Fixed frequency calibration test method of spacecraft vibration

Abstract

The invention provides a fixed frequency calibration test method of spacecraft vibration. The method comprises the following steps that: a corresponding relation between a support reaction force per unit length and a strain of a spacecraft root is determined, wherein the support reaction force per unit length is generated by the spacecraft during a sinusoidal vibration test, and an auxiliary basis is provided for determination on a concave downward condition of a main frequency range during the sinusoidal vibration test of the spacecraft; more particularly, at an off-resonance range of the spacecraft, by using a lowest working frequency that is allowed by a vibrating table and is normally from 2 to 5 Hz, sinusoidal excitation with a fixed frequency is carried out on the spacecraft under a certain order. After test evaluation is completed, the test method can be applied to vibrating tests of various spacecrafts, so that rationality and effectiveness of the test can be determined. According to the invention, problems that are common in the vibrating test process of a spacecraft can be solved, wherein the problems include a problem of overloading or underloading; and beneficial effects are as follows: the test is reasonable and reliable; the method can be realized simply; and the adaptability is strong and the like.

Description

technical field [0001] The invention relates to a spacecraft vibration test, in particular to a spacecraft vibration fixed-frequency calibration test method. Background technique [0002] With the development of space technology, the requirements for the lightweight structure of spacecraft are becoming increasingly stringent, and the rationality and safety of experiments are becoming more and more important. At present, the vibration test of spacecraft generally adopts the method of controlling the acceleration input on the docking surface between the bottom of the spacecraft and the test fixture and supplemented by the response limitation of the key points of the spacecraft. However, the above method cannot ensure the rationality of the test. " or "under" test phenomena, such as the FY-2 (02) star initial sample star in Nanjing, due to the "over" test caused the hydrazine pipeline to break and the single machine to fall, causing heavy losses; The occurrence of "owed" tests...

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Problems solved by technology

[0005] At present, there is no description or report of a technology similar to the present invention, and no domestic similar data has been collected yet.

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