COMPACT RESONANT OPTICAL GYROMETER WITH THREE FREQUENCIES

专利摘要:
The invention relates to a resonant passive optical gyro (50) comprising a cavity (C) and operating with three frequencies, and comprising: a first injection laser (L1) configured to inject a first optical beam (F1) into the cavity in a first direction, a second injection laser (L2) configured to inject a second optical beam (F2) into the cavity in a direction opposite to the first direction, - a third injection laser (L3) configured to inject a second third optical beam (F3) in the cavity according to one of the two aforementioned directions, a laser among one of the injection lasers being chosen as master laser (L1) having a master frequency (f1), the other two laser injection being denoted respectively first (L2) and second (L3) slave lasers respectively having a first (f2) and a second (f3) slave frequency, -a master servo device (DA1) -a first servo stage comprises nt a first (D2) and a second (D3) slave device, - a second servo-control stage comprising a first (OPLL2-1) and a second (OPLL3-1) optical phase locking device respectively comprising a first (Osc2 ) and a second oscillator (Osc3) configured to generate a first and a second radiofrequency offset signal.
公开号:FR3050025A1
申请号:FR1600581
申请日:2016-04-06
公开日:2017-10-13
发明作者:Sylvain Schwartz；Gilles Feugnet；Arnaud Brignon；Fabien Bretenaker
申请人:Centre National de la Recherche Scientifique CNRS；Thales SA；Ecole Normale Superieure de Cachan；
IPC主号:

专利说明:

Compact resonant optical gyrometer with three frequencies DOMAINE DE L'INVENTION
The field of the invention is that of optical gyrometers, used in particular in the field of inertial navigation. More precisely, the field of the invention is that of resonant passive optical gyrometers.
STATE OF THE ART
Optical gyrometers are based on the principle of measuring the Sagnac effect. The latter induces, under the effect of a rotation, a difference in travel time between two electromagnetic signals propagating in opposite directions along a ring path. This difference in travel time, proportional to the angular velocity of the device, can be measured either as a phase difference in the context of an interferometric assembly or as a difference in natural frequency between the two counter-rotating modes of a cavity. ring.
In the first case, it is necessary to use an optical fiber to maximize the length of the interferometer and therefore the sensitivity of the device. This is called an optical fiber interferometric gyrometer, known by the acronym "l-FOG".
In the second case, the difference between the eigenfrequencies of the modes of the cavity can be measured in two ways. The first is to use an active cavity, that is to say containing an amplifying medium and measure the difference in frequency between the counter-rotating modes emitted by the cavity. We then speak of gyrolaser or "RLG", acronym for "Ring Laser Gyro". The second way is to use a passive resonant cavity and probe the eigenfrequencies of contrarotative modes using a laser. This is called a resonant passive gyro.
The resonant passive gyro has a number of advantages over its competitors. Compared to the RLG, it is notably free from the need to use a gaseous amplifying medium and the high voltage electrode system which is usually associated with it. Compared to the I-FOG, it has the advantage of a much shorter optical path that provides a lower sensitivity to the environment and a greater compactness. Finally, it involves only standard components. This avoids, in particular, the use of superluminescent source.
However, while these three types of gyrometers, l-FOG, RLG and resonant passive gyro have all been experimentally demonstrated, currently only the first two have led to industrial applications. A hindrance to the development of the resonant passive gyro is due to the problem of backscattering of light, which creates couplings between counter-rotating modes, which creates a non-linearity of the frequency response, resulting in a "blind zone" as on the gyrolasers and degrades system performance.
A solution to the problem of the coupling between contrapropagative modes is described in the document FR 1302311. This system probes the eigenfrequencies of the counter-rotating modes of a ring cavity by overcoming the problems usually created by the backscatter, while simultaneously providing a measurement. the cavity length for evaluating (and possibly slaving to a constant value) the scale factor of the resonant passive gyro thus produced.
The principle of this system is to use three beams at three different frequencies (instead of two in conventional gyrometers). The system has a ring cavity and a laser which is divided into three beams of different optical frequency. By way of example, the cavity may consist of a hollow fiber to limit the Kerr effect. Each frequency is separated from the other two frequencies by a value corresponding to an integer multiple of the free spectral interval of the cavity. The free spectral interval ISL of the cavity is classically worth: ISL = c / L c being the speed of light and L the optical length of the ring cavity.
The first beam is slaved to one mode of the cavity in one direction of propagation and the other two are slaved to two other modes of the cavity corresponding to the opposite direction of propagation. It should be noted that it is also possible to perform the inverse servocontrol, that is to say, to slave a first natural frequency corresponding to a first mode of resonance of the cavity at the first frequency of the first optical beam, in enslaving the length of the cavity for example.
The frequencies of the three beams are at each moment sufficiently distant that the effect of the couplings between the beams can be rendered inoperative.
In the absence of rotation, each beam is slaved on a different natural frequency of the cavity that is noted; fi = Ni.c / L for the first beam; f2 = N2.c / L for the second beam; f3 = N3.c / L for the third beam; with Ni, N2 and N3 two-to-two integers different and known.
The frequencies must be close enough so that the difference between the frequencies of each pair of beams can be compatible with the bandwidth of a photodiode.
In the presence of a rotation, the difference of frequencies of the two beams propagating in the same direction gives access to the length of the cavity, whereas the difference of frequency between two contrarotating beams combined with the information on the length of the cavity gives access to the angular velocity of the whole.
Thus a gyroscope operating with 3 frequencies comprises means for measuring the difference in frequencies of the two beams propagating in the same direction, and the difference in frequency between two counter-rotating beams, these two frequencies combined together making it possible to go back to the length of the cavity and at the angular velocity of the cavity along an axis perpendicular to the cavity. To simplify the discussion these conventional measuring means are not shown in the figures.
Indeed, in the presence of a rotation, the eigenfrequencies are shifted by an amount Ω proportional to the angular velocity, which gives: fl = Ni.c / L + Ω / 2; β = N2.C / L - Ω / 2: Î3 = N3.C / L-Q / 2
The length of the cavity is then known at each instant by measuring the difference in frequency Afp between the beams propagating in the same direction, ie in the above example Af2-3:
The speed of rotation is deduced by measuring the difference in frequency Afcp between two beams propagating in the opposite direction, ie in the above example Afi_2:
The architecture proposed in FR 1302311 is shown in FIG. 1 with mirrors. Solid lines correspond to optical paths, and dashed lines refer to electrical connections. The laser L emits a beam which is divided into three beams F'1, F'2 and F'3. To simplify the presentation the measuring means Afp and Afi_2 are not shown. F'1 is for example injected into the annular optical cavity C of length L in the anticlockwise direction or "CCW", an acronym for Counter Clock Wise in English, while the two beams F'2 and F ' 3 are injected into the cavity in a clockwise direction, "CW" acronym for Clock Wise "in English. The portion transmitted through the coupler 10 (partially reflecting mirror) of the beams F'2 and F'3 pass through the optical fiber and are reflected by the optical coupler 11, then the coupler 10, so as to form the cavity. The part transmitted through the coupler 11 of the bundle F'1 passes through the optical fiber and the coupler 11, and is reflected by the coupler 10 so as to constitute the cavity. At resonance, the retroreflected intensity at the cavity output is minimal, and this property is used to control the frequencies of the three beams on the eigen modes of the cavity. For example, the beam 101 reflected by the coupler 11 towards the bottom of FIG. 1 is used to slave the frequency of F'I. It corresponds to the coherent superposition of the portion of the beam F'1 directly reflected by 11 and the portion constituted by the beams propagating in the cavity in the CCW direction, which result from the superposition of the beams having made one, two, three. ... turns the cavity in the CCW direction. Similarly beams 102 and 103 going upwards in Figure 1 are used respectively to slave the frequencies of F'2 and F'3. They correspond to the coherent superposition of the portion of F'2 and F'3 directly reflected by the coupler 10 and portions of F'2 and F'3 transmitted by this coupler 10, then propagating in the cavity in the CW direction , then reflected by 11 and finally transmitted by 10, corresponding to the superposition of the beams having made one, two, three, etc. .... turns of the cavity in the CW direction.
The beam F'1 is slaved to a specific mode of the cavity by a direct feedback on the laser L using the photodiode PhDI and the servo device DA'I, which has an optical portion DA'ol and a electric part DA'el.
The beams F'2 and F'3 are slaved on eigen modes of the cavity using the photodiode PhD23 and servo devices DA'2, DA'3, each having an optical part acting directly on the optical frequency (DA'o2, DA'o3) and an electrical part (DA'e2, DA'e3).
More generally, one of the beams has a natural frequency maintained at resonance by a direct control on the laser, according to the non-limiting example the beam F'1 (but this could be one of the other two beams) according to an option Optl illustrated in FIG. 2. According to another option Opt2 illustrated in FIG. 3, the frequency of the beam F'1 is maintained at resonance by directly slaving the length L of the cavity, for example by means of a piezoelectric modulator.
We will now explain how the direct control on the laser is performed, as shown in Figure 2. The beam F'1 passes through a phase modulator PMI to generate sidebands or "side bands" necessary to obtaining a frequency error signal ε1 enabling the frequency to be servocontrolled to obtain (absence of rotation) or to conserve (presence of rotation) the frequency of the beam F'1 resonating with the cavity mode considered. This method is based on the so-called Pound Drever Hall technique, named after its inventors and well known to those skilled in the art.
The beam 101 is modulated by a phase modulator PMI, placed in the optical part DA'ol, so as to create lateral components, "side-bands", in frequency, separated from the initial frequency f1 by multiples of the frequency of modulation, fmi, applied by the oscillator Osl via PMI. This frequency is chosen, if possible, to be larger than the width of the resonance of the cavity (and smaller than the free spectral interval of the cavity) so that the sidebands are not resonant with the cavity. To simplify the explanation, we considered only the first two side-bands, separated by ± fmi from the initial frequency f1. The beam 101 (which therefore has three spectral components at f1-fmi, f1 and f1 + fmi) is detected on a PhDi photodiode whose output signal is demodulated by the modulation signal applied to PMI with an adjustment of their respective phases. (Dphi phase shifter) requiring the use of an electric mixer Ml. A low-pass filter (not shown) then makes it possible to keep only the DC component of the demodulated signal whose amplitude, ε1, is then proportional to the difference between the frequency f1 of the laser and the resonance frequency of the cavity. Indeed, when the frequency f1 of the laser and the resonant frequency of the cavity deviate a little, the two side-bands are unchanged (if they are well off resonances) while the phase and amplitude of the beam at the frequency fl evolve (since it is no longer resonant). The coherence properties between the three spectral components of 101 then allow a measurement of these fluctuations (three-beam interference) which result in this linear variation of the demodulated signal which can thus be used as a frequency error signal, ε1 s canceling when the beam F'1 is resonant with a mode of the cavity. This feedback is then carried out by means of feedback electronics ER1 according to the conventional control methods, for example, without being restrictive, with feedback electronics PI or PID for Proportional Integral Derivative, allusion to the three modes of control. action on the error signal of the feedback electronics. This type of feedback making it possible to converge the error signal to a zero value is well known in automatic mode.
Regarding the choice of the modulation frequency to be applied to PM1, if the fineness of the cavity is large, the width of the cavity will be small in front of the free spectral range and the modulation frequency can be chosen very large compared to the frequency width of the resonance peaks of the cavity. We will then be in the optimal situation, corresponding to the above explanation, for this servocontrol. A Γ opposite, if the fineness of the cavity is not very large, the modulation frequency will be close to the frequency width of the resonance peaks of the cavity. The sidebands are then partially modified when the frequency f 1 deviates from the resonance and the servocontrol is less efficient.
The servo loop feedback on the laser for example via the injected current (Figure 2) so as to obtain (absence of rotation) or keep (presence of angular rotation Ω) the frequency of the laser f1 on a resonant frequency of the cavity ; f'1 = Ni.c / L + Q / 2
In the embodiment of FIG. 3, the servocontrol is performed along the length of the cavity, the frequency of the laser remaining fixed.
Thus, the optical part DA'o1 of the servo-control device DA'1 comprises the phase modulator PM1, the electrical part DA'e1 at the output of the photodetector PhDi comprises a demodulation part comprising the phase-shifter PhD1, the mixer M1, and the oscillator Os1 at the fmi frequency which is also used to supply PM1, and the feedback electronics ER1.
An example of servo-control of the frequencies f2 and f3 respectively of the beams F'2 and F'3 is shown schematically in FIG. 4. The servo-control device is the same as for F'1. But, as there is only one laser (or only one cavity) we can no longer act on these elements. It is therefore necessary to introduce two additional components to recover two additional degrees of freedom to enslave f2 and f3.
