A fiber optic gyro combination device for satellite attitude control

A technology of satellite attitude control and fiber optic gyroscope, which is applied in the direction of measuring device, Sagnac effect gyroscope, gyroscope/steering sensing equipment, etc. Good manufacturability, short heat dissipation path, and high heat conduction efficiency

Active Publication Date: 2021-10-01
INNOVATION ACAD FOR MICROSATELLITES OF CAS +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

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

Method used

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  • A fiber optic gyro combination device for satellite attitude control
  • A fiber optic gyro combination device for satellite attitude control
  • A fiber optic gyro combination device for satellite attitude control

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Embodiment 1

[0044] A fiber optic gyro combination device for satellite attitude control, comprising:

[0045] An outer cover 7 and a bottom cover 8 for packaging, the outer cover 7 and the bottom cover 8 are connected to form a cavity;

[0046] The outer cover 7 and the bottom cover 8 connected with the system body 1, the electrical connector assembly 4 connected with the system body 1, and the two gyro circuits 5 installed on the system body 1; secondary power circuit assembly 6;

[0047] The system body 1 includes a flange 10, four supporting columns 11 on the mounting flange 10, a supporting side plate 12 arranged between every two adjacent supporting columns 11, and a support side plate 12 between the four supporting columns 11. A support horizontal plate 13 arranged in the middle; four support columns 11 and four support side plates 12 form a rectangular cavity;

[0048] Two of the orthogonal optical path components 2 are respectively installed on three adjacent support columns 11;...

Embodiment 2

[0067] Such as figure 1 Shown is a schematic diagram of the composition of the three-axis integrated fiber optic gyro device. It can be seen from the figure that the fiber optic gyro combination device mainly includes three orthogonal optical path components 2, a light source drive component 3, an electrical connector component 5, two gyro circuits 5, and a secondary power supply Circuit assembly 6 , system body 1 , housing 7 and bottom cover 8 .

[0068] Such as image 3 It is the installation relationship diagram of optical path components, wherein the optical path components include fiber ring 21, fiber ring mounting base 22, Y waveguide 23, 2×2 coupler 24, magnetic shielding upper cover 25; the light source drive component includes SLD laser 31, drive module 32, Drive circuit 33, 3×1 coupler 34; optical fiber ring mounting base 22 is overlapped with the groove of magnetic shielding upper cover 25, forming a closed space inside, optical fiber ring 21 is installed in the in...

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Abstract

A fiber optic gyro combination device used for satellite attitude control, innovatively designed the system body in the structural form of H-shaped longitudinal section and mouth-shaped cross-sectional connection surface connecting four support columns. The system body is the main structure supporting each component, while ensuring three orthogonal mounting surfaces for the three orthogonal optical path components; in order to ensure the stable operation of the device, it provides an independent working area for the secondary power circuit components; the present invention It has a good heat dissipation design to ensure the accuracy and reliability of the equipment during the satellite's working process; the invention has sufficient structural natural frequency and good mechanical resistance. The present invention optimizes materials and processing methods for non-load-bearing parts (outer cover, bottom cover), and realizes light weight and low cost. The invention has good processability in designing and assembling, and modularizes components with relatively independent functions, and belongs to the technical field of structural design of optical fiber gyro devices.

Description

technical field [0001] The invention relates to an optical fiber gyroscope assembly device for satellite attitude control, belonging to the technical field of optical fiber gyroscope device structure design. Background technique [0002] The fiber optic gyro device 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 during the satellite attitude control process and is a key component of the satellite attitude control system. [0003] Satellite 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 device has obvious advantages such as miniaturization, light weight, and high integration. With the rapid development of satellites, the weight and volume requirements of the three-axis integrated fiber optic gyro device are becoming more and more...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C21/18G01C19/72
CPCG01C19/722G01C21/18
Inventor 张锐何进谢祥华黄志伟魏垚严玲玲
Owner INNOVATION ACAD FOR MICROSATELLITES OF CAS
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