火星大气非平衡条件下驻点热流计算公式的探讨

Discussion on Calculation Formula of Stagnation Heat flux in Martian Atmosphere under Non-equilibrium Condition

针对目前绝大多数火星再入飞行器驻点热流公式未考虑热力学非平衡效应故而适用性及准确性存疑的问题,分析了典型的零攻角驻点热流公式Fay-Riddell公式在火星再入飞行器热力学非平衡驻点热流计算中的局限性;然后采用数值计算方法,对涵盖火星再入飞行器飞行状态的大范围计算状况开展了热力学非平衡模拟,并对模拟得到的驻点热流公式进行拟合,得到了适用于火星再入飞行器热力学非平衡条件下的零攻角驻点热流计算公式;利用Mars Pathfinder飞行数据对公式进行了验证,计算表明,对于验证的计算状态,该公式的计算误差小于10%,符合工程预估的可接受误差范围。

In order to solve the problem of accuracy and applicability caused by thermodynamic non-equilibrium effect of Mars reentry vehicle, the limitation of the typical zero attack angle stagnationheat flow formula-the Fay-Riddle equation was analyzed in this paper. Then the numerical methodwas adopted to cover a wide flight range of reentry spacecraft on Mars reentry vehicle calculation,and suitable zero angle of attack stagnation heat transfer formula for the reentry spacecraft of Marswas obtained under the condition of non-equilibrium thermodynamics zero angle of attack station heattransfer equation. Also, the formula was verified by the Mars Pathfinder flight data, and the resultsshowed that the error of the equation was less than 10%, which can be accepted for the industry.