Research On Control?Strategy Method Of Side-jet?Aerodynamic Fins Compound Of Intercoptor Missile

In the face of increasingly fierce threat from the air.With the use of precision-guided weapons,hypersonic vehicles and large maneuverable ballistic missiles,the fragmentation of the traditional interceptor is difficult to destroy the target due to the energy limited,which lead to increase the probability of penetration.All of these theats impose more stringent air defense interception technology.The traditional aerodynamic fins control has the restriction and delay of the angle of rudder deflection.It can not fill the requirements of modern accurate interception.The loading of direct force engine on the projectile can significantly improve the response speed and maneuver ability of the missile,which track the overload demand and destroy the target by hit-to-kill technology.This paper presents the design of control of side-jet & dynamic fins compound.The main contributions of this paper are as follows.Firstly,the mathematical models of interceptor missile with side-jet & dynamic fins compound were constituted.Calcutate the aerodynamic parameters of missile through the software of aerodynamic and interpolated it.The aerodynamic parameters of the missile flight process are given and the interpolation is fitted Through Dat Com.Then the required coordinate system is given.Two new coordinate systems are defined for the spin of the projectile,and the conversion relation between the coordinate systems is given.The dynamic equation of the missile rotation motion is established under the quasi projectile system,and the simulation verification of the uncontrolled missile is carried out.The correctness and stability of the missile model are verified,which lays a foundation for the design of the later paper.Secondly,the control methord was presented for the interceptor missile with the control of side-jet & dynamic fins compound.First of all,based on the engineering practice,based on the classical control theory,the approximate decoupling of the equation is realized,and the direct / gas compound control law is designed.The stability of the system is analyzed and the simulation verification is given.Then,the direct / gas complex motion is designed based on the inverse system theory without considering these assumptions.The state inversion control law is designed,and the extended state observer is designed for the sensitivity of the dynamic inverse control to the model.The simulation results verify the rationality of the design of the control system.Thirdly,the ignition strategy of pulse thrusters was presented for spinning interceptor missile with side-jet & dynamic fins compound.Establish the mathematical model of pulse thrusters.Aiming at the shortage of the traditional ignition strategy,the ignition strategy is redesigned considering the influence of the direct force component of the projectile spin.The ignition strategy based on the instruction decomposition and the error compensation superposition ignition strategy are proposed,and the simulation is carried out to verify the ignition strategy.The last,the guidance and control system simulation of interceptor missile with side-jet & dynamic fins compound.First and foremost,in order to ensure the interception accuracy,a guidance law based on the eye angle acceleration based on the projectile is proposed by the tracking differentiator in the auto disturbance rejection theory,and then the interception simulation is carried out for the reentry ballistic missile,the snake type maneuvering reentry ballistic missile,the hypersonic vehicle and the large mobile cruise missile,and the two control rules are given.The law is compared and analyzed.Considering the constant drift of the inertial navigation system and the measurement error of the seeker,Gauss white noise is added to the two components.6 DOF simulation of the system,verify the robustness of the guidance and control system.