2.4m跨声速风洞虚拟飞行试验支撑装置研制
|
摘要
风洞虚拟飞行试验是开展气动/飞行力学一体化研究的有效手段,也是连接地面模拟与飞行试验的桥梁和纽带,为了实现风洞虚拟飞行试验真实模拟飞行器机动运动的要求,需要研制一种模型支撑机构研究风洞虚拟飞行试验技术。文中以2.4 m跨声速风洞虚拟飞行试验为背景,设计了风洞虚拟飞行试验支撑装置,并对其进行了力学建模,根据得到的数学模型对结构静力学特性和动力学特性进行了仿真分析,同时也利用CFD技术对其进行了支撑干扰分析。仿真分析结果和试验结果均表明风洞虚拟飞行试验支撑装置设计合理,具有较好的强度特性、刚度特性和较小的支撑干扰,满足风洞虚拟飞行试验研究要求,为该类试验的风洞支撑问题提供了一个可行的技术方案。
The virtual-flight test based on the wind tunnel is effective for the study on the integrated pneumatic and flight mechanics,and it links the ground-based simulation and the flight test.In order to accurately simulate the motions of aircraft in the wind-tunnel virtual-flight test,a model-support device is developed for technical exploration.In this article,a virtual-flight test support based on the 2.4 m transonic wind tunnel is presented and modeled mechanically; based on the mathematical model,the simulation analysis is conducted on its characteristics of static mechanics and dynamics.In addition,the analysis is made on the support interference by means of the CFD technology.The simulation and test results show that the wind-tunnel support,characterized with strong strength,high rigidity and minor support interference,meets the requirements of the wind-tunnel virtual-flight test,and provides a feasible technical scheme for those issues related to wind-tunnel supports.
The virtual-flight test based on the wind tunnel is effective for the study on the integrated pneumatic and flight mechanics,and it links the ground-based simulation and the flight test.In order to accurately simulate the motions of aircraft in the wind-tunnel virtual-flight test,a model-support device is developed for technical exploration.In this article,a virtual-flight test support based on the 2.4 m transonic wind tunnel is presented and modeled mechanically; based on the mathematical model,the simulation analysis is conducted on its characteristics of static mechanics and dynamics.In addition,the analysis is made on the support interference by means of the CFD technology.The simulation and test results show that the wind-tunnel support,characterized with strong strength,high rigidity and minor support interference,meets the requirements of the wind-tunnel virtual-flight test,and provides a feasible technical scheme for those issues related to wind-tunnel supports.
引文
[1]Ratliff C L,Marquart E J.Bridging the gap between ground and flight tes:Virtual Flight Testing(VFT):AIAA-1995-3875[R].Reston:AIAA,1995.
[2]Ratliff C L,Marquart E J.An assessment of a potential test technique:Virtual Flight Testing(VFT):AIAA-1995-3415[R].Reston:AIAA,1995.
[3]Gebert G,Kelly J,Lopez J.Wind tunnel based virtual flight testing:AIAA-2000-0829[R].Reston:AIAA,2000.
[4]Gebert G,Kelly J,Lopez J.Virtual flight testing in a ground test facility:AIAA-2000-4019[R].Reston:AIAA,2000.
[5]Lawrence F C,Mills B H.Status update of the AEDC wind tunnel virtual flight testing development program:AIAA-2002-0168[R].Reston:AIAA,2002.
[6]Magill J C,Wehef S D.Initial test of a wire suspension mount for missile virtual flight testing:AIAA-2002-0169[R].Reston:AIAA,2002.
[7]Magill J C,Cataldi P,Morency J R,et al.Design of a wire suspension system for dynamic testing in AEDC 16T:AIAA-2003-0452[R].Reston:AIAA,2003.
[8]Magill J C,Cataldi P,Morency J R.Demonstration of a wire suspension system for dynamic wind tunnel testing:AIAA2004-1296[R].Reston:AIAA,2004.
[9]Magill J C,Cataldi P,Morency J R,et al.Active yaw control with a wire suspension system for dynamic wind tunne testing:AIAA-2005-1295[R].Reston:AIAA,2005.
[10]Magill J C,Cataldi P,Morency J R,et al.Demonstration of a wire suspension for wind-tunnel virtual flight testing[J]Journal of Spacecraft and Rockets,2009,46(3):624-633.
[11]赵忠良,吴军强,李浩,等.2.4 m跨声速风洞虚拟飞行试验技术研究[J].航空学报,2016,37(2):504-512.
[13]Bergmanna A,Huebnerb A,Loeser T.Experimental and numerical research on the aerodynamics of unsteady moving aircraft[J].Progress in Aerospace Sciences,2008,44(4):121-137.
