航天器环境工程2017，Vol.34Issue(3)：290-294,5.DOI:10.3969/j.issn.1673-1379.2017.03.011
一种气动式冲击响应谱试验系统的设计与分析
Design and analysis of a pneumatic test system for shock response spectrum
摘要
Abstract
The impact test for spacecraft is generally required with a magnitude between 1000g-2000g, sometime even more than 3000g. In a high-magnitude impact test for large (>500kg) products, it is difficult for the pendulum impact test equipment and the drop impact test equipment to meet the test requirements. In order to solve these problems, a pneumatic impact test system is designed for the high-magnitude impact test. The system uses the compressed air as the power source, and the instantaneous release of gas to expand the impact mass block, which is accelerated to impact the resonant plate, so that a spectrum similar to the complex damped sine wave is generated in the resonant plate. The test results show that when the system is unloaded, the impact value is up to 8000g. When the load is 200kg, the impact value is up to 5000g. The time domain curve is the shock attenuation wave, and the duration is less than 10ms. The method proposed in this paper can serve as a reference and theoretical basis for the design of this kind of impact test systems.关键词
气动/冲击响应谱试验/试验系统设计Key words
pneumatic/shock response spectrum test/test system design分类
机械制造引用本文复制引用
晏廷飞,沈志强,张俊刚..一种气动式冲击响应谱试验系统的设计与分析[J].航天器环境工程,2017,34(3):290-294,5.基金项目
总装备部共性技术课题(编号:51334050101) （编号:51334050101）
