针对某大型运载火箭姿态控制系统，研究了利用混合灵敏度Ｈ∞控制技术对同时具有实参数不确定性和未建模动态不确定性的系统进行控制和设计的方法。考虑到运载火箭飞行过程中存在较大的气动特性不确定性，运用μ分析理论，分析控制系统对参数摄动的鲁棒稳定性和鲁棒性能。仿真实例表明该Ｈ∞鲁棒控制方法有较好的参数鲁棒特性。 Aiming at a large launch vehicle attitude control system, a hybrid H∞ control technique is used to control and design a system with both real parameter uncertainties and unmodeled dynamic uncertainties. Taking into account the larger aerodynamic characteristics of the launch vehicle during the flight, the μ analysis theory is used to analyze the robust stability and robustness of the control system to perturbed parameters. The simulation results show that the H∞ robust control method has better robustness of parameters.