扰流片式推力矢量喷管气动特性数值模拟研究
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摘要
为了满足工程应用中扰流片式推力矢量喷管控制率建模以及优化设计的需求,本文选取了三种几何外形的扰流片,并通过数值模拟手段,研究了扰流片几何形状对于轴对称喷管推力矢量气动特性的影响规律,提出了减小扰流片推力损失的设计方法。数值模拟结果表明,推力矢量角与推力损失系数都随着扰流片插入高度的增加而增加;对于矩形扰流片,可以通过增加扰流片宽度的方式减小推力损失,对于扇形扰流片,可以通过减小上圆弧圆心与扇形顶点距离的方式减小推力损失;在插入高度及面积一定时,对比不同形状的扰流片,弧顶矩形扰流片的推力矢量角及推力损失系数均为最大,圆形扰流片均为最小。
The jet tab thrust vector control technology discussed in this paper has outstanding advantages in less thrust loss,faster response,stronger control forces,compared with jet vane technology,which meet the needs of future air combat for advanced air-to-air missile.In order to meet the requirements of control rate modeling and optimization of jet tab thrust vector control system,conical nozzle with spoilers in three different shapes,which are round,rectangle and sector,are numerically simulated.The effects of spoiler geometry parameters on the thrust vector performance are analyzed.The design method of reducing thrust loss of spoiler is presented.The results indicate that thrust vector angle and thrust loss ratio increases with increasing insertion depth of the spoiler.For the rectangular spoiler,thrust loss ratio decreases with the increase of spoiler width;and for the sector spoiler,thrust loss ratio decreases with the increase of the design parameter l.When the spoiler inserted depth and inserted area is constant,rectangle spoiler has the maximum thrust vector angle and thrust loss ratio,while round spoiler has the minimum.
The jet tab thrust vector control technology discussed in this paper has outstanding advantages in less thrust loss,faster response,stronger control forces,compared with jet vane technology,which meet the needs of future air combat for advanced air-to-air missile.In order to meet the requirements of control rate modeling and optimization of jet tab thrust vector control system,conical nozzle with spoilers in three different shapes,which are round,rectangle and sector,are numerically simulated.The effects of spoiler geometry parameters on the thrust vector performance are analyzed.The design method of reducing thrust loss of spoiler is presented.The results indicate that thrust vector angle and thrust loss ratio increases with increasing insertion depth of the spoiler.For the rectangular spoiler,thrust loss ratio decreases with the increase of spoiler width;and for the sector spoiler,thrust loss ratio decreases with the increase of the design parameter l.When the spoiler inserted depth and inserted area is constant,rectangle spoiler has the maximum thrust vector angle and thrust loss ratio,while round spoiler has the minimum.
引文
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[13]李国占.发动机喷管推力矢量控制研究[D].黑龙江:哈尔滨工业大学,2014:30-36.LI G Z.Research on thrust vector control of engine nozzle[D].Heilongjiang:Harbin Institute of Technology,2014:30-36.(in Chinese)
[14]贾洪印,吴晓军,周乃春,等.导弹侧向喷流干扰及多喷口耦合效应数值模拟[J].空气动力学学报,2017,35(6):857-840.JIA H Y,WU X J,ZHOU N C,et al.Numerical investigation on coupling effects of multiple spouts and lateral jet interaction over missile missile configuration[J].Acta Aerodynamica Sinica,2017,35(6):857-840.(in Chinese)
[15]BLAZEK J.Computational fluid dynamics:Principles and applications[M].Switzerland:Alstom Power Ltd,2001:41-45.
[16]BACK L H,CUFFEL R F.Detection of oblique shocks in a conical nozzle with a circular-arc throat[J].AIAA Journal,1966,12(4):2219-2221.
[2]谢永强,李舜,周须峰,等.推力矢量技术在空空导弹上的应用分析[J].科学技术与工程,2009,20(9):6110-6113.XIE Y Q,LI S,ZHOU X F,et al.The application analysis of thrust vector control systems of air to air missile[J].Science Technology and Engineering,2009,20(9):6110-6113.(in Chinese)
[3]BREVIG O,SLEIGH K,CASEBOLT R,et al.Underwater test qualification of the Tomahawk booster and jet tab TVCsystem Thrust Vector Control[C]//AIAA,Sae,&Asme,Joint Propulsion Conference,Las Vegas,Nev,June,AIAA 13P.2013.
[4]钟华.扰流片式弹射火箭推力矢量控制技术研究[D].西安:西北工业大学,2005.ZHONG H.Study on a thrust-vector control technique of the ejection-rocket with the spoiler[D].Xi’an:Northwestern Polytechnical University,2005.(in Chinese)
[5]HOLLSTEIN H J.Jet tab thrust vector control[J].Journal of Spacecraft and Rockets,1965,2(6):927-930.
[6]EATOUGH R G.Jet tab thrust vector control system demonstration[R].AIAA-71-752,1971.
[7]EATOUGH R G.Improved jet tab thrust vector control for the RGM-34CBooster[R].AD 9-13,1986.
[8]THANIGAIARASU S,JAYAPRAKASH S,et al.Influence of tab geometry and its orientation on under-expanded sonic jets[J].Aerospace Engineering,2007,331-336.
[9]STEFFEN C J,REDDY D R,ZAMAN K B M Q.Numerical modeling of jet entrainment for nozzles fitted with delta tabs[R].AIAA-97-0709,1997.
[10]杨晓光,林学书.R-73弹推力矢量及副翼系统结构分析[J].航空兵器,1998,2:11-16.YANG X G,LIN X S.Structure analysis of thrust vector and aileron systems of R-73missile[J].Aero Weaponry,1998,2:11-16.(in Chinese)
[11]韩文超.扰流片式推力矢量控制系统研究[D].南京:南京理工大学,2011.HAN W C.Research on jet tab thrust vector control system[D].Nanjing:Nanjing University of Science and Technology,2011.(in Chinese)
[12]崔业兵,陈雄,周长省,等.扰流片推力矢量控制系统动态特性研究[J].推进技术,2013,34(8):1030-1034.CUI Y B,CHEN X,ZHOU C S,et al.Research on spoiler dynamic characteristic for thrust vector control[J].Journal of Propulsion Technology,2013,34(8):1030-1034.(in Chinese)
[13]李国占.发动机喷管推力矢量控制研究[D].黑龙江:哈尔滨工业大学,2014:30-36.LI G Z.Research on thrust vector control of engine nozzle[D].Heilongjiang:Harbin Institute of Technology,2014:30-36.(in Chinese)
[14]贾洪印,吴晓军,周乃春,等.导弹侧向喷流干扰及多喷口耦合效应数值模拟[J].空气动力学学报,2017,35(6):857-840.JIA H Y,WU X J,ZHOU N C,et al.Numerical investigation on coupling effects of multiple spouts and lateral jet interaction over missile missile configuration[J].Acta Aerodynamica Sinica,2017,35(6):857-840.(in Chinese)
[15]BLAZEK J.Computational fluid dynamics:Principles and applications[M].Switzerland:Alstom Power Ltd,2001:41-45.
[16]BACK L H,CUFFEL R F.Detection of oblique shocks in a conical nozzle with a circular-arc throat[J].AIAA Journal,1966,12(4):2219-2221.