Research on Gas Dynamics in Relation to Performance of Sail-type Spacecraft for Exploration to Outer Planets and Interstellar Region

气体动力学与外行星及星际探索帆式航天器性能关系研究

• 批准号: 17360408
• 负责人: SUZUKI Kojiro
• 金额: $ 9.3万
• 依托单位: The University of Tokyo
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for Scientific Research (B)
• 财政年份: 2005
• 资助国家: 日本
• 起止时间: 2005 至 2007
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-17360408/
• 关键词: Deep Space Exploration; Aeroassist; Solar Sail; Magnetic Sail; Hypersonic Aerodynamics; Membrane Structure; Plasma Wind Tunnel; Aerodynamic Heating; 耐熱膜材料; 柔構造飛翔体; 惑星探査; プラズマ流; エアロキャプチャ; ウェイブライダー; 柔軟膜構造; 誘導結合プラズマ; 電磁流体加速; 希薄気体力学; プラズマ気流診

The methods to augment the ability of the sail type spacecraft by using the aerodynamic force during the atmospheric pass are investigated.1. The plasma flow of the solar wind around the magnetic sail is numerically analyzed by full-PIC method. The magnetic sail can generate the thrust, but it is much smaller than that obtained by the solar sail with the same size. Consequently, the solar sail should be chosen as the first generation's sail-type spacecraft.2. The secondary use of the sail as an aerodynamic decelerator for the spacecraft to be inserted into an orbit around a planet enables us to make the nearly fuel-free orbiter mission for planetary exploration. The low ballistic coefficient atmospheric entry widens the entry corridor, and reduces the aerodynamic heat and load.3. The aerodynamic performance of the hoop-supported membrane vehicle is investigated in the hypersonic wind tunnel It is demonstrated that the automatically deployed aeroshell can be realized by using the shape memory alloy for the hoop. This system is suitable for small atmospheric entry probes. Shape like delta wing can be obtained by the multi-hoop structure. High lift-to-drag ratio of about 5 is expected after shape optimization.4. The rarefied hydrogen plasma wind tunnel has been developed to simulate the aerodynamic heating environment at atmospheric entry to outer planets. The heating tests suggest that the multi-layer material made by the combination of high temperature membranes and high strength ones is promising.5. The combination of the solar sail and the aero-gravity-assist is investigated. The trajectory analysis shows that the membrane spacecraft with length 220 m and mass 410 kg will leave the solar system at velocity 30 km/s and reach the Kuiper belt in 30 years. The proposed vehicle seems promising as the first generations interstellar probe.

研究了利用帆式航天器大气层通过过程中的气动力来增强其能力的方法.采用全粒子模拟方法对磁帆周围太阳风等离子体流场进行了数值分析。磁帆可以产生推力，但它比相同尺寸的太阳帆所获得的推力要小得多。因此，第一代帆型航天器应选择太阳帆。帆的第二用途是作为航天器插入行星轨道的空气动力减速器，使我们能够进行几乎不需要燃料的行星探测轨道飞行器使命。低弹道系数大气层进入拓宽了进入走廊，降低了气动热和气动载荷.在高超声速风洞中对环支撑薄膜飞行器的气动性能进行了实验研究，结果表明，采用形状记忆合金环支撑薄膜飞行器可以实现自动展开。该系统适用于小型大气层进入探测器。多环箍结构可以获得类似三角翼的外形。外形优化后，升阻比有望达到5左右.稀薄氢等离子体风洞是为模拟外行星进入大气层时的气动加热环境而研制的。加热试验表明，高温膜与高强度膜相结合的多层膜材料是很有前途的.研究了太阳帆与气动重力辅助的组合。轨道分析表明，长220米，质量410公斤的膜航天器将以30公里/秒的速度离开太阳系，并在30年内到达柯伊伯带。作为第一代星际探测器，拟议中的飞行器似乎很有希望。

项目成果

極超音速気流中における展開式膜面エアロシェルの空力特性

高超声速气流中可展开膜航空壳的气动特性

• 发表时间: 2007
• 作者: Hamada;T.;et. al.;今村 宰
• 通讯作者: 今村 宰

Heat Shield Design for Small Solar Probe Mission

小型太阳能探测器任务的隔热罩设计

• 发表时间: 2005
• 作者: Hamada;T.;et. al.;Kojiro Suzuki;Kojiro Suzuki
• 通讯作者: Kojiro Suzuki

Shape Optimization of Hypersonic Axisymmetric Body for Low Drag and Low Heating Rate

低阻力低加热速率高超声速轴对称体形状优化

• 发表时间: 2007
• 期刊: CFD Journal, Refereed Paper Vol.15
• 作者: Atsushi Ueno;Kojiro Suzuki
• 通讯作者: Kojiro Suzuki

Numerical Study of Behavior of Outgas from Heat Shield of Solar Probe

太阳探测器隔热罩放气行为的数值研究

• 发表时间: 2006
• 期刊: Journal of Spacecraft and Rockets, Refereed Paper Vol.43
• 作者: 山口健太朗、鈴木えり子、濃田 勉;高木昌宏;Kojiro Suzuki
• 通讯作者: Kojiro Suzuki

CFD-based Shape Optimization of Hypersonic Vehicles Considering Transonic Aerodynamic Perfbrmance

考虑跨音速气动性能的基于CFD的高超声速飞行器形状优化

• 发表时间: 2008
• 作者: Ueno;A.
• 通讯作者: A.