火星大气非平衡条件下驻点热流计算公式的探讨
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摘要
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 stagnation heat flow formula-the Fay-Riddle equation was analyzed in this paper. Then the numerical method was 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 Mars was obtained under the condition of non-equilibrium thermodynamics zero angle of attack station heat transfer equation. Also, the formula was verified by the Mars Pathfinder flight data, and the results showed that the error of the equation was less than 10%, which can be accepted for the industry.
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 stagnation heat flow formula-the Fay-Riddle equation was analyzed in this paper. Then the numerical method was 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 Mars was obtained under the condition of non-equilibrium thermodynamics zero angle of attack station heat transfer equation. Also, the formula was verified by the Mars Pathfinder flight data, and the results showed that the error of the equation was less than 10%, which can be accepted for the industry.
引文
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[2] Sutton K, Grave R A. A general stagnation-point convective heating equation for arbitrary gas mixtures[R].NASA-TR-R-376, 1971.
[3] Anderson Jr J D. Hypersonic and High-Temperature Gas Dynamics[M]. 2nd Edition: American Institute of Aeronautics and Astronautics, 2006.
[4] Page W A, Woodward H T. Radiative and convective heating during Venus entry[J]. AIAA Journal, 1972, 10(10): 1379-1381.
[5] Zoby E V. Empirical stagnation-point heat-transfer relation in several gas mixtures at high enthalpy levels[R]. NASA-TN-D-4799, 1968.
[6] Edquist K, Dyakonov A, Wright M, et al. Aerothermodynamic environments definition for the Mars Science Laboratory entry capsule[C]//45th AIAA Aerospace Sciences Meeting and Exhibit, 2007: 1206.
[7] Olynick D, Loomis M, Chen Y K, et al. New TPS design strategies for planetary entry vehicle design[C]//37th aerospace sciences meeting and exhibit. 1999: 348.
[8] Milos F, Chen Y K, Congdon W, et al. Mars Pathfinder entry temperature data, aerothermal heating, and heatshield material response[J]. Journal of Spacecraft and Rockets, 1999, 36(3): 380-91.
[9] 中国人民解放军总装备部军事训练教材工作委员会. 高超声速气动热和热防护[M]. 北京: 国防工业出版社, 2003: 77-79.Working Committee on Military Training Textbooks of the General Armament Department of the People’s Liberation Army of China. Hypersonic Areoheat and Aerothermal Protection[M]. Beijing: National Defense Industry Press, 2003: 77-79.(in Chinese)
[10] 杨肖峰. 火星探测器气动力热和传热特性研究[D]. 绵阳: 中国空气动力研究与发展中心, 2013.Yang Xiaofeng. Aerodynamics, Aerothermodynamics and Heat-Transfer Investigation for Mars Entry Vehicle [D]. Mianyang: China Aerodynamics Research and development Center, 2013. (in Chinese)
[11] Hollis B R. Experimental and computational aerothermodynamics of a Mars entry vehicle3[R]. NASA-CR-20163, 1996.
[12] Park C, Howe J T, Jaffe R L, et al. Review of chemical-kinetic problems of future NASA missions. II - Mars entries[J]. Journal of Thermophysics and Heat Transfer, 1994, 8(1): 9-23.
[13] Sutton K, Graves J R. A general stagnation-point convective heating equation for arbitrary gas mixtures[R]. NASA-TR-R-376, 1971.
[14] Gnoffo P A, Weilmuenster K J, Braun R D, et al. Influence of sonic-line location on Mars Pathfinder probe aerothermodynamics [J]. Journal of Spacecraft and Rockets, 1996, 33(2): 169-177.