论文部分内容阅读
针对受环境干扰的带有太阳能帆板的挠性航天器,研究了航天器姿态机动控制的参数优化问题。建立了挠性航天器姿态机动控制参数的联合优化模型,并采用一种基于精英机制的多目标优化算法,设计机动路径和控制器参数,在保证闭环系统稳定的前提下,以获得较好的机动快速性和较高的稳态精度。地面模拟实验验证了所提方法的有效性。
Aiming at the flexible spacecraft with solar panels that is disturbed by the environment, the parameter optimization of spacecraft attitude maneuver control is studied. A joint optimization model of attitude maneuvering control parameters of flexible spacecraft is set up and a multi-objective optimization algorithm based on elitism mechanism is adopted to design the parameters of maneuvering path and controller. Under the premise of ensuring the stability of the closed-loop system, Maneuverability and high steady-state accuracy. Ground simulation experiments verify the effectiveness of the proposed method.