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Showing papers on "Ring laser gyroscope published in 2014"


Journal ArticleDOI
TL;DR: In this paper, the authors present the historical context of Sagnac's experiment, the origin of all optical gyros, and the challenge being the ultimate inertial navigation performance of one nautical mile per month corresponding to a long-term bias stability of 10 − 5 ° / h.

62 citations


Proceedings ArticleDOI
03 Apr 2014
TL;DR: In the past fifty years, significant evolutionary and revolutionary changes have taken place in the designs of inertial sensors and systems, including the progression from fluid-filled to dry instruments and the transition from mechanically complex stabilized inertial platforms to computationally intensive strapdown systems.
Abstract: Inertial navigation provides a unique ability to know where one has been, where one is currently, and where one is going, given only a starting position. The laws of physics permit the sensing of dynamic motion without external information, making inertial systems impervious to jamming, masking, or spoofing. Measurements of six degrees of freedom are required - three linear accelerations, and three angular rates - to fully propagate the velocity, position, and orientation of the system. The first inertial sensors are traced to the early 19th century and specialized inertial guidance systems appeared in the 1940s, yet inertial navigation systems did not become commonplace until the 1960s. This is largely due to the fact that requirements for navigation accuracy inertial sensors - accelerometers and gyroscopes - are very challenging. In the past fifty years, significant evolutionary and revolutionary changes have taken place in the designs of inertial sensors and systems. These include the progression from fluid-filled to dry instruments and the transition from mechanically complex stabilized inertial platforms to computationally intensive strapdown systems. Gyroscopes have evolved from large mechanical devices to highly refined precision mechanical sensors. Optical rotation sensors such as the ring laser gyro and the fiber optic gyro have enabled new system designs and capabilities. Coriolis vibratory gyroscopes such as the hemispherical resonator gyro are capable of extreme accuracy and reliability; new opportunities for miniaturizing these types of sensors will lead to new classes of accuracy for inertial navigation systems. Advanced gyroscope technologies such as the nuclear magnetic resonance gyroscope which uses atomic spin to detect rotation have already been demonstrated to achieve navigation accuracy requirements. Cold atom technologies may also provide the opportunity for very high accuracy accelerometers and gyroscopes in the future. Inertial navigation technologies and applications of the past, present, and future are discussed.

59 citations


Journal ArticleDOI
TL;DR: In this paper, a model based on Lamb's theory of gas lasers is applied to a He-Ne ring laser (RL) gyroscope to estimate and remove the laser dynamics contribution from the rotation measurements.
Abstract: A model based on Lamb's theory of gas lasers is applied to a He–Ne ring laser (RL) gyroscope to estimate and remove the laser dynamics contribution from the rotation measurements. The intensities of the counter-propagating laser beams exiting one cavity mirror are continuously observed together with a monitor of the laser population inversion. These observables, once properly calibrated with a dedicated procedure, allow us to estimate cold cavity and active medium parameters driving the main part of the non-linearities of the system. The quantitative estimation of intrinsic non-reciprocal effects due to cavity and active medium non-linear coupling plays a key role in testing fundamental symmetries of space–time with RLs. The parameter identification and noise subtraction procedure has been verified by means of a Monte Carlo study of the system, and experimentally tested on the G-PISA RL oriented with the normal to the ring plane almost parallel to the Earth's rotation axis. In this configuration the Earth's rotation rate provides the maximum Sagnac effect while the contribution of the orientation error is reduced to a minimum. After the subtraction of laser dynamics by a Kalman filter, the relative systematic errors of G-PISA reduce from 50 to 5 parts in 103 and can be attributed to the residual uncertainties on geometrical scale factor and orientation of the ring.

