A fiber optic gyroscope assembly with four-axis redundant power supply and circuit board cold backup

Abstract

A four-axle redundant configured optic fiber gyroscope assembly with power supply and circuit board cold backup relates to the technical field of moonlet inertial measurement. The optic fiber gyroscope comprises a housing, an upper cover, a main body, a light source set, gyroscope sets, a Y waveguide, a coupler, a gyroscope three-route digital circuit board, a circuit board support, a gyroscope single-route digital circuit board, gyroscope simulation drive circuit boards, signal processing and interface circuit boards, and a transformer. The upper cover is in fixed installation to the upper surface of the housing; the main body is in fixed installation to the center of a groove of the housing. The main body, the light source set, the gyroscope sets, the Y waveguide, the coupler, the gyroscope three-route digital circuit board, the circuit board support, the gyroscope single-route digital circuit board, the gyroscope simulation drive circuit boards, the signal processing and interface circuit boards, and the transformer are arranged in a sealed housing formed by the housing and the upper cover from bottom to top. The optic fiber gyroscope assembly is good in tensile strength and reduced in structural weight. Through optoelectronic integration integrated design, power consumption of the assembly is reduced, faults can be detected and separated, and the optic fiber gyroscope is high in reliability.

Description

technical field [0001] The invention relates to the technical field of inertial measurement of small satellites, in particular to a fiber optic gyroscope assembly with a four-axis redundant configuration power supply and circuit board cold backup. Background technique [0002] With the development and transformation of the aerospace field and the entire aerospace ecosystem, small satellites with many advantages such as low investment and operating costs, strong emergency capability and flexibility, and short system construction period are widely used in communications, science, technology experiments, military, Education and earth observation have broad development prospects in military and civilian fields, and the popularization, commercialization and market competition of small satellites have shown an irresistible trend. [0003] As a key component of the attitude control system, the inertial instrument directly affects the accuracy and performance of the system. With th...

AI Technical Summary

Problems solved by technology

[0006] Most of the existing fiber optic gyroscope components adopt a three-axis design scheme. There is no redundant design of the fiber optic gyroscope. When any axis fails, the attitude of the three axes relative to the inertial space cannot be provided, and fault detection and isolation cannot be realized.

At the same time, the optoelectronic modules are separated. Under the premise of meeting the requirements of technical indicators such as precision, the volume and weight of the components are relatively large; there is no backup for the light source, secondary power supply and signal processing circuit boards, and there is a single point of failure, and the reliability is poor.

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