| With the enhancement of missile maneuver ability,the requirements of the missile interception technology is higher.The traditional pneumatic control method can not meet the requirements of the interceptor,so the control method based on the direct lateral force is more widely used.Therefore,we do a research on compound control method taking the interception projectile with direct lateral force and aerodynamic compound control as a object in this paper.Mainly include the following aspects:(1)The ignition-logic of the attitude control engine group is designed.Because of its non-reusable features,it must be designed a reasonable ignition logic for the attitude control engine group,to ensure the efficiency and accuracy of the direct force execution.With the method of vector decomposition,we designed the ignition-logic in this paper,and realized the better efficiency of the attitude control engine group.(2)The design of the compound control system based on the sliding mode variable structure(SMVS)control,parallel control and hybrid control method.SMVS control is realized by using lateral force control on the reaching stage,and the aerodynamic control is used on the sliding motion stage.The method of fuzzy control is used to realize the parallel control.According to the distance of the projectile and the size of the overload error,the allocation rules are established.Then,the overload instructions are assigned to direct force and aerodynamic control loops.For the hybrid control,the aerodynamic control loop is used as the inner loop,then the design of the direct force control loop is carried out.Finally,the numerical simulation and verification of these control methods are carried out.(3)The design of simulation system based on DSP controller.The simulation system is build between Matlab and DSP,which communicate through the machine serial communication.We implemented the control method in DSP and run the missile dynamics model program in the simulator. |
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