Apparatus for measuring inertia of fiber gyro composite unit and its calibration method

An inertial measurement device and fiber optic gyroscope technology, applied in the field of inertial measurement, can solve the problems of inability to provide three-axis inertial space, failure to isolate faults, poor reliability, etc., to improve mechanical resistance, improve on-orbit accuracy, The effect of improving reliability

Active Publication Date: 2012-10-17
BEIJING AEROSPACE TIMES OPTICAL ELECTRONICS TECH
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AI Technical Summary

Problems solved by technology

[0004] In the prior art, the inertial measurement device of the fiber optic gyro assembly mostly adopts a three-axis design scheme, so that the attitude of the three axes of the spacecraft relative to the inertial space

Method used

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  • Apparatus for measuring inertia of fiber gyro composite unit and its calibration method
  • Apparatus for measuring inertia of fiber gyro composite unit and its calibration method
  • Apparatus for measuring inertia of fiber gyro composite unit and its calibration method

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Embodiment

[0020] Fiber optic gyro-combined inertial measurement devices, such as figure 1 As shown, it includes a hexagonal pyramid 1 and a base 2; six fiber optic gyroscopes 3 are evenly distributed on the six sides of the hexagonal pyramid 1, and 6 signal processing and interface circuits and 6 secondary power supplies are installed in the base 2 6 connectors 4 are also installed on the four corners of the base 2, wherein two connectors 4 are respectively installed on two corners, and one connector 4 is respectively installed on the other two corners; A reference mirror 5 is installed on the corner; four cooling grooves 6 are opened on the base 2 for heat dissipation; there are one mounting hole 13 on each of the four corners of the base 2 for fixing on the spacecraft structure ;

[0021] 6 signal processing and interface circuits respectively receive the output information of 6 fiber optic gyroscopes, and at the same time send the processed data to the control subsystem;

[0022] T...

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Abstract

The invention relates to an apparatus for measuring inertia of a fiber gyro composite unit and its calibration method, and especially relates to the apparatus for measuring the inertia of the fiber gyro composite unit with miniaturization, high reliability and redundant multi-tables used for navigation, guidance and control of spacecrafts, which belongs to the inertia measurement technical field. The apparatus comprises a hexangular pyramid and a pedestal; six fiber gyroscopes are uniformly distributed on six side surfaces of the hexangular pyramid, six signal processing and interface circuits and six secondary power sources are arranged in the pedestal. According to the invention, the gravity center is positioned at a geometric center as possible, and the anti-mechanical capacity is good; the six fiber gyroscopes are redundant backup with each other; the reliability is high; in the process of in-orbit operation, a triaxial attitude angle speed can be still provided even the fault is generated by no more than three shafts at will, and the fault detection and the isolation can be realized. The calibration method can accurately calibrate zero position, scale factor and installation error, and can effectively enhance the in-orbit usage precision.

Description

technical field [0001] The invention relates to an inertial measurement device for a fiber optic gyroscope assembly and a calibration method thereof, in particular to a miniaturized, highly reliable, multi-meter redundant fiber optic gyroscope assembly inertial measurement device for spacecraft navigation, guidance and control, which belongs to inertial measurement technology field. Background technique [0002] As a symbol of high-tech development, spacecraft plays an extremely important role in my country's national defense construction. Local wars under high-tech conditions in the future will put forward high requirements on the ability to obtain information. The attitude stability of aerospace is the premise and guarantee for effectively performing various tasks such as aiming and docking. Among them, the inertial instrument is the key to the attitude control system. Key sensors, which directly affect the accuracy and performance of the attitude control system. Spacecr...

Claims

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Application Information

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IPC IPC(8): G01C19/72G01C25/00
Inventor 王巍向政张东旭杨清生孟祥涛廉明张峰
Owner BEIJING AEROSPACE TIMES OPTICAL ELECTRONICS TECH
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