一种新的空间飞行器再入制导律研究  

Research of the Guidance Law Based on a New Method in Spacecraft Entry

作　　者：陈敬志[1] 杨一栋[1] 

机构地区：[1]南京航空航天大学301教研室

出　　处：《飞行力学》2007年第3期58-61,共4页Flight Dynamics

基　　金：国家高科技S863-706预研基金项目(2004-031-019)

摘　　要：基于阻力与能量关系的优化剖面,以该再入剖面作为基准轨迹,给出了跟踪这一基准轨迹的空间飞行器再入制导律与控制律,将基准轨迹转化为相应的迎角剖面和滚转角剖面,设计了相应的结构配置。仿真结果表明,基于阻力与能量关系剖面设计的制导律满足了各项约束条件,并能成功地控制飞行器到达所要求的位置。Based on drag vs energy profile which is obtained by optimization method, and the profile is regarded as drag reference. The guidance law and the control law are derived to track the drag reference, the alpha profile and the bank angle profile are empoldered, and the control structure configuration is designed. Flight simulation results show that the control system operates effectively and the spacecraft flies to the demanded place within certain restrictions and satisfies the demand of range.

关 键 词：空间飞行器 再入段 阻力 能量 制导律 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]