舰载机全机落震试验机翼升力模拟方法研究
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摘要
舰载机全机落震试验机翼升力模拟是在实验室测试飞机着陆载荷时,给飞机动态施加飞机着陆时刻机翼升力,模拟飞机着陆真实受载,机翼升力施加是否合理是全机落震试验成功与否的关键技术。给出了全机落震试验机翼升力模拟准则,提出了一种适用于全机落震试验的模拟机翼升力加载方法。根据该方法介绍了机翼升力加载装置设计原理,并对设计的机翼升力模拟装置进行了力学性能测试。将此方法和装置应用于某型飞机全机落震试验中,分别从施加模拟机翼升力大小、飞机姿态影响、下沉速度影响和着陆能量吸收四个方面对全机落震试验机翼升力模拟方法进行验证和评估。试验结果表明,该方法符合全机落震试验升力模拟准则,可用于舰载机全机落震试验。
Wing lift simulation during full scale carrier-based aircraft drop tests is to impose a dynamic load on an aircraft's wing under indoor environment,so as to completely simulate the real wing load-bearing of the aircraft under landing condition. Whether or not applying wing lift is reasonable is the key of successful full scale carrier-based aircraft drop tests. Here,the simulation criterion of wing lift for full scale carrier-based aircraft drop tests was given,a simulating wing lift loading method for full scale carrier-based aircraft drop tests was proposed. According to the proposed method,the design principles of a wing lift loading device were presented,the mechanical performances of the wing lift simulator were tested. The method and the device were applied in the full scale aircraft drop tests of a certain aircraft. This method was verified and evaluated from four aspects including applied wing lift values,effect of aircraft attitude,effect of going down speed and landing energy absorption. The test results showed that the proposed method satisfies the simulation criterion of wing lift for full scale carrier-based aircraft drop tests; it can be used to simulate wing lift loading for such tests.
Wing lift simulation during full scale carrier-based aircraft drop tests is to impose a dynamic load on an aircraft's wing under indoor environment,so as to completely simulate the real wing load-bearing of the aircraft under landing condition. Whether or not applying wing lift is reasonable is the key of successful full scale carrier-based aircraft drop tests. Here,the simulation criterion of wing lift for full scale carrier-based aircraft drop tests was given,a simulating wing lift loading method for full scale carrier-based aircraft drop tests was proposed. According to the proposed method,the design principles of a wing lift loading device were presented,the mechanical performances of the wing lift simulator were tested. The method and the device were applied in the full scale aircraft drop tests of a certain aircraft. This method was verified and evaluated from four aspects including applied wing lift values,effect of aircraft attitude,effect of going down speed and landing energy absorption. The test results showed that the proposed method satisfies the simulation criterion of wing lift for full scale carrier-based aircraft drop tests; it can be used to simulate wing lift loading for such tests.
引文
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[2]史海文,张大千.落震试验中起转和回弹载荷的模拟情况对试验结果的影响[J].航空学报,2001,21(1):39-41.SHI Haiwen,ZHANG Daqian.Influence of imitation condition of spin-up and spring back drag loads on drop test result[J].Acta Aeronautica et Astronautica Sinica,2001,21(1):39-41.
[3]豆清波,史惟琦,牟让科,等.基于落震试验的油气式起落架气体压缩多变指数变化规律研究[J].实验力学,2015,30(2):215-220.DOU Qingbo,SHI Weiqi,MU Rangke,et al.On the gas compression polytropic index variation of oil-gas landing gear based on drop test[J].Journal of Experimental Mechanics,2015,30(2):215-220.
[4]杨一栋.舰载机进场着舰规范评估[M].北京:国防工业出版社,2006.
[5]聂宏,彭一明,魏小辉,等.舰载飞机着舰拦阻动力学研究综述[J].航空学报,2013,35(1):1-12.NIE Hong,PENG Yi Ming,WEI Xiaohui,et al.Overview of carrier-based aircraft arrested deck-landing dynamics[J].Acta Aeronautica et Astronautica Sinica,2013,35(1):1-12.
[6]王钱生.关于舰载机下沉速度的初步研究[J].飞机设计,2007,27(3):1-6.WANG Qiansheng.A preliminary research of sinking velocity for carrier-based aircraft[J].Aircraft Design,2007,27(3):1-6.
[7]张鑫.舰载机拦阻着舰动力学分析及仿真[D].西安:西北工业大学,2007.
[8]MIL-A-8860.Airplane strength and rigidity,general specification for[S].Naval Air Systems Command,1987.
[9]MIL-A-8863C.Airplane strength and rigidity,ground loads for carrier-based aircraft[S].Naval Air Systems Command,1993.
[10]MIL-A-8867.Airplane strength and rigidity,ground test[S].Naval Air Systems Command,1987.
[11]段萍萍.舰载飞机着舰过程动力学性能分析[D].南京:南京航空航天大学,2012.
[12]魏小辉,聂宏.基于降落区概念的飞机起落架着陆动力学分析[J].航空学报,2005,26(1):8-12.WEI Xiaohui,NIE Hong.Analysis of landing impact force of aircraft landing gears based on the conception of landing area[J].Acta Aeronautica et Astronautica Sinica,2005,26(1):8-12.
[13]朱琳.舰载飞机拦阻着舰过程起落架载荷研究[D].南京:南京航空航天大学,2009.
[14]姚念奎,周栋.固定翼舰载机全机落震试验[J].飞机设计,2014,34(4):31-36YAO Niankui,ZHOU Dong.Full-scale drop test of fixed-wing carrier-based aircraft[J].Aircraft Design,2014,34(4):31-36.
[15]姚念奎,隋福成,王成波.舰载机的自由飞行勾住情况[J].飞机设计,2011,31(6):10-15.YAO Niankui,SUI Fucheng,WANG Chengbo.Free flight engagement condition of carrier-based aircraft[J].Aircraft Design,2011,31(6):10-15.
[16]齐丕骞,史惟琦,戚志民,等.起落架落震试验中的仿升动力模拟[J].机械科学与技术.2002,21(增刊1):36-37QI Peiqian,SHI Weiqi,QI Zhimin,et al.Wing lift simulation in landing-gear drop Test[J].Mechanical Science And Technology,2002,21(Sup1):36-37.