电动力绳系卫星系统长期离轨动力学建模与控制设计方法  

Dynamics modeling and control design method for long‑term deorbiting of an electrodynamic tether system

作　　者：颜家慧 陈提 文浩[1] 罗操群 彭文轩 恽卫东 YAN Jia‑hui;CHEN Ti;WEN Hao;LUO Cao‑qun;PENG Wen‑xuan;YUN Wei‑dong(State Key Laboratory of Mechanics and Control for Aerospace Structures,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Shanghai Institute of Aerospace System Engineering,Shanghai 201108,China)

机构地区：[1]南京航空航天大学航空航天结构力学及控制全国重点实验室,江苏南京210016 [2]上海宇航系统工程研究所,上海201108

出　　处：《振动工程学报》2024年第10期1792-1802,共11页Journal of Vibration Engineering

基　　金：国防科技工业局空间碎片专项资助项目(KJSP2020010301)。

摘　　要：本文针对电动力绳系卫星系统的长期离轨问题,研究离轨过程中系统的非线性动力学建模以及离轨控制设计方法。基于哑铃模型假设,进行系统的姿态动力学建模。为提高动力学建模精度,计入电动力、大气阻力和地球J_(2)摄动等动力学载荷对系统轨道运动的影响,采用修正的非奇异轨道要素描述系统的轨道动力学。针对离轨的动力学控制问题,提出了常值电流输入、方向可变的电流输入和最优控制三种电流控制设计方法,通过系绳电流设计调节电动力载荷实现离轨机动。在最优控制设计方法中,构建了带非线性约束的动力学反问题,基于非线性规划算法求解该反问题,得到最优控制参考轨迹,通过闭环反馈跟踪修正电流进行离轨。另外,提出了一种基于能量的电流开关控制策略辅助离轨,以保持系统姿态稳定和高效地利用电动力。为高效离轨对系统进行了动力学设计,并通过仿真算例对比分析了控制方法的离轨效率,验证了控制方法的有效性。This paper investigates the dynamics and control problems of the long-term deorbiting of an electrodynamic tethered satellite system.The dynamics modeling of the system is carried out based on a dumbbell model assumption.To improve the accuracy of the system model,the orbital dynamics is described using a set of modified equinoctial elements,involving the effects of Lorentz force,atmospheric drag and J_(2) perturbation force.Three current control strategies are proposed to regulate the electrodynamic forces for achieving a stable long-term deorbiting process,namely,the constant current input,the directionally variable current input,and the optimal control strategies.In the design of the optimal control strategy,the long-term deorbiting problem is formulated as an inverse problem of dynamics with nonlinear constraints,which is further solved via a nonlinear programming method to obtain the optimal reference trajectories.The deorbiting of the system is then achieved using the modified current control input obtained from a tracking feedback control law.Additionally,an energy-based current switch control strategy is adopted to ensure the stability of system and the efficient utilization of Lorentz force.Case studies of the system with designed physical parameters are conducted to analyze the deorbiting efficiency and to validate the effectiveness of the proposed control strategies.

关 键 词：绳系卫星系统 电动力 最优控制 长期离轨 

分 类 号：O313.7[理学—一般力学与力学基础] V412.4[理学—力学]