29 citations


Journal ArticleDOI
TL;DR: In this article, the authors present an experimental test of a method for controlling the absolute length of the diagonals of square ring laser gyroscopes using a single diode laser, injection locked to a frequency stabilized He?Ne/iodine frequency standard, and a single electro-optic modulator.
Abstract: We present the experimental test of a method for controlling the absolute length of the diagonals of square ring laser gyroscopes. The purpose of this is to actively stabilize the ring cavity geometry and to enhance the rotation sensor stability in order to reach the requirements for the detection of the relativistic Lense?Thirring effect with a ground-based array of optical gyroscopes. The test apparatus consists of two optical cavities 1.32 m in length, reproducing the features of the ring cavity diagonal resonators of large-frame He?Ne ring laser gyroscopes. The proposed measurement technique is based on the use of a single diode laser, injection locked to a frequency stabilized He?Ne/iodine frequency standard, and a single electro-optic modulator. The laser is modulated with a combination of three frequencies, allowing us to lock the two cavities to the same resonance frequency and, at the same time, to determine the cavity free spectral range (FSR). We obtain a stable lock of the two cavities to the same optical frequency reference, providing a length stabilization at the level of 1 part in , and the determination of the two FSRs with a relative precision of ?2 ? 10?7. This is equivalent to an error of on the absolute length difference between the two cavities.

26 citations


Proceedings ArticleDOI
02 Jun 2014
TL;DR: In this paper, a bench-top resonator fiber optic gyroscope (RFOG) was assembled and tested, showing encouraging progress toward a navigation grade performance, achieving an angle random walk (ARW) of 0.008 deg/rt-hr.
Abstract: A bench-top resonator fiber optic gyroscope (RFOG) was assembled and tested, showing encouraging progress toward navigation grade performance. The gyro employed a fiber length of 19 meters of polarizing fiber for the sensing coil which was wound on an 11.5 cm diameter PZT cylinder. A bias stability of approximately 0.1 deg/hr was observed over a 2 hour timeframe, which is the best bias stability reported to date in an RFOG to our knowledge. Special care was taken to minimize laser phase noise, including stabilization to an optical cavity which was also used for optical filtering, giving angle random walk (ARW) values in the range of 0.008 deg/rt-hr. The ARW performance and bias stability are within 2x and 10x, respectively, of many civil inertial navigation grade requirements.

22 citations


Journal ArticleDOI
03 Sep 2014-Sensors
TL;DR: The results show that deflections of the vertical can achieve a precision of better than 1″ for a single survey line and can be applied to a gravimetry system based on a ground vehicle or ship with a speed lower than 25 m/s.
Abstract: A new method for dynamic measurement of deflections of the vertical (DOV) is proposed in this paper. The integration of an inertial navigation system (INS) and global navigation satellite system (GNSS) is constructed to measure the body's attitude with respect to the astronomical coordinates. Simultaneously, the attitude with respect to the geodetic coordinates is initially measured by a star sensor under quasi-static condition and then maintained by the laser gyroscope unit (LGU), which is composed of three gyroscopes in the INS, when the vehicle travels along survey lines. Deflections of the vertical are calculated by using the difference between the attitudes with respect to the geodetic coordinates and astronomical coordinates. Moreover, an algorithm for removing the trend error of the vertical deflections is developed with the aid of Earth Gravitational Model 2008 (EGM2008). In comparison with traditional methods, the new method required less accurate GNSS, because the dynamic acceleration calculation is avoided. The errors of inertial sensors are well resolved in the INS/GNSS integration, which is implemented by a Rauch–Tung–Striebel (RTS) smoother. In addition, a single-axis indexed INS is adopted to improve the observability of the system errors and to restrain the inertial sensor errors. The proposed method is validated by Monte Carlo simulations. The results show that deflections of the vertical can achieve a precision of better than 1″ for a single survey line. The proposed method can be applied to a gravimetry system based on a ground vehicle or ship with a speed lower than 25 m/s.

15 citations


Journal ArticleDOI
TL;DR: In this paper, the authors summarized the recent development of highly sensitive large Sagnac gyroscopes, and presented unique results from the measurements of rotations of the earth, including the effect of diurnal polar motion, the Chandler and the Annual wobbles as well as tilts from the solid Earth tides.