[14]赵忠良,任斌,汪清.风洞模型自由翻滚试验技术[J].空气动力学学报,2000,18(4):383-389.
[15]陶洋,赵忠良,杨海泳.翼身组合体摇滚特性高速试验研究[J].实验流体力学,2011,25(6):45-48.
[16]李志强,黄达,史志伟,等.俯仰-滚转耦合两自由度大振幅非定常实验技术[J].南京航空航天大学学报,1999,31(2):121-126.
[17]李其畅,伍开元,郑世华.高速风洞大振幅俯仰动态试验技术研究[J].流体力学实验与测量,2004,18(4):67-71.
[18]王兵,黄存栋,马宝峰,等.精确复现机翼摇滚运动的控制技术[J].实验流体力学,2009,23(1):79-84,104.
[19]胡静,李潜.风洞虚拟飞行技术初步研究[J].实验流体力学,2010,24(1):95-99.
[20]谢志江,孙小勇,孙海生,等.低速风洞动态试验的高速并联机构设计及动力学分析[J].航空学报,2013,34(3):487-494.
[21]孙海生,岑飞,聂博文,等.水平风洞模型自由飞试验技术研究现状及展望[J].实验流体力学,2011,25(4):103-108.
[22]张来平,徐庆新,张涵信.非结构网格及混合网格复杂无粘流场并行计算方法研究[J].空气动力学学报,2002,20(增刊):14-20.
[2]Ratliff C L,Marquart E J.An assessment of a potential test technique:Virtual Flight Testing(VFT):AIAA-1995-3415[R].Reston:AIAA,1995.
[3]Gebert G,Kelly J,Lopez J.Wind tunnel based virtual flight testing:AIAA-2000-0829[R].Reston:AIAA,2000.
[4]Gebert G,Kelly J,Lopez J.Virtual flight testing in a ground test facility:AIAA-2000-4019[R].Reston:AIAA,2000.
[5]Lawrence F C,Mills B H.Status update of the AEDC wind tunnel virtual flight testing development program:AIAA-2002-0168[R].Reston:AIAA,2002.
[6]Magill J C,Wehef S D.Initial test of a wire suspension mount for missile virtual flight testing:AIAA-2002-0169[R].Reston:AIAA,2002.
[7]Magill J C,Cataldi P,Morency J R,et al.Design of a wire suspension system for dynamic testing in AEDC 16T:AIAA-2003-0452[R].Reston:AIAA,2003.
[8]Magill J C,Cataldi P,Morency J R.Demonstration of a wire suspension system for dynamic wind tunnel testing:AIAA2004-1296[R].Reston:AIAA,2004.
[9]Magill J C,Cataldi P,Morency J R,et al.Active yaw control with a wire suspension system for dynamic wind tunne testing:AIAA-2005-1295[R].Reston:AIAA,2005.
[10]Magill J C,Cataldi P,Morency J R,et al.Demonstration of a wire suspension for wind-tunnel virtual flight testing[J]Journal of Spacecraft and Rockets,2009,46(3):624-633.
[11]赵忠良,吴军强,李浩,等.2.4 m跨声速风洞虚拟飞行试验技术研究[J].航空学报,2016,37(2):504-512.
[13]Bergmanna A,Huebnerb A,Loeser T.Experimental and numerical research on the aerodynamics of unsteady moving aircraft[J].Progress in Aerospace Sciences,2008,44(4):121-137.
[14]赵忠良,任斌,汪清.风洞模型自由翻滚试验技术[J].空气动力学学报,2000,18(4):383-389.
[15]陶洋,赵忠良,杨海泳.翼身组合体摇滚特性高速试验研究[J].实验流体力学,2011,25(6):45-48.
[16]李志强,黄达,史志伟,等.俯仰-滚转耦合两自由度大振幅非定常实验技术[J].南京航空航天大学学报,1999,31(2):121-126.
[17]李其畅,伍开元,郑世华.高速风洞大振幅俯仰动态试验技术研究[J].流体力学实验与测量,2004,18(4):67-71.
[18]王兵,黄存栋,马宝峰,等.精确复现机翼摇滚运动的控制技术[J].实验流体力学,2009,23(1):79-84,104.
[19]胡静,李潜.风洞虚拟飞行技术初步研究[J].实验流体力学,2010,24(1):95-99.
[20]谢志江,孙小勇,孙海生,等.低速风洞动态试验的高速并联机构设计及动力学分析[J].航空学报,2013,34(3):487-494.
[21]孙海生,岑飞,聂博文,等.水平风洞模型自由飞试验技术研究现状及展望[J].实验流体力学,2011,25(4):103-108.
[22]张来平,徐庆新,张涵信.非结构网格及混合网格复杂无粘流场并行计算方法研究[J].空气动力学学报,2002,20(增刊):14-20.