防区外机载布撒器总体设计关键技术研究
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摘要
本文是结合某型防区外机载布撒器的战术技术要求开展的防区外机载布撒器总体设计方面的一些预研工作。完成的工作主要包括两个方面：一是非圆截面弹身飞行器的空气动力估算的方法研究；二是弹用涡轮发动机计算机辅助稳态性能计算与分析系统设计。这是防区外机载布撒器总体方案初步设计阶段需要解决的两个关键技术。
本文第二章在分析了非圆截面弹身飞行器气动特性的基础上，建立了一套非圆截面弹身飞行器气动估算方法：用等效圆截面弹身飞行器的气动特性来等效非圆截面弹身飞行器的气动特性，并引入非圆截面修正因子(非圆因子、翼身干扰因子修正系数和牛顿修正因子)加以修正。然后利用细长体理论推导出了非圆因子F_(SB)和翼身干扰因子修正系数足K_c的表观面积表达式，并通过构造了一种基本解——二维常值偶极子分布线元，建立了任意形状截面表观面积的计算模型。最后用算例验证了本文所提出的表观面积计算方法和非圆截面修正因子计算方法，证明了这种方法的正确性和准确性。
本文第三章首先建立了弹用涡轮发动机(包括涡喷和涡扇发动机)稳态性能计算的数学模型，然后以此为基础设计开发了弹用涡轮发动机计算机辅助稳态性能计算与分析系统，给出了系统的功能设计、程序结构、操作步骤。最后用两个算例验证了这一系统的正确性和方便实用性，这一系统可以用于导弹总体方案初步设计阶段发动机稳态性能的计算。
This paper is some advanced research work on conceptual design of standoff airborne spreader according to tactical and technical requirements of a certain standoff airborne spreader. The completed work includes two aspects: one is the method study of aerodynamic estimation of aircraft with noncircular shape cross section body; the other is the design and development of computer-aided steady-state performance analysis system of turbine engines used in missiles. These two aspects are key technology need to be solved in the phase of overall project preliminary design of standoff airborne spreader.
In chapter 2, a set of aerodynamic estimation methods of aircraft with noncircular shape cross section body are established based on the analysis of aerodynamic characteristic of aircraft with noncircular shape cross section body. The methods used the aerodynamic estimation method of aircraft with circular shape cross section body to calculate the aerodynamic characteristic of aircraft with noncircular shape cross section body by inducing noncircular shape cross section
adjustment factors (including noncircular shape factor FSB , coefficient Kc of correction of the interference factor between wing and body Kc, and Newton adjustment factor Fm.). Then the mathematic expressions of calculating Fsa and
Kc are derived, and the computational model to calculate the apparent area of
arbitrary shape cross section is established by constructing a new basic solution: two-dimensional constant dipole distributing linear element. The examples in this chapter validate the correctness and accuracy of the methods.
In chapter 3, the computational model to calculate the steady-state performance of turbine engines (including turbojet engine and turbofan engine) used in missiles is established firstly, and then the computer-aided steady-state performance analysis system of turbine engines used in missiles is designed and realized, and the functional design, program structure and operational procedure of the system are given. And finally the system is proved to be correct, convenient and practical by two examples given in this paper, and so it can be used for the steady-state performance calculation of turbine engine in the phase of overall project preliminary design.
本文第二章在分析了非圆截面弹身飞行器气动特性的基础上，建立了一套非圆截面弹身飞行器气动估算方法：用等效圆截面弹身飞行器的气动特性来等效非圆截面弹身飞行器的气动特性，并引入非圆截面修正因子(非圆因子、翼身干扰因子修正系数和牛顿修正因子)加以修正。然后利用细长体理论推导出了非圆因子F_(SB)和翼身干扰因子修正系数足K_c的表观面积表达式，并通过构造了一种基本解——二维常值偶极子分布线元，建立了任意形状截面表观面积的计算模型。最后用算例验证了本文所提出的表观面积计算方法和非圆截面修正因子计算方法，证明了这种方法的正确性和准确性。
本文第三章首先建立了弹用涡轮发动机(包括涡喷和涡扇发动机)稳态性能计算的数学模型，然后以此为基础设计开发了弹用涡轮发动机计算机辅助稳态性能计算与分析系统，给出了系统的功能设计、程序结构、操作步骤。最后用两个算例验证了这一系统的正确性和方便实用性，这一系统可以用于导弹总体方案初步设计阶段发动机稳态性能的计算。
This paper is some advanced research work on conceptual design of standoff airborne spreader according to tactical and technical requirements of a certain standoff airborne spreader. The completed work includes two aspects: one is the method study of aerodynamic estimation of aircraft with noncircular shape cross section body; the other is the design and development of computer-aided steady-state performance analysis system of turbine engines used in missiles. These two aspects are key technology need to be solved in the phase of overall project preliminary design of standoff airborne spreader.
