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Four-point vibration damping system for fiber optic rate gyroscope of launch vehicle

A rate gyroscope and launch vehicle technology, applied in Sagnac effect gyroscopes, gyroscopes/steering sensing equipment, measuring devices, etc., can solve the problem of high requirements on product centroid, large line angle coupling, and difficulty in meeting fiber optic rate gyroscopes Use 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: 2018-06-15
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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  • Four-point vibration damping system for fiber optic rate gyroscope of launch vehicle
  • Four-point vibration damping system for fiber optic rate gyroscope of launch vehicle

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Embodiment Construction

[0017] The present invention will be further described below in conjunction with the drawings.

[0018] A four-point vibration reduction system for launch vehicle fiber optic rate gyro, such as figure 1 As shown, it includes a rear cover 1, a control circuit board 2, a connector 3, an optical assembly 4, a light source and temperature control circuit board 5, a front cover 6, a shock absorber 7, a housing 8, a base 9 and a power circuit board 10. The control circuit board 2, the optical assembly 4, the light source and the temperature control circuit board 5 are 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 back cover The board 1 and the front cover 6 are connected to the end frames on the left and right sides of the casing 8. The control circuit board 2, the optical assembly 4, the light source and the temperature control circuit board 5 are enclosed in...

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Abstract

The invention discloses a four-point vibration damping system for a fiber optic rate gyroscope of a launch vehicle. A T-type vibration damper has equal rigidity along three directions, can greatly inhibit the coupling of line angles, can improve the accuracy of the fiber optic rate gyroscope under the mechanical environment, has a wide silicon rubber temperature adaptability range, covers the workambient temperature of the fiber optic rate gyroscope, and has the inherent frequency of 160Hz to 200Hz. The inherent frequency of the internal components of the product is 1000Hz or more. The vibration damper effectively attenuates the high frequency vibration, effectively prevents the resonant frequency of the components and improves the mechanical environment adaptability of the product.

Description

Technical field [0001] The invention relates to a four-point vibration reduction system for a launch vehicle fiber optic rate gyro, which belongs to the technical field of attitude control. Background technique [0002] The fiber-optic rate gyroscope is an 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 the flight, and to control the attitude stability. [0003] Vibration and shock environments will affect the accuracy and reliability of the fiber rate gyroscope, causing damage to circuit components, structural deformation, etc., resulting in product performance degradation and normal operation. In order to eliminate or reduce the influence 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 depends on the product s...

Claims

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Application Information

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Patent Type & Authority Applications(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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