Thus, the beam F '2 passes through an acousto-optical modulator AOM2 intended to modify the frequency thereof (alternatively a phase modulator can be used which makes it possible to make frequency changes by means of serrodyne modulation), then the transmitted part is injected into the cavity in the CW propagation direction.
In the absence of rotation, the average value of the frequency offset, denoted Afa in FIG. 2, is chosen equal to a multiple of the free spectral interval ISL. At this average value is also added (via ΓΑΟΜ2) a modulation signal intended to generate the necessary sidebands to obtain the signal enabling the average value to be enslaved so as to obtain (absence of rotation) or conserve (presence of rotation). the frequency of the beam F'2 resonance with the cavity mode considered. The frequency f2 of the beam F'2 is then slaved via Afa on a self-mode of the cavity from which the difference at the frequency f'1 is selected, and verifies, taking into account a possible rotation at the angular velocity Ω: F'2 = (Ni +1) .c / L + Ω / 2 is Afa = c / L - Ω / 2
For this, the beam 102 described above is detected on a PhDaa photodiode (which is the same for the two beams F'2 and F'3). It is then treated in the same way as for the F'1 beam with the same considerations concerning the choice of the frequency of the local oscillator Osc2 (imz frequency) which modulates AOM2 and serves during the modulation phase.
An error signal ε2 is thus generated canceling when the beam F'2 is resonant with the mode of the cavity.
It is the same with F'3 except that the frequency of the oscillator Osc3 is different from that of the oscillator Osc2 but must meet the same criteria as F'1 and F'2 with respect to the frequency width of the peaks of resonance of the cavity and its free spectral range. It is thus possible from the single signal delivered by the photodiode PhD23 to generate the two distinct frequency error signals, ε2 and ε3, for respectively F'2 and F'3.
This signal ε2 is used by the feedback electronics ER2, for example PID type, to retroact on the acousto-optical modulator AOM2, so as to maintain the frequency f2 of the beam F'2 resonant with the mode of the cavity. For this purpose, the aforementioned modulation signal is obtained via the adder S2 and the oscillator Os2, by generating sidebands in order to obtain the modulated signal which is detected on the photodiode.
Thus, the optical part DA'o2 of the servo-control device DA'2 comprises the acousto-optical modulator AOM2, the electrical part DA'e2 at the output of the photodetector PhDaa comprises the phase-shifter Dph2, the mixer M2, the oscillator Os2 , the adder S2, and the feedback electronics ER2.
In this system the acousto-optical modulators are used both to control the frequency of the corresponding beam (f2 or f'3) on a natural frequency of the cavity, different from the frequency f 1 and having an offset with respect to f 1 chosen (and corresponding to an integer multiple of different ISL for each beam), and to follow in real time the shift of this natural frequency due to the rotation Ω. The acousto-optic modulator must therefore be capable of effecting a frequency shift of at least one free spectral interval ISL (at least for example N2 = N1 + 1 and N3 = N1 + 2), which introduces a limitation on the length minimum of the cavity.
An AOM is typically limited to an offset of the order of 1 GHz, ie a cavity having a length of 20 cm (taking in this example an optical fiber cavity of index 1.5). A cavity of a much smaller length is therefore no longer compatible. In addition AOM are bulky and consume a lot of power (typically the RF power can be of the order of several Watt). To achieve a sufficiently long cavity, while maintaining, for reasons of space, a diameter of a few cm to about ten centimeters, a cavity is made with an optical fiber that makes several turns.
Thus, the presence of acousto-optic modulators in the 3-frequency system of document FR 1302311 makes it incompatible with a "short" cavity.
Now to realize a short-cavity optical gyroscope has several advantages: -reduction of the thermal sensitivity of the fiber by reducing the number of turns, -compatibility with a cavity in free space with mirrors (a single turn), which would present the advantage of eliminating the Kerr effect which is a known non-linear effect to limit the accuracy of resonant or non-resonant fiber gyroscopes, - compatibility with integrated optics, current technology limiting to one the number of turns. Indeed to make several turns, it would be necessary to cross without losses or a non-planar optical integrated circuit so that the path to loop the cavity passes below or above to avoid crossings. It should also be noted that acousto-optic modulators are currently difficult to achieve in integrated optics.
An object of the present invention is to overcome the aforementioned drawbacks by proposing a resonant gyrometer 3 compatible frequencies of a short cavity and / or compatible with an embodiment of optical functionalities in integrated optics.
DESCRIPTION OF THE INVENTION
The present invention relates to a resonant passive optical gyroscope comprising a cavity and operating with three frequencies, and comprising: a first injection laser configured to inject a first optical beam into the cavity in a first direction; injection configured to inject a second optical beam into the cavity in a direction opposite to the first direction, - a third injection laser configured to inject a third optical beam into the cavity according to one of the two aforementioned senses, a laser of the one of the injection lasers being chosen as a master laser having a master frequency, the two other injection lasers being respectively designated first and second slave lasers respectively having a first and a second slave frequency, -a configured master servo device to directly slave the master frequency to a correct natural frequency responding to a resonance mode of the cavity or to slave a natural frequency corresponding to a resonance mode of the cavity at the master frequency of the master laser. a first servo-control stage comprising a first and a second slave device respectively configured to generate a first and a second frequency error signal having a minimum absolute value respectively when the first and second slave frequencies each correspond to a resonance mode of the cavity, a second servo-control stage comprising a first and a second optical phase-locking device respectively comprising a first and a second slave oscillator configured to generate a first and a second radiofrequency offset signal, said first and a second second optical phase lock device being configured to make the first slave laser respectively coherent with the master laser and the second slave laser with the master laser and to slave the first and the second slave frequency to cavity resonance modes different from the resonance mode corresponding to the master frequency, each radiofrequency offset signal of the second servo-control stage being determined from the corresponding frequency error signal of the first servo-control stage.
Preferably, the gyroscope according to the invention further comprises: a first photo detector configured to receive one or more optical beams coming from the optical beam or beams injected in the first direction and at least a part of which has made at least one crossing of the cavity; and a second detector image configured to receive the optical beam (s) coming from the optical beam (s) injected in the second direction and at least a part of which has made at least one crossing of the cavity, said photo-detectors being configured to generate three electrical signals from the three optical beams received, each electrical signal being sent in the master servo device or in the first or second corresponding slave device.
According to one embodiment, the master servo-control device comprises: a master phase modulator of the optical beam of the master laser; a master demodulation device disposed at the output of the corresponding photo detector: a master phase-shifter, a master oscillator operating at a predetermined master oscillation frequency also used by the master phase modulator, a master mixer of the signals from the master oscillator and phase shifter, a master frequency error signal being obtained from the signal from the master mixer, a master feedback electronics configured to generate a correction signal from the master frequency error signal, and to feedback directly to the master frequency of the master laser or a length of the cavity, the frequency of the master maser remaining fixed.
According to one embodiment the master phase modulator consists of an electrical signal directly modulating the power supply of the master laser (L1) to the predetermined master oscillation frequency (fm1). Advantageously, the master servo device is of the Pound Drever Hall type.
According to one embodiment, each slave device of the first servo-control stage comprises: a phase modulator of the optical beam of the corresponding slave laser; a demodulation device disposed at the output of the photodetector having detected the corresponding optical beam, and comprising a phase shifter, an oscillator operating at a predetermined oscillation frequency also used by the corresponding phase modulator, a mixer of the signals from the oscillator and the phase-shifter, the frequency error signal being obtained from the signal coming from the mixer, a feedback electronics configured to generate a correction signal from the frequency error signal.
Advantageously, the phase modulator consists of an electrical signal directly modulating the supply current of the slave laser corresponding to the predetermined oscillation frequency.
According to one embodiment, the first and second optical phase-locked devices each comprise a third and a fourth photo-detector respectively configured to generate a first and a second beat signal, respectively between an optical beam from the master laser and an optical beam. from the first slave laser and between an optical beam from the master laser and an optical beam from the second slave laser.
Advantageously, each radiofrequency offset signal has a tunable reference frequency and a reference phase, and wherein each optical phase locking device is configured to feedback on the frequency of the corresponding slave laser so as to slave the beat signal to the radiofrequency offset signal, the reference frequency being made equal to an integer number of free spectral intervals of the cavity by using a correction signal from the corresponding frequency error signal, each slave frequency then being respectively shifted from the master frequency a value corresponding to the corresponding reference frequency. Advantageously, the integer is such that the corresponding reference frequency is within a bandwidth of the corresponding third or fourth photodetector.
According to one embodiment each optical frequency lock device comprises a mixer configured to convert a frequency of the beat signal into a frequency converted in the radio frequency domain, the slaving occurring from the converted frequency. Preferably, each optical phase-locked device comprises, for effecting the slaving of the beat signal on the radiofrequency offset signal: a phase comparator configured to respectively compare a phase of the beat signal or of the converted signal and the phase of the signal radiofrequency offset, the comparator being configured to generate a phase error signal; a feedback electronics configured to generate a correction signal and feedback to the slave frequency of the slave laser from the phase error signal.
According to a variant, the first and the second photo-detector are configured to receive optical beams at least partially reflected by the cavity.
According to another variant, the first and second photo-detectors are configured to receive optical beams transmitted by the cavity.
According to one embodiment, an optical block comprising the paths of the optical beams and the optical components necessary for implementing the gyroscope according to the invention is produced in the form of an integrated photonic circuit. Other features, objects and advantages of the present invention will appear on reading the detailed description which follows and with reference to the appended drawings given by way of non-limiting examples and in which: FIG. 1 already cited illustrates the architecture a resonant passive gyrometer 3 frequencies according to the state of the art.
Figure 2 already cited illustrates a passive gyrometer resonant 3 frequencies according to the state of the art with a direct servo on the corresponding laser of one of the frequencies.
Figure 3 already cited illustrates a passive resonant gyrometer 3 frequencies according to the state of the art with a servo of the length of the cavity, the frequency of the laser remaining fixed.
FIG. 4, already cited, illustrates the servocontrol of the other two frequencies.
FIG. 5 illustrates a resonant passive optical gyroscope 50 operating with 3 frequencies according to the invention.
FIG. 6 illustrates an embodiment of the gyroscope 50 according to the invention and more particularly details the various components used.
Figure 7 illustrates the principle of servocontrol based on an optical phase locked loop.
FIG. 8 schematizes an embodiment of the gyroscope according to the invention, the cavity of which comprises two free-space couplers and an optical fiber. FIG. 9 schematizes an embodiment of the gyrometer according to the invention that is particularly well suited when the cavity consists of an optical fiber.
FIG. 10 schematizes a mode of realization of the gyrometer according to the invention in which the first and the second photo-detector are configured to receive optical beams corresponding to optical beams transmitted by the cavity.
FIG. 11 illustrates a gyroscope according to the invention comprising a photonic circuit realized in integrated optics.
DETAILED DESCRIPTION OF THE INVENTION
FIG. 5 illustrates a resonant passive optical gyroscope 50 operating with 3 frequencies according to the invention. To simplify the presentation the measuring means Afp and Afi-2 (see state of the art) are not shown. We will describe here how to obtain the 3 adequate frequencies.
The 3-frequency gyrometer comprises a cavity C of length L. It comprises a first injection laser L1 configured to inject a first optical beam F1 into the cavity in a first direction, a second injection laser L2 configured to inject a second optical beam F2 in the cavity in a direction opposite to the first direction, and a third injection laser L3 configured to inject a third optical beam F3 into the cavity according to one of the two aforementioned senses.
In the non-limiting example of FIG. 5, the beams F1 and F3 are injected in the CW direction and the beam F2 is injected in the CCW direction.
A laser among one of the injection lasers L1, L2 and L3 is chosen as the master laser, in the example it is L1 but any of the three laser lasers can be chosen as the master laser. The master laser has a master frequency, here fl.
The other two injection lasers are respectively called the first slave laser, L2 in the example of FIG. 5, and the second slave laser, L3 in the example of FIG. 5. The first slave laser has a first slave frequency, f2 in the example of FIG. 5, and the second slave laser L3 has a second peak frequency, f3 in the example of FIG. 5. In the remainder of the explanation, the explanations are given with L1 as master and L2 and L3 as iasers esciaves. but the invention applies identically for any other choice of the master laser and slave lasers.
The gyrometer 50 according to the invention also comprises a master servo device DA1 configured to directly slave the master frequency f1 to a natural frequency of the cavity. The slaving is carried out in a conventional manner, as for example described in the state of the art from the frequency error signal ε1.
According to a first option the error signal ε1 is used to change the frequency of the master laser by acting on the available input (for example a modulation of the current for a semiconductor laser), the servocontrol operating directly on the laser frequency so that it corresponds to a resonance mode of the cavity as shown in Figure 5 (see also Figure 2).
