某机起落架双腔缓冲器设计及突伸动力学研究

Dual-chamber shock absorber design and analysis on fast- extension dynamics of a certain aircraft landing gear

以某机前起落架为研究对象,为满足突伸要求将单腔缓冲器改为双腔缓冲器,并建立了该机前起落架的突伸动力学模型。首先进行突伸动力学性能分析,进而对双腔缓冲器高压腔充气压力以及回油孔面积进行参数影响分析。研究发现:采用双腔缓冲器设计方案在弹射起飞过程中可以快速增大舰载机飞行迎角,无明显航迹下沉现象;双腔缓冲器高压腔充气压力越大,突伸力越大,舰载机离舰后飞行迎角增大得越快;增加缓冲器回油孔面积有利于舰载机弹射起飞半抛物飞行阶段飞行迎角的建立,并且可以提高爬升率。

The fast- extension ability has tremendous influence on takeoff for the carrier based aircraft. It introduces a certain model of aircraft＇s nose gear,changes single- chamber shock absorber into dual- chamber one in order to satisfy fast- extension requirements,builds dynamic model of nose gear fast- extension,and analyzes the fast- extension performance. Based on the parameter analysis for high- chamber＇s pressure and the size of back oil hole,it obtains that dual- chamber design grants a rapid increase of attack angle during takeoff,without evident flight path sinking. The speed rise of attack angle＇s has a positive correlation with high- chamber＇s pressure and fast- extension force. An increase in the area of back oil hole helps establish the attack angle during semi- parabola flight procedure of the catapult takeoff,and enhances rate of climb too.