舰载机弹射起飞前起落架牵制载荷突卸动力学分析

doi:CNKI:11-1929/V.20110517.1516.003

固体力学与飞行器总体设计

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舰载机弹射起飞前起落架牵制载荷突卸动力学分析

于浩, 聂宏, 魏小辉

南京航空航天大学航空宇航学院, 江苏南京 210016

收稿日期:2010-10-28 修回日期:2010-12-20 出版日期:2011-08-25 发布日期:2011-08-19
通讯作者: 聂宏,Tel.: 025-84892411 E-mail: hnie@nuaa.edu.cn E-mail:hnie@nuaa.edu.cn
作者简介:于浩(1982-) 男,博士研究生。主要研究方向:舰载机弹射起飞动力学。 Tel: 025-84892384 E-mail: yuhao@nuaa.edu.cn; 聂宏(1960-) 男,博士,教授,博士生导师。主要研究方向:飞行器起落装置设计、结构疲劳与断裂、飞机起落架自适应控制技术等。 Tel: 025-84892411 E-mail: hnie@nuaa.edu.cn; 魏小辉(1978-) 男,博士,副教授,硕士生导师。主要研究方向:飞行器起落装置设计与分析,飞行器CAD/CAE与飞行仿真。 Tel: 025-84892411 E-mail: wei_xiaohui@nuaa.edu.cn
基金资助:
南京航空航天大学基本科研业务费专项科研项目(NS2010023)

Analysis on the Dynamic Characteristics of Carrier-based Aircraft Nose Landing Gear with Sudden Holdback Load Discharge

YU Hao, NIE Hong, WEI Xiaohui

College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received:2010-10-28 Revised:2010-12-20 Online:2011-08-25 Published:2011-08-19

摘要/Abstract

摘要： 舰载机弹射起飞过程中,由于牵制载荷突卸而产生的前起落架沿航向的快速振动会给机体结构和设备都带来严重的疲劳问题,为研究该振动现象并提出解决方案,建立了舰载机弹射起飞动力学模型,分析计算了前起落架的受载情况,并详细论述其动力学成因,推导了消除前起落架振动现象的充分必要条件。研究结果表明:牵制载荷沿下扭力臂轴向的载荷分量所造成的缓冲器活塞杆的向后弯曲是导致牵制载荷突卸后前起落架振动的主要原因;牵制载荷突卸后,起落架的前后振动导致起落架与机身铰接处的载荷快速、大幅的振荡,对机体结构以及机载设备的寿命和使用安全都会产生不利影响;牵制杆的长度直接影响牵制载荷沿下扭力臂轴向的载荷分量,降低该载荷分量可以有效地解决前起落架由于牵制载荷突卸所带来的振动问题。

关键词: 舰载机, 弹射起飞, 前起落架, 载荷突卸, 牵制载荷

Abstract: The vibration of a nose landing gear caused by the sudden discharge of holdback load during the catapult launch of a carrier-based aircraft could bring serious fatigue both to the structure of the launch and the airborne equipment. To investigate the vibration and seek a solution, a dynamic model of the catapult launch is established. The load of the nose landing gear is calculated, while the kinetics and the way to deal with the phenomenon is also discussed in detail. From the catapult launch calculation, three important conclusions are obtained: during the tension stage, there is a long stroke and aft bending of the nose landing gear; once the holdback load suddenly discharges, the landing gear strut extends and springs forward rapidly; the fore-aft vibration of the nose landing gear produces a rapid and drastic load change at the joint of the gear and the fuselage. This vibration load has an adverse effect on the life and safety of the structure and the equipment of the aircraft. The length of the holdback bar influences the load along the lower torque link directly, and reducing this load has an obvious effect on the reduction of the vibration after a sudden discharge of the holdback load.

Key words: carrier-based aircraft, catapult launch, nose landing gear, sudden load discharge, holdback load

中图分类号:

V226

于浩, 聂宏, 魏小辉. 舰载机弹射起飞前起落架牵制载荷突卸动力学分析[J]. 航空学报, 2011, 32(8): 1435-1444.

YU Hao, NIE Hong, WEI Xiaohui. Analysis on the Dynamic Characteristics of Carrier-based Aircraft Nose Landing Gear with Sudden Holdback Load Discharge[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2011, 32(8): 1435-1444.

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E-mail：hkxb@buaa.edu.cn

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舰载机弹射起飞前起落架牵制载荷突卸动力学分析

Analysis on the Dynamic Characteristics of Carrier-based Aircraft Nose Landing Gear with Sudden Holdback Load Discharge

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