According to a second option the error signal ε1 is used to modulate the length of the cavity via a piezoelectric wedge (for example for a fiber laser) in order to slave a natural frequency corresponding to a mode of resonance of the cavity on the frequency the master laser remaining fixed (see Figure 3).
The gyrometer 50 according to the invention further comprises a first servo-control stage comprising a first slave device, D2 in the example, associated with the first slave laser and a second slave device, D3 in the example, associated with the second slave laser. . The first slave device D2 is configured to generate a first frequency error signal, ε2 in the example of FIG. 5, having a minimum absolute value when the first slave frequency f2 corresponds to a resonance mode of the cavity. The second slave device D3 is configured to generate a second frequency error signal, ε3 in the example of FIG. 5, having a minimum absolute value when the second slave frequency f3 corresponds to a resonance mode of the cavity. Typically the frequency error signals are obtained by conventional means described in the state of the art. These error signals make it possible to quantify the frequency deviation of the slave lasers at resonance and are used by a second servo-control stage of the gyrometer 50 according to the invention.
The second servo-control stage comprises a first optical phase-locking device OPLL2-1 comprising a first oscillator Osc2 (associated with the first slave laser L2) configured to generate a first radiofrequency offset signal ("RF offset signal" in English), the first optical phase locking device OPLL2-1 being configured to make the first slave laser L2 coherent with the master laser L1 and to slave the first slave frequency f2 to a resonance mode of the cavity different from the resonance mode corresponding to the master frequency f1. Typically, the radiofrequency offset signal has a frequency of between a few tens of MHz, for cavities based on optical fibers, up to several tens of GHz for miniature cavities in integrated optics, the maximum difference being limited anyway by the maximum bandwidth of the detectors (typically between 40 and 100 GHz at 1.5 pm).
The second servo-control stage also comprises a second optical phase-locking device OPLL3-1 comprising a second oscillator Osc3 (associated with the second slave laser L3) configured to generate a second radiofrequency offset signal, the second optical phase-locking device. OPLL3-1 being configured to make coherent the second slave laser L3 with the master laser L1 and to slave the second slave frequency f3 to a resonance mode of the cavity different from the resonance mode corresponding to the master frequency f1. The master laser L1 is therefore the laser directly slaved to the cavity and serves as a reference laser on which is looped in phase the other two laser called slaves. The invention therefore uses two optical phase locking devices, called OPLL in English for Optical Phase Lock Loop, to make coherent the slave lasers with the master laser and to laser the two slave lasers on resonance frequencies of the cavity C .
For this purpose, each radiofrequency offset signal of the second servo-control stage is determined from the corresponding frequency error signal ε2, ε3 of the first servo-control stage. In other words, for each slave laser, the gyro according to the invention uses the frequency error signal generated by the first servo-control stage to drive the oscillator of the corresponding phase-locked loop. The detailed operation of an OPLL loop and particular embodiments of implementation of the two OPLL loops of the gyrometer according to the invention are described below.
This architecture has the advantage, compared to the 3-frequency architecture of the state of the art, to suppress the acousto-optical modulators. For memory these modulators allowed from a single laser to have three beams at different frequencies and yet each resonant with the cavity. The gyroscope according to the invention comprises three independent lasers that are made coherent with each other while ensuring that they each have a different frequency and are in resonance with the cavity. Thanks to the use of these three independent lasers, it is possible to have much greater frequency deviations than with acousto-optic modulators and also to improve the compactness.
The coherence relationships between the beams are obtained and controlled by the OPLLs. The frequency error signals ε2 and ε3 make it possible respectively to slave the frequency of the oscillator of IOPLL2-1 (between the beam F1 and the beam F2) and the frequency of the oscillator of IOPLL3-1 (between the beam F1 and the beam F3) so that respectively the first slave laser L2 and the second slave laser L3 are resonant.
Preferably, the gyroscope 50 according to the invention also comprises a first photodetector PhD13 configured to receive one or more optical beams from the optical beam or beams injected in the first direction and at least a part of which has carried out at least one crossing of the cavity, and a second photo detector PhD2 configured to receive one or more optical beams from the optical beams injected in the second direction and at least a portion of which has made at least one crossing of the cavity.
These photo-detectors may be arranged at several locations with respect to the cavity depending on the type of cavity and the type of optical beam collected (reflected or transmitted), as described below. In the example of FIG. 5, the detector PhD13 receives the beams 51 and 53 coming from the injected beams in the CW direction Fl and F3, and the detector PhD2 receives the beam 52 coming from the injected beam in the CCW direction F2.
The photodetectors PhD13 and PhD2 are configured to generate three electrical signals from the 3 detected optical signals 51, 52 and 53.
The detector PhD13 detects the two signals 51 and 53 likely to beat together, but the demodulation step then performed on each of the electrical signals makes it possible to recover only the signal of interest.
Each electrical signal is sent to the corresponding device. In the example, the electrical signal coming from the optical beam 51 (F1) constitutes the input of the master servo device DA1, the electrical signal coming from the optical beam 52 (F2) constitutes the input of the second slave device D2, and the electrical signal from the optical beam 53 (F3) constitutes the input of the first device device DI slave.
FIG. 6 illustrates an embodiment of the gyroscope 50 according to the invention and more particularly details the various components used.
Advantageously, the master servo device DA1 is of the type described in the state of the art in FIGS. 2 or 3. It comprises a master phase modulator PMI of the optical beam from the master laser L1 and a master demodulation device DM1 acting on the electrical signal from the corresponding photodetector PhD13. The device DM1 comprises a master phase shifter, a master oscillator Oscl operating at a predetermined master oscillation frequency fml also used by the master phase modulator and a master mixer of the signals from the master oscillator and the master phase shifter, the signal from the master oscillator. master frequency error ε1 being obtained from the signal from the master mixer. The device DA1 also comprises a master feedback electronics BRI configured to generate a correction signal from the master frequency error signal ε1, and feedback directly to the master frequency f1 of the master laser L1 or feedback on the length L of the cavity , the frequency of the master laser remaining fixed.
Advantageously, the master servo device DA1 is of the Pound Drever Hall type.
According to one variant, the master phase modulator consists of an electrical signal directly modulating the supply current of the master laser L1 to the predetermined master oscillation frequency fm1. Thus, for generating the "side bands", a direct modulation of the laser current L1 at the same frequency fm1 is used, for example when the master injection laser L1 is a laser diode, instead of a modulating PM1 component. phase.
Figure 6 also describes an example of slave devices D2 and D3. These devices have an architecture substantially identical to that of the master servo device DA1;
Advantageously, each slave device D2 or D3 of the first control stage comprises: a phase modulator PM2 or PM3 of the optical beam F2 or F3 of the corresponding slave laser L2 or L3.
According to one variant, the phase modulator consists of an electrical signal directly modulating the supply current of the corresponding slave laser L2, L3, at the predetermined oscillation frequency fm2, fm3.
Instead of the PM2 and / or PM3 phase modulator components, instead of generating the "side bands", a direct modulation of the current of the L2 and L3 lasers at the same frequencies fm2, fm3, when, for example, the injection lasers is used. L2 and L3 are laser diodes.
Each slave device of the first control stage also comprises a demodulation device DM2 or DM3 disposed at the output of the photodetector having detected the corresponding optical beam, 52 detected by PhD2 or 53 detected by PhD13. Each demodulation device comprises a phase-shifter, an oscillator operating at a predetermined oscillation frequency fm2 or fm3 also used by the corresponding phase modulator, a mixer of the signals coming from the oscillator and the phase-shifter, the frequency error signal ε2 or ε3 being obtained from the signal from the mixer, a feedback electronics ER2 or ER3 configured to generate a correction signal from the frequency error signal ε2, ε3.
The error signals ε2, ε3 are not used to directly slave the frequency of the corresponding laser L2, L3 to a cavity mode. They are used as a correction signal to set the frequency of the radiofrequency offset signal, as explained below.
We will now describe the second enslavement stage based on the OPLL principle.
The operation of an OPLL is modeled on the principle of Phase Lock Loop or PLL, and adapted to operate on the relative phase between two optical beams by transposition on an electrical signal. The principle of such an enslavement is illustrated in FIG.
One seeks to enslave a slave frequency fe of a slave laser Le at the master frequency fm of a master laser.
Recall that the frequency of a signal f is proportional to the derivative of the phase φ of the signal with respect to time. Making the phase difference between a slave signal to be enslaved and a reference signal, for example zero, makes it possible to obtain a slave frequency fe controlled by the master frequency fm.
In other words, an OPLL is configured to carry out the servocontrol from an error signal εφ which is a function of a phase difference between, on the one hand, the beat fm-fe between the master frequency and the slave frequency, and on the other hand a reference signal having a predefined fref reference frequency.
According to a preferred embodiment, the OPLL phase-locked loop comprises a PhD photodiode which detects the optical beams from the master and slave laser, and more particularly the beat signal between these frequencies, of frequency fm-fe. The frequency of the slave laser fe is slaved to the frequency of the master laser fm (itself directly slaved to a resonance mode of the cavity of the gyrometer), from this beat fm-fe that it is desired to adjust to a value predetermined.
When the beat frequency between the two lasers is typically of the order of magnitude of the Gigahertz, the phase comparison between these signals is very complex to implement. Then a conversion of the beat frequency fm-fe to a converted lower frequency signal fm-fe-fdc is performed using a mixer M, this operation being referred to as "down conversion" in English. The aim is to make the frequency of the signal to be enslaved compatible with the operating range of the phase comparator Compφ. The obtained signal of frequency fm-fe-fdc and phase Φ = 2π (fm-fe-fd) t + Φm-Φe (it is assumed that the oscillator at the frequency fd to use the down-conversion has a sufficiently stable phase not to be taken into account) typically has a frequency between 1 and 500 MHz. Preferably a filter is added after the mixer to select only the signal of interest of frequency fm-fe-fdc according to the desired range.
The OPLL also includes a reference oscillator Ose configured to generate a radiofrequency offset signal having a radio fref reference frequency and a reference phase Φref.
Then the phase comparator Compφ generates an error signal εφ which is a function of the phase difference Φ - Φref between the converted signal and the radio reference signal.
Finally, an electronic feedback device ER generates a correction signal and feedbacks on the slave frequency fe of the slave laser so as to minimize the error signal φ. For the case of a DFB laser diode, the laser supply current is typically affected, the optical frequency being a function of the current.
Typically on ignition, after a certain time, the frequency of the converted beat signal locks on the frequency fref selected oscillator with: fm - fe - fd = +/- fref
The slave laser then has a slave frequency equal to the master frequency offset from the reference frequency and the down-conversion frequency:
Thus, when two optical beams are fired from two sources on a photo detector, and their frequencies are sufficiently close to the detector bandwidth, a sinusoidal beat signal is obtained whose duration, frequency stability, phase and amplitude stability depends on the degree of coherence between the two sources. The more the sources are coherent (we suppose them constant intensities), the more this beat signal looks like a sinusoidal signal coming from an electric generator with small fluctuations of the frequency and the phase (few discontinuities, jumps, or transient deviations to a sinus). The objective of an OPLL is to enslave the beat signal between two lasers, possibly shifted by offset in the range of frequencies accessible to the phase comparators, on a reference oscillator (thus very stable), the radiofrequency offset signal , so that this beat signal is as sinus as stable as possible from that delivered by the reference oscillator (it is assumed that the down conversion signal is stable enough not to be taken into account).
Once this regime reached, the two lasers, previously independent, have a relationship of coherence between them.
The gyroscope according to the invention uses in an original manner two optical phase-locked loops. The coherence relationship between the three injection lasers of the gyrometer is obtained thanks to two optical phase lock loops, one between the master laser and a first slave, and another between the master laser and a second slave.
Preferably, in order to collect the beat signals, the first optical phase-locked device OPLL2-1 comprises a third photodetector PhD012 which receives the optical beams coming from the master laser L1 and the first slave laser L2 and which generates a first signal. electrical beat between the received optical beams. Similarly, the second optical phase-locked device OPLL3-1 comprises a fourth photodetector PhD013 which receives the optical beams from the master laser L1 and the second slave laser L3 and which generates a second electric beat signal between the optical beams received. .
In addition, if for each OPLL the reference oscillator is tunable, and one of the two lasers (the master laser) is slaved to a resonance of the cavity, then the reference oscillator frequency can be tuned to that the frequency of the beat signal between the two beams (which is ideally a sinusoidal signal maintained by the OPLL) corresponds to an integer number of ISL of the cavity. The slave laser then also lays on a resonance mode of the cavity different from the resonance mode of the master laser.
