为满足小卫星设计要求 ,针对重力梯度稳定微小卫星 ,建立了其大角度姿态机动的动力学模型 ,并应用Pontryagin极大值原理进行了最优控制问题的研究。同时 ,将遗传算法引入卫星姿态控制的数值计算中 ,求解最短时间控制问题和能量最优控制问题 ,发展了一种新的最优控制问题的计算方法 ,避免了对迭代初值进行猜测的困难 ,提高了计算效率。以“清华一号”微小卫星为算例进行了数值仿真计算 ,得到了卫星姿态角度和反作用飞轮控制力矩的变化规律 In order to meet the design requirements of small satellites, a dynamic model of large-angle attitude maneuver is established for the gravitational gradient-stabilized microsatellite. The Pontryagin maximum principle is used to study the optimal control problem. At the same time, the genetic algorithm is introduced into the numerical calculation of satellite attitude control to solve the shortest time control problem and the energy optimal control problem, and a new method to calculate the optimal control problem is developed. It avoids the difficulty of guessing the iterative initial value , Improve the computational efficiency. Taking the “Tsinghua-1” micro-satellite as an example, numerical simulation was carried out, and the changing rules of the satellite attitude angle and reaction flywheel control torque were obtained.