摘要
对不同孔间距模型的气膜冷却现象的流动和换热进行了数值计算,得到了不同吹风比下,展向和流向孔间距对气膜冷却效率的影响规律.研究结果表明,在主流雷诺数为4 797,吹风比为0.2～2.0的条件下:①展向方向上,S1/D=1为最佳布局;②流向方向上,相对于主孔靠后的辅助孔冷却效果较好;③流向方向上,辅助孔在主孔下游的模型受吹风比影响小,并且流向距离的改变,对涡量的量级不发生改变,对涡量的大小和方向影响较大.
Numerical simulation research on surface radiation heat calculation of spacecraft in orbit whole course
The surface radiation heat simulation program based on Microsoft VC＋＋ 6.0 for spacecraft in whole orbit course was presented.Due to complexity of spacecraft structure,the spacecraft structures were decomposed to relatively regular parts.Automatic generation of calculation grid was conducted by using structured grid and unstructured technology.Simulation mainly solved automatic grid generation for arbitrary surface and data transmission between arbitrary shape interfaces,and the geometry structure,physical process,calculation accuracy and efficiency were considered.View factors and radiation transfer coefficients were calculated by combining finite element method and ray uniform distribution.According to the position of surface cells,external heat flux was calculated with integral method for non-shaded surface and with ray uniform distribution method for shaded surface.As the spacecraft surface was wrapped with multilayer insulation material,the temperature field of multilayer insulation material was calculated with nodal network method and finite volume method.The temperature of other parts without wrap was calculated with finite element method.The temperature of unconnected regions available with radiation heat transfer relations was analyzed,and the calculation formulae were deduced.Numerical experiment shows that the simulation program is correct and effective.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2010年第10期2238-2243,共6页
Journal of Aerospace Power
基金
国家自然科学基金(50976008)
航空基金(2008ZB51018)
