Missile full-missile double-platform parallel excitation reliability test method and system based on comprehensive stress

Abstract

The invention provides a missile full-missile double-platform parallel excitation reliability test method and system based on comprehensive stress. The method comprises the steps that a tested comprehensive stress environment profile is determined according to analysis of a mission profile during the use process of a missile, a random vibration scheme of double vibration platforms is determined according to the environment profile, the uniform distribution of vibration input magnitude is guaranteed, a reliability test of a full-missile-grade product is carried out by selecting and using a 20-1scheme in a short time high-risk scheme in GJB 899A, the comprehensive stress is used as the accelerated test stress of the full-missile-grade, and the reliability of the full missile is investigatedthrough double-platform parallel excitation control. According to the method and the system, under the comprehensive stress, a double-platform parallel excitation scheme is simultaneously selected, the full-missile-grade product is selected for testing, and the problems that the full-missile-grade product is difficult to really simulate the environment and the reliability of the full-missile-grade product is difficult to check are solved.

Description

technical field [0001] The invention relates to the technical field of reliability testing, in particular to a reliability testing method and system for full-bomb level double-stage parallel-excited flight based on comprehensive stress. Background technique [0002] At present, the flight reliability test is carried out at the whole missile level. Generally, temperature, humidity, vibration or electrical stress are selected as the single accelerated stress. The failure mechanism of the whole machine induced by the test is relatively simple, and the test efficiency is low. It will lead to unreasonable product energy distribution, failure to meet multispectral shape, too complicated test tooling, and unrealistic simulation of boundary characteristics. [0003] Patent document CN104034498A discloses a kind of fast clamping vibration test bench used for missile vibration testing, by setting on the vibration test bench: a lower base, a vibration table arranged in parallel, and a ...

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Problems solved by technology

[0002] At present, the flight reliability test is carried out at the whole missile level. Generally, temperature, humidity, vibration or electrical stress are selected as the single accelerated stress. The failure mechanism of the whole machine induced by the test is relatively simple, and the test efficiency is low. It will lead to unreasonable product energy distribution, failure to meet multispectral shape, too complicated test tooling, and unrealistic simulation of boundary characteristics

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