可抑制航天器轨控过程中太阳翼大幅振动的新型轨控方法研究  

New Orbit Control Method to Reduce Solar Panel Vibration During Orbit Maneuvering

作　　者：胡军[1] 张国琪[1] 张志方[1] 黎康[1] 何英姿[1] 

机构地区：[1]北京控制工程研究所

出　　处：《载人航天》2011年第2期15-23,44,共10页Manned Spaceflight

摘　　要：针对航天器轨控过程中可能激起太阳翼等大型挠性部件的大幅振动问题,基于被控对象的动力学特点借鉴输入成型法,给出了两种可适用于任意轨控推力配置系统的新型轨控策略,降低既定轨控任务过程中的太阳翼变形幅度和振动幅度。通过开关机时间误差的鲁棒性数学仿真,验证了该方法的有效性。仿真结果表明:新型轨控方法可显著降低在轨控过程中的太阳翼的振动幅值,有效改善太阳翼与星体之间的作用力和作用力矩条件,有利于减少轨控过程中太阳翼因大幅振动而折断的危险。In order to reduce the solar panel vibration of spacecrafts during orbit control, two new control methods are proposed based on the input shaping design. The new methods can greatly reduce the deflection and vibration of solar panels induced by orbit control forces, and can be applied to any orbit control engine configuration. Through the mathematical simulations of the robustness of the on-off time uncertainties, the effectiveness of the methods are verified. Outcome of the simulations show that the new control methods can effectively reduce the solar panel vibration during orbit control, and attain a better mechanical condition between the satellite and flexible solar panels, which will consequently reduce the possibility of structure broken during orbit control.

关 键 词：输入成型 轨控 太阳翼 振动 

分 类 号：V448.222[航空宇航科学与技术—飞行器设计]