北京航空航天大学学报 ›› 2004, Vol. 30 ›› Issue (02): 143-146.

• 论文 • 上一篇    下一篇

推力偏心影响下的飞控系统可靠性研究

陈云霞1, 孙宇锋1, 段朝阳2   

  1. 1. 北京航空航天大学 工程系统工程系, 北京 100083;
    2. 中国空空导弹研究院, 洛阳 471009
  • 收稿日期:2003-07-24 出版日期:2004-02-29 发布日期:2010-09-21
  • 作者简介:陈云霞(1977-),女,安徽怀宁人,博士生, cyx-2000@163.com.

Study on reliability for flight control system under influence of thrust misalignment

Chen Yunxia1, Sun Yufeng1, Duan Chaoyang2   

  1. 1. Dept. of System Engineering of Engineering Technology, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;
    2. China Airborne Missile Academy, Luoyang 471009, China
  • Received:2003-07-24 Online:2004-02-29 Published:2010-09-21

摘要: 发动机推力偏心是引起弹道散布和影响导弹可靠性的重要因素之一.为了尽早暴露系统设计缺陷和提高导弹的可靠性,提出了在推力偏心随机散布情况下进行导弹飞控系统性能和可靠性一体化分析的方法.分析推导了推力偏心引起的扰动力矩,给出了可靠性仿真的算法流程、具体实现方法和相关可靠性指标的计算公式,并以某型导弹飞控系统为案例验证了该方法的可行性.

Abstract: Thrust vector misalignment is an important factor, which causes trajectory scatter and affects missile reliability. In order to find design defect and enhance system reliability, the technique of integrated analysis of performance and reliability under the thrust's random misalignment was put forward. The disturbing moments were deduced and established. The algorithm process of reliability simulation, approach of implementation and formulas of computing reliability were given. The method was verified by X-missile's flight control system.

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