基于交会概念的最省燃料共面有限推力轨道转移方法

Coplanar Orbital Transfer with Finite Thrust Based on Rendezvous Concept

基于交会概念研究了卫星在平面内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。发动机推力大小为常值,方向可调。提供了适合于同平面轨道转移的卫星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。给出了两点边值问题的迭代变量与迭代算法。仿真例子考虑卫星由低圆轨道向同平面高圆轨道的小推力过渡,仿真结果验证了所提供方法的有效性。

Coplanar orbital transfer with finite thrust based on the rendezvous concept is studied. It is supposed that if there is a satellite called imaginary satellite moving on the target orbit, a real satellite will be sent to the target orbit provided that it is controlled to realize soft rendezvous (zero relative position, zero relative velocity) with the imaginary satellite. The thrust value is constant and the thrust direction is variable. A relative motion dynamic model of the real satellite is presented. The optimal thrust direction is derived following pontryagin's principle. Initial boundary conditions of states and adjoints are established. The two-point-boundary-value-problem is computed with the newtonian iteritive method. The satellite is simulated to transfer from low circular orbit to high circular orbit. Simulation results illustrate effectiveness of the method presented.