机动再入飞行器主动段再入点约束闭路制导研究  

Study of the closed-loop guidance law for boost phase with reentry constraints of maneuvering reentry vehicles

作　　者：王小虎[1] 陈翰馥[1] 刘锋[2] 

机构地区：[1]中国科学院数学与系统科学研究院系统所,北京100080 [2]廊坊陆军导弹学院,廊坊065000

出　　处：《宇航学报》2002年第4期37-41,51,共6页Journal of Astronautics

摘　　要：基于机动再入飞行器再入制导段控制条件苛刻和难度大 ,必须为飞行器创造最佳的再入条件。本文对具有再入点约束的主动段闭路制导律进行了研究。根据飞行器椭圆弹道的性质、飞行器再入条件、球面几何和不动点原理给出了理想弹道的计算算法。为使飞行器能在主动段很快地进入到理想弹道上 ,系统采用了非线性的推力向量控制及预测制导方法。通过对新型号再入飞行器的制导系统的设计与仿真 。To provide the best conditions for a maneuvering entry vehicle which faces to the severe and difficult conditions for its control system in reentry phase,the closed-loop guidance law for boost phase with reentry constraints is investigated in this paper.Baced on the properties of elliptical trajectory,the reentry conditions of the vehicles,spherical geometry,and the fixed-point theorem,an algorithm for the ideal trajectory is proposed.In order to enter into the ideal trajectory with minimal energy,the nonlinear thrust vector control and the prediction guidance are adopted in the missile guidance control system.The simulation shows that the proposed design method provides a good flight performance for vehicles.

关 键 词：机动再入飞行器 再入点 闭路制导 再入制导 制导律 主动段 显式制导 

分 类 号：V448.235[航空宇航科学与技术—飞行器设计]