空间平台发射服务器动力学与双脉冲最优交会  

DYNAMICS OF SPACE PLATFORM LAUNCHING SERVER AND OPTIMAL DOUBLE PULSE RENDEZVOUS

作　　者：韩艳铧 李伟康 张勇 Han Yanhua;Li Weikang;Zhang Yong(College of Astronautics,Nanjing University of Aeronautics and Astronautics,Nanjing 211106,China;UAV Research Institute,Narnjing University of Aeronautics and Astronautics,Nanjing 210016,China;Key Laboratory of UAV Technology,Nanjing University of Aeronautics and Astronautics,Ministry of Industry and Information Technology,Nanjing 210016,China)

机构地区：[1]南京航空航天大学航天学院,南京211106 [2]南京航空航天大学无人机研究院,南京210016 [3]南京航空航天大学中小型无人机先进技术工业和信息化部重点实验室,南京210016

出　　处：《动力学与控制学报》2022年第4期63-73,共11页Journal of Dynamics and Control

基　　金：中央高校基本科研业务费青年科技创新基金(NT2020025)。

摘　　要：本文研究了空间平台发射服务器的两体耦合动力学,以及服务器与目标星交会对接的双脉冲能耗最省制导问题.平台首先与目标星形成绕飞关系,保持其发射筒轴线瞄准目标星.接到发射指令后,服务器从发射筒中射出.本文采用凯恩方法建立了发射过程平台-服务器两体动力学模型.因为两体耦合影响,平台姿态偏转,服务器出筒时的速度已经不能瞄准目标星.通过小型火箭发动机给其施加初始和末端共两次速度脉冲.初始脉冲发生于服务器出筒瞬间,改变其航向,保证其与目标星准确交会;末端脉冲发生于服务器与目标星交会瞬间,将其相对于目标星的速度减为零,实现软对接.优化指标是能耗最省,即两次速度脉冲幅值的平方和最小,本文将其归结为非线性规划问题.在服务器交会飞行时间远小于平台绕飞目标星周期的情况下,可将平台绕飞平均角速度视作小参数,采用摄动法求出上述非线性规划的一阶近似解,然后以此为迭代初值,快速可靠地找到精确最优解.最后进行了数值仿真验证.The paper studies the two-body coupling dynamics between the space platform and server while launching process,as well as energy saving optimization of the double pulse control of the server during rendezvousing and docking to the target satellite.Firstly,the space platform forms an orbiting relationship with the target satellite,keeping its launch tube axis aiming at the target satellite.After receiving the launch command,the server shoots out from the launch tube.The Kane method is used to establish the platform-server two-body dynamics model.Due to the effect of the coupling of the two bodies,the attitude of the platform is perturbed,causing the server unable to accurately aim at the target satellite while separating the tube.Two velocity pulses are applied to the server through its small rocket engine.The initial pulse occurs at the moment when the server is separating the tube,changing its course to ensure accurate rendezvous with the target satellite;the end pulse occurs at the moment when the server rendezvous to the target satellite,reducing its relative velocity to zero to achieve soft docking.The optimization index is the least energy-efficient,that is to minimize the sum of the squares of the two pulse amplitudes.The paper summarizes it as a nonlinear programming problem.Under the condition that the rendezvous flight time is small compared to the period of the platform orbiting the target satellite,the average angular velocity of the orbiting flight can be regarded as a small parameter,and the canonical perturbation method can be used to obtain the first-order approximate solution of the nonlinear programming.Then the optimizing iteration process is started from the approximate solution as its initial guess.Finally,a numerical simulation verification is carried out.

关 键 词：多体动力学 凯恩方法 在轨服务 C-W方程 交会对接 双脉冲制导 小参数摄动法 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]