| 航天器振动试验力限条件设计半经验方法 |
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| 引用本文： | 李正举,马兴瑞,韩增尧.航天器振动试验力限条件设计半经验方法[J].中国空间科学技术,2011,31(1):1-7. |
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| 作者姓名： | 李正举 马兴瑞 韩增尧 |
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| 作者单位： | 1. 中国空间技术研究院,北京,100094
2. 中国航天科技集团公司,北京,100037 |
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| 摘 要： | 力限振动试验可以缓解传统加速度控制振动试验在试验件共振频率处产生的振动"过试验"现象.计算力限条件是进行力限振动试验的前提.介绍了力限振动试验的基本原理,给出了计算力限条件的基本过程,采用二自由度系统模型详细推导了半经验系数的计算方法,基于此方法计算了某航天器有效载荷力限随机振动试验的力限条件.结果显示,该方法可合理确...
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| 关 键 词： | 振动试验 力限条件 半经验方法 二自由度系统 航天器 |
Semi-empirical Method for Force Specification in Force Limited Vibration Test |
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| Li Zhengju,Ma Xingrui,Han Zengyao.Semi-empirical Method for Force Specification in Force Limited Vibration Test[J].Chinese Space Science and Technology,2011,31(1):1-7. |
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| Authors: | Li Zhengju Ma Xingrui Han Zengyao |
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| Institution: | Li Zhengju1 Ma Xingrui2 Han Zengyao1(1 China Academy of Space Technology,Beijing 100094)(2 China Aerospace Science and Technology Group Co.,Beijing 100037) |
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| Abstract: | The force limited vibration test can alleviate the over-testing phenomenon generated by the resonant frequency in the acceleration-controlled vibration test.Force specification estimation is a prerequisite for the force limited vibration test.The principle of force limited vibration test was introduced.And the calculation method for semi-empirical coefficient was derived by the two degree of freedom system.Furthermore,the force specification of some spacecraft payload was caculated in the random vibration t... |
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| Keywords: | Vibration test Force limited specification Semi-empirical method Two degree of freedom system Spacecraft |
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