二元推力矢量喷管的结构设计及优化
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摘要
为了在现代空战中取得战场优势,在新型战斗机设计中采用高新技术提高改善现代战斗机的技术战术性能是十分必要的。
本文根据某型发动机的特定工作条件,为某型发动机改装二元推力矢量喷管进行了改装设计,将发动机喷管设计成了由导流管、调节板和导流板三部分组成的一个喷管,该结构喷管结构简单,成本低,发动机改动少,使用方便,且系统的可靠性、可维修性很好,使用寿命也很高。本文利用有限元软件对设计喷管的各个组成部件进行了分析计算,分别得出了导流管、调节板和导流板的应力分布和位移分布特征。其中导流管的应力分布和位移分布跟传统的轴流式喷管大不相同,特别是最大位移的出现位置发生了很大变化,为此,本文对导流管局部部位进行了加厚处理,并对局部部位加装了加强框,经过局部加强框的加装和局部厚度的加厚,导流管的最大应力和最大位移分布得到改善,减小了导流管的最大应力值和最大位移值,并且,最大应力和最大位移出现的位置也发生了变化,通过改进方案的实施,导流管的结构能够胜任发动机出口气流的要求,满足飞机的安全要求。本文在设计导流板时考虑到飞机特定的工作状态,为了防止翼尖失速现象的出现,参照国外飞机二元推力矢量喷管的设计,将导流板设计成由三角形板和矩形板组成的导流板,并分别对不同宽度的矩形板和不同高度的三角形板的组合进行了分析计算,得到了导流板的最大应力和最大位移分布跟三角形高度和矩形宽度之间的关系,并根据这个关系提出了优化设计方案。
In order to achieve the superiority in the air in the modern battlefield, It is very necessary for us to improve the technical and tactics capability of the fighter in the design.
The paper designed a dual-engine thrust-vectoring nozzle based on a certain type of the specific working conditions of the engine, the engine nozzle design will be a compose of the conductance, adjust board and the control board. The nozzle structure is good at simple structure, low cost, small engine changes, easy-to-use, and the system's reliability, high maintainability. The paper analysed the various components of the nozzle by using the finite element software and get the character of the composing part。The diversion of the displacement and the stress distribution is different with the distribution of traditional axial-flow nozzle, particularly the largest displacement of a great changes have taken place here。The paper dealing with a thicker and enhanced box on the diversion of local sites, the diversion of the maximum displacement and stress distribution has improved and reduced,the biggest stress and the maximum displacement position has also undergone a change, by improving the implementation of the programmer, the structure can meet the need of the engine on airflow and the safety requirements of the aircraft. This paper designed the control board as a diversion of the triangular and rectangular plates, to take into account the specific working conditions to prevent the emergence of the phenomenon wingtips stall, the United States aircraft reference to the dual thrust vectoring nozzle design。The paper analyse the control board composed of different width heights of the rectangular plates and triangular plate, get the greatest stress and displacement distribution of the control board, then we get the optimized design .
本文根据某型发动机的特定工作条件,为某型发动机改装二元推力矢量喷管进行了改装设计,将发动机喷管设计成了由导流管、调节板和导流板三部分组成的一个喷管,该结构喷管结构简单,成本低,发动机改动少,使用方便,且系统的可靠性、可维修性很好,使用寿命也很高。本文利用有限元软件对设计喷管的各个组成部件进行了分析计算,分别得出了导流管、调节板和导流板的应力分布和位移分布特征。其中导流管的应力分布和位移分布跟传统的轴流式喷管大不相同,特别是最大位移的出现位置发生了很大变化,为此,本文对导流管局部部位进行了加厚处理,并对局部部位加装了加强框,经过局部加强框的加装和局部厚度的加厚,导流管的最大应力和最大位移分布得到改善,减小了导流管的最大应力值和最大位移值,并且,最大应力和最大位移出现的位置也发生了变化,通过改进方案的实施,导流管的结构能够胜任发动机出口气流的要求,满足飞机的安全要求。本文在设计导流板时考虑到飞机特定的工作状态,为了防止翼尖失速现象的出现,参照国外飞机二元推力矢量喷管的设计,将导流板设计成由三角形板和矩形板组成的导流板,并分别对不同宽度的矩形板和不同高度的三角形板的组合进行了分析计算,得到了导流板的最大应力和最大位移分布跟三角形高度和矩形宽度之间的关系,并根据这个关系提出了优化设计方案。
In order to achieve the superiority in the air in the modern battlefield, It is very necessary for us to improve the technical and tactics capability of the fighter in the design.
