High-heat-dissipation, light and small three-axis integrated fiber-optic gyroscope structure

Abstract

A high-heat-dissipation, light and small three-axis integrated fiber-optic gyroscope structure comprises a shell, orthogonal optical fiber ring assemblies, a light source driving assembly, orthogonallight path assemblies, a power supply assembly, a system circuit assembly, a prism, an upper cover and side covers. The orthogonal optical fiber ring assemblies are respectively mounted on mounting platforms in the X-axis direction, the Y-axis direction and the Z-axis direction of the shell, and the Z-axis direction platform is located in the shell. The orthogonal light path assemblies are installed in the center circles of the mounting platforms in the X-axis direction, the Y-axis direction and the Z-axis direction of the shell respectively, and the light source driving assembly is installedon the back face of the mounting platform in the Z-axis direction. The system circuit assembly is installed on supporting columns on the back face of the Z-direction mounting platform and located below the upper cover. The upper cover is installed at the top of the shell, the prism is installed at the top of the shell, the power supply assembly is installed at the bottom of the shell, and the sidecovers cover visible windows on the two sides of the shell. The high-heat-dissipation, light and small three-axis integrated fiber-optic gyroscope structure has the advantages of small volume, low weight, good heat dissipation, good assembly manufacturability and the like.

Description

technical field [0001] The invention relates to an optical fiber gyroscope assembly structure, in particular to a three-axis integrated optical fiber gyroscope assembly structure layout for attitude control. Background technique [0002] The fiber optic gyro component is an all-solid-state inertial instrument based on the Sagnac effect. It is used to measure the angular rate of the carrier. It must work well in the satellite attitude control and is a key component of the attitude control system. [0003] Attitude control needs to measure the angular rate in three orthogonal directions. Considering the strict limitation of the space load of the satellite system, the three-axis integrated fiber optic gyro component has obvious advantages such as compact structure, high integration, and small size. With the rapid development of satellites, the weight and volume requirements for the three-axis fiber optic gyroscope components are becoming more and more stringent; at the same tim...

AI Technical Summary

Problems solved by technology

[0004] Due to the temperature sensitivity of the optical components of the existing three-axis integrated fiber optic gyroscope components for attitude control, the secondary power supply components with high power and high heat generation rate are generally separated from the optical path components, gyro circuits, and light source drive components; but The three-axis integrated fiber optic gyro component of this design has too many volume and mass limits, which cannot meet the needs of the current attitude control system.

Images