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当空间拦截器由中制导阶段转入末制导阶段时，受不确定因素的影响，其姿态可能与预定姿态相差较远。在这种情况下，拦截器必须进行大角度姿态机动。这时的姿态控制系统是一个非线性、多输入多输出耦合控制系统。在拦截器不滚转的前提下，上述复杂系统可以视为３个简单子系统的组合。在每个子系统中，应用变结构＋ＰＩＤ组合控制器，这样各子系统抗干扰能力强，收敛速度快，超调小，而且稳态精度高，无抖动。仿真结果证明了组合控制方法的有效性。
When the space interceptor is transferred from the intermediate guidance stage to the final guidance stage, the attitude of the space interceptor may be far away from the predetermined attitude due to the influence of the uncertain factors. In this case, the interceptor must maneuver in a wide-angle attitude. The attitude control system at this time is a non-linear, multi-input multi-output coupling control system. In the interceptor does not roll under the premise of the complex system can be regarded as a combination of three simple subsystems. In each subsystem, the application of variable structure + PID controller, so that the anti-interference ability of each subsystem, fast convergence, small overshoot, and steady high precision, no jitter. Simulation results prove the effectiveness of the combined control method.