"Advanced Application of Gas-dynamic to Planetary Exploration"

“气体动力学在行星探索中的高级应用”

• 批准号: 08305036
• 负责人: ABE Takashi
• 金额: $ 16.9万
• 依托单位: Institute of Space and Astronautical Science
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for Scientific Research (A)
• 财政年份: 1996
• 资助国家: 日本
• 起止时间: 1996 至 1998
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-08305036/
• 关键词: planetary exploration; reentry; hypersonic flow; non-equilibrium flow; heat shield; penetrator; ramaccelerator; reentry; penetrator; 惑星探査; 再突入体; 気体力学; 高温非平衝流; 耐熱構造; 高温プラズマ; ラム加速; ペネトレータ; 高温非平衡流

The extensive research was made on application of gas-dynamics on the future planetary exploration, mainly focusing on the reentry capsule which is planned for MUSES-C mission. MUSES-C mission planned by ISAS is to have a rendezvous with an asteroid and to bring back its soil to Earth. Since its reentry speed is quite high (-l3 km/sec), a variety of gas-dynamical problem must be resolved.In the present research, research effort was focused on the following main problems ; 1) the radiation efficient estimation from high temperature shock layer ahead of the vehicle, 2) the interaction of the high temperature air with the heat shield material of the vehicle, 3) the estimation of aerodynamic heat flux caused by highly-nonequilibrium high temperature shock layer. One of the main topics is the highly thermally-nonequilibrium phenomena, which is observed experimentally. This result is expected to have an impact on improving the current flow model, and to be helpful to improve the estimation accuracy by the improved flow model. Combining the results obtained from various topics, the aerodynamic heating along the flight path was successfully estimated, which was helpful to make a design requirement for such a reentry vehicle. In parallel, the possibility of the flight demonstration of such a reentry vehicle was studied.Other than the reentry vehicle, a study was conducted on the use of penetrator system for future planetary explanation, in a gas-dynamical point of view, This system study successfully clarified a design requirement of such a penetrator system. Also, the RAM accelerator system was studied, which is useful for the transportation of the exploration result from Moon. Even in a laboratory scale, the RAM accelerator was successfully demonstrated.

对气体动力学在未来行星探测中的应用进行了广泛的研究，主要集中在计划用于MUSES-C任务的再入舱上。 ISAS 计划的 MUSES-C 任务是与小行星会合并将其土壤带回地球。由于其再入速度相当高（-l3公里/秒），必须解决多种气体动力学问题。在目前的研究中，研究工作主要集中在以下几个主要问题上； 1）车辆前方高温冲击层的辐射效率估算，2）高温空气与车辆隔热材料的相互作用，3）高非平衡高温冲击引起的气动热通量估算层。主要主题之一是通过实验观察到的高度热非平衡现象。该结果有望对改进当前流量模型产生影响，有助于改进流量模型提高估计精度。结合各个课题获得的结果，成功地估计了沿飞行路径的气动加热，这有助于为此类再入飞行器提出设计要求。同时，研究了这种再入飞行器的飞行演示的可能性。除了再入飞行器之外，还从气体动力学的角度研究了使用穿透器系统来解释未来的行星，该系统研究成功地阐明了这种侵彻系统的设计要求。此外，还研究了RAM加速器系统，这有助于月球探测成果的传输。即使在实验室规模，RAM 加速器也得到了成功演示。

项目成果

K.Suzuki,H.Kubota,K.Fujita,T.Abe: "Numerical Analysis of Aerodynamic Heating on MUSES-C Reentry Capsule," Paper 96-d-25,Proc.20th Int.Symp.on Space Tech.and Sci.

K.Suzuki、H.Kubota、K.Fujita、T.Abe：“MUSES-C 再入舱气动加热的数值分析”，论文 96-d-25，Proc.20th Int.Symp.on Space Tech.and Sci

N.Arai, S.Kawano,and N.Gon-Mori: "Flow field around a Concave body in Low Speed" The 4th KSME-JSME Fluids Engineering Conference. (1998)

N.Arai、S.Kawano 和 N.Gon-Mori：“低速凹体周围的流场”第四届 KSME-JSME 流体工程会议。

S V.Zhluktov,and T.Abe: "Viscous Shock-Layer Simulation of Airflow past Ablating Blunt Body with Carbon Surface" J.Thermophysics and Heat Transfer. 13(1). 50-59 (1999)

S V.Zhluktov 和 T.Abe：“通过碳表面烧蚀钝体的气流的粘性冲击层模拟”J.热物理学和传热。

S.V.Zhluktov, and T.Abe: "Viscous Shock-Layer Simulation of Airflow past Ablating Blunt Body with Carbon Surface" J.Thermophysics and Heat Transfer. 13(1). 50-59 (1999)

S.V.Zhluktov 和 T.Abe：“通过碳表面烧蚀钝体的气流的粘性冲击层模拟”J.热物理学和传热。

K.Suzuki, H.Kubota, F.Fujita, and T.Abe: ""Chemical Nonequilibrium Stagration Ablation Analysis of MUSES-C Superorbital Re-Entry Capsule"" J.Spacecraft and Rockets. Vol.35, No.3. 407-409 (1998)

K.Suzuki、H.Kubota、F.Fujita 和 T.Abe：“MUSES-C 超轨道再入舱的化学非平衡滞留烧蚀分析”J.Spacecraft and Rocket。