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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。
Aiming at the large vibration problem of large flexible components such as solar wing during the orbit control of spacecraft, based on the dynamic characteristics of the controlled object, the input shaping method is introduced, and two kinds of models that can be applied to any rail-based thrust configuration system New rail control strategy to reduce the deformation amplitude and vibration amplitude of the sun wing during a given orbit control mission. Through the robust mathematics simulation of on-off time error, the validity of this method is verified. The simulation results show that the new orbit control method can significantly reduce the vibration amplitude of the solar wing during the orbit control and effectively improve the force and moment between the solar wing and the celestial body, Vibrate and break the danger.