Research On Attitude Control For Missile With Blended Lateral Thrust And Aerodynamic Force

With the development of ballistic missile technology, the air-defense missiles of new generation development rapidly. Traditionally, air-defense missiles use pure aerodynamic force control method, which can’t meet the requirements of rapid response and high payload. In order to improve the maneuverability of air-defense missiles in modern battleground, we use a kind of ACS missile with blended lateral thrust and aerodynamic force, which contain two kind control forces: aerodynamic force generated by tail vane and lateral force generated by pulse jets configured in the front of the mass center. However, the pulse jets are on/off operating thrusters, and the aerodynamic forces are continuous, which brings some challenges to attitude controller design. This thesis takes PAC-3 missile as an example to study the blended control of the lateral thrust and aerodynamic force. The main researches and achievements are as follows.Firstly, considering the configuration of the attitude missiles, build the attitude control model of blended missiles, including kinematics and mechanics model, and the attitude control model, which provides the base knowledge for the following study by analyzing and simplifying characteristics of each model.Secondly, design the firing logic method of blended missile in coupling states. Come up with firing constraints to weaken lateral jet interference and simplify model. Based on that, transform the constraints to mixed logic inequalities. Then, conduct the simulation by AMPL and MATLAB to deal with abundant logic variables. The results show that the firing logic method is of feasible and is of practical significance in terminal guidance of missiles.Thirdly, design the attitude controller of ACS missile based on Active Disturbance Rejection Controller. Taking three channels into consideration, design attitude controller respectively. In addition, introducing three kind of instruction dispatch tactics, and analyzing the advantages and disadvantages respectively. Besides, conduct the simulation to verify the feasibility of attitude control laws. The results of numerical simulations show that the attitude control laws are of capable to satisfy complex forms of attitude angles. And, the instruction dispatch tactics based on control deviation is appropriate for bigger changes of deviation; the instruction dispatch tactics based on number of fired jets is appropriate for large angle maneuvers; the instruction dispatch tactics based on saturation capacity of deflection angle works best, which save the pulse jets most on the premise of meeting the control accuracy.