考虑机身弹性的起落架着陆动态性能分析
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摘要
起落架是飞机的重要部件,对其性能的正确计算是飞机着陆安全的重要保证。通常在计算起落架缓冲性能时将机身视为刚体,忽略了弹性的影响,这样必然造成误差。本文的研究工作就是分析机身弹性对起落架着陆性能的影响。
本文中建立了弹性飞机的着陆模型。其中机身的动力学模型根据拉格朗日方程和虚功原理建立,作用于机身的广义力除起落架垂直支承力和飞机升力外还考虑了起落架作用于机身的弯矩。推导了起落架在起转、回弹阶段的动力学方程以及各分力的计算方法。为了便于对起落架着陆性能进行数值计算,利用经典“龙格-库塔”法对方程组进行了标准化。
在已经建立的模型基础上,开发了考虑机身弹性的起落架着陆性能分析软件。该软件可以计算在给定着陆条件、前五阶对称模态参数、缓冲器性能、轮胎参数等条件下起落架的着陆响应并可以进行简单的运动仿真,可以作为计算机身弹性对起落架着陆性能影响的有效工具。
利用上述软件计分别计算了不同模态广义质量,安装点广义位移和模态振动频率下的起落架着陆响应。算例结果表明飞机的起落架设计有必要考虑机体结构弹性,并从全局出发,采用特殊的构造措施和优化设计技术。
Landing-gear is an important component of the airplane, and the calculation of its performance ensures safe landing. In the conventional design of landing-gears, the airplane is usually assumed as a rigid body. The neglect of airplane flexibility leads to numerical error. In this paper, the effect of airplane flexibility on the landing-gear behavior is discussed.
Flexible airplane landing model is established. The dynamic model of the fuselage is established by the application of Lagrange’s equation and virtual-work principles. The generalized force on the fuselage includes not only vertical force of the landing-gear and airplane lift, but also the landing-gear moment on the airplane. The dynamic equations and calculation of the forces are presented. The R-K method is used to generalize the equations for numerical calculation of the landing-gear behavior.
Based on the model, a software for calculation analysis of landing-gear considering airplane flexibility is developed. The software is an effectual tool for evaluating the performance of landing-gear primarily. It can be used for the calculation of the response of the landing-gear when initial landing condition, feature of the first 5th symmetrical modes, shock-strut performance and tire parameters are given. Landing simulation is also presented by the software.
A series of landing-gear responses are calculated by given different generalized mass, the frequency of the modes and the translation of the modes in the station of landing-gear. From an overall point of view, airplane flexibility must be considered and optimization design must be used in landing-gear design of a flexible airplane.
本文中建立了弹性飞机的着陆模型。其中机身的动力学模型根据拉格朗日方程和虚功原理建立,作用于机身的广义力除起落架垂直支承力和飞机升力外还考虑了起落架作用于机身的弯矩。推导了起落架在起转、回弹阶段的动力学方程以及各分力的计算方法。为了便于对起落架着陆性能进行数值计算,利用经典“龙格-库塔”法对方程组进行了标准化。
在已经建立的模型基础上,开发了考虑机身弹性的起落架着陆性能分析软件。该软件可以计算在给定着陆条件、前五阶对称模态参数、缓冲器性能、轮胎参数等条件下起落架的着陆响应并可以进行简单的运动仿真,可以作为计算机身弹性对起落架着陆性能影响的有效工具。
利用上述软件计分别计算了不同模态广义质量,安装点广义位移和模态振动频率下的起落架着陆响应。算例结果表明飞机的起落架设计有必要考虑机体结构弹性,并从全局出发,采用特殊的构造措施和优化设计技术。
Landing-gear is an important component of the airplane, and the calculation of its performance ensures safe landing. In the conventional design of landing-gears, the airplane is usually assumed as a rigid body. The neglect of airplane flexibility leads to numerical error. In this paper, the effect of airplane flexibility on the landing-gear behavior is discussed.
