Missile Cabin Installation Structure Optimization And Power-flow Isolation Design

With the development of modern missiles, missile structural mass requiressmaller, device integration requires higher, and assembly requires more convenient.In order to improve the operational performance and the range of the missile, it isneeded to improve the delivery efficiency of the missile.The integrated design ofthe missile cabin structure can improve the delivery efficiency of cabin structure,which carrys as much as possible to save the space and weight for the engine andwarhead. Missile system consists of integrated mechatronic structure and functionmodules. The anti-vibration ability of function module is limited, and it issusceptible for function module to fail under the influence of vibration and shockduring the work process. Therefore, in order to avoid functional modules’s failurefrom external environmental factors, to adapt a variety of operating environmentsof vibration and shock, it has important engineering significance to the analyze thestatics and dynamics of the structure and to design the isolator of the integrationmounting structure.In this paper, for the issues of missile cabin integration structure design, thestatic optimization design of the cabin mounting structure and power-flow isolatordesign is a major consideration, and the main specific contents are as follows:The cabin static structure optimization is studied. Firstly, plate part on thecabin structure is topology and shape optimized based on ANSYS Workbench. Theresult obtained is analyzed and shape fitted, and a comparative analysis betweenthe structures before and after the optimization from the viewpoint of stiffnessindicates that the effect of topology and shape optimization is significant.Secondly, the size of plate part on the cabin structure is multi-targets optimized.Geometric model is established for static analysis by ANSYS, and the parametricvariables are optimized. Based on this, the design variables and the strength andstiffness constraints are determined, the lightest mass optimization objective issettled, the experimental results are updated, after which the design is optimizedand the influence of variables for each target is analyzed. A comparative analysisbetween the structures before and after the optimization from the viewpoint ofstiffness indicates that the effect of multi-targets optimization is significant.For the issue of the isolator design on the integrated mounting structure, onthe base of evaluation indicator for each isolator design, an evaluation indicator ofentire-frequency power-flow transmissibility is proposed, and its applicability forthe missile dynamic environment is described. The isolator re-designed with theevaluation indicator of entire-frequency power-flow transmissibility, and the optimal solution is given under the new evaluation system. Isolation system issimulated and analyzed based on ANSYS Workbench and the principle ofpower-flow. Further more, the effection of mass, stiffness and damping of missilebody on the isolation respectively is analyzed.Finally, according to the proposed design method, metal rubber isolator islinearized designed and the effects are verified.