13 citations


Journal ArticleDOI
TL;DR: In this article, the Sagnac effect in a two-dimensional array of evanescently coupled optical microring resonators was analyzed and it was shown that the sensitivity to inertial rotations greatly exceeds that of a single resonator with equal enclosed area.
Abstract: Micron-scale-integrated optical gyroscopes based on the Sagnac effect have a broad array of potential applications in navigation and inertial motion sensing due to the benefit of on-chip integration and potential sensitivities exceeding micro-electromechanical gyroscopes. Here, we analyze the Sagnac effect in a two-dimensional array of evanescently coupled optical microring resonators. We show that the sensitivity to inertial rotations greatly exceeds that of a single resonator with equal enclosed area. Moreover, a comparison between two-dimensional arrays and Sagnac gyroscopes consisting of one-dimensional distributed microresonators arrays of equal footprint shows that the sensitivity to rotations of the two-dimensional array exceeds that of the one-dimensional structures by as much as several orders of magnitude for smaller arrays.

13 citations


Patent
Li Hong, Li Haizhou, Sun Qian, Shan Kun, Mu De 
19 Nov 2014
TL;DR: In this paper, a vehicle positioning device based on a laser gyroscope strapdown inertial measurement unit is presented, aiming to enhance a rapid maneuvering capability and an object targeting precision of a weapon system and satisfy requirements of a quick response, a high precision, a strong independence and a good reliability of the system on a V2V positioning device.
Abstract: The invention, aiming to enhance a rapid maneuvering capability and an object targeting precision of a weapon system and satisfy requirements of a quick response, a high precision, a strong independence and a good reliability of the system on a vehicle positioning device, provides the vehicle positioning device based on a laser gyroscope strapdown inertial measurement unit. The vehicle positioning device includes: a laser strapdown inertial measurement unit in which a laser gyroscope is employed, an odometer assembly used for measuring a running speed and a running distance of a vehicle on ground, an elevation meter used for obtaining an altitude by measuring an atmosphere pressure of a level of the vehicle, a multimode satellite system which is compatible with single antenna and double antennas, and a display controlling apparatus assembly used for carrying out an intelligent match between positioning information of the vehicle positioning device and a road network electronic map. By means of advantages of being high in precision, stable in performance, wide in dynamic range, short in response time and high in reliability of the laser gyroscope, a positioning and orienting function which is high in precision, strong in independence and good in reliability is achieved through methods, such as a gyroscope demodulation technology, a multi-information fusion technology and the like, on the basis of a digital filter.

13 citations


Journal ArticleDOI
TL;DR: In this paper, a vibration isolation system (VIS) is employed inside a mechanically dithered Ring Laser Gyroscope (RLG) based Position and Orientation System (POS) to attenuate such disturbance but induces additional attitude measurement errors.

12 citations


Patent
11 Jun 2014
TL;DR: Optical gyroscope devices and methods based on optical interferometric configurations to minimize optical loss and enhance the device energy efficiency are discussed in this paper, where the authors use optical polarization control to reduce the optical loss in routing light to and from an optical ring.
Abstract: Optical gyroscope devices and methods based on optical interferometric configurations to minimize optical loss and enhance the device energy efficiency. In one implementation, optical polarization control is provided in an optical gyroscope to reduce the optical loss in routing light to and from an optical ring that senses the rotation.

Patent
03 Jan 2014
TL;DR: In this article, a disc resonator gyroscope system may include a quadrature stabilization circuit configured to measure the quadratures error and generate a regulating voltage to cancel an effect of voltage flicker before being applied to a tuning electrode.
Abstract: A gyroscope system may include a disc resonator gyroscope including a plurality of electrodes embedded in the disc resonator gyroscope. The electrodes may be configured for at least applying a drive voltage and a tuning voltage to the disc resonator gyroscope and for sensing operating parameters of the disc resonator gyroscope. The gyroscope system may also include a quadrature stabilization circuit configured to measure a quadrature error and generate a quadrature regulating voltage based on the quadrature error. The tuning voltage may be adjusted by the quadrature regulating voltage to cancel an effect of voltage flicker before being applied to a tuning electrode of the disc resonator gyroscope.

