考虑进排气的飞翼静、动态气动特性数值模拟
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摘要
采用计算流体力学(CFD)数值模拟技术,以二维模型为例,建立了基于小幅度非定常运动的动导数计算方法,构建了考虑喷流引射效应的进排气模型、考虑管道效应的通气模型以及常规的保形模型,分别对其静态以及动态气动特性进行了数值模拟计算,并辨识了其纵向俯仰力矩系数组合动导数。研究表明:非定常动导数辨识方法较为准确可靠,相比保形模型,进排气以及通气模型的静态失速攻角(AOAs)增大,升力系数、阻力系数及俯仰力矩系数也增大,但力矩系数斜率基本不变,说明静态稳定性差异不大。而相同攻角下,进排气影响下的俯仰力矩系数组合动导数绝对值最大,表明了进排气模型具有最大的动态阻尼,而通气模型次之,保形模型的动导数绝对值最小。
Based on the computational fluid dynamics(CFD)technique,a two-dimensional model was adopted to carry out the simulation.A method to identify combined dynamic derivative was developed and testified with small amplitude oscillation,then three computational models:the model with intake and exhaust effect,the model with ventilating effect and traditional fairing model,were built,furthermore the stable and dynamic aerodynamics of the models was numerically simulated,and the dynamic derivatives were also calculated.Results and their analysis indicate that the method to obtain dynamic derivative is reliable,and compared with faring model,the stable stall angles of attack(AOAs)of the other two models are bigger with increasing lift,drag and pitching moment coefficients,however,the slopes of pitching moment coefficient are almost the same,showing there is no clear difference of static stabilities among the models.Moreover,the absolute value of dynamic derivative of intake and exhaust models is the largest for all the models at the same AOA,showing this model has the largest dynamic damping,the model with ventilating effect takes the second place and the fairing model has the minimum value.
Based on the computational fluid dynamics(CFD)technique,a two-dimensional model was adopted to carry out the simulation.A method to identify combined dynamic derivative was developed and testified with small amplitude oscillation,then three computational models:the model with intake and exhaust effect,the model with ventilating effect and traditional fairing model,were built,furthermore the stable and dynamic aerodynamics of the models was numerically simulated,and the dynamic derivatives were also calculated.Results and their analysis indicate that the method to obtain dynamic derivative is reliable,and compared with faring model,the stable stall angles of attack(AOAs)of the other two models are bigger with increasing lift,drag and pitching moment coefficients,however,the slopes of pitching moment coefficient are almost the same,showing there is no clear difference of static stabilities among the models.Moreover,the absolute value of dynamic derivative of intake and exhaust models is the largest for all the models at the same AOA,showing this model has the largest dynamic damping,the model with ventilating effect takes the second place and the fairing model has the minimum value.
引文
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[2]陈世春,黄沛霖,姬金祖.典型隐身飞机的RCS起伏统计特性[J].航空学报,2014,35(12):3304-3314.CHEN Shichun,HUANG Peilin,JI Jinzu.Radar cross section fluctuation characteristics of typical stealth aircraft[J].Acta Aeronautica et Astronautica Sinica,2014,35(12):3304-3314.(in Chinese)
[3]郁新华,陶于金,张琳,等.飞翼布局无人机进排气影响及机理分析[J].北京航空航天大学学报,2015,41(5):786-792.YU Xinhua,TAO Yujin,ZHANG Lin,et al.Influence of engine inlet and exhaust on flying wing UAV and its mechanism analysis[J].Journal of Beijing University of Aeronautics and Astronautics,2015,41(5):786-792.(in Chinese)
[4]张乐,周洲,许晓平,等.飞翼无人机保形进排气系统动力数值模拟与流场特性分析[J].西北工业大学学报,2015,33(3):353-360.ZHANG Le,ZHOU Zhou,XU Xiaoping,et al.Numerical simulation of power and flow field characteristics of conformal intake and exhaust for flying wing unmanned aerial vehicle[J].Journal of Northwestern Polytechnical University,2015,33(3):353-360.(in Chinese)
[5]HYOUNGJIN K,MENGSING L.Flow simulation of N2B hybrid wing body configuration[R].AIAA-2012-0838,2012.
