高性能直升机起落架动力学研究
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摘要
具有可收放抗坠起落架的高性能直升机是新一代直升机的发展趋势,航空发达国家在这方面已经取得了巨大成功,一批先进的直升机已经投入使用。但国内在此领域的研究才刚刚起步,还属于航空业界的一个薄弱环节。本文基于这一现实,以串列式双腔油气缓冲器起落架为模型,综合考虑高性能直升机的使用环境和特点,对此展开系统研究。
研究从高性能直升机的使用背景和使用特点出发,全面考察了双腔油气式缓冲器的受力情况,对全机力学模型和起落架力学模型进行了全面的数值分析;对直升机抗坠特性特别是起落架的抗坠特性进行了综合分析,在国内首次提出了在起落架上采用抗坠套管进行辅助抗坠的概念;此外,论文还对直升机起落架的“地面共振”特性和可抗坠起落架的收放实现问题进行了分析和探讨,给出了三种抗坠毁起落架实现收放的运动简图;在ADAMS/Aircraft中建立了摇臂式抗坠起落架的数字模型并进行了动力学仿真,仿真结果表明采用双腔油气式缓冲器的某型直升机起落架可以满足常规着陆和硬着陆的要求,结合机体和座椅的抗坠设置可以满足抗坠着陆的要求,当采用抗坠套管后有助于实现直升机在高速坠撞情况下的抗坠毁着陆要求。
The advanced helicopter with retractable crashworthy landing gear is an inevitable tendency in the future. Tremendous achievements have been made in aviation well developed countries and some new generation advanced helicopters have been put into service. In our country, on one hand the research on advanced helicopter landing gear is a relative weak link; on the other hand abundance achievements have been made on fixed-wing-craft landing gear. Since there are some common features between landing gears of fixed-wing-craft and rotorcraft, many of the results are available for helicopter so as to accelerate the technical innovation and shorten the research periods. Based on these points both domestic and international experiences can be used for reference. Considering these situations the new generation helicopter landing gear is been investigated.
According to the historical background and operating conditions, the force characteristics and crashworthy features of dual-chamber oleo-pneumatic shock absorber while landing are comprehensively investigated. The numerical analysis of the force act on the whole craft and landing gear is done and the ground resonance is analyzed. Then the notion that uses Crash Tube as an auxiliary crashworthy method is presented and the motion sketches are listed. Finally, a digital model is built and simulations are performed by commercial software ADAMS/Aircraft. The results from investigations and simulations show that the dual-chamber oleo-pneumatic shock absorber can meet the requirements of normal landing and hard landing; with the crash subfloor and crash seats, the landing gear is adaptable to crash landing and the overload factor is acceptable. The performance of crash landing can be obviously improved with Crash Tube (CT).
研究从高性能直升机的使用背景和使用特点出发,全面考察了双腔油气式缓冲器的受力情况,对全机力学模型和起落架力学模型进行了全面的数值分析;对直升机抗坠特性特别是起落架的抗坠特性进行了综合分析,在国内首次提出了在起落架上采用抗坠套管进行辅助抗坠的概念;此外,论文还对直升机起落架的“地面共振”特性和可抗坠起落架的收放实现问题进行了分析和探讨,给出了三种抗坠毁起落架实现收放的运动简图;在ADAMS/Aircraft中建立了摇臂式抗坠起落架的数字模型并进行了动力学仿真,仿真结果表明采用双腔油气式缓冲器的某型直升机起落架可以满足常规着陆和硬着陆的要求,结合机体和座椅的抗坠设置可以满足抗坠着陆的要求,当采用抗坠套管后有助于实现直升机在高速坠撞情况下的抗坠毁着陆要求。
The advanced helicopter with retractable crashworthy landing gear is an inevitable tendency in the future. Tremendous achievements have been made in aviation well developed countries and some new generation advanced helicopters have been put into service. In our country, on one hand the research on advanced helicopter landing gear is a relative weak link; on the other hand abundance achievements have been made on fixed-wing-craft landing gear. Since there are some common features between landing gears of fixed-wing-craft and rotorcraft, many of the results are available for helicopter so as to accelerate the technical innovation and shorten the research periods. Based on these points both domestic and international experiences can be used for reference. Considering these situations the new generation helicopter landing gear is been investigated.
