An Investigation of Thermal Protection System of a Jupiter-Entry Capsule by Using Ablation

利用烧蚀研究进入木星舱的热保护系统

• 批准号: 15360450
• 负责人: ABE Ken-ichi
• 金额: $ 9.15万
• 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: 2003
• 资助国家: 日本
• 起止时间: 2003 至 2005
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-15360450/
• 关键词: Jupiter; Hypersonic flow; Atmospheric entry; Thermal Protection System; Ablation; 木星; 非平衡流; 水素; ヘリウム

(a)Shock layer around a Jupiter-entry vehicle with carbon ablator has been calculated, taking into account three-temperature model and nonequilibrium chemical reaction of an ablator air.(b)Nonequilibrium viscous-shock-layer calculation was performed for hypersonic H2 flow with ablation.(c)An investigation of the effect of the ablation gas for thermal protection system was performed as well as a prediction of the entry conditions. In particular, it has been elucidated that the effect of thermal nonequilibrium is stronger than what was expected.(d)Spallation particles emitted from an ablating test model mounted in a supersonic arc-heated air flow were experimentally and computationally investigated. Emission spectra resulted from the spallation particles which are CN violet band and C2 swan band can identified not only inside the shock layer of the ablator but also outside of it.(e)Experimental investigations of particle distributions were tested through a wave filter suitable for species in an ablation plume by using a high-quality CCD camera with high-speed gate.(f)For the development of an analysis of unsteady hypersonic turbulent flows around a Jupiter-entry vehicle, a new LES/RANS turbulence model has been investigated and proposed.

（a）考虑三温模型和烧蚀剂空气的非平衡化学反应，计算了带碳烧蚀剂的再入飞行器的激波层。（B）对高超声速H2烧蚀流场进行了非平衡粘性激波层计算。(c)An研究了烧蚀气体对热防护系统的影响，并预测了进入条件。特别是，它已阐明，热不平衡的影响是强于预期的。（d）对安装在超音速电弧加热气流中的烧蚀试验模型发射的火花粒子进行了实验和计算研究。在烧蚀体激波层内和激波层外都能看到CN紫带和C2天鹅带等闪烁粒子的发射光谱。（e）通过一个适合于烧蚀羽流中各种物质的滤波器，使用一台带高速门的高质量CCD照相机，对粒子分布进行了实验研究。（f）为了分析再入飞行器的非定常高超声速湍流流动，研究并提出了一种新的LES/RANS湍流模型。

项目成果

READ飛行実験での高々度取得スペクトルについて

关于READ飞行实验中高空获取的光谱

• 发表时间: 2005
• 期刊: 宇宙航空研究開発機構 研究開発報告 JAXA-RR-05-018
• 作者: 松田 淳;大津広敬;藤田和央;鈴木俊之;澤田恵介;安部隆士
• 通讯作者: 安部隆士

An Investigation of Wall-Anisotropy Expressions and Length-Scale Equations for Non-Linear Eddy-Viscosity Model

非线性涡粘模型壁各向异性表达式和长度尺度方程的研究

• 发表时间: 2003
• 期刊: International Journal of Heat and Fluid Flow Vol. 24
• 作者: Ken-ichi ABE;Yong-Jun JANG;Michael A. LESCHZINER
• 通讯作者: Michael A. LESCHZINER

An Investigation of Algebraic Turbulence and Turbulent Scalar-Flux Models for Complex Flow Fields with Impingement and Separation

具有冲击和分离的复杂流场的代数湍流和湍流标量通量模型的研究

• 发表时间: 2003
• 期刊: 3rd International Symposium on Turbulence and Shear Flow Phenomena, Sendai
• 作者: Michio NISHIDA;Ken-ichi ABE;Hisashi KIHARA;Ken-ichi ABE
• 通讯作者: Ken-ichi ABE

Chemical Nonequilibrium Viscous Shock-Layer Analysis over Ablating Surface of Superorbital Re-Entry Capsule

超轨道返回舱烧蚀表面的化学非平衡粘性激波层分析

• 发表时间: 2003
• 期刊: The Institute of Space and Astronautical Science Report Vol.17
• 作者: T.Noguchi;K.Nagayama;K.Suzuki et al.
• 通讯作者: K.Suzuki et al.

K.Suzuki, K.Fujita, T.Abe: "Chemical Nonequilbrium Shock-Layer Analysis over Ablating Surface of Superorbital Re-Entry Capsule"The Institute of Space and Astronautical Science Report. SP No.17. 23-42 (2003)

K.Suzuki、K.Fujita、T.Abe：“超轨道再入舱烧蚀表面的化学非平衡冲击层分析”空间与宇航科学研究所报告。