Thus, advantageously, the first radiofrequency offset signal has a first reference frequency f2ref tunable and a reference phase 02ref, and the first optical phase lock device OPLL2-1 is configured to feedback on the frequency f2 of the first slave laser L2 to slave the first beat signal, possibly converted in the low frequency domain, to the first radiofrequency offset signal, the first reference frequency f2ref without downconverting or the sum of the first reference frequency f2ref and the down frequency fdc -conversion in the opposite case, being made equal to an integer n1 free spectral interval ISL of the cavity by using the correction signal from the first frequency error signal ε2 delivered by the first servo-control stage.
Similarly, the second radiofrequency offset signal has a second tunable fSref reference frequency and a reference phase 03ref, and the second optical phase lock device OPLL3-1is configured to feedback on the frequency f3 of the second slave laser L3. to slave the second beat signal, possibly converted in the low frequency domain, to the second radiofrequency offset signal, the second reference frequency f3ref without downconverting or the sum of the second reference frequency f3ref and the down frequency -conversion fdc 'in the opposite case, being made equal to an integer n2 free spectral interval ISL of the cavity by using the correction signal from the second frequency error signal ε3 delivered by the first servo-control stage.
When the frequencies are locked and in the absence of rotation, the slave frequency f2 is shifted from the master frequency f1 by a value corresponding to the reference frequency f2ref + fd = n1 .ISL. f2-f1 = +/- (f2ref + fd) = +/- nl.lSL
Similarly, the slave frequency f3 is shifted from the master frequency f1 by a value corresponding to the reference frequency f3ref + fd = n2.ISL. F3-f1 = +/- (f3ref + fd) = +/- n2.ISL
When the gyro is angularly rotated, the resonance frequencies change over time. The operation of the servo is similar to that of a looped system whose operating point is changed to ensure the follow-up of the resonances.
One embodiment of the OPLLs is described in FIG.
Each optical phase-locked device OPLL2-1 (OPLL3-1) comprises, to achieve the control of the beat signal on the radiofrequency offset signal: a phase comparator PC (PC ') configured to compare a phase of the signal of beats or of the converted signal Φ2 (Φ3) and the phase Φ2ref (Φ3ref) of the corresponding radio frequency shift signal, the comparator being configured to generate a phase error signal εΦ (εΦ '), - an electronic feedback circuit ER ( ER ') configured to generate a correction signal and feedback on the slave frequency f2 (f3) of the slave laser L2 (L3) from the phase error signal εΦ (εΦ').
Compared with the use of a single laser and acousto-optic modulators, a laser gyrometer 3 is obtained in which:
• the coherence relationships between the beams are obtained and controlled by the OPLLs
The frequency deviations between the three beams, making it possible to slave the frequency of each beam to obtain (absence of rotation) or to preserve (presence of rotation) their resonance are controlled via the control of the frequency of the reference oscillator of each of the OPLLs • the error signal ε1 makes it possible, as before, to slave the laser L1 to the cavity or vice versa. The error signals ε2 and ε3 make it possible respectively to slave the frequency f2ref of the oscillator of IOPLL1-2 and the frequency f3ref of IOPLL1-3 so that L2 and L3 are resonant.
To ensure proper operation of the OPLLs the integers n1, n2 and the frequencies fdc and fdc 'of down conversion are such that the corresponding reference frequencies f2ref, f3ref are included in a corresponding photodetector bandwidth.
According to an embodiment illustrated in FIG. 6, a "down conversion" is necessary and in this case each optical frequency locking device OPLL1-2 (OPLL1-3) comprises a mixer M (M ') configured to convert a frequency of the signal of beat f2-f1 (f3-f1) in a converted frequency f2-f1-fdc (f3-f1-fdc ') in the radio frequency domain, the slaving occurring from the converted frequency.
Typically each converted frequency is between 1 and 500 MHz. Such a frequency is compatible with a phase comparator realized in integrated optics.
According to a variant, a filter is placed at the outlet of each mixer.
The gyrometer according to the invention can operate from different optical signals 51, 52, 53 received by the first PhD13 and second PhD2 detectors. According to a first embodiment illustrated in FIGS. 8 and 9, the first and second photo-detectors are configured to receive optical beams 51, 52, 53 corresponding to optical beams at least partially reflected by the cavity. When the reflected intensities are used, they are maximum off resonance and minimum resonance and servo is adapted accordingly. Wax and wax circulators are inserted in the path of the optical beams in order to separate the reflected beams from the incident beams in the case of an optical fiber embodiment (FIG. 9). The use of reflected beams to deliver the error signals ε1, ε2 and ε3 is the most optimal, because in this case the maximum value of the modulation frequency of PMI, PM2 and PM3 is only limited by the interval free spectral ISL.
According to a second embodiment illustrated in FIG. 10, the first and second photo-detectors are configured to receive optical beams 51, 52, 53 corresponding to optical beams transmitted by the cavity. When the intensities transmitted are used, these are minimum resonant and maximum resonance and servo is adapted accordingly. One advantage is that lasers generally comprising insulators, the presence of insulators Iso and lso 'is not essential, and the realization of cavity C and couplers C1 and C2 is compatible with an implementation in integrated optics.
The gyro according to the invention is also compatible with any type of cavity, free space, hollow fiber, integrated optical resonator ...
According to one embodiment, the cavity C of the gyrometer 50 comprises two free-space couplers 10, 11, the remainder of the cavity being for example in free space, with mirrors) or comprising an optical fiber OF, as illustrated in FIGS.
Another embodiment illustrated in FIG. 9 is particularly well suited when the cavity consists of an optical fiber OF. The cavity comprises, in addition to the optical fiber OF, a first coupler 2 by 2 Cl, this first coupler being configured to inject the optical beams Fl, F2, F3 into the cavity and to direct the reflected optical beams 51, 52, 53 by the cavity to the first PHD13 and the second photo detector PhD2.
According to another embodiment, the fiber-optic cavity comprises a first coupler 2 by 2 Cl and a second coupler 2 by 2 C2, the first coupler C1 being configured to inject the optical beams F1, F2, F3 into the cavity, the second coupler C2 being configured to direct the optical beams 51, 52, and 53 transmitted by the cavity to the first PHD13 and the second PhD2 photo detector.
An exemplary order of magnitude for the gyrometer 50 is given below without limitation.
We consider injection lasers L1 L2 and L3 of semiconductor or optical fiber type emitting at a wavelength of 1.55 pm for example. Consider a cavity of length 5 cm index 1.6 made in integrated optics (in this example in Si3N4 to have low loss of propagation), an ISL of 3.75 GHz .This length is a good compromise because we do not necessarily seek to make very small cavities because the sensitivity depends on the surface.
For a master frequency f1 of about 1.94 × 10 -3 Hz (λ = 1.55 μm), there is therefore an NI of the order of 51000.
We seek to shift the slave frequencies f2 and f3 by at least one integer value of ISL;
We can do +1. ISL (N2 = NI +1), and -1 .ISL (N3 = NI -1)
Or we can also do +1. ISL, and + 2.ISL (N2 = N1 + 1 and N3 = N1 + 2) ... or -1. ISL, and -2.ISL (N2 = N1 - 1 and N3 = N1 - 2).
Taking into account the value of the ISL, one will be satisfied with a shift of some ISL to remain compatible of photodiodes integrable in integrated optics .......
The gyrometer 50 according to the invention is compatible with an embodiment in integrated optics, because it does not require acousto-optic modulators.
In addition, the use of OPLL loops is compatible with orders of magnitude of the offsets to be carried out and an implementation in integrated photonics, which makes it possible to drastically reduce the size and the total cost.
The optical block of the gyroscope 50 is defined which comprises the paths of the optical beams and the optical components necessary for implementing said gyrometer (such as phase modulators) and including the photodetectors.
According to a first integration level illustrated in FIG. 11, the optical block is a PIC photonic circuit realized in integrated optics, for example on Silicon or InP substrate, or any other compatible material of the required functionalities. The coupling in and out of the PIC circuit can be done by the slice or directly out of the plane of the circuit using networks. In addition, in FIG. 11, each PMI modulator PM2, PM3 is equipped with a photodiode. This allows to measure and control the power of the three beams and thus reduce the Kerr effect related to a difference in power between the two counterpropagating waves in the cavity. This PIC circuit can then be connected to a cavity-based mirror (Figure 11) or fiber. Thus the optical block is made in the form of at least one integrated circuit.
According to a higher level of integration, the cavity and / or injection lasers are also made in integrated optics.
For the sake of clarity, the measurement of the frequencies f 1, f 2 and f 2 making it possible to go back to the length of the cavity and to the speed of rotation are not shown. This measurement can be done in two ways.
According to one variant, a calibration of the feedback signals injected into the OPLLs and the master laser is used to go back to fl, f2 and f3.
According to another variant, the optical beams are used directly. For example, by taking part of F1 and F3 before coupler 10 (FIGS. 5 and 11) or before coupler C1 (FIGS. 9 and 10) and sending this optical signal to a photodiode, f1-f3 is measured directly at using a frequency counter. As it is a beat, one can also directly use the methods of the RLG gyrolasers (provided to adapt the bandwidth). Similarly, by taking and combining Fl, F3 and F2, the electrical beat signal will have components at -F3, F1-F2, F2-F3 that can be filtered and measured. According to another variant, a configuration which is a mix of FIGS. 9 and 10 is used: the reflected beams are used to slave (which also gives a first set of values of cavity length and rotation speed) and the recombined transmitted beams in beat to deduce a second set of values of cavity length and rotation speed.
Compact resonant optical gyrometer with three frequencies DOMAINE DE L'INVENTION
The field of the invention is that of optical gyrometers, used in particular in the field of inertial navigation. More precisely, the field of the invention is that of resonant passive optical gyrometers.
STATE OF THE ART
Optical gyrometers are based on the principle of measuring the Sagnac effect. The latter induces, under the effect of a rotation, a difference in travel time between two electromagnetic signals propagating in opposite directions along a ring path. This difference in travel time, proportional to the angular velocity of the device, can be measured either as a phase difference in the context of an interferometric assembly or as a difference in natural frequency between the two counter-rotating modes of a cavity. ring.
In the first case, it is necessary to use an optical fiber to maximize the length of the interferometer and therefore the sensitivity of the device. This is called an optical fiber interferometric gyrometer, known by the acronym "l-FOG".
In the second case, the difference between the eigenfrequencies of the modes of the cavity can be measured in two ways. The first is to use an active cavity, that is to say containing an amplifying medium and measure the difference in frequency between the counter-rotating modes emitted by the cavity. We then speak of gyrolaser or "RLG", acronym for "Ring Laser Gyro". The second way is to use a passive resonant cavity and probe the eigenfrequencies of contrarotative modes using a laser. This is called a resonant passive gyro.
The resonant passive gyro has a number of advantages over its competitors. Compared to the RLG, it is notably free from the need to use a gaseous amplifying medium and the high voltage electrode system which is usually associated with it. Compared to the I-FOG, it has the advantage of a much shorter optical path that provides a lower sensitivity to the environment and a greater compactness. Finally, it involves only standard components. This avoids, in particular, the use of superluminescent source.
However, while these three types of gyrometers, l-FOG, RLG and resonant passive gyro have all been experimentally demonstrated, currently only the first two have led to industrial applications. A hindrance to the development of the resonant passive gyro is due to the problem of backscattering of light, which creates couplings between counter-rotating modes, which creates a non-linearity of the frequency response, resulting in a "blind zone" as on the gyrolasers and degrades system performance.
A solution to the problem of the coupling between contrapropagative modes is described in the document FR 1302311. This system probes the eigenfrequencies of the counter-rotating modes of a ring cavity by overcoming the problems usually created by the backscatter, while simultaneously providing a measurement. the cavity length for evaluating (and possibly slaving to a constant value) the scale factor of the resonant passive gyro thus produced.
The principle of this system is to use three beams at three different frequencies (instead of two in conventional gyrometers). The system has a ring cavity and a laser which is divided into three beams of different optical frequency. By way of example, the cavity may consist of a hollow fiber to limit the Kerr effect. Each frequency is separated from the other two frequencies by a value corresponding to an integer multiple of the free spectral interval of the cavity. The free spectral interval ISL of the cavity is classically worth: ISL = c / L c being the speed of light and L the optical length of the ring cavity.
The first beam is slaved to one mode of the cavity in one direction of propagation and the other two are slaved to two other modes of the cavity corresponding to the opposite direction of propagation. It should be noted that it is also possible to perform the inverse servocontrol, that is to say, to slave a first natural frequency corresponding to a first mode of resonance of the cavity at the first frequency of the first optical beam, in enslaving the length of the cavity for example.
The frequencies of the three beams are at each moment sufficiently distant that the effect of the couplings between the beams can be rendered inoperative.
In the absence of rotation, each beam is slaved on a different natural frequency of the cavity that is noted; fi = Ni.c / L for the first beam; f2 = N2.c / L for the second beam; f3 = N3.c / L for the third beam; with Ni, N2 and N3 two-to-two integers different and known.
