to the magnitude of the recombined beams; and processing means for generating a feedback signal in response to the output of the detector and providing the feedback signal to splitter/modulator.
4. A fiber optic gyroscope as set forth in claim 3, further comprising means, responsive to the light output, for detecting common mode noise.
5. A fiber optic gyroscope as set forth in claim 3, further comprising polarization adjustment means, responsive to the other of d e components of me light output, for balancing the first and second components.
PCT/US1998/003096 1997-02-14 1998-02-12 Optical signal noise reduction for fiber optic gyroscopes Ceased WO1998036243A1 (en)

Priority Applications (3)

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DE69802166T DE69802166T2 (en) 1997-02-14 1998-02-12 REDUCTION OF OPTICAL SIGNAL NOISE FOR A FIBER OPTICAL GYRO
AT98908580T ATE207608T1 (en) 1997-02-14 1998-02-12 REDUCING OPTICAL SIGNAL NOISE FOR A FIBER OPTICAL GYRO
EP98908580A EP0960319B1 (en) 1997-02-14 1998-02-12 Optical signal noise reduction for fiber optic gyroscopes

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EP2251641A1 (en) * 2009-05-11 2010-11-17 Honeywell International Inc. Systems and methods for effective relative intensity noise (rin) subtraction in depolarized gyros
JP2019522218A (en) * 2016-06-20 2019-08-08 イクスブルー Measuring system and gyroscope including such system

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DE69802166T2 (en) 2002-11-28
US5898496A (en) 1999-04-27
EP0960319A1 (en) 1999-12-01
ATE207608T1 (en) 2001-11-15
EP0960319B1 (en) 2001-10-24
DE69802166D1 (en) 2001-11-29

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