鸭式布局不同尾翼结构对弹箭滚转及其它气动特性的影响
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摘要
本文主要讨论了鸭式布局弹箭的滚转力矩特性,分析了鸭舵下洗的机理及其影响。共设计六套弹箭组合模型,通过风洞实验的方法得到了跨音速、超音速下六套弹箭组合模型的气动力数据,由实验数据分析了弹箭滚转特性、升力特性、阻力特性、俯仰力矩特性随马赫数以及攻角的变化规律,比较了不同的鸭式气动布局给上述气动特性带来的变化。分析结果表明,对于常规的鸭式布局弹箭,当鸭舵做副翼偏转进行滚转控制时,弹箭上会产生数值比较大的反向诱导滚转力矩,使鸭舵难以进行滚转控制,然而,增大鸭舵展弦比、鸭舵后掠,都减小了作用在尾翼上的反向滚转力矩,布局合理甚至能够完全消除副翼的反效现象。因此,通过改变气动布局设计,包括改变尾翼形状等等,可以提高鸭式布局弹箭的滚转控制效率,使鸭舵对弹箭进行有效滚转控制,布局的变化同时使弹箭的升力特性、阻力特性、俯仰力矩特性发生了变化,从而为弹箭的气动布局设计提供了一定的帮助。
In this thesis, the rolling moment characteristics of canard missiles are studied, the mechanism and influence of downwash of canard is analyzed. First, I design six groups of missile model, then process them by steel. Wind tunnel investigation is conducted on this six different canard configuration models over the range of Mach from 0.8 to 2.5. Based on the experiment data, I analyze the regulation of rolling characteristics, lift characteristics, drag characteristics and pitching moment characteristics with Mach number and angle of attack, and the effect of these characteristics for different canard configurations is compared. The results indicate that canards are ineffective as rolling control devices for normal canard missiles, because noticeable reverse rolling moments are induced when the canards have rolling command deflection. With canard of big aspect ratio, and sweep angle, the reversed induced rolling moments could be reduced, even the phenomenon of anti-effect has disappeared completely when the configurations are logical. Wind tunnel experiments show that some new configurations improve the rolling control efficiency, allowing the canard to execute the rolling control, with the change of configurations, its lift characteristics, drag characteristics and pitching moment characteristics also change. So, it is helpful for aerodynamic configuration design of canard missiles.
In this thesis, the rolling moment characteristics of canard missiles are studied, the mechanism and influence of downwash of canard is analyzed. First, I design six groups of missile model, then process them by steel. Wind tunnel investigation is conducted on this six different canard configuration models over the range of Mach from 0.8 to 2.5. Based on the experiment data, I analyze the regulation of rolling characteristics, lift characteristics, drag characteristics and pitching moment characteristics with Mach number and angle of attack, and the effect of these characteristics for different canard configurations is compared. The results indicate that canards are ineffective as rolling control devices for normal canard missiles, because noticeable reverse rolling moments are induced when the canards have rolling command deflection. With canard of big aspect ratio, and sweep angle, the reversed induced rolling moments could be reduced, even the phenomenon of anti-effect has disappeared completely when the configurations are logical. Wind tunnel experiments show that some new configurations improve the rolling control efficiency, allowing the canard to execute the rolling control, with the change of configurations, its lift characteristics, drag characteristics and pitching moment characteristics also change. So, it is helpful for aerodynamic configuration design of canard missiles.
