北京航空航天大学学报 ›› 2007, Vol. 33 ›› Issue (04): 397-400.

• 论文 • 上一篇    下一篇

大气层内拦截弹脉冲姿控发动机快响应控制

王进1, 陈万春1, 殷兴良2   

  1. 1. 北京航空航天大学 宇航学院, 北京 100083;
    2. 中国航天科工集团公司, 北京 100830
  • 收稿日期:2006-05-10 出版日期:2007-04-30 发布日期:2010-09-19
  • 作者简介:王 进(1981-),男,四川汉源人,博士生,99missile@sohu.com.

Endoatmospheric interceptor fast response control using impulse attitude control motor

Wang Jin1, Chen Wanchun1, Yin Xingliang2   

  1. 1. School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China;
    2. China Aerospace Science & Industry Corp, Beijing 100830, China
  • Received:2006-05-10 Online:2007-04-30 Published:2010-09-19

摘要: 气动控制在低动压时其效率会有相当下降,为了使导弹在低动压时仍然具有一定的快速响应性,在导弹上安装脉冲姿控发动机参与姿态控制是一条可行的途径.对此方法的应用作了初步研究.分析了脉冲发动机作用对导弹动力学的影响,在一系列的简化后设计了俯仰平面内的控制策略,其设计思想是用气动舵平衡气动力矩使总的气动力矩为零,使导弹姿态主要由脉冲姿控发动机来控制,并用俯仰角的变化代替攻角的变化设计脉冲姿控发动机控制策略.给出了对阶跃加速度指令的响应仿真结果,表明在具有足够动压时气动控制仍可同脉冲姿控发动机控制媲美,而在低动压时脉冲姿控发动机相对气动控制具有较大优势.

Abstract: The effectiveness of aero control decreases as dynamic pressure decreases. Therefore impulse attitude control motor(ACM) is to be used to maintain fast response of missile in low dynamic pressure. A preliminary study of the method was given. The impact of ACM on the dynamics of missile was analyzed using assessment data. Then a control strategy was designed on the pitch plane after some simplifications. Aero-fin was used to counteract the aerodynamic moment so that the total aerodynamic moment would be zero and the attitude of missile would be mainly controlled by ACM. ACM control strategy was designed with the assumption that the increment of pitch angle was equal to the increment of angle of attack. Simulation results were given for step acceleration command which show that aero control is effective as ACM control in high dynamic pressure and ACM control becomes more effective than aero control as dynamic pressure decreases.

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