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A Four-Point Vibration Reduction System for Launch Vehicle Fiber Optic Rate Gyroscope

A rate gyroscope and launch vehicle technology, applied in Sagnac effect gyroscopes, gyroscopes/steering sensing equipment, instruments, etc., can solve the problem of high requirements on the center of mass of the product, large line angle coupling, and difficult to meet the use of fiber optic rate gyroscopes requirements and other issues, to achieve the effect of improving the adaptability of the mechanical environment, avoiding the resonance frequency and improving the accuracy

Active Publication Date: 2021-12-07
SHANGHAI AEROSPACE CONTROL TECH INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The existing vibration absorber installation method has high requirements for the center of mass of the product, and the line-angle coupling is large, which is difficult to meet the requirements for the use of fiber-optic rate gyroscopes in launch vehicles.

Method used

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  • A Four-Point Vibration Reduction System for Launch Vehicle Fiber Optic Rate Gyroscope
  • A Four-Point Vibration Reduction System for Launch Vehicle Fiber Optic Rate Gyroscope

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Experimental program
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Embodiment Construction

[0017] The present invention is further described below in conjunction with accompanying drawing.

[0018] A four-point damping system for a fiber optic rate gyro used in a launch vehicle, such as figure 1 As shown, it includes rear cover 1, control circuit board 2, connector 3, optical assembly 4, light source and temperature control circuit board 5, front cover 6, shock absorber 7, housing 8, base 9 and power circuit board 10. The control circuit board 2, optical components 4, light source and temperature control circuit board 5 are sequentially connected in the housing 8 along the same horizontal axis of the housing 8, the power supply circuit board 10 is connected in the housing 8 below the horizontal axis, and the rear cover The board 1 and the front cover 6 are connected to the end frames on the left and right sides of the housing 8, and the control circuit board 2, the optical component 4, the light source and the temperature control circuit board 5 are sealed in the ho...

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Abstract

The invention discloses a four-point vibration reduction system for a launch vehicle optical fiber rate gyroscope. The T-shaped shock absorber has equal stiffness in three directions, which can greatly suppress line-angle coupling and improve the accuracy of the optical fiber rate gyroscope in a mechanical environment. Silicone rubber has a wide range of temperature adaptability, covering the working environment temperature of fiber optic rate gyro; the natural frequency of the shock absorber is 160Hz-200Hz, and the natural frequency of the internal components of the product is above 1000Hz. The shock absorber effectively attenuates high-frequency vibrations and effectively avoids The resonant frequency of the components is opened, and the mechanical environment adaptability of the product is improved.

Description

technical field [0001] The invention relates to a four-point vibration reduction system for a launch vehicle fiber optic rate gyroscope, belonging to the technical field of attitude control. Background technique [0002] The fiber optic rate gyroscope is the angular rate sensitive element of the launch vehicle control system. Its main function is to measure the rate of change of the pitch angle, yaw angle and roll angle of the rocket body during flight, and to perform attitude stability control. [0003] The vibration and shock environment will affect the accuracy and reliability of the fiber optic rate gyroscope, causing damage to circuit components and structural deformation, which will cause product performance degradation and affect normal work. In order to eliminate or reduce the impact of vibration and shock, the fiber optic rate gyroscope adopts vibration reduction / shock isolation measures. [0004] There are many ways to install the shock absorber, which mainly depe...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01C19/72
CPCG01C19/721
Inventor 安震李强陈珊刘吉孙茂强
Owner SHANGHAI AEROSPACE CONTROL TECH INST
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