Progress of nonequilibrium models toward the realization of highly reliable prediction of superorbital velocity flow fields

2021 Fiscal Year Final Research Report

• Project/Area Number: 19K04842
• Research Category: Grant-in-Aid for Scientific Research (C)
• Allocation Type: Multi-year Fund
• Section: 一般
• Review Section: Basic Section 24010:Aerospace engineering-related
• Research Institution: Kochi University of Technology
• Principal Investigator: OGINO Yousuke 高知工科大学, システム工学群, 講師 (90586463)
• Project Period (FY): 2019-04-01 – 2022-03-31
• Keywords: 衝突輻射モデル / 高エンタルピー流の数値計算 / 原子・分子過程 / 輻射熱輸送 / 分光計測

Outline of Final Research Achievements

The purpose of this study is to develop and suggest a new analysis model based on actual physical processes that can be an alternative to conventional ones regarding thermochemical nonequilibrium and radiative heat transfer in the sever aerodynamic and radiative heating environments experienced by spacecraft during atmospheric entry. A numerical analysis of the arc heating wind tunnel airflow was performed, and the radiation spectra incident on the wall surface of test model was compared and verified with measurements. It was confirmed that the accuracy superior to the conventional model could be obtained. The numerical results have been summarized and presented at international and domestic conferences held online.

Free Research Field

非平衡性を伴う流れの数値シミュレーション

Academic Significance and Societal Importance of the Research Achievements

宇宙空間から地球大気圏へ突入するカプセル宇宙機が溶融することなく地上まで帰還するためには、厳重な熱防護設計が不可欠となる。突入時の安全対策に万全を期すため、カプセル前面に熱防護材が装備されるが、これは非常に重い。高重量な熱防護材の重さを軽減できれば、ロケット打ち上げ時に搭載する実験機材や人員を増やすことにも繋がり、将来の宇宙探査の可能性をさらに広げる。本研究では、カプセルまわりの過酷な加熱環境と、壁面入射する強烈な熱負荷を高精度に予測できる次世代の数値解析手法を構築提案した。