Journal ArticleDOI
TL;DR: In this article, a closed loop driving and detect circuit of piezoelectric solid-state micro gyroscope is proposed in order to track the resonance frequency drift, stabilize the driving voltage value and detect the Gyroscope output.
Abstract: Piezoelectric solid-state micro gyroscope is a novel kind of rotating rate sensor, which is based on the special thickness-shear vibrating mode of a piezoelectric body. Compared with the general vibratory micro gyroscope, it has no evident mass-spring component in its structure, so it has larger stiffness and robust resistance to shake and strike. Therefore, piezoelectric solid-state micro gyroscope can be used in the high-g environment. In this paper, piezoelectric solid-state micro gyroscope working principle is described. The closed loop driving and detect circuit of piezoelectric solid-state micro gyroscope is proposed in order to track the resonance frequency drift, stabilize the driving voltage value and detect the gyroscope output. The closed loop driving circuit (CLDC) mainly contains phase lock loop circuit, automatic gain circuit. Detect circuit mainly contains de-modulator, difference amplifier, Phase shift circuit and low pass filter. Experimental results show that the frequency of CLDC fluctuates within ±15 Hz with the resonance frequency of 357.9 kHz when get its stable status and the fluctuation of reference voltage is within ±7 mv, while the fluctuation of reference voltage in open loop driving circuit is ±23 mv. In the experiment, the sensitivity of the gyroscope with 740 mv/rad/s is observed. The work in the paper provides the theoretical and experimental foundation for realizing for this kind of gyroscope.

Proceedings ArticleDOI
02 Jun 2014
TL;DR: In this article, an experimental fiber optic gyroscope (FOG) utilizing a 1085m coil of 8-cm diameter driven with a laser of 10-MHz linewidth, with a record rotation-rate noise as low as 0.2 deg/h/ Hz and a drift below 0.038 deg /h.
Abstract: We report an experimental fiber optic gyroscope (FOG) utilizing a 1085-m coil of 8-cm diameter driven with a laser of 10-MHz linewidth, with a record rotation-rate noise as low as 0.2 deg/h/ Hz and a drift below 0.038 deg/h. Simulations and comparison to the measured performance of a similar 150-m FOG show that the dominant phase-bias errors have complicated length dependencies and consist of a combination of coherent backscattering and polarization coupling errors. Keywords: Fiber optic gyroscope, inertial navigation, rotation sensing, Sagnac interferometer 1. INTRODUCTION Fiber optic gyroscopes (FOGs) based on the Sagnac effect exhibit remarkable performance characteristics, thanks in part to their inherent reciprocity, which provides superior thermal stability and immunity to several sources of noise, and to the broadband light source used to interrogate them, which pract ically eliminates other sources of noise and drift in the fiber interferometer 1 . Commercial FOGs have very low noise and drift, for example 0.1 deg/ h and 1 deg/h, respectively, in the LN-200 unit from Northrop-Grumman

Journal ArticleDOI
TL;DR: In this article, the authors presented a miniaturized 3-axis gyroscope with vibratory ring springs, whose total size is 2mmx2mm and its resonance frequencies are respectively 16.9 kHz, 17.04 kHz, and 16.47 kHz for the pitch and rolling sensing modes.

Journal ArticleDOI
TL;DR: In this paper, the fabrication of silicon double mirrors for the miniaturization of an optical ring laser gyroscope (RLG) is described, which can provide a reduction of misalignment errors.

