方形截面飞行器多配平点时的运动特性分析
|
摘要
飞行器从发射阶段到巡航阶段,飞行速度跨度很大,而随着马赫数的变化,飞行器的稳定特性可能会发生显著改变,甚至会发生配平点数量改变的极端情况,对飞行安全产生不利影响.针对某方形截面细长飞行器外形,采用数值模拟的手段,研究飞行器由稳定转变为不稳定、由单个配平点转变为3个配平点后,其运动特性变化的问题.研究表明,该飞行器存在一临界马赫数,低于该马赫数,飞行器俯仰方向存在唯一的配平攻角;大于临界马赫数,飞行器配平点转变为3个,新衍生的两个配平点是稳定的,而原有的配平点转变为不稳定的.在3个配平点情况下,飞行器的俯仰运动在相图上呈现鞍结点分岔形态,且最终收敛位置对初值条件高度敏感.飞行器可能收敛到其中的一个稳定配平点,但来流条件的微小变化,就有可能使飞行器的收敛位置转变到另一个配平点.
The velocity range of vehicle is quite considerable from launch phase to cruise phase, and the stability would be significantly altered with the change of Mach number, even worse, the number of trim angle of attack may be altered in some cases. Variety of kinematic characteristics is studied using the numerical simulation method on a square cross section vehicle which was changed from stable to instable, from one trim angle of attack to three trim angles of attack with the increase of Mach number. The simulation results show the existence of the critical Mach number Mcr in the aspect of stability. The vehicle is stable nearby the unique equilibrium point where Ma is smaller than Mcr; otherwise, the number of equilibrium points would increase to three, the pre-equilibrium point is instable and the two new equilibrium points are stable. The saddle-node bifurcation phenomenon will take place in the pitching motion of the vehicle in case of having three equilibrium points, and the final convergent position is extremely sensitive to the variety of initial condition. The pitching motion could be convergent to one trim angle of attack under certain conditions, but the convergence may alter to the other trim angle of attack with little change in the initial conditions.
The velocity range of vehicle is quite considerable from launch phase to cruise phase, and the stability would be significantly altered with the change of Mach number, even worse, the number of trim angle of attack may be altered in some cases. Variety of kinematic characteristics is studied using the numerical simulation method on a square cross section vehicle which was changed from stable to instable, from one trim angle of attack to three trim angles of attack with the increase of Mach number. The simulation results show the existence of the critical Mach number Mcr in the aspect of stability. The vehicle is stable nearby the unique equilibrium point where Ma is smaller than Mcr; otherwise, the number of equilibrium points would increase to three, the pre-equilibrium point is instable and the two new equilibrium points are stable. The saddle-node bifurcation phenomenon will take place in the pitching motion of the vehicle in case of having three equilibrium points, and the final convergent position is extremely sensitive to the variety of initial condition. The pitching motion could be convergent to one trim angle of attack under certain conditions, but the convergence may alter to the other trim angle of attack with little change in the initial conditions.
引文
1 Birch T J,Cleminson J R.Aerodynamic characteristics of a square cross-section missile configuration at supersonic speeds.In:22nd Applied Aerodynamics Conference and Exhibit.Providence,2004.AIAA 2004-5197
2 陈琦,陈坚强,袁先旭,等.飞行器俯仰振荡对滚转特性的影响.力学学报,2016,48:1290–1300
3 Mahjoob S,Mani M,Taeibi-Rahni M.Aerodynamic analysis of circular and noncircular bodies using computational and semi-empirical methods.J Aircraft,2004,41:399–402
4 孙凯军,宋文萍,韩忠华.基于Kriging模型的高超声速舵面优化设计.航空计算技术,2012,42:9–12
5 陈坚强,陈琦,袁先旭,等.方形截面飞行器上仰机动对滚转特性影响的数值模拟研究.航空学报,2016,37:2565–2573
6 陶洋,袁先旭,范召林,等.方形截面导弹摇滚特性数值研究.空气动力学学报,2010,28:285–290
7 Sahu J,Silton S,Heavey K.Numerical computations of supersonic flow over non-axisymmetric configurations.In:22nd Applied Aerodynamics Conference and Exhibit.Providence,2004.AIAA2004-5456
8 C Hoke,V Burnley,G Schwabacher.Aerodynamic analysis of complex missile configurations using AVUS(Air Vehicles Unstructured Solver).In:22nd Applied Aerodynamics Conference and Exhibit.Providence,2004.AIAA2004-5452
9 J Sahu,K Heavey.Computations of supersonic flow over a complex elliptical missile configuration.In:AIAA Atmospheric Flight Mechanics Conference.Chicago,2009.AIAA2009-5714
10 李剑,李斌,敬代勇.方形截面导弹气动特性数值研究.弹箭与制导学报,2015,35:111–113
