表面涂漆对火箭尾翼热结构的影响

Effect of paint coating on the internal thermal structure of rocket wing

建立了运载火箭的气动加热工程计算方法,计算区域横跨连续流、稀薄过渡流和自由分子流,包括层流、转捩和湍流等各流态。重点研究了尾翼与芯级间的干扰加热,数值求解了自然正交曲线坐标系下尾翼内部二维单层和双层材料热传导方程,给出了典型部位的内外表面温度计算结果,表明表面涂漆对尾翼前缘并不能起到防热隔热效果。

In this paper, flowfields around rocket were calculated by engineering methods, while flying from continuons region to rarefied region and then to free molecule region, including laminar flow, transitional flow and turbulent flow. The heat flux on the rear wing of the rocket, espacially induced by interaction of wing with body, was obtained by correlation of experimental data. The internal multi-layer heat transfer inside the wing materials was studied by solving one and two dimensional heat transfer equations in a perpendicular curve line coordinate. Through comparison of temperature distribution, it can be seen that paint coating on the wing will be disadvantageous to heat protection of the wing.