以原理验证机为背景，建立了无尾布局垂直/短距起降飞行器的数学模型，并通过智能自适应方法对其进行了闭环飞行控制，控制量通过控制分配合理的协调各操纵面，最后在MATLAB7.0/Simulink环境下通过数值仿真进行了验证。结果显示，该平台具备垂直/短距起降能力和较好的飞行性能。

The mathematical model was studied by mechanical analysis and CFD (computing fluid dynamics) computation. Besides, an intelligent adaptive based control law was proposed and the optimization approach is employed to solve the constrained control allocation problem. The results show good closed loop performance and validate the intelligent optimization approach of constrained control allocation for flight control.