引文
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[7]余旭东编著.导弹现代结构设计.国防工业出版社,2007
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[20]张彬乾,B.Laschka.前掠翼鸭式布局中鸭翼的气动特性.西北工业大学学报,1990,8(3):327-333
[21]吕志咏,蔡为民,马玉明.鸭翼双三角翼流态及气动力特性研究.空气动力学学报,1994,9,12(3):344-349
[22]牛东兵.战术导弹横滚稳定性的气动外形设计.航空兵器,No 5,1998,17-21
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[24]吴甲生,雷娟棉.制导兵器气动布局发展趋势及有关气动技术[J].北京理工大学学报,2003,23(6):665-670
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[27]马宝峰,刘沛清,邓学蓥.大迎角下鸭翼涡与边条涡的干扰特性.航空学报,Vol.26,No.6.Nov 2002
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[29]王良益.翼涡与体涡的相互干扰及其对翼涡破裂的影响.南京航空航天大学学报,Vol.26,No.2,Apr 1994
[30]雷棉娟,吴甲生.自旋尾翼导弹鸭舵的滚转控制特性.全国航空航天领域中的力学问题学术研讨会
[31]Michael G.Landers and Lamar M.Auman,"Experimental Investigation of Nose-Mounted Controls for a Hypersonic Missile",19~(th)AIAA Applied Aerodynamics Conference,AIAA 2001-2433,June 2001,Anaheim,California
[32]Michael G.Landers,Les H.Hall and Lamar M.Auman,"Aerodynamic Predictions of Pitch and Roll Control for Canard-Controlled Missiles"18~(th)AIAA Applied Aerodynamics Conference,AIAA 2000-4516,August 2000,Denver,Co
[33]Ulbrich,N,"Determination of a Rolling Moment Coefficient Correction due to Wall Interference Effects",43rd AIAA Aerospace Sciences Meeting and Exhibit;Reno,NV;USA;10-13 Ja.2005.10 pp.2005
[34]Lamar M.Auman,"Aerodynamic Characteristics of a Canard-Controlled Missile with a Free-Spining Tail",AL 35898-5252
[35]Lu Zhiyong and Zhu Liguo,"Study on forms of Vortex Beakdown over Delta wing",Feb 2004
[36]Payne F.M,"Visualization and Flow Surveys of the L.E.Vortex structure on Delta Wing Planforms",AIAA-86-0330
[37]Nelson R.C.,"Visualization Techniques for studying High Angle of Attack Separated Vortical Flows",AIAA-88-2025
[38]Reynolds,"An experimental investigation of circumstances which determine whether the motion of water shall be direct or sinuous and of the law of regisance in parallel channels",Phil.Trans.Roy.Soc.London,174(1883)
[39]A.J.Ponton and M.V.Lowson,"The Evaluation of canard couplings at High Angles of Attack",AIAA Paper 92-0281
[40]Lesieutre,Daniel J,Love,John F and Dillenius,Marnix D.F,"Prediction of the nonlinear aerodynamic characteristics of tandem-control and rolling-tail missiles",AIAA Atmospheric Flight Mechanics Conference and Exhibit,Monterey,CA,Aug.5-8,2002
[41]张天肖.“T”型尾翼跨音速颤振模型风洞实验研究.民用飞机设计与方案,1997
[42]雷娟棉,居贤铭,苗瑞生.多片尾翼布局弹箭气动特性数值计算.北京理工大学学报,2003,23(6):686-689
[43]吴甲生,雷娟棉.制导兵器气动布局发展趋势及有关气动技术.北京理工大学学报,2003,23(6):665-670
[44]Y.Neumeier,M.Hanin.装有自由旋转尾翼的鸭式导弹的滚动发散.
