EFFECT OF NONEQUILIBRIUM BEHIND A STRONG SHOCK UPON RE-ENTRY AERODYNAMIC HEATING

再入气动加热强冲击背后的非平衡效应

• 批准号: 05452305
• 负责人: NISHIDA Michio
• 金额: $ 4.54万
• 依托单位: KYUSHU UNIVERSITY
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for General Scientific Research (B)
• 财政年份: 1993
• 资助国家: 日本
• 起止时间: 1993 至 1995
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/en/grant/KAKENHI-PROJECT-05452305/
• 关键词: RE-ENTRY AERODYNAMICS; RE-ENTRY AERODYNAMIC HEATING; NONEQUILIBRIUM FLOW; STRONG SHOCK WAVE; HYPERSONIC FLOWS; HIGH TEMPERATURE GAS; NUMERICAL STUDY; SPACE; 空力加熱; 衝撃波

The atmospheric entry of space transportation systems at high altitudes generates a very strong shock wave. Such a shock wave causes vibrational excitation, dissociation and ionization of the shock layr gas, and the flow will be in thermal and chemical nonequilibrium due to very low density. Although rotational temperature is quickly equilibrated with translational temperature of heavy particle, vibrational temperature and electron temperature deviate from translational temperature. Therefore, in order to estimate re-entry aerodynamic heating, the following items should be revealed :(1) Effect of thermal nonequilibrium : energy transfer rates among translational, vibrational and electron-translational energy modes,(2) Radiative effect : Radiative intensity in high temperature gas behind a strong shock,(3) Effects of wall conditions : effect of catalytic wall on aerodynamic heating, wall condition for vibrational temperature.In the present investigations, nonequilibrium flows including the above three conditions are studied experimentally and numerically. In the numerical study of viscous shock layr (VSL) analysis of the thermochemical nonequilibrium flows over a blunt body, a three temperature model was treated and thereby the structure of nonequilibrium shock layr flows was revealed. In addition, the effect of wall catalysis on aerodynamic heating was investigated. Also, experiments were carried out using a piston-driven shock tube, and radiation spectrum emitting from the high-temperature gas behind a strong shock wave was observed. wall vibrational-condition has been deduced from theoretical analysis considering vibrational energy flux at the edge of Knudsen layr.

航天运输系统在高空进入大气层会产生很强的冲击波。这种激波会引起激波气体的振动激发、解离和电离，由于密度很低，流动将处于热和化学非平衡状态。虽然转动温度与重粒子的平移温度很快达到平衡，但振动温度和电子温度偏离了平移温度。因此，为了估算再入气动加热，必须揭示以下几点：(1)热非平衡效应：平动、振动和电子-平动能量模式之间的能量传递速率；(2)辐射效应：强激波后高温气体中的辐射强度；(3)壁面条件的影响：催化壁对气动加热的影响；壁面条件对振动温度的影响。在钝体热化学非平衡流动的粘性激波分层(VSL)分析的数值研究中，采用三温度模型，揭示了非平衡激波分层流动的结构。此外，还研究了壁面催化对气动加热的影响。此外，还利用活塞驱动激波管进行了实验，观测到了强激波后高温气体的辐射光谱。通过考虑克努森层边缘振动能流的理论分析，得到了壁面振动的条件。

项目成果

李民揆,西田迪雄: "衝撃波によって誘起される非定常ノズル流の数値計算" 日本機械学会論文集(B編). 60. 2267-2272 (1994)

Min-ki Li，Michio Nishida：“冲击波引起的非稳态喷嘴流的数值计算”日本机械工程师学会会刊（ed.B）60.2267-2272（1994）。

M.Nishida and Y.Sakamura: "Nonequilibrium Flows around a Hypersonic Reentry Vehicle Model" Proceedings of the Asian-Pacific Conference on Aerospace Technlogy and Science, International Academic Publishers, Beijing. 637-642 (1994)

M.Nishida和Y.Sakamura：“高超音速再入飞行器模型周围的非平衡流”亚太航空航天技术与科学会议论文集，国际学术出版社，北京。

M.Nishida and Y.Sakamura: "Nonequilibrium Viscous Shock Layr Analysis Using a Three Temperature Model" Rarefied Gas Dynamics, Progress in Astronautics and Aeronautics. Vol.158. 401-412 (1994)

M.Nishida 和 Y.Sakamura：“使用三温度模型的非平衡粘性激波层分析”稀薄气体动力学，航天和航空进展。

Y.Sakamura and M.Nishida: "Viscous Shock Layr Analysis Using a Three-Temperature Model" Shock Waves (R.Brun & L.Z.Dumitrescu, ed., Springer Verlag). Vol.II. 333-338 (1995)

Y.Sakamura 和 M.Nishida：“使用三温度模型的粘性冲击层分析”冲击波 (R.Brun

M.Nishida, K.Tanabe, Y.Sakamura and Y.Yamamoto: "Wall Slip Condition of Vibrational Temperature" Rarefied Gas Dynamics 19 (J.Harvey & G.Lord, ed., Oxford University Press). 981-987 (1995)

M.Nishida、K.Tanabe、Y.Sakamura 和 Y.Yamamoto：“振动温度的壁面滑移条件”稀有气体动力学 19 (J.Harvey