According to the historical background and operating conditions, the force characteristics and crashworthy features of dual-chamber oleo-pneumatic shock absorber while landing are comprehensively investigated. The numerical analysis of the force act on the whole craft and landing gear is done and the ground resonance is analyzed. Then the notion that uses Crash Tube as an auxiliary crashworthy method is presented and the motion sketches are listed. Finally, a digital model is built and simulations are performed by commercial software ADAMS/Aircraft. The results from investigations and simulations show that the dual-chamber oleo-pneumatic shock absorber can meet the requirements of normal landing and hard landing; with the crash subfloor and crash seats, the landing gear is adaptable to crash landing and the overload factor is acceptable. The performance of crash landing can be obviously improved with Crash Tube (CT).
引文
[1]倪先平.直升机手册.北京:航空工业出版社, 2003, 10.
[2]汪东林等.军用直升机发展新动态及启示.北京:总参陆航研究所, 2005.
[3]栗琳.直升机发展历程.北京:航空工业出版社, 2007. 9.
[4]韩国玺.直升机起落架构型分析与仿真试验. [硕士学位论文],南京航空航天大学, 2008, 1
[5]赵凡.先进复合材料在直升机起落架上的应用探讨.直升机技术, 2001, 4.
[6]陈志富,聂宏.直升机起落架发展现状与趋势.第五届长三角科技论坛暨航空航天科技创新与发展论坛论文集,上海,上海市航空学会等, 2008, 11: 281-288.
[7]张彦仲.中国直升机运输机的未来发展.中国工程科学, 2002, 4(8): 1-7
[8]陈建中等.直升机构造学.北京:长城出版社, 1996, 7.
[9] H.G.SJ. Thuis. The development of composite landing gear components for aerospace applications. NLR-TP-2004-141.
[10] T. Staassen (Geldrop, The Netherlands). Metal Matrix Composite Landing Gear Component. SP aerospace, June 23, 2003.
[11] Dennis F. Shanahan. Basic Principles of Helicopter Crashworthiness. AD-A267099, Feb. 1993.
[12]《飞机设计手册》总编委员会.飞机设计手册第14分册.北京:航空工业出版社, 2002, 12.
[13] Norman S. Currey(诺曼.斯.柯里).起落架设计手册.航空工业部, 1982, 1.
[14]中国航空科学技术研究院编.飞机起落架结构耐久性设计与分析指南.中国航空工业总公司《AFFD》系统工程出版, 1995.
[15]聂宏.起落架的缓冲性能分析与设计及其寿命计算方法. [博士学位论文],南京:南京航空航天大学, 1990, 4.
[16]直升机强度规范.航空工业部直升机强度规范编写办公室, 1985, 1.
[17]麻士东.飞机起落架系统动力学仿真研究. [硕士学位论文],南京:南京航空航天大学, 2004
[18]赵凡.摇臂式耐坠毁起落架性能计算研究. [硕士学位论文],南京:南京航空航天大学, 2002
[19]胡国才、陈军民.直升机起落架双腔式缓冲支柱的动刚度研究.海军航空工程学院学报, 2007, 22(6): 601-614.
[20]航空机轮和刹车装置设计规范课题组.《航空机轮和刹车装置设计规范论证资料》.第三机械工业部第609研究所, 1980, 8.
[21]张呈林,张晓谷,郭士龙.直升机部件设计.航空专业教材编审组, 1986, 7.
[22] D. Lowry, Advanced Technology helicopter landing gear preliminary design investigation,AD-A162097, Oct,1985.
[23] W. Flugge, Landing Gear Impact, National Advisory Committee For Aeronautics, Technical Note 2743, Oct, 1952.
[24]王唯.直升机“地面共振”半主动自适应控制. [博士学位论文],南京:南京航空航天大学, 2007, 4: 4-6.
[25]薛海峰,李晓谷.直升机旋翼与机体耦合的空中与地面共振稳定性分析.飞机设计, 2003, 2.
[26]顾仲权.直升机地面共振力学模型的探讨.航空学报. 1990, 3: 78-83.
[27]顾仲权.直升机地面共振力学模型的再讨.航空学报. 1990, 11: 71-77.
[28]汤德满.直升机“地面共振”的非线性稳定性分析.航空学报, 1988, 7: 23-29.
[29] D M Tang, Dowell E H. Influence of Nonlinear Blade Damping on helicopter Ground Resonance Instability. J.Aircraft, 1985,23 (2): 104-110.
