Optimization Study, Based On Dynamic Constraints Of The Ejection Institutions

The airborne ejection system or missile is the key part of the modern missile weapon system. With the implementation of transonic mechanization, transonic cruise, invisibility and other performances of the fourth generation fighter plane and the use of the new generation airborne missile, it demands that the airborne ejection system should be matched with the fighter plane performance and the development of weapon system. To meet with the requirement of modern air battles, the research of the airborne ejection device has been developed with a lot of human talents and financial investment in China and other countries. In this thesis, the optimize analysis of ejection mechanism is applied to lessen the ejection mechanism weight for meeting the demand of research, design and manufacture of product. The new ejection mechanism model is lighter and more reasonable than the former one. The research provides further reference for the future design study of the airborne ejection device of missile.Firstly, Dynamics simulation and mode analysis of ejection mechanism are performed in this thesis. Vertical velocity of missile and frequency of ejection mechanism are obtained after the dynamics simulation and mode analysis. Then, in one hand, the results offer the restriction for optimization analysis. Another hand, they are the basis of the comparison between the two ejection mechanisms in performance. Secondly, the object of ejection mechanism optimization is weight, restriction condition is the vertical velocity of missile and dimensions of components in ejection mechanism are design variables. In third steps, a new ejection mechanism model with less weight is acquired after the optimization analysis.Finally, the intensity, dynamics simulation and mode of the new ejection mechanism are analyzed for the optimized ejection mechanisms in the thesis. The new ejection mechanism meets with the mechanics capability of material in the intensity analysis. The missile ejection separation velocity meets with the demand of experimentation. These researches are proved the new ejection mechanism applicable. Besides, the kinetic and dynamic calculation of new ejection mechanism is performed in software ADAMS during the whole ejection process. The data from the former analysis are analyzed correspondingly to indicate displacement in wholeejection process and ejection velocity, ejection separation time and ejection acceleration under different ejection gas pressure. And the first rank frequencies of the new ejection mechanism is gotten in the mode analyze. The results are compared with the first rank frequencies of the former ejection mechanism. This can be the proof for evaluating how to reduce the possibility of resonance between the optimized ejection mechanism and fighter plane.The analysis method in this thesis can easily ensure the ejection parameters of ejection mechanism, and these eject parameters infect the capability of missile ejection. The research can reduce the times of design and experiment of ejection mechanism. The calculation, analysis and results are instructive to the airborne ejection device of missile design and engineering application. These can help the future research in theory and application of the airborne ejection device of missile.