摘要
基于多体动力软件LMS Virtual.lab建立了某型飞机弹射起飞的刚柔耦合虚拟样机模型,使用一对点和柔性曲线约束副来模拟活塞杆和外筒的运动,分析了目标飞机的弹射起飞安全性及弹射过程中飞机的动力学响应。仿真表明:目标飞机的舰首下沉量能够满求,可以安全起飞。纵摇和垂荡的耦合会使飞机舰首下沉量增大;分离时的动态响应情况与分离载荷的大小和衰减速度有关。
A flex-rigid virtual prototype model was built in LMS Virtual. lab to mmulate the catapult launch process of carrier-based aircraft. A pair of flex point curve joints were used to simu late the movements of the piston rod and the outer tube. The catapult security and dynamics response of the target aircraft were analyzed. Simulation results show that：the target aircraft meets the criteria requirements,and can take off safely;the coupling of pitch and heave will increase subsidence;the dy namic resr）onse caused by separation is related to the size and decay rate of separate load.
出处
《中国机械工程》
EI
CAS
CSCD
北大核心
2013年第4期522-527,共6页
China Mechanical Engineering
基金
国家自然科学基金资助项目(51075203)
关键词
舰载飞机
航母运动
弹射起飞
柔性起落架
动力学响应
carrier-based aircraft
deck motion
catapult takeoff
Flexible landing-gear
dynamics response