Flexible airplane landing model is established. The dynamic model of the fuselage is established by the application of Lagrange’s equation and virtual-work principles. The generalized force on the fuselage includes not only vertical force of the landing-gear and airplane lift, but also the landing-gear moment on the airplane. The dynamic equations and calculation of the forces are presented. The R-K method is used to generalize the equations for numerical calculation of the landing-gear behavior.
Based on the model, a software for calculation analysis of landing-gear considering airplane flexibility is developed. The software is an effectual tool for evaluating the performance of landing-gear primarily. It can be used for the calculation of the response of the landing-gear when initial landing condition, feature of the first 5th symmetrical modes, shock-strut performance and tire parameters are given. Landing simulation is also presented by the software.
A series of landing-gear responses are calculated by given different generalized mass, the frequency of the modes and the translation of the modes in the station of landing-gear. From an overall point of view, airplane flexibility must be considered and optimization design must be used in landing-gear design of a flexible airplane.
引文
[1] 《飞机设计手册》总编委会. 《飞机设计手册》第 14 分册. 北京, 航空工业出版社,2002
[2] 聂宏. 飞机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
[3] Milwitzky B, Cook F E. Analysis of landing-gear behavior. NACA 1154, 1953
[4] Cook F E, Milwitzky B. Effect of interaction on landing gear behavior and dynamic loads in a flexible airplane structure. NACA 1278, 1955
[5] Carden H D, Mogeee J R. Validation of a flexible aircraft take - off and analysis, NASA 1025, 1977
[6] 中国航空科学技术研究院. 飞机起落架结构耐久性设计与分析指南. 西安, 1995
[7] 哈尔滨工业大学理论力学教研组. 理论力学(第五版). 北京, 高等教育出版社, 2001
[8] 晋萍. 飞机起落架动态性能仿真分析. [硕士学位论文], 南京, 南京航空航天大学, 2003
[9] 方平. 小车式飞机起落架着陆与滑跑动态性能仿真分析. [硕士学位论文], 南京, 南京航空航天大学, 2004
[10] 牟让科, 罗俊杰. 飞机结构弹性对起落架缓冲性能的影响. 航空学报, 1995, 16(2):205-208
[11] 齐丕骞, 牟让科. 飞机起落架缓冲性能分析、试验、设计一体化技术. 航空学报, 1998,19(3):332-334
[12] 史友进, 张曾錩. 大柔性飞机着陆撞击多质量块等效模型. 航空学报, 2006, 27(4):635-640
[13] 史友进, 张曾錩. 大柔性飞机着陆响应弹性机体模型. 东南大学学报,2005.7
[14] 史友进. 柔性飞机起落架设计探析. 盐城工学院学报,2005,18(1):1-5
[15] 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. 航空学报, 2005,26(1):8-12
[16] 晋萍. 飞机着陆动力学响应模型与分析. 安徽工业大学学报,2005,22(2):150-152
[17] 李霞. 飞机主起落架缓冲系统性能分析研究. 西飞科技,2000,1(1):2-6
[18] 税清才, 王秦华. 一种用于飞机起起飞性能计算的数值仿真模型. 飞行力学, 2001,19(4):70-72
