Research On Guidance And Control For Missile With Aerodynamic And Thrust

With the requirement of modern military technology,missile developing t towards high speed and high mobility maneuver ability,this trend set a higher demand on interceptor's high maneuverability and guidance accuracy.Because of traditional missile cannot effectively follow the guidance instruction,therefore the guidance accuracy decline obliviously with the high mobility of the target motion.In this paper,in order to intercept the target effectively,improve the mobility and guidance precision of missiles,we consider introducing lateral direct force of the rail type missile to our research.In this paper,we define the atmosphere in a certain type of interceptor missile as the research background,by analyzing the characteristics of the missile,to make a better lateral/aerodynamic compound control and guidance strategy.First of all,we establish the mathematical model of missile control and guidance system,including the mathematical target model of relative movement between missile and target missile in pitching channel and yawing channel,a mathematical model of the roll channel.Secondly,we studied the classical proportional guidance missile,using sliding mode variable structure control theory,the optimal sliding-mode guidance law,and a discrete sliding mode guidance law is analyzed and designed.Then we make the simulation analysis by writing program,it is concluded that the optimal guidance law for the missile control system optimization guidance commands is obtained.Thirdly,we study the rail type missile aerodynamic lateral/aerodynamic force composite control system.And based on the classical control theory,lateral/aerodynamic compound control system is designed by the method of frequency domain direct lateral,according to a certain frequency performance indicators.And based on the theory of sliding mode variable structure control we design and analyze missile aerodynamic lateral/aerodynamic force composite control system.Mathematical simulation shows that the overload response of the composite control system dynamic performance is superior to the aerodynamic control system.In the end,Simulation analysis was made to verify the validity of the design of the compound control method,and we compare the results of aerodynamic lateral/aerodynamic force composite control and control precision.It is concluded that the missile aerodynamic force/direct force composite control system can effectively track the missile guidance instruction,thus ensuring the guidance precision.