航天飞机的最优再入轨迹与制导  

Optimal Reentry Trajectory and Guidance of Space Shuttle

作　　者：李小龙[1] 陈士橹[1] 

机构地区：[1]西北工业大学,西安710072

出　　处：《宇航学报》1993年第1期7-13,共7页Journal of Astronautics

基　　金：高校博士点基金

摘　　要：本文研究航天飞机受过载、动压及加热约束情况下,总加热量最小的最优再入轨迹与制导问题。文中给出了确定阻力参考型、再入飞行走廊的方法与模型,建立了相应的制导律,以总加热量最小为性能指标,通过适当选取阻力参考型的变化,将再入轨迹的优化转换成参数的优化问题。并以美国航天飞机数据为例进行了模拟计算,得到了满意的结果。The optimal reentry trajectory is designed with the help of Drag Reference Profile (DRP). The DRP is first selected in the reentry flight corridor formed by fundamental contraints, such as, maximal dynamic pressure, maximal heating rate, maximal acceleration overload and maximal surface temperature limits. Then the DRP is adjusted to satisfy the required footprint and the terminal guidance demands. Finally, the DRP is determined by optimization of minimal total heat load input with satisfication of above two considerations. The guidance law for the Shuttle reentry is given and some numerical calculations using the data of American Space Shuttle are made to verify the method. The results are satisfied.

关 键 词：航天飞机 再入制导 再入轨迹 

分 类 号：V448.235[航空宇航科学与技术—飞行器设计]