Patent
20 Aug 2014
TL;DR: In this article, a double-longitudinal mode frequency self-offset detection system and detection method of a prism laser gyro are presented. But the system is not suitable for the detection of a single-laser gyro.
Abstract: The invention discloses a double-longitudinal mode frequency self-offset detection system and detection method of a prism laser gyro. The system comprises a prism-type laser prism-type resonant cavity respectively connected to a high-frequency oscillator and an ignition transformer. A light beam emitted by the prism-type laser prism-type resonant cavity goes through a spectroscope and then irradiates into a photoelectric detector (a) and a focal spherical swept-frequency interferometer. The photoelectric detector (a) is respectively connected to an oscilloscope (a) and a resonant cavity modal control servo system. The resonant cavity modal control servo system is connected to a prism-type laser so that a loop is formed. The focal spherical swept-frequency interferometer is respectively connected to a sawtooth wave control box and a photoelectric detector (b). The photoelectric detector (b) is connected to an oscilloscope (b). Through change of voltage of a heater strip of the resonant cavity modal control servo system, the resonator optical cavity length is changed. A photo-signal is amplified and shaped so that square wave is formed, a phase-demodulation process is carried out in a field programmable gate array (FPGA), pulse number and gyro light-intensity information of the prism laser gyro under frequency self-offset are output and transmitted to an upper computer, and the upper computer carries out self-offset frequency point calculation so that prism laser gyro performances are improved.


Journal ArticleDOI
TL;DR: In this paper, the authors report progress towards a solid-state ring laser gyroscope (RLG), where mode competition is circumvented by active control of differential losses, and nonlinear effects are mitigated by longitudinal vibration of the gain medium.


Proceedings ArticleDOI
13 Mar 2014
TL;DR: In this article, the scale factor and bias of a commercial Coriolis force gyroscope were measured by imaging an optical diffraction pattern created by an incident laser off diffraction gratings on the dither stage.
Abstract: We demonstrate 107-ppm accurate scale-factor and bias calibration of a commercial Coriolis force gyroscope, in which the typical un-calibrated scale factor variations are ~100,000-ppm. In this paper, we present a proof-of-concept result on calibration architecture - Diffractive Optics Metrology Enabled Dithering Inertial Sensor Calibration (DOME-DISC). DOME-DISC consists of a piezoelectric dither stage to provide built-in mechanical stimulus to the gyroscope attached to it. The motion of the dithering stage is measured by imaging an optical diffraction pattern created by an incident laser off diffraction gratings on the dither stage. In order to calibrate the gyroscope, the stage motion needs to be measured accurately and precisely. The motion of the stage is measured using the Nano Optical Ruler Imaging System (NORIS), with absolute accuracy of ~30nm over several millimeters, stable over several hours. NORIS provides parts-per-million stage motion measurement accuracy. In this paper, an angular dither motion of 0.1 to 0.5 degrees was optically measured with ~ 0.1 millidegree resolution. By measuring the scale factor and bias for a gyroscope on the dither stage mounted directly on a commercial rate table, and matching the gyroscope input-output curve to 100ppm, we demonstrate the capability to measure in-package gyroscope characteristics within the error limits of the commercial rate table.

Patent
12 Mar 2014
TL;DR: In this article, a laser gyroscope IMU (inertial measurement unit) calibration method combining discrete analysis and Kalman filtration is presented. But the method is limited to the case of a single laser and does not address the problem of drift.
Abstract: The invention provides a laser gyroscope IMU (inertial measurement unit) calibration method combining discrete analysis and Kalman filtration. The method combines the advantages of two calibration methods, namely discrete analysis and system-level filtration. All 24 calibration coefficients of an angular speed and acceleration channel are preliminarily calibrated by a four-direction rotating rate discrete analysis method according to an angular speed and acceleration channel error model of a laser gyroscope IMU; then error values of the calibration coefficients are estimated by a Kalman filtration method with a lever-arm effect compensation function by taking the error values of the calibration coefficients as state variables, and the precise calibration coefficients are corrected. According to the method, errors caused by random errors such as deformation of a shock absorption device, and drifting of a gyroscope and an accelerator in a calibration process are eliminated, the precision of the calibration coefficient is improved, and the error of navigation calculation is alleviated.