[19] 徐冬苓、李玉忍. 飞机起落架数学模型的研究. 系统仿真学报,2005,17(4):831-833
[20] 晋萍,聂宏. 起落架着陆动态仿真分析模型及参数优化设计.南京航空航天大学学报,2003,35(5):498-502
[21] Lucas G H, Robert H D, and Veloria J M. Modeling and Validation of a Navy A6-Intruder Actively Controlled Landing Gear System. NASA/TP-1999-209124, 1999
[22] Brent W.York, Omeed Alaverdi. A physically representative aircraft landing gear model for real-time simulation. AIAA A96-35033,1996
[23] Wilbur L M. Hydrodynamic impact of a system with a single elastic mode I theory and generalized solution with an application to an elastic airframe. NACA 1074, 1952
[24] Brent W Y. A physically representative aircraft landing gear model for real-time simulation. 1996
[25] Martin Spieck. Simulation of Aircraft Landing Impact Under Consideration of Aerodynamic Forces on the Flexible Structure. AIAA 2004-4333, 2004
[26] D E Huntington,C S Lyrintzis. Random parametric vibration in aircraft landing gear. AIAA-96-1360-CP, 1996
[27] Ned J Lindsley. A new tire model for aircraft landing gear dynamics. 1999
[28] 刘俊, 林砺宗, 刘小平, 王刚. ADAMS 柔性体运动仿真分析研究及运用.现代制造工程, 2004(5):53-55
[29] 袁东. 飞机起落架仿真数学模型建立方法. 飞行力学,2002,20(4):44-47
[30] 马晓利, 郭军. 应用 ADAMS/Aircraft 建立飞机起落架模型. 结构强度研究,2004(2):35-39
[31] 牟让科, 胡孟权. 飞机非对称着陆和滑跑载荷分析. 机械科学与技术,2000(9):41-47
[32] 沈航. 飞机起落架着陆与滑跑性能分析. 应用力学学报, 2001,18(增刊):198-202
[33] 李霞. 某型飞机主起落架缓冲系统性能分析研究. 航空工程, 2000(6):24-25,31
[34] 齐丕骞, 史惟琦, 戚志民, 史庆起. 起落架落震试验中的仿升动力模拟. 机械科学与技术, 2002,21(增刊):36-37
[35] 牟让科, 齐丕骞, 吴启荣, 彭宗梁. 一种自适应双腔缓冲器动力特性研究. 应用力学学报, 2001,18(z1):23-28
[36] 史海文, 张大千. 在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. 航空学报, 2001,22(1):39-41
[37] 姜百盈. 大型军用运输机的起落架特点综述. 飞机工程, 2003(1):21-26
[38] 徐焱. 飞机滑跑响应研究. 2005(1):17-19
[39] 史永胜, 宋云雪. 飞机起落架设计专家系统研究. 飞机设计, 1999(4):6-9,40
[40] 史永胜, 宋云雪. 基于特征的参数化方法在起落架缓冲器设计中的应用研究. 飞机设计, 2002(2):21-24
[41] 谭浩强. C++程序设计. 北京, 清华大学出版社, 2004
[42] David Simon, 周瑜萍. Visual C++6.0 编程宝典. 北京, 电子工业出版社, 2005
[2] 聂宏. 飞机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
[3] Milwitzky B, Cook F E. Analysis of landing-gear behavior. NACA 1154, 1953
[4] Cook F E, Milwitzky B. Effect of interaction on landing gear behavior and dynamic loads in a flexible airplane structure. NACA 1278, 1955
[5] Carden H D, Mogeee J R. Validation of a flexible aircraft take - off and analysis, NASA 1025, 1977
[6] 中国航空科学技术研究院. 飞机起落架结构耐久性设计与分析指南. 西安, 1995
[7] 哈尔滨工业大学理论力学教研组. 理论力学(第五版). 北京, 高等教育出版社, 2001
[8] 晋萍. 飞机起落架动态性能仿真分析. [硕士学位论文], 南京, 南京航空航天大学, 2003