[45]唐敏中,王铁,张伟,徐忠利.振动鸭翼复杂流场测量.空气动力学学报,Vol.14,No.4,Dec 1996
[46]倪嘉敏.栅格翼的应用与气动特性研究.第十届全国高超声速气动力(热)学术交流会
[47]陆中荣,杨骥.栅格尾翼导弹空气动力特性的计算与分析.导弹与航天运载技术,No.3,2001,Sum No.251
[48]陈少松,赵润祥,丁则胜,谭俊杰.格栅翼的气动特性研究评述.弹道学报,Vol.11,No.2.June 1999
[49]陆中荣,王海文.栅格翼绕流特性的实验研究.流体力学实验与测量,2002,(01)
[50]陈少松,张建叶.格宽翼弦比对栅格翼气动特性的影响.南京理工大学学报,2005,(06)
[51]张建叶.格栅翼的空气动力特性实验研究.南京理工大学硕士学位论文,2004
[52]刑琳琳.远程弹滚转特性的实验研究.南京理工大学硕士学位论文,2006
[53]余永刚.亚跨音速栅格翼气动特性研究.南京理工大学硕士学位论文,2007
[54]陈霞.鸭式布局弹箭滚转气动特性的研究.南京理工大学硕士学位论文,2007
[55]陈少松,徐琴,王福华,赵润祥.格栅翼减阻特性研究.流体力学实验与测量,2001,(04)
[56]陈少松,徐琴,王福华,赵润祥.格栅翼组合体的超音速气动特性研究.弹道学报,2002,(02)
[2]纪楚群主编.导弹空气动力学.宇航出版社,1996
[3]《箭弹空气动力特性分析与计算》编写组编.箭弹空气动力特性分析与计 算.国防工业出版社,1979
[4]苗瑞生,居贤铭,吴甲生编著.导弹空气动力学.国防工业出版社,2006
[5]钱杏芳,林瑞雄,赵亚男编著.导弹飞行力学.北京理工大学出版社,2006
[6]钱翼稷编著.空气动力学.北京航空航天大学出版社,2004
[7]余旭东编著.导弹现代结构设计.国防工业出版社,2007
[8]S.S.秦编著.导弹外形设计.国防工业出版社,1965
[9]沈仲书,刘亚飞编著.弹丸空气动力学.南京理工大学,1983
[10]吕国鑫编著.飞航导弹气动设计.宇航出版社,1991
[11]徐明友,丁松滨编著.飞行动力学.科学出版社,2003
[12]臧国才,李树常编著.弹箭空气动力学.兵器工业出版社,1989
[13]王福军编著.计算流体动力学分析.清华大学出版社,2004
[14]恽起麟编著.实验空气动力学.国防工业出版社,1991
[15]恽起麟编著.风洞实验.国防工业出版社,2000
[16]李新国,方群编著.有翼导弹飞行动力学.西北工业大学出版社,2005
[17]谷良贤,温炳恒.导弹总体设计原理.西北工业大学出版社,2004
[18]曾广存,丁庆国,秦伊贤,袁幼新.鸭式布局导弹滚动气动控制方案及力矩分析.北京空气动力研究所,Vol.6 No.3,1988
[19]曾广存,丁庆国,秦伊贤.鸭式布局导弹滚动气动方案研究.北京空气动力研究所,1984
[20]张彬乾,B.Laschka.前掠翼鸭式布局中鸭翼的气动特性.西北工业大学学报,1990,8(3):327-333
[21]吕志咏,蔡为民,马玉明.鸭翼双三角翼流态及气动力特性研究.空气动力学学报,1994,9,12(3):344-349
[22]牛东兵.战术导弹横滚稳定性的气动外形设计.航空兵器,No 5,1998,17-21
[23]马宝峰,刘沛清,邓学蓥.近距耦合鸭式布局气动研究进展.空气动力学学报,2003,9,21(3):320-329
[24]吴甲生,雷娟棉.制导兵器气动布局发展趋势及有关气动技术[J].北京理工大学学报,2003,23(6):665-670
[25]雷娟棉,居贤铭,吴甲生.自旋尾翼鸭式布局导弹的滚转特性.北京理工大学学报,Vol.24,No.8,Aug 2004
[26]曾广存,丁庆国,秦伊贤.“T”型翼片组合尾翼导弹气动特性研究.北京空气动力研究所,1984
[27]马宝峰,刘沛清,邓学蓥.大迎角下鸭翼涡与边条涡的干扰特性.航空学报,Vol.26,No.6.Nov 2002
[28]张彬乾,杨永年.鸭式布局旋涡干扰特性研究.西北工业大学学报,Vol.9,No.4,Oct 1991
[29]王良益.翼涡与体涡的相互干扰及其对翼涡破裂的影响.南京航空航天大学学报,Vol.26,No.2,Apr 1994
[30]雷棉娟,吴甲生.自旋尾翼导弹鸭舵的滚转控制特性.全国航空航天领域中的力学问题学术研讨会
[31]Michael G.Landers and Lamar M.Auman,"Experimental Investigation of Nose-Mounted Controls for a Hypersonic Missile",19~(th)AIAA Applied Aerodynamics Conference,AIAA 2001-2433,June 2001,Anaheim,California