The frequencies must be close enough so that the difference between the frequencies of each pair of beams can be compatible with the bandwidth of a photodiode.
In the presence of a rotation, the difference of frequencies of the two beams propagating in the same direction gives access to the length of the cavity, whereas the difference of frequency between two contrarotating beams combined with the information on the length of the cavity gives access to the angular velocity of the whole.
Thus a gyroscope operating with 3 frequencies comprises means for measuring the difference in frequencies of the two beams propagating in the same direction, and the difference in frequency between two counter-rotating beams, these two frequencies combined together making it possible to go back to the length of the cavity and at the angular velocity of the cavity along an axis perpendicular to the cavity. To simplify the discussion these conventional measuring means are not shown in the figures.
Indeed, in the presence of a rotation, the eigenfrequencies are shifted by an amount Ω proportional to the angular velocity, which gives: fl = Ni.c / L + Ω / 2; β = N2.C / L - Ω / 2: Î3 = N3.C / L-Q / 2
The length of the cavity is then known at each instant by measuring the difference in frequency Afp between the beams propagating in the same direction, ie in the above example Af2-3:
The speed of rotation is deduced by measuring the difference in frequency Afcp between two beams propagating in the opposite direction, ie in the above example Afi_2:
The architecture proposed in FR 1302311 is shown in FIG. 1 with mirrors. Solid lines correspond to optical paths, and dashed lines refer to electrical connections. The laser L emits a beam which is divided into three beams F'1, F'2 and F'3. To simplify the presentation the measuring means Afp and Afi_2 are not shown. F'1 is for example injected into the annular optical cavity C of length L in the anticlockwise direction or "CCW", an acronym for Counter Clock Wise in English, while the two beams F'2 and F ' 3 are injected into the cavity in a clockwise direction, "CW" acronym for Clock Wise "in English. The portion transmitted through the coupler 10 (partially reflecting mirror) of the beams F'2 and F'3 pass through the optical fiber and are reflected by the optical coupler 11, then the coupler 10, so as to form the cavity. The part transmitted through the coupler 11 of the bundle F'1 passes through the optical fiber and the coupler 11, and is reflected by the coupler 10 so as to constitute the cavity. At resonance, the retroreflected intensity at the cavity output is minimal, and this property is used to control the frequencies of the three beams on the eigen modes of the cavity. For example, the beam 101 reflected by the coupler 11 towards the bottom of FIG. 1 is used to slave the frequency of F'I. It corresponds to the coherent superposition of the portion of the beam F'1 directly reflected by 11 and the portion constituted by the beams propagating in the cavity in the CCW direction, which result from the superposition of the beams having made one, two, three. ... turns the cavity in the CCW direction. Similarly beams 102 and 103 going upwards in Figure 1 are used respectively to slave the frequencies of F'2 and F'3. They correspond to the coherent superposition of the portion of F'2 and F'3 directly reflected by the coupler 10 and portions of F'2 and F'3 transmitted by this coupler 10, then propagating in the cavity in the CW direction , then reflected by 11 and finally transmitted by 10, corresponding to the superposition of the beams having made one, two, three, etc. .... turns of the cavity in the CW direction.
The beam F'1 is slaved to a specific mode of the cavity by a direct feedback on the laser L using the photodiode PhDI and the servo device DA'I, which has an optical portion DA'ol and a electric part DA'el.
The beams F'2 and F'3 are slaved on eigen modes of the cavity using the photodiode PhD23 and servo devices DA'2, DA'3, each having an optical part acting directly on the optical frequency (DA'o2, DA'o3) and an electrical part (DA'e2, DA'e3).
More generally, one of the beams has a natural frequency maintained at resonance by a direct control on the laser, according to the non-limiting example the beam F'1 (but this could be one of the other two beams) according to an option Optl illustrated in FIG. 2. According to another option Opt2 illustrated in FIG. 3, the frequency of the beam F'1 is maintained at resonance by directly slaving the length L of the cavity, for example by means of a piezoelectric modulator.
We will now explain how the direct control on the laser is performed, as shown in Figure 2. The beam F'1 passes through a phase modulator PMI to generate sidebands or "side bands" necessary to obtaining a frequency error signal ε1 enabling the frequency to be servocontrolled to obtain (absence of rotation) or to conserve (presence of rotation) the frequency of the beam F'1 resonating with the cavity mode considered. This method is based on the so-called Pound Drever Hall technique, named after its inventors and well known to those skilled in the art.
The beam 101 is modulated by a phase modulator PMI, placed in the optical part DA'ol, so as to create lateral components, "side-bands", in frequency, separated from the initial frequency f1 by multiples of the frequency of modulation, fmi, applied by the oscillator Osl via PMI. This frequency is chosen, if possible, to be larger than the width of the resonance of the cavity (and smaller than the free spectral interval of the cavity) so that the sidebands are not resonant with the cavity. To simplify the explanation, we considered only the first two side-bands, separated by ± fmi from the initial frequency f1. The beam 101 (which therefore has three spectral components at f1-fmi, f1 and f1 + fmi) is detected on a PhDi photodiode whose output signal is demodulated by the modulation signal applied to PMI with an adjustment of their respective phases. (Dphi phase shifter) requiring the use of an electric mixer Ml. A low-pass filter (not shown) then makes it possible to keep only the DC component of the demodulated signal whose amplitude, ε1, is then proportional to the difference between the frequency f1 of the laser and the resonance frequency of the cavity. Indeed, when the frequency f1 of the laser and the resonant frequency of the cavity deviate a little, the two side-bands are unchanged (if they are well off resonances) while the phase and amplitude of the beam at the frequency fl evolve (since it is no longer resonant). The coherence properties between the three spectral components of 101 then allow a measurement of these fluctuations (three-beam interference) which result in this linear variation of the demodulated signal which can thus be used as a frequency error signal, ε1 s canceling when the beam F'1 is resonant with a mode of the cavity. This feedback is then carried out by means of feedback electronics ER1 according to the conventional control methods, for example, without being restrictive, with feedback electronics PI or PID for Proportional Integral Derivative, allusion to the three modes of control. action on the error signal of the feedback electronics. This type of feedback making it possible to converge the error signal to a zero value is well known in automatic mode.
Regarding the choice of the modulation frequency to be applied to PM1, if the fineness of the cavity is large, the width of the cavity will be small in front of the free spectral range and the modulation frequency can be chosen very large compared to the frequency width of the resonance peaks of the cavity. We will then be in the optimal situation, corresponding to the above explanation, for this servocontrol. A Γ opposite, if the fineness of the cavity is not very large, the modulation frequency will be close to the frequency width of the resonance peaks of the cavity. The sidebands are then partially modified when the frequency f 1 deviates from the resonance and the servocontrol is less efficient.
The servo loop feedback on the laser for example via the injected current (Figure 2) so as to obtain (absence of rotation) or keep (presence of angular rotation Ω) the frequency of the laser f1 on a resonant frequency of the cavity ; f'1 = Ni.c / L + Q / 2
In the embodiment of FIG. 3, the servocontrol is performed along the length of the cavity, the frequency of the laser remaining fixed.
Thus, the optical part DA'o1 of the servo-control device DA'1 comprises the phase modulator PM1, the electrical part DA'e1 at the output of the photodetector PhDi comprises a demodulation part comprising the phase-shifter PhD1, the mixer M1, and the oscillator Os1 at the fmi frequency which is also used to supply PM1, and the feedback electronics ER1.
An example of servo-control of the frequencies f2 and f3 respectively of the beams F'2 and F'3 is shown schematically in FIG. 4. The servo-control device is the same as for F'1. But, as there is only one laser (or only one cavity) we can no longer act on these elements. It is therefore necessary to introduce two additional components to recover two additional degrees of freedom to enslave f2 and f3.
Thus, the beam F '2 passes through an acousto-optical modulator AOM2 intended to modify the frequency thereof (alternatively a phase modulator can be used which makes it possible to make frequency changes by means of serrodyne modulation), then the transmitted part is injected into the cavity in the CW propagation direction.
In the absence of rotation, the average value of the frequency offset, denoted Afa in FIG. 2, is chosen equal to a multiple of the free spectral interval ISL. At this average value is also added (via ΓΑΟΜ2) a modulation signal intended to generate the necessary sidebands to obtain the signal enabling the average value to be enslaved so as to obtain (absence of rotation) or conserve (presence of rotation). the frequency of the beam F'2 resonance with the cavity mode considered. The frequency f2 of the beam F'2 is then slaved via Afa on a self-mode of the cavity from which the difference at the frequency f'1 is selected, and verifies, taking into account a possible rotation at the angular velocity Ω: F'2 = (Ni +1) .c / L + Ω / 2 is Afa = c / L - Ω / 2
For this, the beam 102 described above is detected on a PhDaa photodiode (which is the same for the two beams F'2 and F'3). It is then treated in the same way as for the F'1 beam with the same considerations concerning the choice of the frequency of the local oscillator Osc2 (imz frequency) which modulates AOM2 and serves during the modulation phase.
An error signal ε2 is thus generated canceling when the beam F'2 is resonant with the mode of the cavity.
It is the same with F'3 except that the frequency of the oscillator Osc3 is different from that of the oscillator Osc2 but must meet the same criteria as F'1 and F'2 with respect to the frequency width of the peaks of resonance of the cavity and its free spectral range. It is thus possible from the single signal delivered by the photodiode PhD23 to generate the two distinct frequency error signals, ε2 and ε3, for respectively F'2 and F'3.
This signal ε2 is used by the feedback electronics ER2, for example PID type, to retroact on the acousto-optical modulator AOM2, so as to maintain the frequency f2 of the beam F'2 resonant with the mode of the cavity. For this purpose, the aforementioned modulation signal is obtained via the adder S2 and the oscillator Os2, by generating sidebands in order to obtain the modulated signal which is detected on the photodiode.
Thus, the optical part DA'o2 of the servo-control device DA'2 comprises the acousto-optical modulator AOM2, the electrical part DA'e2 at the output of the photodetector PhDaa comprises the phase-shifter Dph2, the mixer M2, the oscillator Os2 , the adder S2, and the feedback electronics ER2.
In this system the acousto-optical modulators are used both to control the frequency of the corresponding beam (f2 or f'3) on a natural frequency of the cavity, different from the frequency f 1 and having an offset with respect to f 1 chosen (and corresponding to an integer multiple of different ISL for each beam), and to follow in real time the shift of this natural frequency due to the rotation Ω. The acousto-optic modulator must therefore be capable of effecting a frequency shift of at least one free spectral interval ISL (at least for example N2 = N1 + 1 and N3 = N1 + 2), which introduces a limitation on the length minimum of the cavity.
An AOM is typically limited to an offset of the order of 1 GHz, ie a cavity having a length of 20 cm (taking in this example an optical fiber cavity of index 1.5). A cavity of a much smaller length is therefore no longer compatible. In addition AOM are bulky and consume a lot of power (typically the RF power can be of the order of several Watt). To achieve a sufficiently long cavity, while maintaining, for reasons of space, a diameter of a few cm to about ten centimeters, a cavity is made with an optical fiber that makes several turns.
Thus, the presence of acousto-optic modulators in the 3-frequency system of document FR 1302311 makes it incompatible with a "short" cavity.
Now to realize a short-cavity optical gyroscope has several advantages: -reduction of the thermal sensitivity of the fiber by reducing the number of turns, -compatibility with a cavity in free space with mirrors (a single turn), which would present the advantage of eliminating the Kerr effect which is a known non-linear effect to limit the accuracy of resonant or non-resonant fiber gyroscopes, - compatibility with integrated optics, current technology limiting to one the number of turns. Indeed to make several turns, it would be necessary to cross without losses or a non-planar optical integrated circuit so that the path to loop the cavity passes below or above to avoid crossings. It should also be noted that acousto-optic modulators are currently difficult to achieve in integrated optics.
An object of the present invention is to overcome the aforementioned drawbacks by proposing a resonant gyrometer 3 compatible frequencies of a short cavity and / or compatible with an embodiment of optical functionalities in integrated optics.
DESCRIPTION OF THE INVENTION
The present invention relates to a resonant passive optical gyroscope comprising a cavity and operating with three frequencies, and comprising: a first injection laser configured to inject a first optical beam into the cavity in a first direction; injection configured to inject a second optical beam into the cavity in a direction opposite to the first direction, - a third injection laser configured to inject a third optical beam into the cavity according to one of the two aforementioned senses, a laser of the one of the injection lasers being chosen as a master laser having a master frequency, the two other injection lasers being respectively designated first and second slave lasers respectively having a first and a second slave frequency, -a configured master servo device to directly slave the master frequency to a correct natural frequency responding to a resonance mode of the cavity or to slave a natural frequency corresponding to a resonance mode of the cavity at the master frequency of the master laser. a first servo-control stage comprising a first and a second slave device respectively configured to generate a first and a second frequency error signal having a minimum absolute value respectively when the first and second slave frequencies each correspond to a resonance mode of the cavity, a second servo-control stage comprising a first and a second optical phase-locking device respectively comprising a first and a second slave oscillator configured to generate a first and a second radiofrequency offset signal, said first and a second second optical phase lock device being configured to make the first slave laser respectively coherent with the master laser and the second slave laser with the master laser and to slave the first and the second slave frequency to cavity resonance modes different from the resonance mode corresponding to the master frequency, each radiofrequency offset signal of the second servo-control stage being determined from the corresponding frequency error signal of the first servo-control stage.
