摘要
为研究舰载机前轮拖拽弹射起飞技术,基于多体系统动力学理论,建立模拟舰载机前起落架突伸的4自由度多体动力学模型,推导出系统的动力学微分方程.利用该模型,用数值方法仿真舰载机前起落架的突伸运动,得出突伸过程中舰载机的重心位置、俯仰角和前起落架空气弹簧力等参数的动态响应特性.仿真结果可为舰载机及其起落架设计提供参考.
To study the nose wheel-towing catapult launching technology of carrier-based aircraft,a multi-body dynamics model with four degrees of freedom is built according to multi-body system dynamics theory,which is used to simulate the nose landing gear fast-extension of a carrier-based aircraft,and the dynamic differential equation are derived.By using the model,numerical method is used to obtain the dynamic response characteristics of the parameters such as center of gravity position,pitch angle of carrier-based aircraft and air spring force of nose landing gear in the fast-extension process.The simulation results can provide some references for the design of carrier-based aircraft and its landing gear.
出处
《计算机辅助工程》
2010年第4期55-57,共3页
Computer Aided Engineering
关键词
舰载机
前起落架
突伸
动力学
carrier-based aircraft
nose landing gear
fast-extension
dynamics
