有限推力椭圆轨道近距离拦截方法  

A Thurst-Limited Short-Distance Interception Scheme on Elliptical Orbit

作　　者：周荻[1] 张刚[1] 孙胜[1] 

机构地区：[1]哈尔滨工业大学,哈尔滨150001

出　　处：《宇航学报》2010年第7期1762-1767,共6页Journal of Astronautics

基　　金：国家自然科学基金(60674102);新世纪优秀人才资助计划(NECT-08-0153)

摘　　要：针对椭圆轨道近距离飞行器确定时间最小能量拦截问题,研究了有限推力一次机动作用下的点火时刻以及发动机推力方向的确定方法。经典两点边值问题是在初始时刻施加速度脉冲,在固定时间达到要求位置。根据能量最优要求,给出了脉冲推力条件下的最佳点火时刻的确定方法,通常不是初始时刻。并证明了发动机推力方向始终对准速度增益方向时,所需能量最小。仿真结果表明选取最佳点火时刻可减小发动机工作时间,且速度增益制导方法可提高命中精度。For the fixed time,min-fuel interception problem on elliptical orbits,a method for solving the ignition time and thrust direction with a thrust-limited maneuver is proposed. Classical two-point boundary value problem requires that the thruster imposes an impulse on an interceptor at initial time,such that the interceptor can reach a desired position at the terminal time. For the min-fuel demand,a method for calculating the optimal ignition time with the impulse-thrust is analyzed; usually that is not the initial time. Moreover,it is proved that the fuel is minimized by aligning the thrust direction with the relative velocity-to-be-gained vector. Simulation results show that selecting the optimal ignition time can reduce the burning time of thruster,and the velocity gain guidance method can enhance the accuracy of interception.

关 键 词：椭圆轨道 有限推力 相对运动 速度增益制导 

分 类 号：V448[航空宇航科学与技术—飞行器设计]