由于过渡区域流动的物理现象的复杂性和流动控制方程的非线性,航天飞行器设计所需要的气动加热特性目前主要由工程计算方法得到.为了使计算过渡流区热流的Linear桥函数方法能适用于广泛应用的钝锥体外形,拟合得到了相应的调节参数,使用DSMC方法对计算结果进行验证.验证结果表明该调节参数适用于钝锥体外形,使得Linear桥函数在过渡流区能比较准确地计算钝锥体物面热流. Because of the complexity of the physical phenomenon of the flow in the transition area and the nonlinearity of the flow control equation, the aerodynamic heating characteristics required by the spacecraft design are mainly obtained by engineering calculation method. In order to make the Linear Bridge function method for calculating the heat flux in the transition flow area applicable to The widely used blunt pyramidal shape is fitted and the corresponding adjusting parameters are obtained by fitting, and the DSMC method is used to verify the calculation results. The verification results show that the adjusting parameters are suitable for the blunt pyramidal shape and make the Linear Bridge function more accurate in the transitional flow region Calculate the heat flow of dull cone surface.