舰载机弹射起飞动力学虚拟试验研究

中国机械工程 ›› 2013, Vol. 24 ›› Issue (4): 522-527.

舰载机弹射起飞动力学虚拟试验研究

隋成国;许锋;聂宏

南京航空航天大学飞行器先进设计技术国防重点学科实验室,南京,210016

出版日期:2013-02-25 发布日期:2013-02-28
基金资助:
国家自然科学基金资助项目(51075203)
National Natural Science Foundation of China（No. 51075203）

Research on Dynamics during Catapult Takeoff of Carrier-based Aircraft

Sui Chengguo;Xu Feng;Nie Hong

Key Laboratory of Fundamental Science for National Defense-advanced Design Technology of Flight Vehicle,Nanjing University of Aeronautics & Astronautics,Nanjing,210016

Online:2013-02-25 Published:2013-02-28
Supported by:
National Natural Science Foundation of China（No. 51075203）

摘要/Abstract

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。


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

Abstract:

A flex-rigid virtual prototype model was built in LMS Virtual. lab to simulate the catapult launch process of carrier-based aircraft.A pair of flex point curve joints were used to simulate 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 dynamic response caused by separation is related to the size and decay rate of separate load. 

Key words: carrier-based aircraft, deck motion, catapult takeoff, Flexible landing-gear, dynamics response

中图分类号:

隋成国, 许锋, 聂宏. 舰载机弹射起飞动力学虚拟试验研究[J]. 中国机械工程, 2013, 24(4): 522-527.

DUO Cheng-Guo, HU Feng, NIE Hong. Research on Dynamics during Catapult Takeoff of Carrier-based Aircraft[J]. China Mechanical Engineering, 2013, 24(4): 522-527.

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