计及弹射滑车质量的某舰载无人机弹射动态响应分析

doi:10.7527/S1000-6893.2018.22237

固体力学与飞行器总体设计

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计及弹射滑车质量的某舰载无人机弹射动态响应分析

房兴波¹, 聂宏^1,2, 张钊¹, 魏小辉^1,2, 张明¹

1. 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;
2. 南京航空航天大学机械结构力学及控制国家重点实验室, 南京 210016

收稿日期:2018-04-23 修回日期:2018-07-09 出版日期:2018-12-15 发布日期:2018-10-10
通讯作者: 聂宏 E-mail:hnie@nuaa.edu.cn
基金资助:
国家自然科学基金（11372129）；机械结构力学及控制国家重点实验室（南京航空航天大学）自主研究课题（MCMS-0217G01）；中央高校基本科研业务费专项资金（NP2017401）

Dynamic response analysis on carrier-based UAV considering catapult shuttle mass

FANG Xingbo¹, NIE Hong^1,2, ZHANG Zhao¹, WEI Xiaohui^1,2, ZHANG Ming¹

1. Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received:2018-04-23 Revised:2018-07-09 Online:2018-12-15 Published:2018-10-10
Supported by:
National Natural Science Foundation of China (11372129); The Research Fund of State Key Laboratory of Mechanics and Control of Mechanical Structures (Nanjing University of Aeronautics and Astronautics) (MCMS-0271G01); The Fundamental Research Funds for the Central Universities (NP2017401)

摘要/Abstract

摘要： 舰载无人机是未来海上作战的关键装备，其弹射动态性能严重影响起飞安全。弹射滑车与舰载机起落架弹射杆相连，在牵制杆突卸弹射滑跑过程中共同组成一个耦合动力学系统。目前，国内外尚缺乏对此耦合系统动力学特性的研究。以由某无人机改造的弹射型为研究对象，建立了包含弹射滑车质量的弹射动力学模型，并开展了拖拽弹射过程的动态响应分析，结果表明：弹射滑车的惯性力会沿着弹射杆传递到前起落架上，拖拽弹射过程中前起落架载荷波动幅度增大，前起落架撑杆、弹射杆以及前轮垂向载荷峰值分别增加了23.4%、21.6%和14.0%；前起落架缓冲器压缩量变化范围扩大了30.4%；前起落架纵向和垂向的载荷振荡频率分别从90.9 Hz和5.2 Hz降到26.3 Hz和4.4 Hz。

关键词: 舰载无人机, 拖拽弹射, 弹射滑车, 前起落架, 动态响应

Abstract: Carrier-based UAV is a key asset in the future marine warfare, and its catapult dynamic performance plays an essential role in takeoff security. The catapult shuttle connects to the landing gear, forming a coupled dynamic system together during the catapult progress. At present, the research on such a coupled dynamic system is rare both at home and abroad. Taking a catapulting type of UAV as the research subject, a catapult dynamic system including shuttle mass has been constructed, and the dynamic response after sudden discharge of the holdback load has been analyzed. Results denote that inertia force of catapult shuttle is exerted on the nose landing gear along the catapult link. The nose landing gear load massively fluctuates during catapult dragging. Vertical load of nose landing gear strut, catapult link and nose wheel increase by 23.4%, 21.6%, and 14.0%, respectively. The range of the nose landing gear stroke increases by 30.4%. Moreover, the fluctuation frequency of the longitudinal and vertical loads of the nose landing gear decreases from 90.9 Hz and 5.2 Hz to 26.3 Hz and 4.4 Hz.

Key words: carrier-based UAV, tow catapulting, catapult shuttle, nose landing gear, dynamic response

中图分类号:

V226

房兴波, 聂宏, 张钊, 魏小辉, 张明. 计及弹射滑车质量的某舰载无人机弹射动态响应分析[J]. 航空学报, 2018, 39(12): 222237-222237.

FANG Xingbo, NIE Hong, ZHANG Zhao, WEI Xiaohui, ZHANG Ming. Dynamic response analysis on carrier-based UAV considering catapult shuttle mass[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2018, 39(12): 222237-222237.

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E-mail：hkxb@buaa.edu.cn

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计及弹射滑车质量的某舰载无人机弹射动态响应分析

Dynamic response analysis on carrier-based UAV considering catapult shuttle mass

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