基于滑移网格技术的翼伞动导数分析
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摘要
翼伞在航天回收领域有着广泛的应用前景,为了提高对翼伞动稳定性认识,文章针对某型号的翼伞进行动导数的分析。基于滑移网格技术,采用计算流体学的方法对翼伞进行了三维数值模拟。重点分析了翼伞做小幅度俯仰、偏航和滚转运动时的动导数,通过改变攻角和减缩频率这两项重要参数,获取了多组力矩系数迟滞曲线,利用时间平均法对非定常气动力数据进行处理,得到了翼伞绕三个坐标轴的阻尼系数。计算结果表明:翼伞在小攻角下做小幅度强迫运动时,在俯仰和滚转方向上阻尼导数为负,翼伞具有俯仰和偏航方向上的动稳定性,在偏航方向阻尼导数为正,翼伞不具有偏航方向的动稳定性;攻角和减缩频率的选取均会影响翼伞阻尼导数的计算结果,其中,攻角的增加不仅能影响迟滞环面积的大小还能影响迟滞环的动态特性,使翼伞的动稳定性发生变化,而减缩频率的改变仅影响迟滞环面积的大小,对偏航方向的动稳定性没有影响。
Parofil in the field of spacecraft recovery has widely prospect. To improve the understanding of dynamic stability of the specific parafoil, the dynamic derivative of a type of parafoil is analyzed in this paper. Based on the Computational Fluid Dynamics(CFD), a three-dimensional numerical simulation was completed by using sliding mesh. The emphasis is on the analysis of the small amplitude pitch, yaw and roll oscillation. Furthermore, different angles of attack and the reduction of frequency are choose to achieve the hysteresis curve of moment coefficient, and a time average method was built to calculate damp dynamic derivative around three axes. The results show that when the parafoil moves in small amplitude oscillatory motion at small angle of attack, the dynamic derivative is negative in the direction of pitch and roll. It has the dynamic stability in pitch and roll direction. However, in the yaw direction, the dynamic derivative is positive which means that it is unstable. Angle of attack and the reduce frequency would affect the dynamic derivative of parafoil, the increment of angle of attack can not only affect the size of hysteresis loop but also the dynamic characteristics of hysteresis loop, thus changing the dynamic stability. However, reducing frequency only affects the size of hysteresis loop, the dynamic stability will not change.
Parofil in the field of spacecraft recovery has widely prospect. To improve the understanding of dynamic stability of the specific parafoil, the dynamic derivative of a type of parafoil is analyzed in this paper. Based on the Computational Fluid Dynamics(CFD), a three-dimensional numerical simulation was completed by using sliding mesh. The emphasis is on the analysis of the small amplitude pitch, yaw and roll oscillation. Furthermore, different angles of attack and the reduction of frequency are choose to achieve the hysteresis curve of moment coefficient, and a time average method was built to calculate damp dynamic derivative around three axes. The results show that when the parafoil moves in small amplitude oscillatory motion at small angle of attack, the dynamic derivative is negative in the direction of pitch and roll. It has the dynamic stability in pitch and roll direction. However, in the yaw direction, the dynamic derivative is positive which means that it is unstable. Angle of attack and the reduce frequency would affect the dynamic derivative of parafoil, the increment of angle of attack can not only affect the size of hysteresis loop but also the dynamic characteristics of hysteresis loop, thus changing the dynamic stability. However, reducing frequency only affects the size of hysteresis loop, the dynamic stability will not change.
引文
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[10]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 Jangtao.Identify of Aircraft Dynamic Derivatives Based on CFD Technology and Analysis of Reduce Frequency[J].Flight Dynamics,2011,29(4):15-18.(in Chinese)
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[14]汪龙芳,贺卫亮.基于索膜有限元模型的翼伞气动变形仿真[J].北京航空航天大学学报,2017,43(1):47-52.WANG Longfang,HE Weiliang.Parafoil Aerodynamic Deformation Simulation Based on Cable-membrane Finite Element Model[J].Journal of Beijing University of Aeronautics and Astronautics,2017,43(1):47-52.(in Chinese)
[15]黄炎,张红英,杨璐瑜,等.前缘切口参数对大型冲压式翼伞的性能影响分析[J].航天返回与遥感,2017,38(5):10-17.HUANG Yan,ZHANG Hongying,YANG Luyu,et al.Analysis of Leading Edge Cut Parameters on Performance of Large Ram-air Parachute[J].Spacecraft Recovery&Remote Sensing,2017,38(5):10-17.(in Chinese)
[16]ETKIN B.Dynamics of Flight:Stability and Control[M].New York and London:John Wiley and Sons,Inc.,1959.
[17]汪龙芳,贺卫亮,王世超.伞衣透气性对翼伞气动特性的影响[J].北京航空航天大学学报,2017,43(10):2021-2029.WANG Longfang,HE Weiliang,WANG Shichao.Effects of Canopy's Air Permeability on Parafoil Aerodynamic Performance[J].2017,43(10):2021-2029.(in Chinese)
[18]JANN T.Aerodynamic Coefficients for a Parafoil Wing with Arc Anhedral-theoretical and Experimental Results[C]//17th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar.California,2003.
