舰载机及其尾钩的动力学建模与分析
2024,46(5):131-140
丁智深
海军工程大学 电磁能技术全国重点实验室, 湖北 武汉 430033，djq3467@163.com,ydoyb@163.com
欧阳斌
海军工程大学 电磁能技术全国重点实验室, 湖北 武汉 430033，djq3467@163.com,ydoyb@163.com
刘勇
海军工程大学 电磁能技术全国重点实验室, 湖北 武汉 430033
海军工程大学 电磁能技术全国重点实验室, 湖北 武汉 430033，djq3467@163.com,ydoyb@163.com
欧阳斌
海军工程大学 电磁能技术全国重点实验室, 湖北 武汉 430033，djq3467@163.com,ydoyb@163.com
刘勇
海军工程大学 电磁能技术全国重点实验室, 湖北 武汉 430033
摘要：
为了研究舰载机尾钩的动力学特性对阻拦结果的影响,建立了舰载机的平面运动刚体动力学模型和考虑尾钩纵向缓冲作用的尾钩空间运动刚体动力学模型。使用拉格朗日第一类方程建立了舰载机及其尾钩之间的转动副模型,进而构建了舰载机及其尾钩组成的系统动力学模型,将该模型与阻拦装置的系统模型联合组成了完整的阻拦动态仿真模型。开展了飞机的阻拦试验,并将试验结果与仿真结果进行对比分析,结果验证了舰载机及其尾钩动力学模型的有效性和准确性,揭示了尾钩特性对舰载机阻拦过载的重要影响。
为了研究舰载机尾钩的动力学特性对阻拦结果的影响,建立了舰载机的平面运动刚体动力学模型和考虑尾钩纵向缓冲作用的尾钩空间运动刚体动力学模型。使用拉格朗日第一类方程建立了舰载机及其尾钩之间的转动副模型,进而构建了舰载机及其尾钩组成的系统动力学模型,将该模型与阻拦装置的系统模型联合组成了完整的阻拦动态仿真模型。开展了飞机的阻拦试验,并将试验结果与仿真结果进行对比分析,结果验证了舰载机及其尾钩动力学模型的有效性和准确性,揭示了尾钩特性对舰载机阻拦过载的重要影响。
基金项目：
卓越青年科学基金资助项目(2021-JCJQ-ZQ-004)
卓越青年科学基金资助项目(2021-JCJQ-ZQ-004)
Dynamic modeling and analysis of carrier-based aircraft and arresting hook
DING Zhishen
National Key Laboratory of Electromagnetic Energy, Naval University of Engineering, Wuhan 430033, China,djq3467@163.com,ydoyb@163.com
OUYANG Bin
National Key Laboratory of Electromagnetic Energy, Naval University of Engineering, Wuhan 430033, China,djq3467@163.com,ydoyb@163.com
LIU Yong
National Key Laboratory of Electromagnetic Energy, Naval University of Engineering, Wuhan 430033, China
National Key Laboratory of Electromagnetic Energy, Naval University of Engineering, Wuhan 430033, China,djq3467@163.com,ydoyb@163.com
OUYANG Bin
National Key Laboratory of Electromagnetic Energy, Naval University of Engineering, Wuhan 430033, China,djq3467@163.com,ydoyb@163.com
LIU Yong
National Key Laboratory of Electromagnetic Energy, Naval University of Engineering, Wuhan 430033, China
Abstract：
To study the influence of dynamic characteristics of the arresting hook of carrier-based aircraft on arresting results, the rigid body dynamics model of the plane motion carrier-based aircraft was established. The rigid body dynamics model of the spatial motion arresting hook was established considering the effect of longitudinal cushioning of the arresting hook. Lagrange′s equation of first kind was employed to establish the revolute joint model of the carrier-based aircraft and the arresting hook, and then the dynamics models of the system consists of the carrier-based aircraft and its arresting hook were established. The models were united with dynamics model of arresting gear to form the complete blocking dynamic simulation model. The experiment of the arresting process of aircraft was carried out. The experiment results and simulation results of the arresting process were compared and analyzed. The results demonstrate the effectiveness and accuracy of the dynamics model of the carrier-based aircraft and arresting hook, and reveal the significant influence of characteristics of the arresting hook on arresting overload.
To study the influence of dynamic characteristics of the arresting hook of carrier-based aircraft on arresting results, the rigid body dynamics model of the plane motion carrier-based aircraft was established. The rigid body dynamics model of the spatial motion arresting hook was established considering the effect of longitudinal cushioning of the arresting hook. Lagrange′s equation of first kind was employed to establish the revolute joint model of the carrier-based aircraft and the arresting hook, and then the dynamics models of the system consists of the carrier-based aircraft and its arresting hook were established. The models were united with dynamics model of arresting gear to form the complete blocking dynamic simulation model. The experiment of the arresting process of aircraft was carried out. The experiment results and simulation results of the arresting process were compared and analyzed. The results demonstrate the effectiveness and accuracy of the dynamics model of the carrier-based aircraft and arresting hook, and reveal the significant influence of characteristics of the arresting hook on arresting overload.
收稿日期：
2022-05-06
2022-05-06
