减冲击装置可以有效降低基础对有效载荷的冲击，在航天领域内的有效载荷及箭体分离过程中应用广泛。建立了减冲击装置数学模型，设计优化了结构尺寸，并制作了减冲击环样机。在响应板式爆炸冲击台上开展了冲击试验，并对冲击数据进行了冲击响应谱分析。结果表明，所设计的减冲击装置满足指标要求，而且大幅衰减了冲击幅值。此外，讨论了阻尼层对结构动力学特性及减冲击特性的影响。减冲击环结构适用于航空航天冲击环境，也适用于各类导弹仪器舱的整体冲击隔离，具有广阔的应用前景。
Abstract
In spacecraft design, isolator can be optimally located in aft of the satellite in order to attenuate shock load from the launch vehicle. Based on proposed analytical model, a shock isolator has been designed, analyzed, and tested. Impact test has been conducted with mechanical impulse pyro shock (MIPS) system. Experimental results show that the multi-layered shock isolator provides obvious reduction in shock load transmission from support base to payload. Moreover, the effect of structure damping on stiffness, vibration transmission characteristics and shock attenuation is discussed. The shock isolator is suitable for use on spacecraft launch system, and the presented structure will develop to be a very effective means with great application prospect.
关键词
整星减冲击装置 /
模型 /
冲击试验 /
冲击响应谱
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Key words
whole spacecraft shock isolator /
analytical model /
impact test /
shock response spectra.
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参考文献
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