Abstract
The captive flight vibration is the main induced force environment encountered in the use of air-to-air missile, because of its high vibration intensity and long duration, which has a great impact on the structure and performance of the missile. The captive vibration of the missile is mainly caused by the aerodynamic disturbance around the missile. The captive vibration in the whole missile reliability test should adopt the broadband random vibration of 20 ~ 2000 Hz, and the vibration magnitude of the missile head should be 3 ~ 6 dB lower than that of the missile tail, so as to truly simulate the vibration effect caused by aerodynamic disturbance In this paper, according to the test conditions and calculation formula of airborne external captive flight vibration given in GJB150.16-2009, the power spectral density of captive flight vibration of this type of engine is obtained, and the characteristics and parameters of random vibration are analyzed. The formulas for calculating the power spectral density and the root mean square acceleration at the starting points of the ascending and descending sections corresponding to the slope of the random vibration test condition expressed by the octave are given. The practice shows that the laboratory test results using the research results are similar to those of the air hang flight test.
Highlights
IntroductionThe captive flight vibration is the main stage of the the equipment carrying out the mission, and has the most serious impact on the life
The equipment consists of five parts, including guidance capsule, flight control cabin, rudder cabin, combat Department cabin and engine cabin
The captive flight vibration is the main stage of the the equipment carrying out the mission, and has the most serious impact on the life
Summary
The captive flight vibration is the main stage of the the equipment carrying out the mission, and has the most serious impact on the life. The vibration caused by equipment launching and flying is random. The purpose of functional vibration test is to test the working stress of air-to-air missile exposed to the most severe vibration environment. The purpose of durability vibration test is to ensure the structural integrity of air-to-air missile in the whole life cycle. The determination of experimental stress and duration should be careful to minimize the impact on the performance of electronic components while ensuring the fatigue life of air-to-air missile [4]. Fan Huitao and Guo qiangling successively discussed the environmental conditions of captive flight vibration test of air-to-air missile [5]. In the life extension test, it is necessary to test the reliability of equipment by random vibration test to identify and eliminate the faults caused by product technology and components, the quality and reliability of the products can be improved, and the basis for the equipment repair is extended
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