[6]谭兆光,陈迎春.机体/动力装置一体化分析中的动力影响效应数值模拟[J].航空动力学报,2009,24(8):1766-1772.TAN Zhaoguang,CHEN Yingchun.Numerical simulation method for the powered effects in airframe/propulsion in tegration analysis[J].Journal of Aerospace Power,2009,24(8):1766-1772.(in Chinese)
[7]JOHANSSON M.Propulsion integration in an UAV[R].AIAA-2006-2834,2006.
[8]方振平,陈万春,张曙光.航空飞行器飞行动力学[M].北京:北京航空航天大学出版社,2005.
[9]马松辉,吴成富,陈怀民.飞翼飞机稳定性与操纵性研究[J].飞行力学,2006,24(3):17-21.MA Songhui,WU Chenfu,CHWN Huaimin.Study on stability and maneuverability of flying wing aircraft[J].Flight Dynamics,2006,24(3):17-21.(in Chinese)
[10]张子军,王磊,王立新,等.大展弦比飞翼布局飞机的三轴稳定特性[J].系统工程理论和实践,2012,32(5):1130-1135.ZHANG Zijun,WANG Lei,WANG Lixin,et al.Three-axis stability characteristics of flying wing with high aspect ratio[J].System Engineering Theory and Practice,2012,32(5):1130-1135.(in Chinese)
[11]刘绪,刘伟,周云龙,等.吸气式内外流一体化飞行器动导数数值模拟[J].空气动力学学报,2015,33(2):147-155.LIU Xu,LIU Wei,ZHOU Yunlong,et al.Numerical simulation of dynamic derivatives for air breathing hypersonic vehicle[J].Acta Aerodynamica Sinca,2015,33(2):147-155.(in Chinese)
[12]叶川,马东立.利用CFD技术计算飞行器动导数[J].北京航空航天大学学报,2013,39(2):196-200.YE Chuan,MA Dongli.Aircraft dynamic derivatives calculation using CFD techniques[J].Journal of Beijing University of Aeronautics and Astronautics,2013,39(2):196-200.(in Chinese)
[13]孙涛,高正红,黄江涛.基于CFD的动导数计算与减缩频率影响分析[J].飞行力学,2011,29(4):15-18.SUN Tao,GAO Zhenghong,HUANG Jiangtao.Identify of aircraft dynamic derivatives based on CFD technology and analysis of reduce frequency[J].Flight Dynamics,2011,29(4):15-18.(in Chinese)
[14]RONCH A D,VALLESPIN D.Computation of dynamic derivatives using CFD[R].AIAA-2010-4817,2010.
[15]席柯,阎超,黄宇,等.俯仰阻尼导数分量的CFD数值模拟[J].北京航空航天大学学报,2015,41(2):222-227.XI Ke,YAN Chao,HUANG Yu,et al.Numeriacal simulation of individual components of pitcing-damping coefficient sum[J].Journal of Beijing University of Aeronautics and Astronautics,2015,41(2):222-227.(in Chinese)
[16]JEAN-FRANCOIS L,STEPHANE M,DOMINIQUE F.Static and dynamic derivatives on generic UCAV without and with leading edge control[R].AIAA-2014-2391,2014.
[17]JEAN-FRANCOIS L,STEPHANE M.SACCON CFD static and dynamic derivatives using elsA[R].AIAA-2010-4562,2010.
[18]VICROY D D,LOESER T D,SCHUTTE A.SACCON forced oscillation tests at DNW-NWB and NASA Langley14×22-foot tunnel[R].AIAA-2010-4394,2010.
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