机载导弹发射动力学建模与虚拟样机仿真

Launching Dynamics Modeling of Guided Aircraft Missile and Virtual Prototype Simulation

基于导弹在发射导轨上的运动特征,以"捕食者"机载导弹发射系统为物理原形,建立了发射动力学和运动学模型,并应用MSC.ADAMS软件建立导轨发射条件下弹-架系统动力学模型,进行了动力学仿真试验,研究结果表明,理论计算值和仿真结果相符,得到了发射过程中导弹的位置、速度和加速度随时间的变化关系以及导弹与载机分离时对载机位置、速度和加速度的影响规律.

Based on the physical model of ＂Predator＂ UAV airborne missile launching system, the launch dynamics and kinematics models were established. By employing MSC. ADAMS software, the dynamic modeling the missile and launcher system was fulfilled for simulation. The simulation test of rigid body dynamics was implemented under different slide-way launching conditions. The results show that the simulation data are in accordance with the values of theoretical calculation. acceleration are achieved The time-dependent transformation of missile position, velocity and during the launching process as well as the separating process of missile from the plane.