摘要
舰载机弹射起飞对前起落架突伸性能要求严格,针对双气腔油气式起落架进行突伸动力学建模,编制程序分析起落架的突伸动态过程。设计了一套弹射起落架突伸试验方案,成功地对前起落架突伸动态性能进行了测试与验证,并对试验过程中的现象进行了分析。分析结果与试验结果符合性好。研究了缓冲器内部结构、充填参数变化对突伸性能的影响,通过优化回油孔直径、缓冲器充气压力、轮胎压力,高低压腔体积比、油针尺寸等参数,可以提高起落架突伸性能。
The Extension performance plays an important role in take-off of Carrier-based aircraft. In this paper, the extension dynamic performance of an oleo-pneumatic shock absorber with a dual-chamber is modeled, and studied with the home made simulation code. The test for catapult launch-extension of the nose landing gear is designed, and the data of extension dynamic performance was obtained successfully in the test, and the phenomenon of the test is analyzed. The simulation results agree well with that of the test. The effect of variations of a set of structural and filling parameters from the original design data on the extension performance of the landing gear is studied. The results show thatthe extension performance can be improved with the optimal parameters including the oil gallery diameter, the initial pressure of chamber, the initial pressure of tire, the low-pressure volume ratio of the dual-chamber and the dimension of the metering pin.
出处
《机械科学与技术》
CSCD
北大核心
2016年第11期1686-1690,共5页
Mechanical Science and Technology for Aerospace Engineering
关键词
舰载机
前起落架
突伸
缓冲器
试验验证
分析
carrier-based aircraft
nose landing gear
extension
shock absorber
test
analysis
