Nonequilibrium Aerodynamics for a Super-orbital Reentry

超轨道再入的非平衡空气动力学

• 批准号: 11694165
• 负责人: NISHIDA Michio
• 金额: $ 4.93万
• 依托单位: Kyushu University
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for Scientific Research (B)
• 财政年份: 1999
• 资助国家: 日本
• 起止时间: 1999 至 2001
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/en/grant/KAKENHI-PROJECT-11694165/
• 关键词: Reentry; Hypersonic flows; Space transpotation; Nonequilibrium flows; Aerodynamic heating; Wall catalysis; Shock wave; Super-orbital reentry; アブレーション

1. Investiation of a noneguilibrium shock layer around a super-orbital reentry capsuleUsing the VSL (Viscous Shock Layer) method, a thermochemical nonequilibrium shock layer around a super-orbital orbital reentry space vehicle was numerically investigated. Heat flux on the vehicle wall was estimated from the computed flow properties. In addition, radiative heat flux was also calculated. It was revealed that the dominant spectra were the line spactra of N, O and N+ in the ultra-violet and vacuum ultra-violet region.2. Ablation coolingThe VSL analysis was extended to a nonequilibrium shock layer with ablation cooling. The vehicle wall temperature for which the ablation cooling warks efficiently was investigated. The spectrum caused by the ablation was C swan band.3. Structure of a very strong shock wave caused by a super-orbital reentryA very strong shock wave was generated by a piston^driven shock tube and electron density was measured behind it using a one-dimensional imaging spectroscopic method developed by one of the invesigators of this research. The results showed that ionization rate was faster than that predicted by the conventional model.

1.超轨道再入舱周围非平衡激波层的研究利用粘性激波层(VSL)方法，对超轨道再入航天器周围的热化学非平衡激波层进行了数值研究。根据计算的流动特性估算了车辆壁面上的热流密度。此外，还计算了辐射热流密度。结果表明，在紫外区和真空紫外区，主要光谱是N、O和N+的线空间。烧蚀冷却VSL分析扩展到具有烧蚀冷却的非平衡激波层。对烧蚀冷却有效的车壁温度进行了研究。消融引起的频谱为C-天鹅带。超轨道再入引起的极强激波的结构由活塞驱动激波管产生的极强激波，其背后的电子密度是用一维成像光谱方法测量的，该方法是由本研究的研究者之一开发的。结果表明，电离速率比传统模型预测的要快。

项目成果

S. Kuchi-Ishi and M. Nishida: "Numerical Simulation of a Nitrogen Arcjet Thruster"Transactions of the Japan Society for Aeronautics and Space Science. Vol.42 No.136. 357-360 (1999)

S. Kuchi-Ishi 和 M. Nishida：“氮电弧喷射推进器的数值模拟”日本航空航天学会会刊。

鈴木宏二郎,田辺義慶,山田和彦,越野勝一郎,本郷素行: "極厚デルタ形状リフティングボディーの超音速大迎角空力特性"日本航空宇宙学会誌. 48巻,561号. 549-553 (2000)

Kojiro Suzuki、Yoshiyoshi Tanabe、Kazuhiko Yamada、Katsuichiro Koshino、Motoyuki Hongo：“超厚三角升力体的超音速大迎角空气动力特性”日本航空航天研究所学报第 48 卷。 ，第561。549-553（2000））

K. Matsuura,K. Funabiki,T. Abe: "Detection of Propagation g Wave Fronts by Means of ∂ρ/∂t Plots and Short-time-interval Interferometry"ISSW 22 Paper 2910. (in press).

K. Matsuura、K. Funabiki、T. Abe：“通过 ∂ρ/∂t 图和短时间隔干涉测量法检测传播 g 波前”ISSW 22 论文 2910。（出版中）。

K.Fujita, S.Sato, T.Abe, A.Matsuda: "Electron Temperature and Density Measurement ahead of Strong Shod Waves"AIAA 2001-2765, 35th AIAA Thermophysics Conference. (2001)

K.Fujita、S.Sato、T.Abe、A.Matsuda：“强 Shod 波之前的电子温度和密度测量”AIAA 2001-2765，第 35 届 AIAA 热物理学会议。

平川 誠,市毛敬介,西田迪雄,武石賢一郎,松浦正昭: "触媒性壁面への熱流束予備試験"日本航空宇宙学会論文集. 47巻 548号. 357-360 (1999)

Makoto Hirakawa、Keisuke Ichige、Michio Nishida、Kenichiro Takeishi、Masaaki Matsuura：“催化壁的初步热通量测试”日本航空学会学报第 47 卷，第 548 期。357-360（1999 年）。