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High-reliability redundant four-shaft optical fiber gyroscope inertia measurement device

A technology of fiber optic gyroscope and fiber optic gyroscope, which is applied in the field of inertial measurement, can solve problems such as poor reliability, inability to realize system reconfiguration, and inability to provide attitude in three-axis inertial space, etc., to achieve the effect of improving device reliability and reliability

Active Publication Date: 2014-04-02
BEIJING AEROSPACE TIMES OPTICAL ELECTRONICS TECH
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AI Technical Summary

Problems solved by technology

[0003] In the prior art, the fiber optic gyro inertial measurement device mostly adopts a three-axis scheme, so that the attitude of the three axes of the spacecraft relative to the inertial space can be measured, but this scheme cannot provide the attitude of the three axes relative to the inertial space when one axis fails. Poor reliability, unable to realize system reconstruction

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  • High-reliability redundant four-shaft optical fiber gyroscope inertia measurement device
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  • High-reliability redundant four-shaft optical fiber gyroscope inertia measurement device

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Embodiment Construction

[0017] Such as figure 1 As shown, the present invention’s optical fiber gyroscope inertial measurement device has a primary secondary power supply 1, a primary signal processing and interface circuit 2, an X fiber optic gyroscope 3, a Y fiber optic gyroscope 4, a Z fiber optic gyroscope 5, an S fiber optic gyroscope 6, Backup secondary power supply 7, backup signal processing and interface circuit 8, body structure 9; X fiber optic gyroscope 3, Y fiber optic gyroscope 4, Z fiber optic gyroscope 5 three orthogonal, S fiber optic gyroscope 6 and X fiber optic gyroscope The included angles between instrument 3, Y fiber optic gyroscope 4, and Z fiber optic gyroscope 5 are θ, θ=54.74°, and the four fiber optic gyroscopes are used to output sensitive angular velocity information; the main secondary power supply 1 and the backup two The secondary power supply 7 is cold backup for each other, and is used to supply power to four fiber optic gyroscopes and signal processing and interfac...

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Abstract

The invention relates to a high-reliability redundant four-shaft optical fiber gyroscope inertia measurement device, in particular to a long-life high-reliability redundant inertia measurement device for spacecraft navigation, guidance and control, and belongs to the technical field of inertia measurement. The device comprises a body structure with three orthogonal shafts and one oblique shaft, wherein four optical fiber gyroscopes, two signal processing and interface circuits and two secondary power circuits are arranged in the body. According to the device, the two signal processing and interface circuits are mutually redundant; the two secondary power circuits are mutually redundant; the reliability is high; when the device is used on a track and any one shaft or channel has a fault, the three-shaft attitude angular velocity still can be provided, the redundant configuration can be achieved, and normal product functions can be guaranteed.

Description

technical field [0001] The invention relates to a highly reliable redundant four-axis fiber optic gyro inertial measurement device, in particular to a miniaturized, highly reliable, multi-table redundant fiber optic gyro inertial measurement device for spacecraft navigation, guidance and control, which belongs to inertial The field of measurement technology. Background technique [0002] The fiber optic gyroscope is an all-solid-state inertial instrument, which has advantages that traditional electromechanical instruments do not have. It is a closed-loop system composed of optical devices and electronic devices. It determines its own angular velocity by detecting the phase difference of two beams of light. Therefore, it is a completely solid-state gyroscope structurally without any moving parts. It is precisely because of its principle and structural advantages that the fiber optic gyroscope has obvious advantages in many application fields, especially on spacecraft that re...

Claims

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Application Information

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IPC IPC(8): G01C19/72
CPCG01C19/72
Inventor 王巍向政张峰何熠王颂邦孟祥涛郑极石
Owner BEIJING AEROSPACE TIMES OPTICAL ELECTRONICS TECH
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