The paper designed a dual-engine thrust-vectoring nozzle based on a certain type of the specific working conditions of the engine, the engine nozzle design will be a compose of the conductance, adjust board and the control board. The nozzle structure is good at simple structure, low cost, small engine changes, easy-to-use, and the system's reliability, high maintainability. The paper analysed the various components of the nozzle by using the finite element software and get the character of the composing part。The diversion of the displacement and the stress distribution is different with the distribution of traditional axial-flow nozzle, particularly the largest displacement of a great changes have taken place here。The paper dealing with a thicker and enhanced box on the diversion of local sites, the diversion of the maximum displacement and stress distribution has improved and reduced,the biggest stress and the maximum displacement position has also undergone a change, by improving the implementation of the programmer, the structure can meet the need of the engine on airflow and the safety requirements of the aircraft. This paper designed the control board as a diversion of the triangular and rectangular plates, to take into account the specific working conditions to prevent the emergence of the phenomenon wingtips stall, the United States aircraft reference to the dual thrust vectoring nozzle design。The paper analyse the control board composed of different width heights of the rectangular plates and triangular plate, get the greatest stress and displacement distribution of the control board, then we get the optimized design .
引文
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[3]范文正李明,推力矢量喷管现状和发展趋势,航空科学技术,2006年,1:21~22页。
[4]李振宇,美俄推力矢量技术差异谈,兵工科技,2007年,2:51~54页。
[5]陶增元李军程邦勤,Thrust Vector Technique,the Vital Technology of Aircraft Propulsion System ,空军工程大学学报,2000年,1(02):86~91页。
[6]M.D.Messina. Simulation Model of the F/A-18 High Angle- of-Attack Research Vehicle Utilized for the Design of Advanced Control Laws. NASA TM-110216,1996。
[7]Berrier B L,M ason M L. Static Investigation of Post-Exit Vanes for Multiaxis Thrust Vectoring,AIAA 87-1834,1987。
[8]Gar-Or B. Thrust vectoring for flight control& safety: a review. Intern .J .Turbo & Jet Engine,1 994,11.119-136。
[9]Polities M,Dugge and Hodgkinson ,Guidance, navigation and control . Aerospace America, Vo1.30, No.12, December 1992 ,pp 18-19。
[10]Mihaloew J R. Flight propulsion control integration for V/STOL ,Aircraft.(N ASA).Intern .J .Turbo& Jet Engine,Vol,9,1992。
[11]Capone F J. Comparative investigation of multiple thrust vectoring nozzles ,AIAA,92-3263。
[12]Karr C L. Two-dimensional thrust vectoring nozzle optimization techniques ,A IAA 91-0473。
[13]Fiddell J H, Franke M. Confined jet thrust vector control nozzle studies,AIAA 90-2027。
[44]Weir R A, Cowan J R. Development and test of electromechanical actuators for thrust vector control ,AIAA 93 -2458。
[15]Gar-Or B. Mathematical phenomenology for thrust vectoring induced agility comparisons .J .Aircraft ,1993, Vole 30, No.2。
[66]Johnson S. A simple dynamic engine model for use in a real- time aircraft simulation with thrust vectoring,AIAA 90-2166。
[17]Khalid S J and Faherty M F. Propulsion system flight test analysis using modeling techniques,AIAA 90-3307。