[30]张晓谷,刘强.复数坐标及互激励分析在直升机“地面共振”分析中的运用.航空学报, 1992, 11: 18-25.
[31] Tongue Benson H. Limit Cycle Oscillations of a Nonlinear Rotorcraft Model. AIAA Journal, 1984,22(7): 967-974.
[32]成志清,周传荣,程金送.直升机阻尼非线性地面共振的极限环分析.航空学报, 1994,5.
[33]顾仲权.抑制直升机“地面共振”的优化设计.航空学报, 1989,10(3): A113-A118.
[34]程金送.某新型直升机“地面共振”初步分析.应用力学学报, 2001,18(S).
[35]孙之钊,萧秋庭,徐桂祺编著.直升机强度.航空工业出版社, 1990, 11.
[36]米里等,宁航译.直升飞机计算和设计.第二卷,国防工业出版社, 1976.
[37] Robert P Coleman, Arnold M M Feingold. Theory of Self-excited Mechanical Oscillations of Helicopter Roters with Hinged Blades. NACA Report 1351.
[38] Lytwyn R T, Woitsch W. Airborne and Ground Resonance of Hingeless Rotors. Journal of the American Helicopter Society, 1971, 16(2):2-9.
[39] Sharf and L.Monterrubio. Influence of landing gear design on helicopter ground resonance. 1999, AIAA-99-4327:452-462.
[40] Tom Irvine. Helicopter ground resonance (Revision B). Feb. 23, 2005.
[41] Michael W. Votaw and Joyanto K Sen. A Systems Approach for Designing A Crashworthy Helicopter Using Program KRASH. AIAA/AHS/ASEE Aircraft Design Systems and Operations Meeting, California, AIAA, Oct. 1984.
[42] Jyrki Majamaki. Impact Simulations of a Composite Helicopter Structure with MSC.Dytran. Eurocopter Deutschland GmbH.
[43] Alessandro Airoldi, Gerardus Janszen. A design solution for a crashworthy landing gear with anew triggering mechanism for the plastic collapse of metallic tubes. Aerospace Science and Technology 9(2005)445-455.
[44] J.F.M. Wiggenraad. Crashworthiness research at NLR(1990-2003). National Aerospace Laboratory NLR (Netherlands), NLR-TP-2003-317.
[45] U. S. Army Aviation Systems Command.“Military Standard, Light Fixed and Rotary-Wing Aircraft, Crash Resistance”, MIL-STD-1290A (AV).
[46] Stanley P. Desjardins. The Evolution of Energy Absorption Systems for Crashworthy Helicopter Seats. American Helicopter Society 59th Annual Forum, May 6-8, 2003.
[47]杨嘉陵,吴卫华.武装直升机抗坠毁设计研究.机械工程学报, 2001, 37(5).
[48]杨嘉陵,吴卫华等.直升机整体抗坠毁设计的简化力学模型.机械工程学报, 2003, 39(12).
[49]聂宏,乔新等.起落架双腔缓冲器初始压力的优化设计.航空学报, 1992, 13(6).
[50] HB5985-86.直升机强度规范(1986.4).
[51]《飞机设计手册》总编委.飞机设计手册第14册. 2002年.
[52] Chiara Bisagni. Crashworthiness of helicopter subfloor structures. International Journal of Impact Engineering 27(2002) 1067-1082.
[53] Joseph W. Coltman. Rotorcraft Crashworthy Airframe and Fuel system Technology Development Program. DOT/FAA/CT-91/7, Oct, 1994.
[54] N. S. Currey. Aircraft landing gear design: Principles and Practices. AIAA Education Series, AIAA, 1988.
[55] Charles W. Clarke, William Townsend, etc. Crash Testing of Helicopter Airframe Fittings.
[56]牟让科,齐丕骞等.一种自适应双腔缓冲器动力特性研究.应用力学学报, 2001, 18(S).
[57] Gil Wittlin, Michael Smith etc. Airframe Water Impact Analysis Using A combined MSC.Dytran–DRI/KRASH Approach. American Helicopter Society 53rd Annual Forum, Virginia, April 1997.
[58] About the DRI/KRASH and their affiliates and user. Available from http://www.dri-krash.com.
[59] Michael W. Votaw and Joyanto K Sen. A Systems Approach for Designing A Crashworthy Helicopter Using Program KRASH. AIAA/AHS/ASEE Aircraft Design Systems and Operations Meeting, Oct. 1984.