[9] 方平. 小车式飞机起落架着陆与滑跑动态性能仿真分析. [硕士学位论文], 南京, 南京航空航天大学, 2004
[10] 牟让科, 罗俊杰. 飞机结构弹性对起落架缓冲性能的影响. 航空学报, 1995, 16(2):205-208
[11] 齐丕骞, 牟让科. 飞机起落架缓冲性能分析、试验、设计一体化技术. 航空学报, 1998,19(3):332-334
[12] 史友进, 张曾錩. 大柔性飞机着陆撞击多质量块等效模型. 航空学报, 2006, 27(4):635-640
[13] 史友进, 张曾錩. 大柔性飞机着陆响应弹性机体模型. 东南大学学报,2005.7
[14] 史友进. 柔性飞机起落架设计探析. 盐城工学院学报,2005,18(1):1-5
[15] 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. 航空学报, 2005,26(1):8-12
[16] 晋萍. 飞机着陆动力学响应模型与分析. 安徽工业大学学报,2005,22(2):150-152
[17] 李霞. 飞机主起落架缓冲系统性能分析研究. 西飞科技,2000,1(1):2-6
[18] 税清才, 王秦华. 一种用于飞机起起飞性能计算的数值仿真模型. 飞行力学, 2001,19(4):70-72
[19] 徐冬苓、李玉忍. 飞机起落架数学模型的研究. 系统仿真学报,2005,17(4):831-833
[20] 晋萍,聂宏. 起落架着陆动态仿真分析模型及参数优化设计.南京航空航天大学学报,2003,35(5):498-502
[21] Lucas G H, Robert H D, and Veloria J M. Modeling and Validation of a Navy A6-Intruder Actively Controlled Landing Gear System. NASA/TP-1999-209124, 1999
[22] Brent W.York, Omeed Alaverdi. A physically representative aircraft landing gear model for real-time simulation. AIAA A96-35033,1996
[23] Wilbur L M. Hydrodynamic impact of a system with a single elastic mode I theory and generalized solution with an application to an elastic airframe. NACA 1074, 1952
[24] Brent W Y. A physically representative aircraft landing gear model for real-time simulation. 1996
[25] Martin Spieck. Simulation of Aircraft Landing Impact Under Consideration of Aerodynamic Forces on the Flexible Structure. AIAA 2004-4333, 2004
[26] D E Huntington,C S Lyrintzis. Random parametric vibration in aircraft landing gear. AIAA-96-1360-CP, 1996
[27] Ned J Lindsley. A new tire model for aircraft landing gear dynamics. 1999
[28] 刘俊, 林砺宗, 刘小平, 王刚. ADAMS 柔性体运动仿真分析研究及运用.现代制造工程, 2004(5):53-55
[29] 袁东. 飞机起落架仿真数学模型建立方法. 飞行力学,2002,20(4):44-47
[30] 马晓利, 郭军. 应用 ADAMS/Aircraft 建立飞机起落架模型. 结构强度研究,2004(2):35-39
[31] 牟让科, 胡孟权. 飞机非对称着陆和滑跑载荷分析. 机械科学与技术,2000(9):41-47
[32] 沈航. 飞机起落架着陆与滑跑性能分析. 应用力学学报, 2001,18(增刊):198-202
[33] 李霞. 某型飞机主起落架缓冲系统性能分析研究. 航空工程, 2000(6):24-25,31
[34] 齐丕骞, 史惟琦, 戚志民, 史庆起. 起落架落震试验中的仿升动力模拟. 机械科学与技术, 2002,21(增刊):36-37
[35] 牟让科, 齐丕骞, 吴启荣, 彭宗梁. 一种自适应双腔缓冲器动力特性研究. 应用力学学报, 2001,18(z1):23-28
[36] 史海文, 张大千. 在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. 航空学报, 2001,22(1):39-41
[37] 姜百盈. 大型军用运输机的起落架特点综述. 飞机工程, 2003(1):21-26
[38] 徐焱. 飞机滑跑响应研究. 2005(1):17-19
[39] 史永胜, 宋云雪. 飞机起落架设计专家系统研究. 飞机设计, 1999(4):6-9,40
[40] 史永胜, 宋云雪. 基于特征的参数化方法在起落架缓冲器设计中的应用研究. 飞机设计, 2002(2):21-24
[41] 谭浩强. C++程序设计. 北京, 清华大学出版社, 2004
[42] David Simon, 周瑜萍. Visual C++6.0 编程宝典. 北京, 电子工业出版社, 2005