In chapter 2, a set of aerodynamic estimation methods of aircraft with noncircular shape cross section body are established based on the analysis of aerodynamic characteristic of aircraft with noncircular shape cross section body. The methods used the aerodynamic estimation method of aircraft with circular shape cross section body to calculate the aerodynamic characteristic of aircraft with noncircular shape cross section body by inducing noncircular shape cross section
adjustment factors (including noncircular shape factor FSB , coefficient Kc of correction of the interference factor between wing and body Kc, and Newton adjustment factor Fm.). Then the mathematic expressions of calculating Fsa and
Kc are derived, and the computational model to calculate the apparent area of
arbitrary shape cross section is established by constructing a new basic solution: two-dimensional constant dipole distributing linear element. The examples in this chapter validate the correctness and accuracy of the methods.
In chapter 3, the computational model to calculate the steady-state performance of turbine engines (including turbojet engine and turbofan engine) used in missiles is established firstly, and then the computer-aided steady-state performance analysis system of turbine engines used in missiles is designed and realized, and the functional design, program structure and operational procedure of the system are given. And finally the system is proved to be correct, convenient and practical by two examples given in this paper, and so it can be used for the steady-state performance calculation of turbine engine in the phase of overall project preliminary design.
引文
【1】徐华舫．空气动力学基础(上册)[M]．北京，北京航空学院出版社，1986．
【2】Brook W. Beall. Application of Slender Body Theory to Bodies with Asbitrary Shaped Cross Sections[J]. AIAA Paper 86-0488, 1986.
【3】李晓斌等．非圆截面形状弹体法向气动力估算方法[J]．弹箭与制导学报，2001年第21卷第3期．
【4】胡汉东等．布撒器气动特性分析[J]．流体力学实验与测量，2002．3第16卷第1期．
【5】黄晓鹏等．非圆截面战术弹纵向气动特性的工程计算方法研究[C]．中国兵工学会火箭导弹分会第七次学术年会，1998．5．
【6】徐春光等．非圆截面弹体附加表面积工程估算方法研究[J]．航空计算技术，2001．9第31卷第3期．
【7】Jorgenson L. H. "Prediction of Static Aerodynamic Characteristics for Slender Bodies Alone And with Lifting Surfaces to Very High Angle of Attack" [R]. NASATRR-474，1977.
【8】Jorgenson L. H. "Prediction of Static Aerodynamic Characteristics for Space Shuttle-like and Other Bodies at Angle of Attack from 0-180°" [R]. NASA TND-6996,1973.
【9】严恒元．飞行器气动特性分析与工程计算[M]．西北工业大学出版社，1990．
【10】[苏联]A．A．列别捷夫，л．С．契尔诺勃洛夫金．无人驾驶飞行器的飞行动力学[M]．国防工业出版社，1964．
【11】Nielsen J. N. "missile Aerodynamics" [M]. McGraw Hill, New York, 1960.
【12】Hess J. L and Smith A.M.O. "Calculation of Potential Flow About Arbitrary Bodies" [J]. Progress Aeronautical Sciences Vol.8, D. Kuchemann, Ed., Pergamon Press, Oxford, 1967.
【13】Asher Sigal and Ehud Lapidot. "THE Aerodynamic Characteristics of Configurations Having Bodies With Square, Rectangular and Circular Cross-Sections at a Mach Number of 0.75"[J]. AIAA 87-2429.
【14】S. R. Vukelich, and McDonnell Douglas. Aerodynamic Prediction of Elliptically-Shaped Missile Configurations Using Component Build-Up Methodology[J]. AIAA 85-0271.
【15】Mahmoud Mani, and Afskin Khajehfard. Aerodynamic Characteristics of
Bodies With Square, Elliptic, and Circular Cross Sections[J]. AIAA 2000-4015.
【16】Asher sigal. An Experimental Investigation of the Aerodynamic Characteristics of Bodies Having Square Cross-Section at Transonic Speed. AIAA 84-2091.
【17】F. G. Moore, R. M. McInville, and T. C. Hymert. A Robust Method For Calculating Aerodynamics of Noncircular-Cross Section Weapons[J]. AIAA 98-37237
【18】S.L. Stoy, S. R. Vukelich. Prediction of Aerodynamic Characteristics of Unconventional Missile Configurations Using Component Build-Up Techniques. aiaa-86-0489.
【19】陈再新等．空气动力学[M]．航空工业出版社，1993．
【20】[美]W.H.Press, S.A. Teukolsky, W.T. Vetterling, B.P. Flannery. c语言数值算法程序大全(第二版)[M]．电子工业出版社，1995年10月．
【21】程云鹏主编．矩阵论[M]．西北工业大学出版社，1999年6月．
【22】吴仲华，燃气的热力性质表[M]，科学出版社，1959。
【23】唐狄毅、廉小纯编．航空燃气轮机原理(下册)[M]．国防工业出版社，1989．
【24】张世铮．燃气热力性质的数学公式表示法[R]．工程热物理学报，1980．
【25】童凯生编．航空涡轮发动机性能变比热计算方法[M]．航空工业出版社，1991．
【26】Robert W. Koenig and Laurence H. Fishbach. GENENG-A Program For Calculating Design and Off-Design Performance for Turbojet and Turbofan[R]. NASATN D-6552, 1972.
