舰载机前起落架缓冲性能参数敏感性研究  

Parameter sensitivity of cushioning performance of carrier aircraftnose landing gear

作　　者：张飞[1] 白春玉[1] 陈熠 杨正权[1] 王计真 ZHANG Fei;BAI Chun-yu;CHEN Yi;YANG Zheng-quan;WANG Ji-zhen(Aviation Key Laboratory of Science and Technology on Structure Impact Dynamics,Aircraft Strength Research Institute of China,Xi′an 710065,China)

机构地区：[1]中国飞机强度研究所结构冲击动力学航空科技重点实验室,陕西西安710065

出　　处：《振动工程学报》2024年第3期505-511,共7页Journal of Vibration Engineering

摘　　要：为了同时满足缓冲和突伸性能,舰载机前起落架常采用双腔缓冲器设计。以某型机前起落架为研究对象,建立前起落架缓冲性能分析动力学模型,并将仿真计算结果与试验结果进行验证对比,验证理论模型的有效性和正确性。对缓冲器高、低压腔初始压力以及体积占比进行参数敏感性分析。结果表明,高、低压腔初始充填压力和体积占比对起落架缓冲性能的影响有别于它们对突伸性能的影响,所以对舰载机前起落架缓冲器的设计需不断优化,同时兼顾缓冲和突伸性能。In order to satisfy both cushioning and fast-extension performances,the carrier aircraft nose landing gear often adopts the dual-chamber buffer design.Based on a certain type nose landing gear,this paper establishes the dynamic model of the cushion-ing performance analysis and compares the simulation calculation results with the test results to ensure the validity and correctness of the theoretical dynamic model.The parameter sensitivity analysis of cushioning performance is carried out for the initial filling pressure and volume ratio of the high-and low-pressure chambers of the buffer.Results show that the effects of the initial filling pressure and high-and low-pressure chambers volume ratios on the cushioning performance is different from their impacts on the fast-extension performance.Therefore,the design of the nose landing gear buffer of the carrier aircraft needs to be continuously op-timized for taking the cushioning and fast-extension performances into account synchronously.

关 键 词：舰载机起落架 缓冲性能 双腔缓冲器 落震试验 落震动力学 

分 类 号：V214.1[航空宇航科学与技术—航空宇航推进理论与工程] V226.4