高超声速飞行器表面气动热传递预测
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摘要
高超声速飞行器与附近大气存在着强烈的压缩与摩擦作用,产生的热传递到飞行器表面,会导致表面材料发生变形甚至烧蚀。在高超声速飞行器的设计阶段,需要准确预测飞行器气动热状况,采取相应防热措施,以保证飞行稳定性与安全性。针对某型号高超声速火箭弹,给出一种用于预测弹头热流密度的工程计算方法。为提高计算准确度,同时考虑了边界层内气体参数的变化与飞行攻角的影响,采用了参考焓法和等价锥法。计算中把弹头分为驻点、圆头和锥面区域三部分,分别采用对应的热流密度计算公式。算例验证表明,上述计算方法简捷有效,计算量小,可在飞行器概念设计与早期分析中使用。最后,将上述算法应用于某型号高超声速火箭弹弹头,计算得到飞行器在一定高度和速度飞行时的驻点和锥身热流密度,并给出不同攻角下弹头的热流密度分布状况,为飞行器设计提供依据。
There is a strong compression and friction between hypersonic vehicle and nearby atmosphere. When the produced heat transfers to the surface of the aircraft,a deformation and even ablation of the surface material will happen. During the design phase of hypersonic vehicle,it is necessary to predict the aero thermal condition of an aircraft accurately in order to take corresponding thermal protection measures and ensure the stability and safety of the aircraft. For a type of hypersonic rocket,in order to considered the boundary layer parameters and the angle of attack,combined with the reference-enthalpy method and equivalent-cone method,we proposed a calculating method for the prediction of heat flux of rocket warhead. This method divided the warhead into three parts,namely,stationary point,round head and cone surface. The corresponding heat flux calculation formula was adopted respectively. Example results show the applicability and effectiveness of this algorithm which can be used in conceptual design and early analysis of hypersonic rocket warhead. In the end,this algorithm was applied to a type of hypersonic rocket warhead. The heat flux of stagnation point at certain altitude and speed,as well as the heat flux distribution of warhead at different degrees of attack angle,was given,which provides a basis for the design of aircraft.
There is a strong compression and friction between hypersonic vehicle and nearby atmosphere. When the produced heat transfers to the surface of the aircraft,a deformation and even ablation of the surface material will happen. During the design phase of hypersonic vehicle,it is necessary to predict the aero thermal condition of an aircraft accurately in order to take corresponding thermal protection measures and ensure the stability and safety of the aircraft. For a type of hypersonic rocket,in order to considered the boundary layer parameters and the angle of attack,combined with the reference-enthalpy method and equivalent-cone method,we proposed a calculating method for the prediction of heat flux of rocket warhead. This method divided the warhead into three parts,namely,stationary point,round head and cone surface. The corresponding heat flux calculation formula was adopted respectively. Example results show the applicability and effectiveness of this algorithm which can be used in conceptual design and early analysis of hypersonic rocket warhead. In the end,this algorithm was applied to a type of hypersonic rocket warhead. The heat flux of stagnation point at certain altitude and speed,as well as the heat flux distribution of warhead at different degrees of attack angle,was given,which provides a basis for the design of aircraft.
引文
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[8]蒋友娣.高超声速飞行器气动热和表面瞬态温度计算研究[D].上海交通大学,2008.
[9]薛鹏飞,龚春林,谷良贤.基于轴对称比拟的气动热计算方法研究[J].计算机仿真,2012,29(6):97-100.
[10]H Parhizkar,S M H Karimian.Application of Axisymmetric Analog to Unstructured Grid for Aeroheating Prediction of Hypersonic Vehicles[J].International Journal of Numerical Methods for Heat&Fluid Flow,2009,19(3/4):501-520.
[11]姜贵庆,刘连元.高速气流传热与烧蚀热防护[M].北京:国防工业出版社,2003.
[12]J W Cleary.Effects of angle of attack and bluntness on the shock-layer properties of a 15 deg cone at a Mach number of 10.6[J].American Heart Journal,1968,88(301):815.
[2]陈东阳,Laith K Abbas,芮筱亭.旋转弹箭气动导数与气动热仿真计算[J].计算机仿真,2014,31(5):26-30.
[3]吕丽丽.高超声速气动热工程算法研究[D].西北工业大学,2005.
[4]范绪箕.气动加热与热防护系统[M].北京:科学出版社,2004.
[5]张志成.高超声速气动热和热防护[M].北京:国防工业出版社,2003.
[6]黄志澄.高超声速飞行器空气动力学[M].北京:国防工业出版社,1995.
[7]D J Kinney.Aero-thermodynamics for conceptual design[R].AIAA-2004-0041,2004.
[8]蒋友娣.高超声速飞行器气动热和表面瞬态温度计算研究[D].上海交通大学,2008.
[9]薛鹏飞,龚春林,谷良贤.基于轴对称比拟的气动热计算方法研究[J].计算机仿真,2012,29(6):97-100.
[10]H Parhizkar,S M H Karimian.Application of Axisymmetric Analog to Unstructured Grid for Aeroheating Prediction of Hypersonic Vehicles[J].International Journal of Numerical Methods for Heat&Fluid Flow,2009,19(3/4):501-520.
[11]姜贵庆,刘连元.高速气流传热与烧蚀热防护[M].北京:国防工业出版社,2003.
[12]J W Cleary.Effects of angle of attack and bluntness on the shock-layer properties of a 15 deg cone at a Mach number of 10.6[J].American Heart Journal,1968,88(301):815.