Proceedings ArticleDOI
TL;DR: In this article, numerical simulations of the maximum sensitivity to absolute rotation of a number of coupled resonator optical waveguide (CROW) gyroscopes consisting of a linear array of coupled ring resonators are presented.
Abstract: This study presents numerical simulations of the maximum sensitivity to absolute rotation of a number of coupled resonator optical waveguide (CROW) gyroscopes consisting of a linear array of coupled ring resonators. It examines in particular the impact on the maximum sensitivity of the number of rings, of the relative spatial orientation of the rings (folded and unfolded), of various sequences of coupling ratios between the rings and various sequences of ring dimensions, and of the number of input/output waveguides (one or two) used to inject and collect the light. In all configurations the sensitivity is maximized by proper selection of the coupling ratio(s) and phase bias, and compared to the maximum sensitivity of a resonant waveguide optical gyroscope (RWOG) utilizing a single ring-resonator waveguide with the same radius and loss as each ring in the CROW. Simulations show that although some configurations are more sensitive than others, in spite of numerous claims to the contrary made in the literature, in all configurations the maximum sensitivity is independent of the number of rings, and does not exceed the maximum sensitivity of an RWOG. There are no sensitivity benefits to utilizing any of these linear CROWs for absolute rotation sensing. For equal total footprint, an RWOG is √N times more sensitive, and it is easier to fabricate and stabilize.

Patent
15 Sep 2014
TL;DR: In this article, a radio frequency based electronic gyroscope function is incorporated in its entirety on a monolithic integrated circuit (IC) for detection and measurement of movement in a particular plane.
Abstract: A radio frequency based electronic gyroscope function that may be incorporated in its entirety on a monolithic integrated circuit (IC). The detection and measurement of movement in a particular plane is based on the Sagnac effect as it applies to a radio frequency signal that propagates in two different directions in a loop that may be subject to rotational perturbation. In one embodiment, three mutually perpendicular loops that are incorporated into the same integrated circuit and are used to detect and measure movement in three planes (roll, pitch and yaw) thereby allowing a signal processing unit to quantify a general three dimensional movement. The gyroscope can be incorporated into an IC that is used in portable device, such as a mobile handset, to provide it with inertial navigation and movement detection and measurement capabilities.

Patent
19 Mar 2014
TL;DR: In this paper, a multi-list redundant strapdown inertial measuring device for a laser gyroscope is presented, where three orthogonally-arranged gyroscopes Gx, Gy and Gz can be used for sensing an angle speed of a carrier moving in an inertial space.
Abstract: The invention provides a multi-list redundant strapdown inertial measuring device for a laser gyroscope. According to the multi-list redundant strapdown inertial measuring device, three orthogonally-arranged gyroscopes Gx, Gy and Gz and two obliquely-arranged gyroscopes Gs and Gt can be used for sensing an angle speed of a carrier moving in an inertial space; three orthogonally-arranged accelerometers Ax, Ay and Az and two obliquely-arranged accelerometers As and At can be used for sensing a specific force of the carrier moving in the inertial space; a resolving computer of the device can be used for collecting inertial information in real time and at a high speed and the inertial information is sent to a navigational computer in real time by a high-speed bus; after the navigational computer obtains inertia type instrument information transmitted by the strapdown inertial measuring device for the laser gyroscope, information including a course, a posture, a speed, a position and the like of the carrier can be calculated and output in real time and is supplied to a guidance and posture control system for use.

Journal ArticleDOI
TL;DR: In this article, the authors point out that in a large number of previous tilt correction models, a significant term is missing, which is related with the Shida number l2 (called l2-term in the following).
Abstract: SUMMARY With the fast development of the large ring laser gyroscope (RLG) technology in the last decades, promising applications in geophysics and geodesy (e.g. observations of highfrequency variations of Earth’s rotation, Earth’s tide tilt and seismic waves) have been realized by various groups with currently running large RLGs. In this letter, we point out that in a large number of previous tilt correction models a significant term is missing. This term is related with the Shida number l2 (called l2-term in the following) and has a contribution, which is comparable with that from high-frequency Earth rotation variations due to ocean tides, to the Sagnac frequency record of RLGs. This term has to be removed (as part of the tilt correction) from the raw data so that RLGs can efficiently be employed as Earth’s rotation detectors.