11 Floyd J Wilcox,Trevor J Birch.Force,surface pressure,and flowfield measurements on a slender missile configuration with square cross-section at supersonic speeds.In:22nd Applied Aerodynamics Conference and Exhibit.Providence,2004.AIAA2004-5451
12 Birch T J,Petterson K.CFD predictions of square and elliptic cross-section missile configurations at supersonic speeds.In:22nd Applied Aerodynamics Conference and Exhibit.Providence,2004.AIAA2004-5453
13 James S G,Benjamin S K,Randolph P L,et al.Crew Exploration Vehicle(CEV)crew module shape selection analysis and CEV aeroscience project overview.In:45th AIAA Aerospace Sciences Meeting and Exhibit.Reno,2007.AIAA2007-603
14 Matsumoto S,Kondoh Y,Nagai S,et al.Aerodynamic oscillation and attitude control analysis for reentry capsule using OREX flight data and wind tunnel data.In:AIAA Guidance,Navigation,and Control Conference.San Diego,2016
15 Zhang H X,Zhang Z,Yuan X X,et al.Physical analysis and numerical simulation for the dynamic behaviour of vehicles in pitching oscillations or rocking motions.Sci China Ser E-Tech Sci,2007,50:385–401
16 张涵信,袁先旭,叶友达,等.飞船返回舱俯仰振荡的动态稳定性研究.空气动力学学报,2002,20:247–259
17 袁先旭,陈琦,张涵信,等.再入飞行器失稳的分叉理论分析与数值仿真验证.气体物理,2016,1:12–26
18 Zhang H X,Zhang F G.NND schemes and their application to numerical simulation of two and three dimensional flows.Adv Appl Mech,1991,29 :193–256
19 Jameson A.Time dependent calculation using multi-grid with application to unsteady flows past airfoils and wings.In:10th Computational Fluid Dynamics Conference.Honolulu,1991.AIAA-1991-1596
2 陈琦,陈坚强,袁先旭,等.飞行器俯仰振荡对滚转特性的影响.力学学报,2016,48:1290–1300
3 Mahjoob S,Mani M,Taeibi-Rahni M.Aerodynamic analysis of circular and noncircular bodies using computational and semi-empirical methods.J Aircraft,2004,41:399–402
4 孙凯军,宋文萍,韩忠华.基于Kriging模型的高超声速舵面优化设计.航空计算技术,2012,42:9–12
5 陈坚强,陈琦,袁先旭,等.方形截面飞行器上仰机动对滚转特性影响的数值模拟研究.航空学报,2016,37:2565–2573
6 陶洋,袁先旭,范召林,等.方形截面导弹摇滚特性数值研究.空气动力学学报,2010,28:285–290
7 Sahu J,Silton S,Heavey K.Numerical computations of supersonic flow over non-axisymmetric configurations.In:22nd Applied Aerodynamics Conference and Exhibit.Providence,2004.AIAA2004-5456
8 C Hoke,V Burnley,G Schwabacher.Aerodynamic analysis of complex missile configurations using AVUS(Air Vehicles Unstructured Solver).In:22nd Applied Aerodynamics Conference and Exhibit.Providence,2004.AIAA2004-5452
9 J Sahu,K Heavey.Computations of supersonic flow over a complex elliptical missile configuration.In:AIAA Atmospheric Flight Mechanics Conference.Chicago,2009.AIAA2009-5714
10 李剑,李斌,敬代勇.方形截面导弹气动特性数值研究.弹箭与制导学报,2015,35:111–113
11 Floyd J Wilcox,Trevor J Birch.Force,surface pressure,and flowfield measurements on a slender missile configuration with square cross-section at supersonic speeds.In:22nd Applied Aerodynamics Conference and Exhibit.Providence,2004.AIAA2004-5451
12 Birch T J,Petterson K.CFD predictions of square and elliptic cross-section missile configurations at supersonic speeds.In:22nd Applied Aerodynamics Conference and Exhibit.Providence,2004.AIAA2004-5453
13 James S G,Benjamin S K,Randolph P L,et al.Crew Exploration Vehicle(CEV)crew module shape selection analysis and CEV aeroscience project overview.In:45th AIAA Aerospace Sciences Meeting and Exhibit.Reno,2007.AIAA2007-603
14 Matsumoto S,Kondoh Y,Nagai S,et al.Aerodynamic oscillation and attitude control analysis for reentry capsule using OREX flight data and wind tunnel data.In:AIAA Guidance,Navigation,and Control Conference.San Diego,2016
15 Zhang H X,Zhang Z,Yuan X X,et al.Physical analysis and numerical simulation for the dynamic behaviour of vehicles in pitching oscillations or rocking motions.Sci China Ser E-Tech Sci,2007,50:385–401
16 张涵信,袁先旭,叶友达,等.飞船返回舱俯仰振荡的动态稳定性研究.空气动力学学报,2002,20:247–259
17 袁先旭,陈琦,张涵信,等.再入飞行器失稳的分叉理论分析与数值仿真验证.气体物理,2016,1:12–26
18 Zhang H X,Zhang F G.NND schemes and their application to numerical simulation of two and three dimensional flows.Adv Appl Mech,1991,29 :193–256
19 Jameson A.Time dependent calculation using multi-grid with application to unsteady flows past airfoils and wings.In:10th Computational Fluid Dynamics Conference.Honolulu,1991.AIAA-1991-1596