Preferably, the gyroscope according to the invention further comprises: a first photo detector configured to receive one or more optical beams coming from the optical beam or beams injected in the first direction and at least a part of which has made at least one crossing of the cavity; and a second detector image configured to receive the optical beam (s) coming from the optical beam (s) injected in the second direction and at least a part of which has made at least one crossing of the cavity, said photo-detectors being configured to generate three electrical signals from the three optical beams received, each electrical signal being sent in the master servo device or in the first or second corresponding slave device.
According to one embodiment, the master servo-control device comprises: a master phase modulator of the optical beam of the master laser; a master demodulation device disposed at the output of the corresponding photo detector: a master phase-shifter, a master oscillator operating at a predetermined master oscillation frequency also used by the master phase modulator, a master mixer of the signals from the master oscillator and phase shifter, a master frequency error signal being obtained from the signal from the master mixer, a master feedback electronics configured to generate a correction signal from the master frequency error signal, and to feedback directly to the master frequency of the master laser or a length of the cavity, the frequency of the master maser remaining fixed.
According to one embodiment the master phase modulator consists of an electrical signal directly modulating the power supply of the master laser (L1) to the predetermined master oscillation frequency (fm1). Advantageously, the master servo device is of the Pound Drever Hall type.
According to one embodiment, each slave device of the first servo-control stage comprises: a phase modulator of the optical beam of the corresponding slave laser; a demodulation device disposed at the output of the photodetector having detected the corresponding optical beam, and comprising a phase shifter, an oscillator operating at a predetermined oscillation frequency also used by the corresponding phase modulator, a mixer of the signals from the oscillator and the phase-shifter, the frequency error signal being obtained from the signal coming from the mixer, a feedback electronics configured to generate a correction signal from the frequency error signal.
Advantageously, the phase modulator consists of an electrical signal directly modulating the supply current of the slave laser corresponding to the predetermined oscillation frequency.
According to one embodiment, the first and second optical phase-locked devices each comprise a third and a fourth photo-detector respectively configured to generate a first and a second beat signal, respectively between an optical beam from the master laser and an optical beam. from the first slave laser and between an optical beam from the master laser and an optical beam from the second slave laser.
Advantageously, each radiofrequency offset signal has a tunable reference frequency and a reference phase, and wherein each optical phase locking device is configured to feedback on the frequency of the corresponding slave laser so as to slave the beat signal to the radiofrequency offset signal, the reference frequency being made equal to an integer number of free spectral intervals of the cavity by using a correction signal from the corresponding frequency error signal, each slave frequency then being respectively shifted from the master frequency a value corresponding to the corresponding reference frequency. Advantageously, the integer is such that the corresponding reference frequency is within a bandwidth of the corresponding third or fourth photodetector.
According to one embodiment each optical frequency lock device comprises a mixer configured to convert a frequency of the beat signal into a frequency converted in the radio frequency domain, the slaving occurring from the converted frequency. Preferably, each optical phase-locked device comprises, for effecting the slaving of the beat signal on the radiofrequency offset signal: a phase comparator configured to respectively compare a phase of the beat signal or of the converted signal and the phase of the signal radiofrequency offset, the comparator being configured to generate a phase error signal; a feedback electronics configured to generate a correction signal and feedback to the slave frequency of the slave laser from the phase error signal.
According to a variant, the first and the second photo-detector are configured to receive optical beams at least partially reflected by the cavity.
According to another variant, the first and second photo-detectors are configured to receive optical beams transmitted by the cavity.
According to one embodiment, an optical block comprising the paths of the optical beams and the optical components necessary for implementing the gyroscope according to the invention is produced in the form of an integrated photonic circuit. Other features, objects and advantages of the present invention will appear on reading the detailed description which follows and with reference to the appended drawings given by way of non-limiting examples and in which: FIG. 1 already cited illustrates the architecture a resonant passive gyrometer 3 frequencies according to the state of the art.
Figure 2 already cited illustrates a passive gyrometer resonant 3 frequencies according to the state of the art with a direct servo on the corresponding laser of one of the frequencies.
Figure 3 already cited illustrates a passive resonant gyrometer 3 frequencies according to the state of the art with a servo of the length of the cavity, the frequency of the laser remaining fixed.
FIG. 4, already cited, illustrates the servocontrol of the other two frequencies.
FIG. 5 illustrates a resonant passive optical gyroscope 50 operating with 3 frequencies according to the invention.
FIG. 6 illustrates an embodiment of the gyroscope 50 according to the invention and more particularly details the various components used.
Figure 7 illustrates the principle of servocontrol based on an optical phase locked loop.
FIG. 8 schematizes an embodiment of the gyroscope according to the invention, the cavity of which comprises two free-space couplers and an optical fiber. FIG. 9 schematizes an embodiment of the gyrometer according to the invention that is particularly well suited when the cavity consists of an optical fiber.
FIG. 10 schematizes a mode of realization of the gyrometer according to the invention in which the first and the second photo-detector are configured to receive optical beams corresponding to optical beams transmitted by the cavity.
FIG. 11 illustrates a gyroscope according to the invention comprising a photonic circuit realized in integrated optics.
DETAILED DESCRIPTION OF THE INVENTION
FIG. 5 illustrates a resonant passive optical gyroscope 50 operating with 3 frequencies according to the invention. To simplify the presentation the measuring means Afp and Afi-2 (see state of the art) are not shown. We will describe here how to obtain the 3 adequate frequencies.
The 3-frequency gyrometer comprises a cavity C of length L. It comprises a first injection laser L1 configured to inject a first optical beam F1 into the cavity in a first direction, a second injection laser L2 configured to inject a second optical beam F2 in the cavity in a direction opposite to the first direction, and a third injection laser L3 configured to inject a third optical beam F3 into the cavity according to one of the two aforementioned senses.
In the non-limiting example of FIG. 5, the beams F1 and F3 are injected in the CW direction and the beam F2 is injected in the CCW direction.
A laser among one of the injection lasers L1, L2 and L3 is chosen as the master laser, in the example it is L1 but any of the three laser lasers can be chosen as the master laser. The master laser has a master frequency, here fl.
The other two injection lasers are respectively called the first slave laser, L2 in the example of FIG. 5, and the second slave laser, L3 in the example of FIG. 5. The first slave laser has a first slave frequency, f2 in the example of FIG. 5, and the second slave laser L3 has a second peak frequency, f3 in the example of FIG. 5. In the remainder of the explanation, the explanations are given with L1 as master and L2 and L3 as iasers esciaves. but the invention applies identically for any other choice of the master laser and slave lasers.
The gyrometer 50 according to the invention also comprises a master servo device DA1 configured to directly slave the master frequency f1 to a natural frequency of the cavity. The slaving is carried out in a conventional manner, as for example described in the state of the art from the frequency error signal ε1.
According to a first option the error signal ε1 is used to change the frequency of the master laser by acting on the available input (for example a modulation of the current for a semiconductor laser), the servocontrol operating directly on the laser frequency so that it corresponds to a resonance mode of the cavity as shown in Figure 5 (see also Figure 2).
According to a second option the error signal ε1 is used to modulate the length of the cavity via a piezoelectric wedge (for example for a fiber laser) in order to slave a natural frequency corresponding to a mode of resonance of the cavity on the frequency the master laser remaining fixed (see Figure 3).
The gyrometer 50 according to the invention further comprises a first servo-control stage comprising a first slave device, D2 in the example, associated with the first slave laser and a second slave device, D3 in the example, associated with the second slave laser. . The first slave device D2 is configured to generate a first frequency error signal, ε2 in the example of FIG. 5, having a minimum absolute value when the first slave frequency f2 corresponds to a resonance mode of the cavity. The second slave device D3 is configured to generate a second frequency error signal, ε3 in the example of FIG. 5, having a minimum absolute value when the second slave frequency f3 corresponds to a resonance mode of the cavity. Typically the frequency error signals are obtained by conventional means described in the state of the art. These error signals make it possible to quantify the frequency deviation of the slave lasers at resonance and are used by a second servo-control stage of the gyrometer 50 according to the invention.
The second servo-control stage comprises a first optical phase-locking device OPLL2-1 comprising a first oscillator Osc2 (associated with the first slave laser L2) configured to generate a first radiofrequency offset signal ("RF offset signal" in English), the first optical phase locking device OPLL2-1 being configured to make the first slave laser L2 coherent with the master laser L1 and to slave the first slave frequency f2 to a resonance mode of the cavity different from the resonance mode corresponding to the master frequency f1. Typically, the radiofrequency offset signal has a frequency of between a few tens of MHz, for cavities based on optical fibers, up to several tens of GHz for miniature cavities in integrated optics, the maximum difference being limited anyway by the maximum bandwidth of the detectors (typically between 40 and 100 GHz at 1.5 pm).
The second servo-control stage also comprises a second optical phase-locking device OPLL3-1 comprising a second oscillator Osc3 (associated with the second slave laser L3) configured to generate a second radiofrequency offset signal, the second optical phase-locking device. OPLL3-1 being configured to make coherent the second slave laser L3 with the master laser L1 and to slave the second slave frequency f3 to a resonance mode of the cavity different from the resonance mode corresponding to the master frequency f1. The master laser L1 is therefore the laser directly slaved to the cavity and serves as a reference laser on which is looped in phase the other two laser called slaves. The invention therefore uses two optical phase locking devices, called OPLL in English for Optical Phase Lock Loop, to make coherent the slave lasers with the master laser and to laser the two slave lasers on resonance frequencies of the cavity C .
For this purpose, each radiofrequency offset signal of the second servo-control stage is determined from the corresponding frequency error signal ε2, ε3 of the first servo-control stage. In other words, for each slave laser, the gyro according to the invention uses the frequency error signal generated by the first servo-control stage to drive the oscillator of the corresponding phase-locked loop. The detailed operation of an OPLL loop and particular embodiments of implementation of the two OPLL loops of the gyrometer according to the invention are described below.
This architecture has the advantage, compared to the 3-frequency architecture of the state of the art, to suppress the acousto-optical modulators. For memory these modulators allowed from a single laser to have three beams at different frequencies and yet each resonant with the cavity. The gyroscope according to the invention comprises three independent lasers that are made coherent with each other while ensuring that they each have a different frequency and are in resonance with the cavity. Thanks to the use of these three independent lasers, it is possible to have much greater frequency deviations than with acousto-optic modulators and also to improve the compactness.
The coherence relationships between the beams are obtained and controlled by the OPLLs. The frequency error signals ε2 and ε3 make it possible respectively to slave the frequency of the oscillator of IOPLL2-1 (between the beam F1 and the beam F2) and the frequency of the oscillator of IOPLL3-1 (between the beam F1 and the beam F3) so that respectively the first slave laser L2 and the second slave laser L3 are resonant.
Preferably, the gyroscope 50 according to the invention also comprises a first photodetector PhD13 configured to receive one or more optical beams from the optical beam or beams injected in the first direction and at least a part of which has carried out at least one crossing of the cavity, and a second photo detector PhD2 configured to receive one or more optical beams from the optical beams injected in the second direction and at least a portion of which has made at least one crossing of the cavity.
These photo-detectors may be arranged at several locations with respect to the cavity depending on the type of cavity and the type of optical beam collected (reflected or transmitted), as described below. In the example of FIG. 5, the detector PhD13 receives the beams 51 and 53 coming from the injected beams in the CW direction Fl and F3, and the detector PhD2 receives the beam 52 coming from the injected beam in the CCW direction F2.
The photodetectors PhD13 and PhD2 are configured to generate three electrical signals from the 3 detected optical signals 51, 52 and 53.
The detector PhD13 detects the two signals 51 and 53 likely to beat together, but the demodulation step then performed on each of the electrical signals makes it possible to recover only the signal of interest.
Each electrical signal is sent to the corresponding device. In the example, the electrical signal coming from the optical beam 51 (F1) constitutes the input of the master servo device DA1, the electrical signal coming from the optical beam 52 (F2) constitutes the input of the second slave device D2, and the electrical signal from the optical beam 53 (F3) constitutes the input of the first device device DI slave.
