Damping Actuator And Autopilot Design Of BTT Missile

To require the deminding of missile’s range and flight speed, the shape of missile isbecoming more and more slender. With the increasing of the aspect ratio, the flexiblecharacteristics of the missile will be more and more obvious. This flexible characteristicswill impact the sensitive components on the missile, and make their accuracy lower.Itwill also bring the problem to the controller design.The research of this paper as follow:Simplify the projectile to beam model, deduce the elastic deformation function ofthe missile body, and use this function to create the flexibility of the equations of motionof the missile; rigid equation of motion of the projectile and missile equipment model.We use the elastic deformation function to analyze the impact from flight speed,thrust and aspect ratio to flexible characteristics flight speed; analyze the elasticdeformation function’s diversification with time and axial coordinates. According to theanalysis of the results, we discuss in the optimal installation location of the sensor.Separate variable for the elasticity of the airframe, add initiative power in theairframe model, damp suppression of the elastic vibration of the airframe, and analyzethe effect of the shock absorber damping. For rigid airframe model, use the classicalcontrol theory, and ignore the coupling between the three channels individually, wedesign three-channel controller, and analyze the controller performance. We usecoordination decoupling method, consider the coupling effect of the three-channelcoordination loop, design the controller and analyze the decoupling performance andtracking performance of the coordination loop.Make the target have four kinds of motor, do the end of the BTT missile guidancesegment6DOF mathematical simulation. We examine the performance of the autopilot;analyze the damping effect of the damping controller when the flight parameters changes.