导弹电磁弹射器有限元仿真及分析

Finite Element Simulation and Analysis of Missile Electromagnetic Launcher

为克服导弹电磁弹射器超大推力与装备质量、体积限制的矛盾,同时降低能量供应和高功率电源控制等的难度,提出一种基于双边有槽直线感应电机的多驱动导弹电磁弹射器设计方案。根据作战实际要求,通过导弹弹射运动学分析,确定弹射器基本性能要求。进行弹射器驱动电机初步设计,通过等值电路分析和迭代计算,得出初始结构性能参数。考虑材质、维修性和制造工艺等要求,建立驱动电机ANSYS Maxwell二维有限元仿真模型,通过参数化仿真方法,研究电机处于稳态时初级结构、次级尺寸和电源等对性能的影响,并根据仿真结果进一步优化电机结构参数。通过瞬态仿真对电机性能进行校验,结果显示:优化后的电机性能得到明显提升,输出推力峰值从500kN提升到700kN左右,推力均值提升到500kN,基本满足设计要求。

In order to resolve the contradiction between the super thrust of missile electromagnetic launcher and the limitation of equipment mass and volume and meanwhile reduce the difficulty of energy supply and high power supply control,a design scheme of multi-drive missile electromagnetic launcher based on bilateral slotted linear induction motor is proposed.According to the actual operational requirements,the basic performance requirements of the catapult are determined through the analysis of missile ejection kinematics.The preliminary design of the catapult drive motor is implemented,and the initial structural performance parameters are obtained through equivalent circuit analysis and iterative calculation.By taking the requirements of material,maintainability and manufacturing process into account,the ANSYS Maxwell two-dimensional finite element simulation model of the drive motor is established.The influence of the primary structure,secondary size and power supply on the performance of the motor in steady state is studied by using parametric simulation method,and the structural parameters of the motor are further optimized according to the simulation results.Through the transient simulation,the performance of the motor is verified.The results show that the performance of the optimized motor is significantly improved,the peak value of thrust is increased from 500kN to 700kN,and the average thrust is increased to 500kN,which basically meets the design requirements.