A method for formulating concave condition of spacecraft sinusoidal vibration test

Abstract

The present invention discloses a spacecraft sinusoidal vibration test recessing condition formulation method which is a rigorous and accurate spacecraft sinusoidal vibration test recessing conditionformulation sequencing method. The method comprises the following steps of: prior to test, determining and collecting all the measurement points to be analyzed, directions, and amplitude limiting conditions of corresponding measurement point channels of a spacecraft; at a test scene, obtaining a feature-level frequency sweeping test result, and performing linear calculation to obtain a theory response curve of an assigned large-scale sinusoidal vibration test; performing comparison of the theory response curve of the large-scale sinusoidal vibration test and the amplitude limiting conditions of corresponding measurement point channels one by one to find frequency points requiring recessing and store low recessed values of the frequency points and corresponding channel names; performing comparison for all the measurement point channels to finally obtain a recessing condition indication curve; and integrally considering non-linear factors, and formulating a recessing condition used for control of the spacecraft sinusoidal vibration test between the response envelope curve and the recessing condition indication curve.

Description

technical field [0001] The invention relates to the technical field of spacecraft, in particular to a method for formulating concave conditions for a sinusoidal vibration test of a spacecraft. Background technique [0002] The spacecraft must undergo sinusoidal vibration tests at each development stage to assess the stiffness and strength design of the structure, and to obtain the response data of the measuring point channels on the spacecraft. In the test, since the resonant frequency of the spacecraft is generally within the test frequency range, it is often necessary to notch the test conditions in order to avoid excessive response. However, setting the concave conditions on site is a tedious and time-consuming process, usually by manually interpreting the results of the feature-level frequency sweep test one by one to determine the focus points and stand-alone equipment (data processing needs to be performed on the test site, which takes a long time and is prone to omiss...

AI Technical Summary

Problems solved by technology

[0008] The whole process involves the interpretation, calculation, estimation and analysis of a large amount of test data. In the past, it was done manually, and the workload was huge, which led to long overtime and waiting for the personnel of the test team at the test site. This is especially true for large-scale spacecraft with a large number of monitoring point channels; and the previous method usually compares several maximum response points, which cannot achieve full-frequency comparison, and the sub-maximum response and partial response are easy to be missed. The determination of the site of concern or stand-alone equipment depends on some human subjective judgments or empirical factors, and the measuring point channels and non-maximum response frequency points that are not identified as the site of concern or stand-alone equipment are selectively ignored

[0009] Therefore, it is difficult to meet the first two criteria mentioned above in a strict sense. This method has a large amount of manual work and is easy to miss, which brings great risks and hidden dangers to the test. Some structures or stand-alone Quality problems such as equipment damage due to over-testing are caused by the shortcomings of this method

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