文章摘要
孙宝元,任宗金,钱敏,张军.轨/姿控火箭发动机推力动态测试系统建模分析[J].,2008,(5):668-672
轨/姿控火箭发动机推力动态测试系统建模分析
Modeling and analysis for dynamic thrust testing system of orbit/attitude control rocket engine
  
DOI:10.7511/dllgxb200805009
中文关键词: 火箭发动机  动态测试  动态性能
英文关键词: rocket engine  dynamic testing  dynamic characteristic
基金项目:国家自然科学基金资助项目(50475152,50675026);863-805国防重大专项资助项目.
作者单位
孙宝元,任宗金,钱敏,张军  
摘要点击次数: 882
全文下载次数: 812
中文摘要:
      根据轨/姿控火箭发动机脉冲点火方式下动态推力测试的特点和要求,设计了推力动态测试系统并进行动力学建模,采用模态分析理论研究系统的动态性能,并进行幅频特性与相频特性分析,为该系统在微阻尼条件下测试的不失真提供了理论依据.结合该模型,对测试信号进行傅里叶变换,通过系统幅相频特性与不同频率信号进行代数运算的方法,求得了测试系统动态测试误差,从理论上证明测试系统动态性能满足设计要求.
英文摘要:
      According to the characteristics and demands of dynamic thrust measurement for orbit/attitude control rocket engine, the dynamic thrust measurement system is researched and designed. The dynamic model is discussed and the dynamic ability is investigated through mode analysis theoretics, then its mathematic model and transfer function are set up, which are proved reliable by experiments. The dynamic transfer characteristic is analyzed and it is proved that the system is authentic with potty damp. Combining the model, the testing signal is changed into Fourier progression, then the dynamic testing errors are obtained when the system dynamic ability and different frequency signals progress in algebra. It is shown that the system dynamic ability satisfies the design requirements.
查看全文   查看/发表评论  下载PDF阅读器
关闭