FIG. 6 illustrates an embodiment of the gyroscope 50 according to the invention and more particularly details the various components used.
Advantageously, the master servo device DA1 is of the type described in the state of the art in FIGS. 2 or 3. It comprises a master phase modulator PMI of the optical beam from the master laser L1 and a master demodulation device DM1 acting on the electrical signal from the corresponding photodetector PhD13. The device DM1 comprises a master phase shifter, a master oscillator Oscl operating at a predetermined master oscillation frequency fml also used by the master phase modulator and a master mixer of the signals from the master oscillator and the master phase shifter, the signal from the master oscillator. master frequency error ε1 being obtained from the signal from the master mixer. The device DA1 also comprises a master feedback electronics BRI configured to generate a correction signal from the master frequency error signal ε1, and feedback directly to the master frequency f1 of the master laser L1 or feedback on the length L of the cavity , the frequency of the master laser remaining fixed.
Advantageously, the master servo device DA1 is of the Pound Drever Hall type.
According to one variant, the master phase modulator consists of an electrical signal directly modulating the supply current of the master laser L1 to the predetermined master oscillation frequency fm1. Thus, for generating the "side bands", a direct modulation of the laser current L1 at the same frequency fm1 is used, for example when the master injection laser L1 is a laser diode, instead of a modulating PM1 component. phase.
Figure 6 also describes an example of slave devices D2 and D3. These devices have an architecture substantially identical to that of the master servo device DA1;
Advantageously, each slave device D2 or D3 of the first control stage comprises: a phase modulator PM2 or PM3 of the optical beam F2 or F3 of the corresponding slave laser L2 or L3.
According to one variant, the phase modulator consists of an electrical signal directly modulating the supply current of the corresponding slave laser L2, L3, at the predetermined oscillation frequency fm2, fm3.
Instead of the PM2 and / or PM3 phase modulator components, instead of generating the "side bands", a direct modulation of the current of the L2 and L3 lasers at the same frequencies fm2, fm3, when, for example, the injection lasers is used. L2 and L3 are laser diodes.
Each slave device of the first control stage also comprises a demodulation device DM2 or DM3 disposed at the output of the photodetector having detected the corresponding optical beam, 52 detected by PhD2 or 53 detected by PhD13. Each demodulation device comprises a phase-shifter, an oscillator operating at a predetermined oscillation frequency fm2 or fm3 also used by the corresponding phase modulator, a mixer of the signals coming from the oscillator and the phase-shifter, the frequency error signal ε2 or ε3 being obtained from the signal from the mixer, a feedback electronics ER2 or ER3 configured to generate a correction signal from the frequency error signal ε2, ε3.
The error signals ε2, ε3 are not used to directly slave the frequency of the corresponding laser L2, L3 to a cavity mode. They are used as a correction signal to set the frequency of the radiofrequency offset signal, as explained below.
We will now describe the second enslavement stage based on the OPLL principle.
The operation of an OPLL is modeled on the principle of Phase Lock Loop or PLL, and adapted to operate on the relative phase between two optical beams by transposition on an electrical signal. The principle of such an enslavement is illustrated in FIG.
One seeks to enslave a slave frequency fe of a slave laser Le at the master frequency fm of a master laser.
Recall that the frequency of a signal f is proportional to the derivative of the phase φ of the signal with respect to time. Making the phase difference between a slave signal to be enslaved and a reference signal, for example zero, makes it possible to obtain a slave frequency fe controlled by the master frequency fm.
In other words, an OPLL is configured to carry out the servocontrol from an error signal εφ which is a function of a phase difference between, on the one hand, the beat fm-fe between the master frequency and the slave frequency, and on the other hand a reference signal having a predefined fref reference frequency.
According to a preferred embodiment, the OPLL phase-locked loop comprises a PhD photodiode which detects the optical beams from the master and slave laser, and more particularly the beat signal between these frequencies, of frequency fm-fe. The frequency of the slave laser fe is slaved to the frequency of the master laser fm (itself directly slaved to a resonance mode of the cavity of the gyrometer), from this beat fm-fe that it is desired to adjust to a value predetermined.
When the beat frequency between the two lasers is typically of the order of magnitude of the Gigahertz, the phase comparison between these signals is very complex to implement. Then a conversion of the beat frequency fm-fe to a converted lower frequency signal fm-fe-fdc is performed using a mixer M, this operation being referred to as "down conversion" in English. The aim is to make the frequency of the signal to be enslaved compatible with the operating range of the phase comparator Compφ. The obtained signal of frequency fm-fe-fdc and phase Φ = 2π (fm-fe-fd) t + Φm-Φe (it is assumed that the oscillator at the frequency fd to use the down-conversion has a sufficiently stable phase not to be taken into account) typically has a frequency between 1 and 500 MHz. Preferably a filter is added after the mixer to select only the signal of interest of frequency fm-fe-fdc according to the desired range.
The OPLL also includes a reference oscillator Ose configured to generate a radiofrequency offset signal having a radio fref reference frequency and a reference phase Φref.
Then the phase comparator Compφ generates an error signal εφ which is a function of the phase difference Φ - Φref between the converted signal and the radio reference signal.
Finally, an electronic feedback device ER generates a correction signal and feedbacks on the slave frequency fe of the slave laser so as to minimize the error signal φ. For the case of a DFB laser diode, the laser supply current is typically affected, the optical frequency being a function of the current.
Typically on ignition, after a certain time, the frequency of the converted beat signal locks on the frequency fref selected oscillator with: fm - fe - fd = +/- fref
The slave laser then has a slave frequency equal to the master frequency offset from the reference frequency and the down-conversion frequency:
Thus, when two optical beams are fired from two sources on a photo detector, and their frequencies are sufficiently close to the detector bandwidth, a sinusoidal beat signal is obtained whose duration, frequency stability, phase and amplitude stability depends on the degree of coherence between the two sources. The more the sources are coherent (we suppose them constant intensities), the more this beat signal looks like a sinusoidal signal coming from an electric generator with small fluctuations of the frequency and the phase (few discontinuities, jumps, or transient deviations to a sinus). The objective of an OPLL is to enslave the beat signal between two lasers, possibly shifted by offset in the range of frequencies accessible to the phase comparators, on a reference oscillator (thus very stable), the radiofrequency offset signal , so that this beat signal is as sinus as stable as possible from that delivered by the reference oscillator (it is assumed that the down conversion signal is stable enough not to be taken into account).
Once this regime reached, the two lasers, previously independent, have a relationship of coherence between them.
The gyroscope according to the invention uses in an original manner two optical phase-locked loops. The coherence relationship between the three injection lasers of the gyrometer is obtained thanks to two optical phase lock loops, one between the master laser and a first slave, and another between the master laser and a second slave.
Preferably, in order to collect the beat signals, the first optical phase-locked device OPLL2-1 comprises a third photodetector PhD012 which receives the optical beams coming from the master laser L1 and the first slave laser L2 and which generates a first signal. electrical beat between the received optical beams. Similarly, the second optical phase-locked device OPLL3-1 comprises a fourth photodetector PhD013 which receives the optical beams from the master laser L1 and the second slave laser L3 and which generates a second electric beat signal between the optical beams received. .
In addition, if for each OPLL the reference oscillator is tunable, and one of the two lasers (the master laser) is slaved to a resonance of the cavity, then the reference oscillator frequency can be tuned to that the frequency of the beat signal between the two beams (which is ideally a sinusoidal signal maintained by the OPLL) corresponds to an integer number of ISL of the cavity. The slave laser then also lays on a resonance mode of the cavity different from the resonance mode of the master laser.
Thus, advantageously, the first radiofrequency offset signal has a first reference frequency f2ref tunable and a reference phase 02ref, and the first optical phase lock device OPLL2-1 is configured to feedback on the frequency f2 of the first slave laser L2 to slave the first beat signal, possibly converted in the low frequency domain, to the first radiofrequency offset signal, the first reference frequency f2ref without downconverting or the sum of the first reference frequency f2ref and the down frequency fdc -conversion in the opposite case, being made equal to an integer n1 free spectral interval ISL of the cavity by using the correction signal from the first frequency error signal ε2 delivered by the first servo-control stage.
Similarly, the second radiofrequency offset signal has a second tunable fSref reference frequency and a reference phase 03ref, and the second optical phase lock device OPLL3-1is configured to feedback on the frequency f3 of the second slave laser L3. to slave the second beat signal, possibly converted in the low frequency domain, to the second radiofrequency offset signal, the second reference frequency f3ref without downconverting or the sum of the second reference frequency f3ref and the down frequency -conversion fdc 'in the opposite case, being made equal to an integer n2 free spectral interval ISL of the cavity by using the correction signal from the second frequency error signal ε3 delivered by the first servo-control stage.
When the frequencies are locked and in the absence of rotation, the slave frequency f2 is shifted from the master frequency f1 by a value corresponding to the reference frequency f2ref + fd = n1 .ISL. f2-f1 = +/- (f2ref + fd) = +/- nl.lSL
Similarly, the slave frequency f3 is shifted from the master frequency f1 by a value corresponding to the reference frequency f3ref + fd = n2.ISL. F3-f1 = +/- (f3ref + fd) = +/- n2.ISL
When the gyro is angularly rotated, the resonance frequencies change over time. The operation of the servo is similar to that of a looped system whose operating point is changed to ensure the follow-up of the resonances.
One embodiment of the OPLLs is described in FIG.
Each optical phase-locked device OPLL2-1 (OPLL3-1) comprises, to achieve the control of the beat signal on the radiofrequency offset signal: a phase comparator PC (PC ') configured to compare a phase of the signal of beats or of the converted signal Φ2 (Φ3) and the phase Φ2ref (Φ3ref) of the corresponding radio frequency shift signal, the comparator being configured to generate a phase error signal εΦ (εΦ '), - an electronic feedback circuit ER ( ER ') configured to generate a correction signal and feedback on the slave frequency f2 (f3) of the slave laser L2 (L3) from the phase error signal εΦ (εΦ').
Compared with the use of a single laser and acousto-optic modulators, a laser gyrometer 3 is obtained in which:
• the coherence relationships between the beams are obtained and controlled by the OPLLs
The frequency deviations between the three beams, making it possible to slave the frequency of each beam to obtain (absence of rotation) or to preserve (presence of rotation) their resonance are controlled via the control of the frequency of the reference oscillator of each of the OPLLs • the error signal ε1 makes it possible, as before, to slave the laser L1 to the cavity or vice versa. The error signals ε2 and ε3 make it possible respectively to slave the frequency f2ref of the oscillator of IOPLL1-2 and the frequency f3ref of IOPLL1-3 so that L2 and L3 are resonant.
To ensure proper operation of the OPLLs the integers n1, n2 and the frequencies fdc and fdc 'of down conversion are such that the corresponding reference frequencies f2ref, f3ref are included in a corresponding photodetector bandwidth.
According to an embodiment illustrated in FIG. 6, a "down conversion" is necessary and in this case each optical frequency locking device OPLL1-2 (OPLL1-3) comprises a mixer M (M ') configured to convert a frequency of the signal of beat f2-f1 (f3-f1) in a converted frequency f2-f1-fdc (f3-f1-fdc ') in the radio frequency domain, the slaving occurring from the converted frequency.
Typically each converted frequency is between 1 and 500 MHz. Such a frequency is compatible with a phase comparator realized in integrated optics.
According to a variant, a filter is placed at the outlet of each mixer.
The gyrometer according to the invention can operate from different optical signals 51, 52, 53 received by the first PhD13 and second PhD2 detectors. According to a first embodiment illustrated in FIGS. 8 and 9, the first and second photo-detectors are configured to receive optical beams 51, 52, 53 corresponding to optical beams at least partially reflected by the cavity. When the reflected intensities are used, they are maximum off resonance and minimum resonance and servo is adapted accordingly. Wax and wax circulators are inserted in the path of the optical beams in order to separate the reflected beams from the incident beams in the case of an optical fiber embodiment (FIG. 9). The use of reflected beams to deliver the error signals ε1, ε2 and ε3 is the most optimal, because in this case the maximum value of the modulation frequency of PMI, PM2 and PM3 is only limited by the interval free spectral ISL.
According to a second embodiment illustrated in FIG. 10, the first and second photo-detectors are configured to receive optical beams 51, 52, 53 corresponding to optical beams transmitted by the cavity. When the intensities transmitted are used, these are minimum resonant and maximum resonance and servo is adapted accordingly. One advantage is that lasers generally comprising insulators, the presence of insulators Iso and lso 'is not essential, and the realization of cavity C and couplers C1 and C2 is compatible with an implementation in integrated optics.
The gyro according to the invention is also compatible with any type of cavity, free space, hollow fiber, integrated optical resonator ...
