Study On Guidance And Control Method For BTT Missile

Bank-to-turn(BTT)and skid-to-turn(STT)are two kinds of aircraft control technology.The latter directly control the direction of the aircraft through the "swing",which is faster and adapted to the control of small mobile missiles.But most aircraft use BTT technology for the design of seeker and guidance control law,to meet the high accuracy,large mobility and pneumatic resistance requirements,during the remote design.BTT aircraft achieves lift(or maneuver)mainly through the fuselage tilt,which is applicable to some of the small aircraft resistance,heavy motor overload(or rise to drag ratio)occasions.However,BTT-controlled aircraft is very difficult in the design of the control system,due to the strong coupling and nonlinear time-varying.So people usually ignore the the channel coupling on the three-channel design during the design of the controller.They play an important role in modern and complicated battlefield environment,and also an important development direction of tactical missile control.Guidance control technology has become one of the main research problems.In this paper,the guidance law and autopilot design of BTT vehicle are studied respectively for BTT aircraft,in order to achieve the goal of fast and accurate tracking,and ultimately completed in the project requirements under the conditions of precision strike targets.The main contents of this paper are as follows:First of all,we analyze and solve the motion form of aircraft and establish a mathematical model based on mechanical principle and mathematical method.Then,we will establish a mathematical model of BTT vehicle,further movement of the vehicle,considering the conditions of engineering design,such as the aircraft as a rigid body;ignoring the influence of gravity,only considering the reaction force and air force.It lays the foundation for the next design analysis.Secondly,based on the proportional navigation law,we design a tracking nominal trajectory reentry guidance law aiming at the virtual target point.Then,the BTT180 control model is used to obtain the roll angle command and overload command for reentry vehicle,so as to realize the logical method of reentry guidance law.By using the guidance method,the whole trajectory numerical simulation is carried out,and the simulation results of the guidance law are analyzed.Finally,the controller part of the BTT aircraft is designed,and the equivalent elevator control can be obtained because the FLAP rudder is the actuator and it is mounted vertically at the rear of the aircraft.Because the yaw channel lacks the control amount,the yaw channel needs to add the aileron control so that it can control the two channels,that is,the roll and yaw path,to avoid the side slip angle divergence,the sideslip angle feedback is introduced to the rolling channel.The validity of the designed autopilot is simulated and verified when the aerodynamic parameters are selected properly.