›› 2011, Vol. 31 ›› Issue (1): 1-7.doi: 10.3780/j.issn.1000-758X.2011.01.001

• 研究探讨 •    下一篇

航天器振动试验力限条件设计半经验方法

 李正举1, 马兴瑞2, 韩增尧1    

  1. (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)
  • 收稿日期:2010-05-07 修回日期:2010-09-20 出版日期:2011-02-25 发布日期:2011-02-25
  • 通讯作者: 李正举 联系信箱:北京5142信箱86分箱, 邮编:100094
  • 作者简介:李正举 1979年生,2010年获中国空间技术研究院飞行器设计专业博士学位。研究方向为航天器结构动力学与力学环境试验
  • 基金资助:

    国家重大科技专项工程

Semi-empirical Method for Force Specification in Force Limited Vibration Test

LI  Zheng-Ju1, MA  Xing-Rui2, HAN  Zeng-Yao1   

  1. (1 China Academy of Space Technology, Beijing 100094)(2 China Aerospace Science and Technology Group Co., Beijing 100037)
  • Received:2010-05-07 Revised:2010-09-20 Online:2011-02-25 Published:2011-02-25

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,该方法可合理确定力限振动试验的力限条件。

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

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 test. The results show that this method is reasonable to estimate the force specification.

Key words: Vibration test, Force limited specification, Semi-empirical method, Two degree of freedom system, Spacecraft