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.

A Nonreciprocal Optical Effect in Optical Gyroscopes

Abstract: In a fiberoptic rotation sensor a nonreciprocal phase shift modulation is usually introduced to determine the difference of phase produced by the rotation of the sensor. It is also necessary that some frequency bias technique with nonreciprocal propagation properties be used to prevent lock-in in ring laser gyroscopes. Faraday effect, polar and transverse magneto-optical Kerr effects and optical activity of quartz rotators, which are used in the four frequency differential laser gyro and magnetic mirror laser gyro, can be generalized in the form of dielectric tensors containing off-diagonal and symmetrical complex conjugate elements.

The elimination of gyroscope's non-linear error and the broadening of its passband

Abstract: Theoretical calculation shows that the amplitude of angular velocity measured by micro-machined gyroscope that is based on the Coriolis force principle relates to its frequency. Due to the relationship between amplitude of angular velocity and its frequency, the angular velocity measured by gyroscope will not have a linear relationship with its actual value, which causes gyroscope's non-linear error and restricts its width of passband. This article firstly analysed the working principle of the gyroscope that uses Coriolis force to measure angular velocity. Then put forward a solution that can completely eliminate gyroscope's non-linear error and broaden its passband. The simulation consequence indicated that the method was actually right, which will improve the performance of gyroscope effectively. The conclusion is that the gyroscope can measure angular velocity linearly by using some common circuits and its passband is largely broadened.

Small ZLG triax technology

Abstract: Changing world politics and the advent of the Global Positioning System have resulted in a growing need for very compact guidance and control instruments designed for precision pointing and tracking, pinpoint strikes and accurate target discrimination. Requirements for these systems are not compatible with conventional dithered ring laser gyro technology and are too stringent in terms of random walk versus size for any projected fiber optics systems. However, Litton's Zero-Lock® ring laser gyro (ZLG®) technology, with its mechanically quiet environment and high resolution capabilities, is well matched to this growing arena of applications. We present design details and some preliminary test data from a couple of novel configurations for our ZLG. These designs both package three nonplanar light rings with orthogonal sensing axes into a single easy-to-manufacture glass block, in one case using only four mirrors for all three axes. Using recent advances in our coating technology, we are able to simplify the biasing arrangement for these three-axis systems, and with careful discharge layout we have reduced instrument volume considerably. Test data from an 11 cm path length frame show excellent random walk and scale factor performance with high resolution output.

Light and small laser gyro strapdown inertial measurement unit structure

Abstract: The invention discloses a light and small laser gyroscope strapdown inertial measurement unit structure which comprises three 50-type laser gyroscopes, three quartz accelerometers, a base body, a circuit structure, a shock absorber, an upper cover, a lower cover, a plug connector and an accelerometer base. The three 50-type laser gyroscopes are orthogonally arranged and are arranged in the base body from a lower opening of the base body; after the three quartz accelerometers are orthogonally arranged on the accelerometer base, the three quartz accelerometers are arranged in the base body fromthe upper opening of the base body; the circuit structure is positioned above the three quartz accelerometers and is arranged in the base body from the upper opening of the base body; the upper opening and the lower opening of the base body are respectively connected with the upper cover and the lower cover, so that the packaging of the strapdown inertial measurement unit structure of the laser gyroscope is realized; a plurality of shock absorbers are uniformly distributed at the waist part of the base body; and the plug connectors are uniformly distributed on the side surface of the base body. The strapdown inertial measurement unit structure of the light and small laser gyro is reduced by more than 25% compared with a traditional inertial measurement unit structure, and market requirements can be met.