Triaxial optical fiber gyro structure taking eight-point vibration reduction and accelerometer heat-insulation measures

Abstract

A triaxial optical fiber gyro structure taking eight-point vibration reduction and accelerometer heat-insulation measures comprises a body (1), a first gyro (2), a second gyro (3), a third gyro (4), a first circuit box (5), a second circuit box (6), a third circuit box (7), an accelerometer assembly (8), a circuit box installing supports (9) and vibration reducers (10). The body (1) is a hexahedron frame, eight vibration reducers (10) are installed at eight corners of the body (1) respectively, and the balancing is performed through position adjustment of each assembly, so that the geometric center C1 of the eight vibration reducers and the mass center C2 of all components coincide. No counterweight is added in the mass center adjusting process, the occurrence of liner vibration and angular vibration coupling is avoided effectively, and the vibration reduction performance is improved. A heat-insulation gasket and a silica gel layer are adopted for double-layer heat insulation for the accelerometer assembly (8), the starting heating time of the accelerometer assembly is reduced obviously, and the total power consumption of a gyro assembly is lowered.

Description

technical field [0001] The invention relates to a gyroscope structure, in particular to a three-axis fiber optic gyroscope structure. Background technique [0002] As a symbol of high-tech development, spacecraft plays an extremely important role in my country's national defense and economic construction. The accuracy of attitude and speed measurement is the prerequisite for the stable and reliable operation of spacecraft. Eyes, which directly affect the accuracy and performance of the attitude control system. [0003] The fiber optic gyroscope is an all-solid-state inertial instrument, which has advantages that traditional electromechanical instruments do not have. In terms of structure, it is a completely solid-state gyroscope without any moving parts, which makes it have obvious advantages in many application fields, especially on spacecraft that have high requirements on product reliability and life. [0004] The meter is suitable for measuring static and dynamic accele...

AI Technical Summary

Problems solved by technology

In the prior art, the fiber optic gyro inertial measurement device mostly adopts the design scheme of three-axis independent work, and the position and attitude of the three axes of the spacecraft relative to the inertial space can be measured through the cooperation of the fiber optic gyroscope and the meter. The anti-vibration characteristics are not high, especially the poor adaptability to high-frequency vibration, which restricts the mechanical adaptability of the inertial measurement device. At the same time, in order to make the meter work with high precision and stability, it is necessary to provide a constant temperature environment, and the thermal insulation performance is not good, resulting in poor heat dissipation. Fast, and the matching heating device consumes a lot of power, which also increases the power consumption of the inertial measurement device

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