卫星在降交点地方时不变的最优轨道转移研究  

Fuel-Optimal Orbital Transfer with Invariant Local Time of Descending Node

作　　者：张科[1] 刘满国[1] 

机构地区：[1]西北工业大学航天学院,陕西西安710072

出　　处：《计算机仿真》2016年第5期116-119,共4页Computer Simulation

摘　　要：卫星在运行时要求降交点地方保持不变,而在卫星变轨前后降交点地方时不变情况下要用有限推力燃料达到最优异面轨道转移问题。针对降交点地方时不变、有限推力等难点,利用虚拟目标卫星的概念,建立了轨道转移的相对运动模型,提出了保证降交点位置不变的变轨初始条件;基于极小值原理将燃料最优变轨问题转化为两点边值问题,并采用共轭梯度法进行数值求解。针对变轨时间固定、连续推力情况,以总冲最小、满足各种约束为指标,进行了异面转移轨道的优化设计验证。仿真结果验证了卫星轨道转移策略和算法达到最优转移。To meet the demand of some special space missions,the problem of fuel-optimal finite thrust non-coplanar orbital transfer with invariant local time of descending node is investigated in this paper.To deal with the difficulties such as invariant local time of descending node and finite thrust,the mathematical model of relative motion is established based on the concept of imaginary target satellite.The initial condition for orbital transfer is proposed to keep the invariant local time of descending node.The optimal control problem of fuel-optimal orbital transfer is then translated into a two-point boundary value problem,which is numerically solved by the conjugate gradient method.For fixed transfer time and continuous thrust,the optimal trajectory is designed with many constraints to minimize the total impulse.Simulation results demonstrate the validity of the orbital transfer strategy and algorithm.

关 键 词：轨道转移 异面轨道 降交点地方时不变 燃料最优 有限推力 

分 类 号：V111.8[航空宇航科学与技术—人机与环境工程]