[18]Syed S A, Erhart J J and King F W,Application of CFD pitch /yaw thrust vectoringspherical convergent flap nozzles,AIAA 90-2023。
[19]Gal-Or B. Vectored propulsion. Super maneuverability and robot aircraft,Springer Veriag ,New York,1990。
[20]Froth R E. Thrust vectoring to eliminate the vertical stabilizer ,A D A079852。
[21]Warley D H,Analysis of control surface augmentation in high- performance aircraft by thrust vectoring ,AD 769495。
[22]K Gal-Or B. maximizing thrust-vectoring control power and agility metrics. Jof Aircraft,1992,29(4)。
[23]Paul W. Herrick, Fighter Aircraft Affordability, Survivability and Effectiveness Through Multi-Function Thrust-Vectoring Nozzles,Inter-national Journal of Turbo &Jet-Engines ,V o1.9,No .l , 1 992。
[24]R. Mishler & T. Wilkinson. Emerging Airframe/Propulsion Integration Technologies at General Electric,AIAA 92-3335。
[25]B. Gal-Or, V. Sherbaum, M. Lichtsinder and M. Turgemann,Complete Thrusting Vectoring Control for Future Civil Jets .F- 22 Superiority Fighter and Cruise Missles Part I: Vectored F-22,F -16 and F-15.International Journal of Turbo& Jet-Engine ,V ol.10 ,No.l, 1993。
[26]McLafferty G H, Peterson J H. Results of test of a rectangular vectoring/reversing nozzle on F-100 engine .AIAA 83一1285。Capone F J, Reubush D E. Effect of thrust vectoring and wing maneuver devices on transonic aero propulsive characteristics of a supersonic fighter .N ASA-TP-2119.1 983。
[27]Capone F J, Mason M L. Militaries aircraft control power from thrust vectoring at high angles of attack .N ASA-TM一87741,1986。
[28]贾东兵陈锐,轴対称矢量喷管设计与试验技术研究,航空发动机,2002年,1:1~3页。
[29]艾尔王衍洋屈香菊,气动推力矢量控制面融合方式研究,飞行力学,2005年,23(4):20~24页。
[30]张相毅王如根杨帆,双股气流对流体控制矢量喷管的影响,固体火箭技术,2007年,30(4):295~298页。
[31]Pavlenko, Viktor Fedorovich. Power plants with in-flight thrust vector deflection .Jan.1987。
[32]Rock S M. Integrated flight/propulsion control-Requirements and issues .J an.1 990。
[33]Weiss C, Mcdowel l P, Watts S. STOVL control integration program .N ASA-CR-195358.1994。
[34]Trittler G, Eckert E, Goeing M. Optimization aspects of an ejector type hypersonic thrust nozzle .A SME9 2-GT-402。
[35]Lewis W J. Propulsion systems for supersonic V/STOL aircraft .A SM E 89 -GT-309。
[36]Miller E H. Performance of a forward swept wing fighter utilizing thrust vectoring .A IAA 83-2482.1 983。
[37]Weir R A, Cowan J R. Development and test of electro mechanical actuators for thrust vector control. AIAA93 -2 4 58, 1993。
[38]Mclafferty G H, Peterson J L. Results of tests of a rectangular vectoring/reversing nozzle on an FIN engine , A IAA 83-1285,1983。
[39]Pollard J E. Beam-centroid tracking instrument for ion thruster’s .A D-A293654. May 1995。
[40]Ward B D, Lewis W J. Advantages of thrust vectoring for STOVL .A IAA 87-1708.J un.1 987。
[41]Cavalleri R, Tiarn W, Lewis Lynn. Experimental and theoretical comparison of the Probe Thrust Vector Control concept , AIAA 91-2476.J un.1991。
[42]Wakefield Michael E. The integrated modular engine-c on figurations ,applications and benefits .A IAA 92-1551,May 1992。
[43]Johnson Steven A. A simple dynamic engine model for use in a real- time aircraft simulation with thrust vectoring,N ASA - TM -4240.P resented at the AIAA/SAE/ASME/ASEE Joint Propulsion Conference ,Orlando ,F L,1 6-18 Jul,1990。
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