【27】刘德宏，涡扇发动机建模及解析与解析余度研究[C]，西工大硕士论文
【28】尚义．航空燃气涡轮发动机[M]．国防工业出版社，1985年12月．
【29】曾远文，刘心绪编著．热学与分子物理[M]．四川教育出版社，1987．8．
【30】杨蚱生，俞守勤编著．飞行器部件空气动力学[M]．国防工业出版社，1987．4．
【2】Brook W. Beall. Application of Slender Body Theory to Bodies with Asbitrary Shaped Cross Sections[J]. AIAA Paper 86-0488, 1986.
【3】李晓斌等．非圆截面形状弹体法向气动力估算方法[J]．弹箭与制导学报，2001年第21卷第3期．
【4】胡汉东等．布撒器气动特性分析[J]．流体力学实验与测量，2002．3第16卷第1期．
【5】黄晓鹏等．非圆截面战术弹纵向气动特性的工程计算方法研究[C]．中国兵工学会火箭导弹分会第七次学术年会，1998．5．
【6】徐春光等．非圆截面弹体附加表面积工程估算方法研究[J]．航空计算技术，2001．9第31卷第3期．
【7】Jorgenson L. H. "Prediction of Static Aerodynamic Characteristics for Slender Bodies Alone And with Lifting Surfaces to Very High Angle of Attack" [R]. NASATRR-474，1977.
【8】Jorgenson L. H. "Prediction of Static Aerodynamic Characteristics for Space Shuttle-like and Other Bodies at Angle of Attack from 0-180°" [R]. NASA TND-6996,1973.
【9】严恒元．飞行器气动特性分析与工程计算[M]．西北工业大学出版社，1990．
【10】[苏联]A．A．列别捷夫，л．С．契尔诺勃洛夫金．无人驾驶飞行器的飞行动力学[M]．国防工业出版社，1964．
【11】Nielsen J. N. "missile Aerodynamics" [M]. McGraw Hill, New York, 1960.
【12】Hess J. L and Smith A.M.O. "Calculation of Potential Flow About Arbitrary Bodies" [J]. Progress Aeronautical Sciences Vol.8, D. Kuchemann, Ed., Pergamon Press, Oxford, 1967.
【13】Asher Sigal and Ehud Lapidot. "THE Aerodynamic Characteristics of Configurations Having Bodies With Square, Rectangular and Circular Cross-Sections at a Mach Number of 0.75"[J]. AIAA 87-2429.
【14】S. R. Vukelich, and McDonnell Douglas. Aerodynamic Prediction of Elliptically-Shaped Missile Configurations Using Component Build-Up Methodology[J]. AIAA 85-0271.
【15】Mahmoud Mani, and Afskin Khajehfard. Aerodynamic Characteristics of
Bodies With Square, Elliptic, and Circular Cross Sections[J]. AIAA 2000-4015.
【16】Asher sigal. An Experimental Investigation of the Aerodynamic Characteristics of Bodies Having Square Cross-Section at Transonic Speed. AIAA 84-2091.
【17】F. G. Moore, R. M. McInville, and T. C. Hymert. A Robust Method For Calculating Aerodynamics of Noncircular-Cross Section Weapons[J]. AIAA 98-37237
【18】S.L. Stoy, S. R. Vukelich. Prediction of Aerodynamic Characteristics of Unconventional Missile Configurations Using Component Build-Up Techniques. aiaa-86-0489.
【19】陈再新等．空气动力学[M]．航空工业出版社，1993．
【20】[美]W.H.Press, S.A. Teukolsky, W.T. Vetterling, B.P. Flannery. c语言数值算法程序大全(第二版)[M]．电子工业出版社，1995年10月．
【21】程云鹏主编．矩阵论[M]．西北工业大学出版社，1999年6月．
【22】吴仲华，燃气的热力性质表[M]，科学出版社，1959。
【23】唐狄毅、廉小纯编．航空燃气轮机原理(下册)[M]．国防工业出版社，1989．
【24】张世铮．燃气热力性质的数学公式表示法[R]．工程热物理学报，1980．
【25】童凯生编．航空涡轮发动机性能变比热计算方法[M]．航空工业出版社，1991．
【26】Robert W. Koenig and Laurence H. Fishbach. GENENG-A Program For Calculating Design and Off-Design Performance for Turbojet and Turbofan[R]. NASATN D-6552, 1972.
【27】刘德宏，涡扇发动机建模及解析与解析余度研究[C]，西工大硕士论文
【28】尚义．航空燃气涡轮发动机[M]．国防工业出版社，1985年12月．
【29】曾远文，刘心绪编著．热学与分子物理[M]．四川教育出版社，1987．8．
【30】杨蚱生，俞守勤编著．飞行器部件空气动力学[M]．国防工业出版社，1987．4．