[60]陈立平,张云清,任卫群,等.机械系统动力学分析及ADAMS应用教程.北京:清华大学出版社, 2005.
[61]李军,邢俊文,覃文洁等. ADAMS实例教程.北京:北京理工大学出版社, 2002.
[62]王国强,张进平,马若丁.虚拟样机技术及其在ADAMS上的实践.西安:西北工业大学出版社, 2002, 3.
[2]汪东林等.军用直升机发展新动态及启示.北京:总参陆航研究所, 2005.
[3]栗琳.直升机发展历程.北京:航空工业出版社, 2007. 9.
[4]韩国玺.直升机起落架构型分析与仿真试验. [硕士学位论文],南京航空航天大学, 2008, 1
[5]赵凡.先进复合材料在直升机起落架上的应用探讨.直升机技术, 2001, 4.
[6]陈志富,聂宏.直升机起落架发展现状与趋势.第五届长三角科技论坛暨航空航天科技创新与发展论坛论文集,上海,上海市航空学会等, 2008, 11: 281-288.
[7]张彦仲.中国直升机运输机的未来发展.中国工程科学, 2002, 4(8): 1-7
[8]陈建中等.直升机构造学.北京:长城出版社, 1996, 7.
[9] H.G.SJ. Thuis. The development of composite landing gear components for aerospace applications. NLR-TP-2004-141.
[10] T. Staassen (Geldrop, The Netherlands). Metal Matrix Composite Landing Gear Component. SP aerospace, June 23, 2003.
[11] Dennis F. Shanahan. Basic Principles of Helicopter Crashworthiness. AD-A267099, Feb. 1993.
[12]《飞机设计手册》总编委员会.飞机设计手册第14分册.北京:航空工业出版社, 2002, 12.
[13] Norman S. Currey(诺曼.斯.柯里).起落架设计手册.航空工业部, 1982, 1.
[14]中国航空科学技术研究院编.飞机起落架结构耐久性设计与分析指南.中国航空工业总公司《AFFD》系统工程出版, 1995.
[15]聂宏.起落架的缓冲性能分析与设计及其寿命计算方法. [博士学位论文],南京:南京航空航天大学, 1990, 4.
[16]直升机强度规范.航空工业部直升机强度规范编写办公室, 1985, 1.
[17]麻士东.飞机起落架系统动力学仿真研究. [硕士学位论文],南京:南京航空航天大学, 2004
[18]赵凡.摇臂式耐坠毁起落架性能计算研究. [硕士学位论文],南京:南京航空航天大学, 2002
[19]胡国才、陈军民.直升机起落架双腔式缓冲支柱的动刚度研究.海军航空工程学院学报, 2007, 22(6): 601-614.
[20]航空机轮和刹车装置设计规范课题组.《航空机轮和刹车装置设计规范论证资料》.第三机械工业部第609研究所, 1980, 8.
[21]张呈林,张晓谷,郭士龙.直升机部件设计.航空专业教材编审组, 1986, 7.
[22] D. Lowry, Advanced Technology helicopter landing gear preliminary design investigation,AD-A162097, Oct,1985.
[23] W. Flugge, Landing Gear Impact, National Advisory Committee For Aeronautics, Technical Note 2743, Oct, 1952.
[24]王唯.直升机“地面共振”半主动自适应控制. [博士学位论文],南京:南京航空航天大学, 2007, 4: 4-6.
[25]薛海峰,李晓谷.直升机旋翼与机体耦合的空中与地面共振稳定性分析.飞机设计, 2003, 2.
[26]顾仲权.直升机地面共振力学模型的探讨.航空学报. 1990, 3: 78-83.
[27]顾仲权.直升机地面共振力学模型的再讨.航空学报. 1990, 11: 71-77.
[28]汤德满.直升机“地面共振”的非线性稳定性分析.航空学报, 1988, 7: 23-29.
[29] D M Tang, Dowell E H. Influence of Nonlinear Blade Damping on helicopter Ground Resonance Instability. J.Aircraft, 1985,23 (2): 104-110.
[30]张晓谷,刘强.复数坐标及互激励分析在直升机“地面共振”分析中的运用.航空学报, 1992, 11: 18-25.
