Research On The Control Method Of Agile Turn Of Air-to-air Missile

Capacity of over-the-shoulder launch is required for the next generation ofair-to-air missile, and many countries are researching this technology. This dissertationinvestigates control design of agile turn in over-the-shoulder launch of air-to-airmissiles. The main contents include description of lateral thrust set needed in agile turn,attitude control design of the agile turn, and simulation of terminal guidance trajectory.First, the mathematical model of air-to-air missile is established. Based on theanalysis of the aerodynamic characteristics of the agile turn, small angle-of-attackattitude control model and large angle-of-attack attitude control model of air-to-airmissile using reaction jet device are established.Second, for air-to-air missiles using reaction jet device, the control system of theagile turn is designed using sliding mode control. In the design, firstly the operatingcharacteristics of reaction jet device is analyzed, and then a jet device of air-to-airmissile is utilized, and lastly the jet and aerodynamic compound control is designedusing the sliding mode control.Then, for air-to-air missile using thrust vectoring, the control system of the agileturn is designed using high order sliding mode control. In the design, firstly theoperating characteristics of the thrust vectoring device is analyzed, and gas rudder isintroduced, then the attitude control of agile turn is designed using high order slidingmode control, and finally comparison and analysis of the two different lateral thrustsets are conducted.At last, the trajectory of the terminal guidance in over-the-shoulder launch issimulated using the proportional guidance law. Firstly the mathematical model ofrelative motion between the missile and its target is established, then a simulation iscarried out, and the final results show that the proposed control methods in thisdissertation has accomplished the mission of over-the-shoulder launch in the pitchplane.