A Novel Switching Control Method for Hypersonic Flying Vehicle

With the rapid development of aeronautics technology, hypersonic flying vehicle is playing an increasingly important role, yet control methods on such vehicle were stilled confined with classical PID (proportional, integration and differentiation) or its variations. In order to have better control performance, a switching control method was used to design the attitude control law for hypersonic missile, which guaranteed higher angle precise control than PID. Simulation results showed the effectiveness and the superiority of the proposed switching methods over the classical PID and other typical switching methods.