[31] Tongue Benson H. Limit Cycle Oscillations of a Nonlinear Rotorcraft Model. AIAA Journal, 1984,22(7): 967-974.
[32]成志清,周传荣,程金送.直升机阻尼非线性地面共振的极限环分析.航空学报, 1994,5.
[33]顾仲权.抑制直升机“地面共振”的优化设计.航空学报, 1989,10(3): A113-A118.
[34]程金送.某新型直升机“地面共振”初步分析.应用力学学报, 2001,18(S).
[35]孙之钊,萧秋庭,徐桂祺编著.直升机强度.航空工业出版社, 1990, 11.
[36]米里等,宁航译.直升飞机计算和设计.第二卷,国防工业出版社, 1976.
[37] Robert P Coleman, Arnold M M Feingold. Theory of Self-excited Mechanical Oscillations of Helicopter Roters with Hinged Blades. NACA Report 1351.
[38] Lytwyn R T, Woitsch W. Airborne and Ground Resonance of Hingeless Rotors. Journal of the American Helicopter Society, 1971, 16(2):2-9.
[39] Sharf and L.Monterrubio. Influence of landing gear design on helicopter ground resonance. 1999, AIAA-99-4327:452-462.
[40] Tom Irvine. Helicopter ground resonance (Revision B). Feb. 23, 2005.
[41] Michael W. Votaw and Joyanto K Sen. A Systems Approach for Designing A Crashworthy Helicopter Using Program KRASH. AIAA/AHS/ASEE Aircraft Design Systems and Operations Meeting, California, AIAA, Oct. 1984.
[42] Jyrki Majamaki. Impact Simulations of a Composite Helicopter Structure with MSC.Dytran. Eurocopter Deutschland GmbH.
[43] Alessandro Airoldi, Gerardus Janszen. A design solution for a crashworthy landing gear with anew triggering mechanism for the plastic collapse of metallic tubes. Aerospace Science and Technology 9(2005)445-455.
[44] J.F.M. Wiggenraad. Crashworthiness research at NLR(1990-2003). National Aerospace Laboratory NLR (Netherlands), NLR-TP-2003-317.
[45] U. S. Army Aviation Systems Command.“Military Standard, Light Fixed and Rotary-Wing Aircraft, Crash Resistance”, MIL-STD-1290A (AV).
[46] Stanley P. Desjardins. The Evolution of Energy Absorption Systems for Crashworthy Helicopter Seats. American Helicopter Society 59th Annual Forum, May 6-8, 2003.
[47]杨嘉陵,吴卫华.武装直升机抗坠毁设计研究.机械工程学报, 2001, 37(5).
[48]杨嘉陵,吴卫华等.直升机整体抗坠毁设计的简化力学模型.机械工程学报, 2003, 39(12).
[49]聂宏,乔新等.起落架双腔缓冲器初始压力的优化设计.航空学报, 1992, 13(6).
[50] HB5985-86.直升机强度规范(1986.4).
[51]《飞机设计手册》总编委.飞机设计手册第14册. 2002年.
[52] Chiara Bisagni. Crashworthiness of helicopter subfloor structures. International Journal of Impact Engineering 27(2002) 1067-1082.
[53] Joseph W. Coltman. Rotorcraft Crashworthy Airframe and Fuel system Technology Development Program. DOT/FAA/CT-91/7, Oct, 1994.
[54] N. S. Currey. Aircraft landing gear design: Principles and Practices. AIAA Education Series, AIAA, 1988.
[55] Charles W. Clarke, William Townsend, etc. Crash Testing of Helicopter Airframe Fittings.
[56]牟让科,齐丕骞等.一种自适应双腔缓冲器动力特性研究.应用力学学报, 2001, 18(S).
[57] Gil Wittlin, Michael Smith etc. Airframe Water Impact Analysis Using A combined MSC.Dytran–DRI/KRASH Approach. American Helicopter Society 53rd Annual Forum, Virginia, April 1997.
[58] About the DRI/KRASH and their affiliates and user. Available from http://www.dri-krash.com.
[59] Michael W. Votaw and Joyanto K Sen. A Systems Approach for Designing A Crashworthy Helicopter Using Program KRASH. AIAA/AHS/ASEE Aircraft Design Systems and Operations Meeting, Oct. 1984.
[60]陈立平,张云清,任卫群,等.机械系统动力学分析及ADAMS应用教程.北京:清华大学出版社, 2005.
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