According to one embodiment, the cavity C of the gyrometer 50 comprises two free-space couplers 10, 11, the remainder of the cavity being for example in free space, with mirrors) or comprising an optical fiber OF, as illustrated in FIGS.
Another embodiment illustrated in FIG. 9 is particularly well suited when the cavity consists of an optical fiber OF. The cavity comprises, in addition to the optical fiber OF, a first coupler 2 by 2 Cl, this first coupler being configured to inject the optical beams Fl, F2, F3 into the cavity and to direct the reflected optical beams 51, 52, 53 by the cavity to the first PHD13 and the second photo detector PhD2.
According to another embodiment, the fiber-optic cavity comprises a first coupler 2 by 2 Cl and a second coupler 2 by 2 C2, the first coupler C1 being configured to inject the optical beams F1, F2, F3 into the cavity, the second coupler C2 being configured to direct the optical beams 51, 52, and 53 transmitted by the cavity to the first PHD13 and the second PhD2 photo detector.
An exemplary order of magnitude for the gyrometer 50 is given below without limitation.
We consider injection lasers L1 L2 and L3 of semiconductor or optical fiber type emitting at a wavelength of 1.55 pm for example. Consider a cavity of length 5 cm index 1.6 made in integrated optics (in this example in Si3N4 to have low loss of propagation), an ISL of 3.75 GHz .This length is a good compromise because we do not necessarily seek to make very small cavities because the sensitivity depends on the surface.
For a master frequency f1 of about 1.94 × 10 -3 Hz (λ = 1.55 μm), there is therefore an NI of the order of 51000.
We seek to shift the slave frequencies f2 and f3 by at least one integer value of ISL;
We can do +1. ISL (N2 = NI +1), and -1 .ISL (N3 = NI -1)
Or we can also do +1. ISL, and + 2.ISL (N2 = N1 + 1 and N3 = N1 + 2) ... or -1. ISL, and -2.ISL (N2 = N1 - 1 and N3 = N1 - 2).
Taking into account the value of the ISL, one will be satisfied with a shift of some ISL to remain compatible of photodiodes integrable in integrated optics .......
The gyrometer 50 according to the invention is compatible with an embodiment in integrated optics, because it does not require acousto-optic modulators.
In addition, the use of OPLL loops is compatible with orders of magnitude of the offsets to be carried out and an implementation in integrated photonics, which makes it possible to drastically reduce the size and the total cost.
The optical block of the gyroscope 50 is defined which comprises the paths of the optical beams and the optical components necessary for implementing said gyrometer (such as phase modulators) and including the photodetectors.
According to a first integration level illustrated in FIG. 11, the optical block is a PIC photonic circuit realized in integrated optics, for example on Silicon or InP substrate, or any other compatible material of the required functionalities. The coupling in and out of the PIC circuit can be done by the slice or directly out of the plane of the circuit using networks. In addition, in FIG. 11, each PMI modulator PM2, PM3 is equipped with a photodiode. This allows to measure and control the power of the three beams and thus reduce the Kerr effect related to a difference in power between the two counterpropagating waves in the cavity. This PIC circuit can then be connected to a cavity-based mirror (Figure 11) or fiber. Thus the optical block is made in the form of at least one integrated circuit.
According to a higher level of integration, the cavity and / or injection lasers are also made in integrated optics.
For the sake of clarity, the measurement of the frequencies f 1, f 2 and f 2 making it possible to go back to the length of the cavity and to the speed of rotation are not shown. This measurement can be done in two ways.
According to one variant, a calibration of the feedback signals injected into the OPLLs and the master laser is used to go back to fl, f2 and f3.
According to another variant, the optical beams are used directly. For example, by taking part of F1 and F3 before coupler 10 (FIGS. 5 and 11) or before coupler C1 (FIGS. 9 and 10) and sending this optical signal to a photodiode, f1-f3 is measured directly at using a frequency counter. As it is a beat, one can also directly use the methods of the RLG gyrolasers (provided to adapt the bandwidth). Similarly, by taking and combining Fl, F3 and F2, the electrical beat signal will have components at -F3, F1-F2, F2-F3 that can be filtered and measured. According to another variant, a configuration which is a mix of FIGS. 9 and 10 is used: the reflected beams are used to slave (which also gives a first set of values of cavity length and rotation speed) and the recombined transmitted beams in beat to deduce a second set of values of cavity length and rotation speed.

权利要求:
Claims (15)
[1" id="c-fr-0001]
A resonant passive optical gyroscope (50) comprising a cavity (C) and operating with three frequencies, and comprising: a first injection laser (L1) configured to inject a first optical beam (F1) into the cavity in a first sense, -a second injection laser (L2) configured to inject a second optical beam (F2) into the cavity in a direction opposite to the first direction, - a third injection laser (L3) configured to inject a third optical beam (F3) in the cavity according to one of the two aforementioned directions, a laser of one of the injection lasers being chosen as the master laser (L1) having a master frequency (f1), the other two injection lasers being respectively designated first (L2) and second (L3) slave lasers respectively having a first (f2) and a second (f3) slave frequencies, -a master servo device (DA1) configured to directly slave the f master frequency (f1) at a natural frequency corresponding to a resonance mode of the cavity or for controlling a natural frequency corresponding to a resonance mode of the cavity at the master frequency of the master laser, a first servo-control stage comprising a first (D2) and a second (D3) slave devices respectively configured to generate a first (ε2) and a second (ε3) frequency error signals having a minimum absolute value respectively when the first and second slave frequencies each correspond to a mode resonant cavity, - a second servo-control stage comprising a first (OPLL2-1) and a second (OPLL3-1) optical phase locking device comprising respectively a first (Osc2) and a second (Osc3) oscillators slaves configured to generate first and second radiofrequency offset signals, said first (OPLL2-1) and second ( OPLL3-1) optical phase lock devices being configured to respectively make coherent the first slave laser (L2) with the master laser (L1) and the second slave laser (L3) with the master laser (L1) and to slave the first (f2) and the second (f3) slave frequencies on resonance modes of the cavity different from the resonance mode corresponding to the master frequency (f1), each radio frequency offset signal of the second servo-control stage being determined from the signal corresponding frequency error (ε2, ε3) of the first servo-control stage.
[2" id="c-fr-0002]
2. Gyrometer according to claim 1, further comprising: a first photodetector (PhD13) configured to receive one or more optical beams (51, 53) originating from the optical beam or beams injected in the first direction (F1, F3) and of which at least one part has made at least one crossing of the cavity, and - a second photodetector (PhD2) configured to receive the optical beam or beams (52) coming from the optical beam or beams injected in the second direction (F2) and of which at least one portion has made at least one crossing of the cavity, said photo-detectors being configured to generate three electrical signals from the three optical beams received, each electrical signal being sent to the master servo device or in the first or in the corresponding second slave device.
[3" id="c-fr-0003]
3. Gyrometer according to one of claims 1 or 2 wherein the master servo device comprises: a master phase modulator (PM1) of the optical beam of the master laser, -a master demodulation device (DM1) disposed at the output of the corresponding detector photo: a master phase shifter, a master oscillator (Oscl) operating at a predetermined master oscillation frequency (fml) also used by the master phase modulator, a master mixer of the signals from the oscillator and the phase-shifter masters, a master frequency error signal (ε1) being obtained from the signal from the master mixer, -a master feedback electronics (ER1) configured to generate a correction signal from the master frequency error signal (ε1 ), and to feedback directly to the master (fl) frequency of the master laser (L1) or over a length of the cavity, the frequency of the master laser res so fixed.
[4" id="c-fr-0004]
4. Gyrometer according to claim 3 wherein the master phase modulator consists of an electrical signal directly modulating the power supply of the master laser (L1) to the predetermined master oscillation frequency (fm1).
[5" id="c-fr-0005]
5. Gyrometer according to one of the preceding claims wherein the master servo device (DA1) is Pound Drever Hall type.
[6" id="c-fr-0006]
6. Gyrometer according to one of the preceding claims wherein each slave device (D2, D3) of the first servo-control stage comprises: a phase modulator (PM2, PM3) of the optical beam of the corresponding slave laser; demodulation (DM2, DM3) arranged at the output of the photodetector having detected the corresponding optical beam, and comprising a phase-shifter, an oscillator operating at a predetermined oscillation frequency (fm2, fm3) also used by the corresponding phase modulator, a mixer signals from the oscillator and the phase-shifter, the frequency error signal (ε2, ε3) being obtained from the signal from the mixer, -a feedback electronics (ER2, ER3) configured to generate a correction signal at from the frequency error signal (ε2, ε3).
[7" id="c-fr-0007]
7. Gyrometer according to claim 6 wherein the phase modulator consists of an electrical signal directly modulating the supply current of the corresponding slave laser (L2, L3) at the predetermined oscillation frequency (fm2, fm3).
[8" id="c-fr-0008]
8. Gyrometer according to one of the preceding claims wherein the first (OPLL2-1) and second (OPLL3-1) optical phase lock devices respectively comprise a third (PhD012) and a fourth photodetector (PhD013) configured to generate respectively a first and a second beat signal respectively between an optical beam from the master laser (L1) and an optical beam from the first slave laser (L2) and between an optical beam from the master laser (L1) and an optical beam from the second slave laser (L3).
[9" id="c-fr-0009]
9. A gyrometer according to claim 8 wherein each radiofrequency offset signal has a tunable reference frequency (f2ref, f3ref) and a reference phase (Φ2ref, Φ3ref), and wherein each optical phase lock device is configured to feedback. on the frequency of the corresponding slave laser (f2, f3) so as to slave the beat signal to the radiofrequency shift signal, the reference frequency being made equal to an integer (n1, n2) of free spectral intervals (ISL ) of the cavity by using a correction signal derived from the corresponding frequency error signal (ε2, ε3), each slave frequency (f2, f3) then being respectively shifted from the master frequency (f1) by a value corresponding to the corresponding reference frequency (f2ref, f3ref).
[10" id="c-fr-0010]
10. A gyrometer according to claim 9 wherein the integer (n1, n2) is such that the reference frequency edpondant (f2ref, fSref) is within a bandwidth of the corresponding third or fourth photodetector.
[11" id="c-fr-0011]
11. Gyrometer according to one of claims 8 to 10 wherein each optical frequency locking device (OPLL2-1, OPLL3-1) comprises a mixer (M, M ') configured to convert a frequency of the beat signal (f2 -f1, f3-f1) at a converted frequency (f2-f1-fdc, f3-f1-fdc ') in the radiofrequency domain, the slaving occurring from the converted frequency.
[12" id="c-fr-0012]
12. Gyrometer according to one of claims 9 to 11 wherein each optical phase lock device (OPLL2-1, OPLL3-1) comprises, for performing the control of the beat signal on the radiofrequency shift signal: -un phase comparator (PC, PC ') configured to respectively compare a phase of the beat signal or of the converted signal (Φ2, Φ3) and the phase (Φ2ref, Φ3ref) of the radiofrequency shift signal, the comparator being configured to generate a signal ! of phase error (εΦ, εΦ '), - a feedback electronics (ER, ER') configured to generate a correction signal and feedback on the slave frequency (f2, f3) of the slave laser (L2, L3) to from the phase error signal (εΦ, εΦ ').
[13" id="c-fr-0013]
13. Gyrometer according to one of claims 2 to 12 wherein the first and the second photodetector (PHD13, PhD2) are configured to receive optical beams (51, 52, 53) at least partially reflected by the cavity.
[14" id="c-fr-0014]
14. Gyrometer according to one of claims 2 to 12 wherein the first and the second photodetector (PHD13, PhD2) are configured to receive optical beams (51, 52, 53) transmitted by the cavity.
[15" id="c-fr-0015]
15. Gyrometer according to one of the preceding claims wherein an optical block comprising the paths of the optical beams and optical components necessary for the implementation of said gyrometer are made in the form of at least one integrated photonic circuit (PIC). .

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CN107345811A|2017-11-14|

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US10371524B2|2019-08-06|

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2017-10-13| PLSC| Publication of the preliminary search report|Effective date: 20171013 |

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优先权:

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FR1600581A|FR3050025B1|2016-04-06|2016-04-06|COMPACT RESONANT OPTICAL GYROMETER WITH THREE FREQUENCIES|

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FR1600581|2016-04-06|FR1600581A| FR3050025B1|2016-04-06|2016-04-06|COMPACT RESONANT OPTICAL GYROMETER WITH THREE FREQUENCIES|

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US15/480,129| US10371524B2|2016-04-06|2017-04-05|Compact three-frequency resonant optical gyroscope|

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EP17164910.6A| EP3228987A1|2016-04-06|2017-04-05|Compact resonant optical gyrometer with three frequencies|

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CN201710221667.8A| CN107345811A|2016-04-06|2017-04-06|The frequency resonant optical mode gyroscope of compact three|