基于交会概念的最省燃料异面有限推力轨道转移研究  

Noncoplanar Orbital transfer with Finite Thrust basedon Rendezvous concept

作　　者：荆武兴[1] 吴瑶华[1] 

机构地区：[1]哈尔滨工业大学航天工程与力学系

出　　处：《哈尔滨工业大学学报》1998年第2期124-128,共5页Journal of Harbin Institute of Technology

摘　　要：基于交会概念研究了卫星在三维空间的最省燃料有限推力轨道转移问题。假设有一个飞行器已经在目标轨道上运动，此飞行器称为虚拟卫星。只要控制真实卫星与虚拟卫星软交会，就实现＊了真实卫星向目标轨道的转移。假定发动机推力大小为常值，方向可调。提供了真实卫星的相对运＊动动力学模型，用Ｐｏｎｔｒｙａｇｉｎ极大值原理导出了最省燃料的推力控制策略，建立了状态和共轭状态的初始边界条件。导出的两点边值问题由牛顿代方法求解。仿真结果验证了所提供方法的有效性。Noncoplanar orbital transfer with finite thrust based on rendezvous concept is studied.* It is supposed that there is a satellite called imaginary satellite moving on target orbit. Real* satellite will be sent to target-orbit provided that it is controlled to realize soft rendezvous (zero* relative position, zero relative velocity) with the imaginary satellite. Thrust value is constant and thrust direction variable. Relative motion dynamic model of the real satellite is presented.* Optimal 4hrust direction is derived following Pontryagin's principle. Initial boundary conditions* of states and costates are established. Two-point-boundary-value-problem is computed with* Newtonian iterative method. It is simulated that satellite transfers from geosynchronous transfer* orbit to geosynchronous orbit with plane change. Simulation results show effectiveness of the method presented.*

关 键 词：轨道转移 交会 最优控制 有限元推力 飞行器 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程]