[2]GREEN L,SPENCE A,MURPHY P.Computational Methods for Dynamic Stability and Control Derivatives[R].AIAA2004-0015,2004.
[3]刘绪,刘伟,柴振霞,等.飞行器动态稳定性参数计算方法研究进展[J].航空学报,2016,37(8):2348-2369.LIU Xu,LIU Wei,CHAI Zhenxia,et al.Research Progress of Numerical Method of Dynamic Stability Derivatives of Aircraft[J].Acta Aeronautica et Astronautica Sinica,2016,37(8):2348-2369.(in Chinese)
[4]PARK S H,KIM Y,KWON J H.Prediction of Dynamic Damping Coefficients Using Unsteady Dual-time Stepping Method[C]//AIAA Aerospace Sciences Meeting&Exhibit,2002.
[5]MURMAN S M.Reduced-frequency Approach for Calculating Dynamic Derivatives[J].AIAA Journal,2005,45(6):2005-2840.
[6]刘伟,牟斌.类升力体俯仰阻尼特性数值研究[C]//第十届全国计算流体力学会议论文集.绵阳,2000:381-386.LIU Wei,MOU Bin.Numerical Study of Damping-in-pitch Characteristics for Liftbody-type[C]//National Conference on computational fluid dynamics.Mianyang,2000:381-386.(in Chinese)
[7]刘伟,牟斌.高超声速滚转阻尼导数数值模拟[J].飞行力学,2000,18(2):27-29.LIU Wei,MOU Bin.Numerical Simulation of Damping-in-roll Derivatives of Blunt Cone for Hypersonic Flow[J].Flight Dynamics,2000,18(2):27-29.(in Chinese)
[8]刘伟,瞿章华.强迫振动法求解偏航阻尼导数[J].推进技术,1998,19(3):30-32.LIU Wei,QU Zhanghua.Calculation of Damping-in-yaw Derivatives by Forced Oscillation Method[J].Journal of Propulsion Technology,1998,19(3):30-32.(in Chinese)
[9]米百刚,詹浩,樊华羽.飞行器组合及单独动导数数值求解方法研究[J].西北工业大学学报,2015,33(4):540-545.MI Baigang,ZHAN Hao,FAN Huayu.Calculating Combined and Single Dynamic Derivatives of Flight Vehicle[J].Journal of Northwestern Polytechnical University,2015,33(4):540-545.(in Chinese)
[10]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 Jangtao.Identify of Aircraft Dynamic Derivatives Based on CFD Technology and Analysis of Reduce Frequency[J].Flight Dynamics,2011,29(4):15-18.(in Chinese)
[11]苗伟.飞机横向非定常气动力特性研究[D].南京:南京航空航天大学,2007.MIAO Wei.Research on Lateral Direction Unsteady Aerodynamic Characteristics of Aircraft[D].Nanjing:Nanjing University of Aeronautics and Astronautics,2007.(in Chinese)
[12]朱旭,曹义华.翼伞弧面下反角、翼型和前缘切口对翼伞气动性能的影响[J].航空学报,2012,33(7):1189-2007.ZHU Xu,CAO Yihua.Effects of Arc-anhedral Angle,Airfoil and Leading Edge Cut on Parafoil Aerodynamic Performance[J].Acta Aeronautica et Astronautica Sinica,2012,33(7):1189-1200.(in Chinese)
[13]朱旭,曹义华.翼伞平面形状对翼伞气动性能的影响[J].航空学报,2011,32(11):1998-2007.ZHU Xu,CAO Yihua.Numerical Simulation of Platform Geometry Effect on Parafoil Aerodynamic Performance[J].Acta Aeronautica et Astronautica Sinica,2011,32(11):1998-2007.(in Chinese)
[14]汪龙芳,贺卫亮.基于索膜有限元模型的翼伞气动变形仿真[J].北京航空航天大学学报,2017,43(1):47-52.WANG Longfang,HE Weiliang.Parafoil Aerodynamic Deformation Simulation Based on Cable-membrane Finite Element Model[J].Journal of Beijing University of Aeronautics and Astronautics,2017,43(1):47-52.(in Chinese)
[15]黄炎,张红英,杨璐瑜,等.前缘切口参数对大型冲压式翼伞的性能影响分析[J].航天返回与遥感,2017,38(5):10-17.HUANG Yan,ZHANG Hongying,YANG Luyu,et al.Analysis of Leading Edge Cut Parameters on Performance of Large Ram-air Parachute[J].Spacecraft Recovery&Remote Sensing,2017,38(5):10-17.(in Chinese)
[16]ETKIN B.Dynamics of Flight:Stability and Control[M].New York and London:John Wiley and Sons,Inc.,1959.
[17]汪龙芳,贺卫亮,王世超.伞衣透气性对翼伞气动特性的影响[J].北京航空航天大学学报,2017,43(10):2021-2029.WANG Longfang,HE Weiliang,WANG Shichao.Effects of Canopy's Air Permeability on Parafoil Aerodynamic Performance[J].2017,43(10):2021-2029.(in Chinese)
[18]JANN T.Aerodynamic Coefficients for a Parafoil Wing with Arc Anhedral-theoretical and Experimental Results[C]//17th AIAA Aerodynamic Decelerator Systems Technology Conference and Seminar.California,2003.