Three-axis six-degree-of-freedom vibration test condition design method based on interfacial force equivalence
A technology of vibration test and design method, which is applied in vibration test, machine/structural component test, force/torque/power measuring instrument calibration/test, etc. It can solve the problem of insufficient product test and insufficient product performance assessment , product over-test and other problems, to meet the requirements of mechanical test, improve the efficiency of mechanical test and mass production development, and solve the problem of triaxial test condition design
Pending Publication Date: 2022-06-21
BEIJING INST OF SPACECRAFT ENVIRONMENT ENG
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If the design of the test conditions is too high, the product will be over-tested or even damaged; if the design of the test conditions is too low, the product will be under-tested, and the product performance assessment will not be fully assessed.
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[0023] The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.
[0024] see figure 1 , the present invention provides a kind of technical scheme:
[0025] The method for formulating the test conditions of the triaxial six-degree-of-freedom vibration test based on the equivalent interface force includes the following steps:
[0026] S1: Installation of the interface force measurement device: Specifically, several three-way force sensors are installed between the three-axis six-degree-of-freedom wo...
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The invention discloses a three-axis six-degree-of-freedom vibration test condition design method based on interfacial force equivalence. The method comprises the steps that an interfacial force measuring device is installed; acquiring and calculating the sensitivity of the force sensor; an interface force measurement signal synthesis step; starting a triaxial vibration test system device; a single-axial loading vibration test step of the spacecraft product; a spacecraft product triaxial low-magnitude simultaneous loading test step; a triaxial test condition equivalent design calculation step; carrying out full-magnitude test verification according to a triaxial condition; calculating the error of the triaxial test condition design; and closing the triaxial vibration test system equipment. The invention aims to solve the problem of spacecraft product triaxial test condition design, ensures that the product is fully examined and meets the mechanical test requirement, and greatly improves the mechanical test efficiency and batch production development efficiency of the spacecraft product compared with the traditional uniaxial test method.
Description
technical field [0001] The invention relates to the technical field of spacecraft mechanical environment test, in particular to a design method for three-axis six-degree-of-freedom vibration test conditions based on interface force equivalence. Background technique [0002] The three-axis six-degree-of-freedom vibration test technology for spacecraft products is an advanced vibration test technology with omnidirectional loading and excitation. One of the difficulties of the triaxial six-degree-of-freedom vibration test technology lies in the design and determination of the loading conditions of the vibration test. If the design of the test conditions is too high, the product will be over-tested or even damaged; if the design of the test conditions is too low, the product will be under-tested, and the product performance assessment will not be fully assessed. With the development of spacecraft mechanical environmental test technology, especially the development of advanced f...
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IPC IPC(8): G01M7/02G01M7/04G01M7/06G01L5/00G01L25/00
CPCG01M7/027G01M7/04G01M7/06G01L5/00G01L25/00
Inventor 邱汉平冯咬齐李新明刘闯樊世超朱建斌高非李经纬王潇锋魏博
Owner BEIJING INST OF SPACECRAFT ENVIRONMENT ENG