[32]Michael G.Landers,Les H.Hall and Lamar M.Auman,"Aerodynamic Predictions of Pitch and Roll Control for Canard-Controlled Missiles"18~(th)AIAA Applied Aerodynamics Conference,AIAA 2000-4516,August 2000,Denver,Co
[33]Ulbrich,N,"Determination of a Rolling Moment Coefficient Correction due to Wall Interference Effects",43rd AIAA Aerospace Sciences Meeting and Exhibit;Reno,NV;USA;10-13 Ja.2005.10 pp.2005
[34]Lamar M.Auman,"Aerodynamic Characteristics of a Canard-Controlled Missile with a Free-Spining Tail",AL 35898-5252
[35]Lu Zhiyong and Zhu Liguo,"Study on forms of Vortex Beakdown over Delta wing",Feb 2004
[36]Payne F.M,"Visualization and Flow Surveys of the L.E.Vortex structure on Delta Wing Planforms",AIAA-86-0330
[37]Nelson R.C.,"Visualization Techniques for studying High Angle of Attack Separated Vortical Flows",AIAA-88-2025
[38]Reynolds,"An experimental investigation of circumstances which determine whether the motion of water shall be direct or sinuous and of the law of regisance in parallel channels",Phil.Trans.Roy.Soc.London,174(1883)
[39]A.J.Ponton and M.V.Lowson,"The Evaluation of canard couplings at High Angles of Attack",AIAA Paper 92-0281
[40]Lesieutre,Daniel J,Love,John F and Dillenius,Marnix D.F,"Prediction of the nonlinear aerodynamic characteristics of tandem-control and rolling-tail missiles",AIAA Atmospheric Flight Mechanics Conference and Exhibit,Monterey,CA,Aug.5-8,2002
[41]张天肖.“T”型尾翼跨音速颤振模型风洞实验研究.民用飞机设计与方案,1997
[42]雷娟棉,居贤铭,苗瑞生.多片尾翼布局弹箭气动特性数值计算.北京理工大学学报,2003,23(6):686-689
[43]吴甲生,雷娟棉.制导兵器气动布局发展趋势及有关气动技术.北京理工大学学报,2003,23(6):665-670
[44]Y.Neumeier,M.Hanin.装有自由旋转尾翼的鸭式导弹的滚动发散.
[45]唐敏中,王铁,张伟,徐忠利.振动鸭翼复杂流场测量.空气动力学学报,Vol.14,No.4,Dec 1996
[46]倪嘉敏.栅格翼的应用与气动特性研究.第十届全国高超声速气动力(热)学术交流会
[47]陆中荣,杨骥.栅格尾翼导弹空气动力特性的计算与分析.导弹与航天运载技术,No.3,2001,Sum No.251
[48]陈少松,赵润祥,丁则胜,谭俊杰.格栅翼的气动特性研究评述.弹道学报,Vol.11,No.2.June 1999
[49]陆中荣,王海文.栅格翼绕流特性的实验研究.流体力学实验与测量,2002,(01)
[50]陈少松,张建叶.格宽翼弦比对栅格翼气动特性的影响.南京理工大学学报,2005,(06)
[51]张建叶.格栅翼的空气动力特性实验研究.南京理工大学硕士学位论文,2004
[52]刑琳琳.远程弹滚转特性的实验研究.南京理工大学硕士学位论文,2006
[53]余永刚.亚跨音速栅格翼气动特性研究.南京理工大学硕士学位论文,2007
[54]陈霞.鸭式布局弹箭滚转气动特性的研究.南京理工大学硕士学位论文,2007
[55]陈少松,徐琴,王福华,赵润祥.格栅翼减阻特性研究.流体力学实验与测量,2001,(04)
[56]陈少松,徐琴,王福华,赵润祥.格栅翼组合体的超音速气动特性研究.弹道学报,2002,(02)