Structural Dynamics Analysis And Control Strategy Research Of Kinetic Killed Vehicle

Along with development of advanced martial aerospace technology,the threat from outer space toward China is enhanced increasingly.Development of a new effective antispace weapon system plays the key role in national tactic aerial and space defense.The land-based kinetic anti-satellite missile is one kind of advanced space defense weapon at present.Kinetic Killed Vehicle(KKV)is launched and released as its warhead at prescribed space location,flights independently to enemy satellite under itself guidance and control systems,and strikes the satellite by nearly zero undershoot distance.As a controlled object,KKV is actually a continuum elastic body.The structural dynamics characteristic will effect with guidance control system reciprocally in various problems.The effect is very important to KKV with very high guidance and control precision.Structural dynamics and control technology of KKV is urgently foreland problem of the missile engineering development.The research emphases were putted on the structural dynamics and control technology of KKV.The detail works of the dissertation are as follows:1)A new method of structural dynamics finite element(FE)modeling for KKV which based on finite element model validation technology was built.Because the complicated structure,asymmetry mass and stiffness,the dynamic characteristic of KKV was hard to get by traditional modeling method.Detailed research on FE mode validation was carried out from connotation,theory and method.A new FE model validation method and programs were raised for engineering complicated structures.Then the methods were applied to structural dynamics computational modeling of KKV.The dynamic characteristic prediction shows the method can improve the precision and reliability of complicated KKV structural dynamics modeling.2)The nonlinear mathematical model of KKV in end-guidance flight phase was established.The following equations were included: translational dynamic differential equations,attitude dynamic equations,elastic mode coordinate equations etc.The difference in measuring equations of sensors,force and moments equations of dynamics mathematical model because of elastic vibration was considered.Interaction and Coupling characteristic between structure and control system of KKV were analyzed recur to the mathematical model.3)Simulation and design method of structural dynamics/control problems was built.Firstly,coupling system of attitude stability and control of KKV considered elastic vibration was simulation by using linearization method.The results show that elastic vibration has obviously effect on attitude control system.Secondly,a Virtual Reality emulation method based on ADAMS/Simulink was developed to simulate the dynamic process of floating test of KKV.Thirdly,the relation of vibration and fixed seeker head measuring was studied.Dynamics environment prediction technology was applied to study the effect of vibration on guidance performance.The conclusion is that structural stiffness asymmetry and insufficiency of locally setting stiffness are the primary factors that affect guidance measuring errors.The flight experiments results proved the conclusion.Advanced theory and methods are discussed and applied as artifice to solve problems.The application of production shows that the theory and methods in the dissertation have a certain extent engineering meaning and value to new missile developments.