Journal ArticleDOI
TL;DR: In this paper, the sensitivity of a coupled spiral interferometer (CSPIN) to an absolute rotation of an optical gyroscope has been investigated, where the sensing element is a spiral waveguide with coupling between adjacent arms.
Abstract: This paper reports a study of the sensitivity to an absolute rotation of an optical gyroscope in which the sensing element is a coupled spiral interferometer (CSPIN), which is a spiral waveguide with coupling between adjacent arms. The two physical sensing mechanisms that contribute to this sensitivity are discussed. Numerical simulations show that after optimization, a CSPIN gyroscope has the same maximum possible sensitivity as an optimized resonant waveguide optical gyroscope with the same radius and loss coefficient. This maximum sensitivity is independent of the number of arms, and it decreases as the reciprocal of the waveguide loss coefficient.

Proceedings ArticleDOI
28 Aug 2014
TL;DR: In this article, an apparatus for high precision angle metrology, based on a mid-scale ring laser gyroscope, is developed at the Italian Metrologic Research Institute (INRIM).
Abstract: An apparatus for high precision angle metrology, based on a mid-scale ring laser gyroscope, is in development at the Italian Metrologic Research Institute (INRIM). The aim is to build a portable instrument with an accuracy in the range of some tens nanoradiants. Keywords—Ring laser Gyroscopes; angle metrology

Patent
03 Sep 2014
TL;DR: In this paper, the authors proposed a heat insulation temperature regulating device of a laser gyroscope, which consists of a heat insulating housing of the laser, a heat conducting strip, a temperature sensor, a heating and refrigeration part, and a control part.
Abstract: The utility model provides a heat insulation temperature regulating device of a laser gyroscope. The device comprises a heat insulation housing of the laser gyroscope, a heat-conducting strip, a temperature sensor, a heating and refrigeration part, and a control part. The heat-conducting strip is disposed in the heat insulation housing, and wraps an inertial navigation assembly in the laser gyroscope, so temperature in the laser gyroscope is uniform. The heating and refrigeration part is disposed between the heat-conducting strip and the heat insulation housing, and is connected with the control part. The heating and refrigeration part is used to regulate temperature in the laser gyroscope. The temperature sensor is disposed between the heat insulation housing and the inertial navigation assembly, and is connected with the control part. The temperature sensor detects temperature in the laser gyroscope and output the temperature to the control part. The control part controls the heating and refrigeration part to heat or refrigerate according to detection results of the temperature sensor. The device makes temperature in the gyroscope uniform, thereby solving a problem that a temperature feature point is difficult to choose, and realizing temperature deviation correction of inertial navigation.

Patent
18 Dec 2014
TL;DR: In this paper, a laser gyroscope consisting of a first solid waveguide and a gain medium interaction region where light traveling through the first waveguide interacts with non-solid Doppler-broadened gain medium molecules positioned outside of the first one is presented.
Abstract: A laser gyroscope comprising includes a first solid waveguide; a gain medium interaction region where light traveling through the first solid waveguide interacts with non-solid Doppler-broadened gain medium molecules positioned outside of the first solid waveguide; at least one medium exciter configured to excite the non-solid Doppler-broadened gain medium at the gain medium interaction region, wherein the excited non-solid Doppler-broadened gain medium induces first and second laser fields within the first solid waveguide, wherein the first laser field travels in a clockwise direction within the first solid waveguide and the second laser field travels in a counter-clockwise direction within the first solid waveguide; and a photodetector communicatively coupled to the first solid waveguide and configured to detect the portions of the first and second laser fields.