摘要
卫星在运载火箭飞行过程中经历复杂的振动冲击环境,恶劣的动力学环境给卫星的使用寿命带来不利影响,甚至导致卫星失效和破坏。通过对粘弹性阻尼材料的吸能减振原理的研究,提出基于剪切阻尼的整星减振结构设计方案,针对模拟卫星、适配器及整星减振装置组合体结构开展数值仿真预示和试验验证工作,结果表明两者吻合较好,验证了基于剪切阻尼整星减振技术的有效性。
The satellite experienced complex vibration shock environment during the launch vehicle was in flight. Severe dynamic environment caused bad effects on the life of satellite, made the satellite losing efficacy and even destroyed the satellite completely. In this paper, energy absorption vibration damping principle of viscoelastic damping material was researched and design program of whole-satellite vibration damping structure was proposed. Numerical simulation prediction and test of combination structure of simulated satellite, adapter and whole-satellite vibration damping devices was carried out and the result showed that the simulation results were consistent to the test data which validated the effectiveness of whole-satellite vibration damping technology based on shear damping.
出处
《导弹与航天运载技术》
北大核心
2016年第1期89-91,97,共4页
Missiles and Space Vehicles
基金
探月工程三期预先研究(TY3Q20110019)
关键词
剪切阻尼
整星减振
数值仿真
试验
Shear damping
Whole-satellite vibration damping
Numerical simulation
Test
