Aiming at the combination attitude control after the retired spacecraft is captured by the servicer spacecraft under the disturbance, this paper utilizes the suboptimal nonlinear H-inf state feedback control to solve this problem.For the sake of fulfilling the nonlinear constrains, the output restriction and the overshoot of angular velocity in the control transient process, the Covariance Matrix Adaptation Evolution Strategy (CMA-ES) algorithm is used to find the optimal controller parameters.The numerical simulation is shown at last and it used to demonstrate the rigid spacecraft can have a nice performance in the optimum point from CMA-ES under the nonlinear state feedback H-inf controller.