Significant Aerodynamic Heating Phenomenon ofAblative Heatshield at Downstream Region from Stagnation Point

驻点下游区域烧蚀隔热罩显着的气动加热现象

• 批准号: 11650162
• 负责人: SAWADA Kesuke
• 金额: $ 2.18万
• 依托单位: Tohoku University
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for Scientific Research (C)
• 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/grant/KAKENHI-PROJECT-11650162/
• 关键词: Aerodynamic Heating; Ablator; Ablation Product Gas; Turbulent Transition; Pioneer-Venus; Stardust SRC; Radiative Hydrodynamics; Galileo Entry Capsule; アブレ-タ; MUSES-C; 輻射流れ場; マルチバンドモデル; 密結合計算; パラレル演算処理; 乱流モデル; 密結合解法

We have developed a trajectory-based unified aerodynamic heating analysis code for entry capsule that employs ablator as heatshield. Using the code, an entry flight simulation for Stardust sample return capsule has been conducted in which significant increase of heating rate due to an earlier transition of the boundary layer was indicated. We have also calculated flow field for 4 entry probe vehicles in the Pioneer-Venus mission. Significantly higher heating rate at downstream region was obtained for all probe vehicles. A reasonable agreement is shown in the comparison of thermocouple temperatures with that given in the flight data. It is shown that significant heating phenomenon at downstream region is caused by an earlier turbulent transition due to ablation product gas. It is also indicated that a quantitative prediction of this phenomenon is possible if we employ Park's injection-induced turbulence model that assumes ablation product gas to be inherently turbulent.Significant aerodynamic heating at downstream region was also observed when Galileo probe vehicle entered into Jovian atmosphere. A spectrally detailed radiation coupled CFD code on a parallel computer system has been developed that will be used in the simulation of entry flight for Galileo probe vehicle.

我们开发了一个基于弹道的以烧蚀体为热屏障的统一的进气舱气动热分析程序。利用该程序对星尘样品返回舱的进气飞行进行了模拟，结果表明，由于边界层的提前转变，加热率显著提高。我们还计算了先驱者-金星任务中四个进入探测器的流场。所有探测车在下游区域均获得了较高的升温速率。将热电偶的温度与飞行数据进行了比较，两者吻合较好。结果表明，烧蚀产物气体的提前湍流转变是引起下游显著加热现象的主要原因。研究还表明，如果采用Park的喷注诱导湍流模型，并假定烧蚀产物气体为固有湍流，则可以对这一现象进行定量预测。伽利略探测器进入木星大气时，下游区域也观察到了显著的气动加热。在并行计算机系统上开发了辐射耦合CFD程序，并将其用于伽利略探测器飞行器的进场飞行模拟。

项目成果

Toshiyuki Suzuki: "Unified Calculation of Hypersonic Flowfield for a Reentry Vehicle"Journal of Thermophysics and Heat Transfer. Vol.16, No.1. 94-100 (2002)

Toshiyuki Suzuki：“再入飞行器高超声速流场的统一计算”热物理与传热杂志。

Takeharu Sakai: "Computation of Hypersonic Radiating Flowfield over a Blunt Body"Journal of Thermophysics and Heat Transfer,. Vol.15,No.1(to appear). (2001)

Takeharu Sakai：“钝体上高超声速辐射流场的计算”热物理学与传热杂志，。

Masanori Takahashi: "Simulation of Entry Flight Flowfield over Four Probe Vehicles in Pioneer-Venus Mission"AIAA Paper 2002-0909. 1-11 (2002)

Masanori Takahashi：“先锋-金星任务中四架探测器飞行器入口飞行流场模拟”AIAA Paper 2002-0909。

Masanori Takahashi: "Simulation of Entry Flight Flowfield over Four Probe Vehicles in Pioneer-Venus Mission"AIAA. Paper 2002-0909. 1-11 (2002)

Masanori Takahashi：“先锋金星任务中四架探测器飞行器入口飞行流场模拟”AIAA。

Takeharu Sakai: "Application of Planck-Rosseland-Gray Model for High-Enthalpy Arc Heaters"Journal of Thermophysics and Heat Transfer. Vol.15, No.2. 176-183 (2001)

Takeharu Sakai：“普朗克-罗斯兰-格雷模型在高焓电弧加热器中的应用”热物理与传热杂志。