| As the most important guidance weapons,missile has become the protagonist of the modern battle field and it is an important direction of development of world military power.Missile control system is the core part of the missile which plays a very important role in hitting the target precisely and in the missile flight control stable.However,with the increasing range,the hit precision demand and increasingly complex system structure makes the traditional control methods often can not complete the task of missile control,studying and designing a new missile controller with rapidity and robustness has become the focus of current research.According to the features of STT(Side-To-Turn)missile control system,the paper puts forward a method based on the sliding mode variable structure control theory which has robustness for external disturbance and parameter perturbation and uncertain system problem,and simulation analysis and verification of design system at the same time.This paper will mainly completed work:Firstly,introduces the research background,purpose and significance,for the main design method of the missile control system development status at home and abroad are reviewed.Secondly,establish the mathematical model of STT missile.Introduces the various coordinate and the relationship of mutual conversion between the coordinates,analysis the force and moment in the body coordinate system of the missile meanwhile.According to the characteristics of STT control for missile,establish the mathematical model of STT missile under appropriate conditions.Then,the autopilot design of STT missile.First of all,according to the STT missile autopilot motion model,using the theory of classical control design method of three channel,through the simulation knows when the parameter perturbation is larger the control performance of the controller is not ideal.Then using the sliding mode variable structure control theory has this feature invariance of the internal parameter perturbation and external disturbance,to design the sliding mode variable structure autopilot.At the same time,by using the method of exponential reaching law and the quasi sliding mode are combined to weaken the chattering.Through the observation and contrast of different parameter perturbation simulation curve percentage,to verify the feasibility and superiority of thedesign.Finally,STT missile trajectory simulation.Combined with the control system and the guidance law to build a three-channel co-simulation for STT missile autopilot.With the help of Matlab tool of Simulink software to build the simulation model,and then complete the six degree of freedom trajectory simulation of the missile guidance system.While the use of LabVIEW graphical programming software design visualization trajectory simulation interface,trajectory simulation curve observed by way of human-computer interaction and verify the correctness of the simulation. |
