北京航空航天大学学报 ›› 2009, Vol. 35 ›› Issue (6): 705-708.

• 论文 • 上一篇    下一篇

基于预测校正法的低升阻比飞船再入轨迹设计

李惠峰, 凌 源   

  1. 北京航空航天大学 宇航学院, 北京 100191
  • 收稿日期:2008-05-12 出版日期:2009-06-30 发布日期:2010-09-16
  • 作者简介:李惠峰(1970-),女,陕西蒲城人,副教授,lihuifeng@buaa.edu.cn.
  • 基金资助:

    国家自然科学基金资助项目(60736023)

Reentry trajectory design of low lift-to-drag ( L/D ) ratio spacecraft based on predictor-corrector method

Li Huifeng, Ling Yuan   

  1. School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
  • Received:2008-05-12 Online:2009-06-30 Published:2010-09-16

摘要: 对低升阻比飞船高速再入地球大气层的轨迹规划问题,提出了基于数值预测校正NPC(Numeric Predictor-Corrector)法的预测制导方法,并用时间替代能量作为自变量从而规避奇异问题;由飞船再入的3自由度运动方程推导纵向平面内的运动方程,并使用预测-校正方法获得倾侧角数值;同时通过设计横向漏斗确定倾侧角的符号,最终得到当前需要的倾侧角.仿真结果表明,该方法能根据不同的再入条件得出对应的再入轨迹和倾侧角变化规律,其动压、热流率、过载也符合再入要求.

Abstract: To solve trajectory designing problem of the low lift-to-drag ( L/D ) ratio spacecraft when reentering into atmosphere with high speed, a predict guidance method was proposed, based on numerical predictor-corrector (NPC). The independent variable was changed to time instead of energy in order to avoid singularity. The 3-degree of freedom motion equations were established and longitudinal motion equations were inferential deduced. The value and sign of the bank angle were computed by longitudinal and lateral guidance separately while the main task of the latter was designing a lateral drogue deployment box. The results of simulation show that this method could educe appropriate reentry trajectory and bank angle according to the reentry conditions, and the velocity head, the rate of heat flow and g -loads are all suitable for the reentry desire.

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