Research On Launching Attitude Of Ballistic Missile Unsupported Random Cold Launching

Missile launching technology is an important part of missile technology,which has a crucial influence on missile survivability and operational efficiency.In order to improve the survivability of missile weapons,it has become an important development direction of land-based mobile missiles by using mechanical transport and unsupported random launching technology.However,it brings greater changes of the attitude angle of uncontrolled phase during ejection launching and it is necessary to take in-depth research and preventive measures.Therefore,in this paper,the research on the dynamic modeling,simulation analysis and test verification during ejection launching is carried out based on the research of ballistic missile mechanical transport and unsupported random launching technology.The following results are obtained:Considering the change of the launcher support form and the distribution mode of launching load during mechanical transport and unsupported random launching,and on the basis of analyzing the force and disturbance in the missile launching process,the dynamics simulation software ADAMS is used to build a virtual prototype simulation model of the ejection launching,analysis the process of missile ejecting from the tube.We can predict the attitude of the missile and analyze attitude changes of uncontrolled phase during ejection launching.In order to accurately analyze the attitude change of the launcher when launching,the parameters of the launcher and their coupling relation must be analyzed in detail.Using the established above ADAMS virtual prototype simulation model and aiming at the variation of ejection pressure in the launcher tube with larger affecting parameters of the missile attitude when ejecting from the tube,the frame and vertical cylinder stiffness,parameters of hydraulic vehicle leg and rear cross member stiffness we carried out sensitivity analysis,found out the main factors which influence the attitude of the missile,and laid the foundation for the necessary preventive measures and optimization in later work.Finally,in order to validate the simulation result of the virtual prototype model,a practical system is tested.We compared and analyzed the simulation results and test results of the vertical cylinder pressure and the cylinder pressure of the leg,which provides a reference for improving the simulation model and optimizing the design of the launch system.