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Ring laser gyroscope

About: Ring laser gyroscope is a research topic. Over the lifetime, 2070 publications have been published within this topic receiving 18609 citations. The topic is also known as: Sagnac interferometer.


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Journal ArticleDOI
TL;DR: In this article , the authors proposed a novel exceptional point (EP)-enhanced Brillouin micro-optical gyroscope (BMOG) by using the self-injection locking technique which requires a small-size, low-cost and low-power distributed feedback (DFB) semiconductor laser instead of the narrow-linewidth-tunable laser in the traditional microoptic gyroscopes.

2 citations

Journal ArticleDOI
TL;DR: In this article, a two-degree-of-freedom gyroscope with a ball-in-tube nutation damper mounted in the gimbal is analyzed and the nonlinear coupled equations of motion are solved by using the method of multiple scales.
Abstract: The dynamics of a two-degree-of-freedom gyroscope with a ball-in-tube nutation damper mounted in the gimbal is analyzed. The nonlinear coupled equations of motion are solved by using the method of multiple scales. The results show that, if the natural frequency of the ball-in-tube damper is tuned to equal the nutation frequency of the gyroscope with the damper removed, the wobble motion of the gyroscope will be eliminated most rapidly and the decay time constant of the nutation angle is a concave function of the damping coefficient. If the nutation damper is oriented perpendicular to the spin axis of the rotor, the residual precession due to the gravity effect can be avoided. HE gyroscope is one of the two basic components of all inertial navigation systems (the other is an accelerometer). It serves as directional reference in an inertial frame. Gyro- scopes are also used as motion sensors for stabilizing the mo- tion of ships, aircraft, and other mechanical systems. Its de- sign and control has been an important technological problem for half a century. The two-degree-of-freedom gyroscope has a support that permits the spin axis to have two degrees of rotational freedom with respect to the case of the gyroscope. Such a device is shown schematically in Fig. 1. The Cartesian coordinate system X,Y,Z is fixed on the case of the gyroscope with origin O coinciding with the center of mass of the rotor. The system x,y,z is fixed on the inner gimbal. The inner gimbal can rotate freely about the x axis. The outer gimbal can rotate freely about the Z axis. In the navigation system, the spin axis of the rotor is used to indicate one of the directions of the axes of the navigational frame, i.e., north, east, and down. These physical directions rotate with respect to inertial space due to Earth rotation and vehicle motion. Therefore, the spin axis of the rotor must be rotatable on command. This can be done by applying a calibrated torque to the inner gimbal and the outer gimbal. The rotor will inevitably result in a coning motion (precession and nutation) of the spin axis about the angular momentum vector of the gyroscope (which is fixed in space in the absence of subsequent external torque) after a torque with finite duration has been applied. Therefore, the gyroscope will be of practical value only if the nutation and precession are damped.1 The phenomenon of coning motion also appears for the gyroscope, which serves as a motion sensor. The elimina- tion of the coning motion will not only enhance the gyro- scope's accuracy, but will also reduce the loading of the con- trol unit.2 The coning motion can be suppressed by attaching a vibra- tion damper to the gyroscope at some appropriate place. Phys- ically, the vibration damper might be any device that can dissi- pate the energy of coning motion of the rotor and convert the transverse angular momentum of the gyroscope into spin an- gular momentum. The spin-stabilized satellite will also result in such coning motion after a reorientation maneuver. The commonly used damping devices for removing this coning motion of the satellite are viscous ring nutation dampers,3"5

2 citations

Proceedings ArticleDOI
05 Nov 2007
TL;DR: In this paper, the authors proposed a conventional sculling model based on optimum compensation algorithm, which is called practical velocity-updating algorithm, and emphasized briefly that recurrent compensation algorithm is more practical in AUV with RLG dithering condition.
Abstract: Strapdown inertial navigation system (SINS) with ring laser gyro (RLG) has been used extensively in the autonomous underwater vehicle (AUV) for the apparent advantages of having wide dynamic range, digital output and high accuracy. Because of the dithering motion of RLG to overcome the lock-in threshold and the vibration of AUV, there is sculling error in velocity-updating process of SINS. This paper firstly proposes a conventional sculling model based on optimum compensation algorithm. Recurrent compensation algorithm, which is called practical velocity-updating algorithm, is developed and emphasized briefly. In order to validate the performance of the proposed algorithms, simulation under classical sculling motion and RLG dithering are carried on. Simulation results show that recurrent compensation algorithm is more practical in AUV with RLG dithering condition.

2 citations

Patent
18 Oct 2007
TL;DR: In this paper, a ring laser gyroscope using a semiconductor laser was proposed, which includes a surface light emitting laser element 100, a plurality of mirrors 12 and 13, and a photodetector 15.
Abstract: PROBLEM TO BE SOLVED: To provide a novel ring laser gyroscope using a semiconductor laser. SOLUTION: The ring laser gyroscope includes a surface light emitting laser element 100, a plurality of mirrors 12 and 13, and a photodetector 15. The surface light emitting laser element 100 and the plurality of mirrors 12 and 13 are arranged so as to constitute a polygonal optical path 20. By exciting the surface light emitting laser element 100, a first laser beam 31 clockwise propagated by the polygonal optical path 20 and a second laser beam 32 counterclockwise propagated by the polygonal optical path 20 are excited. The photodetector 15 is disposed at a position where the first laser beam 31 and the second laser beam 32 interfere with each other. COPYRIGHT: (C)2008,JPO&INPIT

2 citations


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Performance
Metrics
No. of papers in the topic in previous years
YearPapers
202347
202275
202130
202062
201963
201841