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Force limit control vibration test system and test method

A vibration test and control system technology, applied in vibration test, machine/structural component test, measuring device, etc.

Active Publication Date: 2012-07-04
BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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  • Abstract
  • Description
  • Claims
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Problems solved by technology

[0004] The object of the present invention is to provide a kind of vibration test system that solves the problem that spacecraft or spacecraft components have been tested in the traditional acceleration control vibration test and use the system to carry out the method of vibration test

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  • Force limit control vibration test system and test method
  • Force limit control vibration test system and test method
  • Force limit control vibration test system and test method

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Embodiment Construction

[0049] The force limit control vibration test system of the present invention will be further described below in conjunction with the accompanying drawings. This description is only exemplary and is not intended to limit the protection scope of the present invention.

[0050] refer to figure 1 , the force limit control vibration test system of the present invention, the vibration table 3, the force measurement device 2 for installing the test piece 1 (a certain type of satellite) installed on the top of the vibration table 3, the vibration test control system 9 and the data acquisition and processing system 8 .

[0051] refer to figure 2 , The force measuring device 2 includes an upper auxiliary tool 10, a lower auxiliary tool 12 and a three-way force sensor 11 installed between the two auxiliary tools. The acceleration sensor 4 installed on the upper auxiliary tooling 10 communicates electrically with the vibration test control system 9 through the acceleration charge ampl...

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Abstract

The invention discloses a force limit control vibration test system and a method utilizing the system for vibration test. The test system includes a vibration table, a force measuring device mounted at the upper part of the vibration table and used for placing a test piece, a vibration test control system and a data collecting and processing system, wherein the force measuring device includes an upper auxiliary tooling, a lower auxiliary tooling and a three-way force sensor arranged between the two auxiliary toolings; and the upper auxiliary tooling, the lower auxiliary tooling and the three-way force sensor are mechanically connected. In the method, as the signal-to-noise ratio of the force signal is higher than that of the acceleration signal, the precision of the force response amplitude limit satisfies 10% as required by GJB1027A, and is superior to the control precision of the conventional acceleration method.

Description

technical field [0001] The invention belongs to the field of spacecraft mechanics environment test, in particular to a force limit control vibration test system for spacecraft environment test and a vibration test method for spacecraft environment test using the vibration test system. Background technique [0002] In domestic spacecraft vibration tests, traditional acceleration control methods have been widely used. However, this method has obvious defects in the resonance frequency band of spacecraft products. During the vibration test process, due to the difference in interface impedance, the spacecraft structure will experience an acceleration response much higher than the actual launch environment, that is, the problem of over-testing will occur. It will cause damage to the payload subsystems, components and even the main structure of the antenna, solar wing, power supply, and various sensors installed on the spacecraft, reducing the reliability and life of the spacecraf...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M7/06
Inventor 岳志勇张俊刚冯咬齐向树红李新明沈风霞王剑王智勇
Owner BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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