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| 舰载机前起落架突伸动力学分析及试验方法 | |
| 引用本文： | 魏小辉,刘成龙,聂宏,张明,尹乔之.舰载机前起落架突伸动力学分析及试验方法[J].航空学报,2013,34(6):1363-1369. |
| 作者姓名： | 魏小辉 刘成龙 聂宏 张明 尹乔之 |
| 作者单位： | 1. 南京航空航天大学机械结构力学及控制国家重点实验室,江苏南京 210016;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,江苏南京 210016 2. 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,江苏南京,210016 |
| 基金项目： | 国家自然科学基金，江苏高校优势学科建设工程资助项目，National Natural Science Foundation of China，Project Funded by the Priority Academic Program Development of Jiangsu Higher Education Institutions |
| 摘 要： | 为了了解舰载机前起落架突伸试验与实际突伸过程的当量关系,本文以某舰载机为研究对象,建立了全机弹射起飞动力学模型,进行了全机弹射起飞动力学分析,得到了前起落架突伸过程中的动态响应。提出了基于当量质量的前起落架突伸动力学试验方法,设计了试验方案,建立了前起落架突伸动力学试验分析模型,进行了突伸动力学分析。进而依据全机突伸动力学分析结果,对基于当量质量的前起落架突伸动力学试验中相关参数的选取进行了探讨研究,结果表明:当突伸当量质量系数取0.8时,突伸动力学响应特性与全机弹射起飞突伸过程的动态响应结果比较吻合。 |
| 关 键 词： | 舰载机 弹射起飞 前起落架 当量质量 突伸试验 |
Dynamics and Test Method of Carrier-based Aircraft Nose Landing Gear Sudden Extension |
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| WEI Xiaohui , LIU Chenglong , NIE Hong , ZHANG Ming , YIN Qiaozhi.Dynamics and Test Method of Carrier-based Aircraft Nose Landing Gear Sudden Extension[J].Acta Aeronautica et Astronautica Sinica,2013,34(6):1363-1369. | |
| Authors: | WEI Xiaohui LIU Chenglong NIE Hong ZHANG Ming YIN Qiaozhi |
| Institution: | 1. State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China; 2. Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicles, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China |
| Abstract: | In order to understand the equivalent relationship of a landing gear's sudden-extension test and the real sudden-extension process of a carrier-based aircraft, a dynamics model of a certain carrier-based aircraft catapult-assisted takeoff process is established. The catapult-assisted takeoff dynamics is simulated and the nose landing gears dynamic response to the sudden-extension process is obtained. A test method is introduced to study the nose landing gear's sudden extension based on equivalent mass. Accordingly, a test program is presented for independent nose landing gear sudden-extension analysis. With simulated results of the models introduced above, the value range of relevant test parameters is studied. It is shown that the independent nose landing gear sudden-extension dynamic response is relatively consistent with the full-aircraft catapult-assisted takeoff dynamics when the equivalent mass coefficient is equal to 0.8. |
| Keywords: | carrier-based aircraft catapult-assisted takeoff nose landing gear equivalent mass sudden-extension test |
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