北京航空航天大学学报 ›› 2009, Vol. 35 ›› Issue (11): 1294-1297.

• 论文 • 上一篇    下一篇

新一代运载火箭姿态控制技术

吴燕生, 何麟书   

  1. 北京航空航天大学 宇航学院, 北京 100191
  • 收稿日期:2008-05-14 出版日期:2009-11-30 发布日期:2010-09-16
  • 作者简介:吴燕生(1963-),男,北京人,博士生,wuysh@spacechina.com.

Attitude control technology of new-generation launch vehicles

Wu Yanshen, He Linshu   

  1. School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
  • Received:2008-05-14 Online:2009-11-30 Published:2010-09-16

摘要: 开展了新一代运载火箭姿态控制设计技术研究,推导了工程适用的姿态动力学模型,基于牛顿-欧拉法建立了刚体质心和绕质心运动方程、液体晃动方程,基于有限元方法建立了火箭弹性振动方程,弹性运动方程基于空间模态,反映了横向、纵向、扭转与助推器局部模态对火箭的姿态与载荷的影响.基于空间模态的姿态动力学模型研究了姿控系统设计方法,给出了工程适用的姿控系统设计方法.开展了容错重构技术研究,分析了伺服机构故障对姿控系统的影响,为提高运载火箭的飞行可靠性和抗故障能力奠定了基础.对主动减载技术进行了研究,能够对高空风产生的气动载荷进行主动抑制,放宽了发射条件,对新一代捆绑运载火箭姿控系统的设计具有重要的借鉴意义.

Abstract: A detail analysis was presented for attitude control design of new-generation launch vehicles. First, rigid body dynamics models and fluid sloshing dynamics models were developed based on Newton-Euler equations, and then elastic dynamics models which suggest a potential for interaction between attitude control and the structural dynamics of the vehicle, was investigated based on finite element method. According to dynamic models, attitude control system was designed. Toward the end, the method to reduce aerodynamics loads and fault tolerance design was aimed. In order to enhance the reliability of launch vehicle, fault-tolerant reconfiguration system was designed, and servo system fault influence on attitude control system was considered. Accelerometer feedback was used to reduce the aerodynamic lateral loads caused by in-flight atmospheric. All the results derived form above research are well suit for attitude control design of new-generation launch vehicles.

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