【摘要】 现代航母舰载机多使用弹射起飞方式,在弹射起飞行程末端,前起落架突伸是一种增加舰载机离舰迎角,提高飞行安全的重要技术手段。设计了一种适用于弹射起飞舰载机起落架突伸性能测试试验方案,搭建了试验系统,并对某型飞机前起落架突伸性能进行了试验验证,对起落架突伸过程进行了分析。通过改变试验初始条件,分析了影响起落架突伸性能的因素,并给出了定量描述。建立了双气腔油气式起落架动力学模型,对某型飞机起落架典型工况突伸性能进行数值模拟,将数值计算结果与试验测试结果进行对比。利用动力学模型对起落架缓冲性能进行计算校核,给出了不同初始条件下起落架缓冲性能变化趋势和数量。结果表明,对于双气腔油气式起落架,起落架突伸性能提升往往会导致起落架缓冲系统效率降低和最大着舰载荷增大。在弹射式舰载机起落架设计时,必须综合考虑突伸性能和缓冲性能。更多还原

【Abstract】 Catapult takeoff is commonly used by modern carrier-based aircraft.At the end of the takeoff trip,the sudden-extension of the nose landing gear is an important technical way to increase the departure angle of the carrier-based aircraft and improve the flight safety.In this article,a test scheme is designed to test the sudden-extension performance of the carrier-based aircraft landing gear.The test system is built and the nose gear landing performance of a certain aircraft is tested.By changing the initial conditions of the test,the factors affecting the sudden-extension performance of the landing gear are analyzed and quantitatively described.The dynamic model of the double-gas-chamber landing gear is established.The numerical simulation results are compared with the test results of the landing gear under some typical operating conditions.The cushioning performance of the landing gear is calculated and checked by the dynamic model,with the trend and quantity of the cushioning performance of the landing gear under different initial conditions given.The results show that the improvement of the landing gear′s sudden-extension performance often leads to the decrease of the landing gear′s efficiency of the shock-absorbing system and the increase of the maximum landing force of landing gear.Therefore,in the design of the landing gear of the catapult carrier aircraft,the sudden performance and the cushioning performance must be taken into account.更多还原