针对存在动力学参数摄动及外部干扰的航天器姿态机动问题,给出一种新的非线性鲁棒H_∞控制方法.通过适当处理和假设,将航天器姿态模型表示为具有凸多面体不确定性的多项式型状态空间方程,并基于Lyapunov稳定性和平方和(SOS)理论,建立非线性状态反馈H_∞控制设计的可解性条件.最后,通过数值仿真实例验证了所提出方法的有效性. Aiming at the problem of attitude maneuvering of spacecraft with perturbation of dynamic parameters and external disturbances, a new nonlinear robust H_∞control method is proposed. The attitude and attitude of the spacecraft are expressed as convex polyhedron with uncertainties Based polynomial state space equation and the Lyapunov stability and SOS theory are used to establish the solvability conditions of the nonlinear state feedback H_∞control design.Finally, numerical simulation examples are given to verify the effectiveness of the proposed method .