173 results on '"空力加熱"'
Search Results
52. Minimum ballistic coefficients of Venus exploration: Possibility of an aerocapture satellite
- Author
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Nakazawa, Eiko, Yamada, Kazuhiko, and Suzuki, Kojiro
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ポリイミド ,金星大気 ,エアロキャプチャ衛星 ,atmospheric model ,空力加熱 ,ballistic coefficient ,feasibility study ,弾道係数 ,polyimide ,research and development ,運動方程式 ,大気モデル ,予備調査 ,equation of motion ,Venus atmosphere ,membrane structure ,aerodynamic heating ,金星探査 ,Venus probe ,aerocapture satellite ,圧力履歴 ,pressure hysteresis ,膜構造 ,研究開発 - Abstract
資料番号: AA0045913027
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- 2003
53. Melting of an orbit falling body and the safety analysis
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Yamada, Tetsuya, Inatani, Yoshifumi, and Nakajima, Takashi
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落下体 ,Mir宇宙ステーション ,melting ,reentry ,高融点材料 ,空力加熱 ,安全解析 ,空力係数 ,ballistic coefficient ,弾道係数 ,heat balance ,safety analysis ,再突入 ,research and development ,溶融 ,Knudsen流 ,aerodynamic heating ,refractory material ,aerodynamic coefficient ,Mir space station ,熱バランス ,falling body ,Knudsen flow ,研究開発 - Abstract
宇宙ステーション・ミールの落下事象は記憶に残るが、設計寿命を越え軌道減衰が著しくなってきた周回衛星も多くなって来た昨今、軌道から地上への落下物に対する関心が高まってきていると言える。大型重量物の軌道落下はもとより、小型でもチタン合金など比較的高融点、高熱容量の材質を利用したものには軌道落下の残存性に関しては注意が必要である。また、基本的にアブレータのように耐熱性能を追及して製造されていないCFRPなど複合材は構造の破壊が起こり焼損する場合が多い。本稿は、溶融解析の方法を整理した後、いくつかの事例を解析し、溶融落下およびその安全性に関する一般的な議論を展開した。, 資料番号: AA0045913033
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- 2003
54. New compact coupling analyses system with 3-D CFD solver & thermal analyzer with nodal method
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Ohara, Tsuyoshi and Shima, Eiji
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空力加熱 ,計算グリッド ,ソフトウェア配置 ,finite element method ,computational grid ,熱フラックス ,heat flux ,熱解析 ,3 dimensional flow ,software configuration ,有限要素法 ,数学モデル ,research and development ,3次元流 ,compact coupling analysis ,aerodynamic heating ,コンパクトカップリング解析 ,H-2A 4S ,CFD ,thermal analysis ,mathematical model ,研究開発 - Abstract
The CFD and thermal coupling analyses system had been developed which software configuration was very compact to need less computational resource named CCAS (Compact Coupling Analyses System). A nodal method was applied for the thermal analyzer in the system because it essentially needed less memory resources and computation time, while a finite element method is generally used in other coupling analyses system. Also a set of assistance software was made that semi-automatically produced a thermal mathematical model from a CFD model to make a series of analyses work more efficient. A test analysis was done around H-2A 4S fairing during a flight. Heat flux at the stagnation point was compared with the value derived from theoretical equations, and analysis value was about 20 percent higher than from theoretical equations. Also compared were temperatures in the faring body with values of actual measurement at the first flight, and these from analysis were a little higher than actual. Although these calculation results of heat flux and temperatures from analysis indicated higher values, its differences were not so significant and were thought to be in the range of error by modeling uncertainty so the results from analysis were relatively correct and the system was confirmed to be valid., 資料番号: AA0045948018, レポート番号: NAL SP-57
- Published
- 2003
55. 金星突入カプセル:突入から観測気球放出まで
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Yamada, Tetsuya, Hiraki, Koju, Izutsu, Naoki, and Honda, Masahisa
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軌道設計 ,金星大気 ,空力加熱 ,惑星間遷移軌道 ,宇宙探査 ,気球放出 ,balloon release ,金星突入カプセル ,Venus atmosphere ,spacecraft propulsion ,Venus entry capsule ,aerodynamic heating ,宇宙機推進 ,orbital design ,space exploration ,interplanetary transfer orbit - Abstract
金星の高度45km近傍に水蒸気気球を浮遊させ、大気観測を行なうミッションを想定し、惑星間遷移軌道から金星突入を行い、観測気球を所定の高度に放出する小型金星カプセルの研究を行なっている。直径50cm、全長20mに及ぶ長大な気球の落下速度要求、伸張終了時点での過度の伸展張力を与えぬなどの要求により、緩降下パラシュートおよび搭載機器側の空力係数間に一定の関係をもたせた気球の放出シナリオが特徴的な検討課題である。本稿では、カプセルの金星突入から気球を安全に放出・伸張させる点に焦点を絞り検討した結果を報告する。, A balloon observation of the Venusian atmosphere by a water-vapor super-pressure balloon is investigated in the initial planning of the solar sail mission working group formed in ISAS. In order to transport the balloon at the appropriate altitude, a small capsule and its direct entry to the Venusian atmosphere has been proposed here. The high-speed entry to the Venusian atmosphere at about 11.5 km/s exerts severe aerodynamic heating on the capsule. The release of the balloon with 50 cm in diameter by 20 m long requires lots on the release scenario and the aerodynamic mechanisms. The entry flight and the release of the long balloon at the altitude of 45 km is focused on and described in this paper., 資料番号: AA0045497031
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- 2003
56. Chemistry of meteor trails
- Author
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Abe, Shinsuke, Ebizuka, Noboru, Yano, Hajime, Hirahara, Yasuhiro, Kasuga, Toshihiro, Sugimoto, Satoshi, and Watanabe, Junichi
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しし座流星群 ,ファーストポジティブバンド ,永続痕 ,空力加熱 ,first positive band ,meteor trail ,発光 ,ablation ,化学発光 ,Earth ionosphere ,plasma cloud ,プラズマ雲 ,化学組成 ,chemical composition ,ultraviolet emitting substance ,化学分析 ,Leonid meteoroid ,流星痕 ,アブレーション ,chemiluminescence ,地球電離層 ,chemical analysis ,aerodynamic heating ,惑星間ダスト ,light emission ,persistent train ,interplanetary dust ,紫外発光物質 - Abstract
資料番号: AA0045981043
- Published
- 2003
57. 付着線境界層遷移への高エンタルピー効果に関する実験的研究
- Author
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Hornung, H. G. and Fujii, Keisuke
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hypersonic vehicle ,境界層遷移 ,hypersonic flow ,吸収率 ,緩和特性 ,空力加熱 ,極超音速衝撃風洞 ,Damkohler数 ,安定性 ,stability ,Reynolds number ,research and development ,Damkohler number ,enthalpy ,aerodynamic heating ,relaxation characteristic frequency ,極超音速機 ,エンタルピー ,hypersonic shock tunnel ,Physics::Chemical Physics ,absorption rate ,boundary layer transition ,極超音速流 ,Reynolds数 ,研究開発 - Abstract
A series of experiments was conducted on high enthalpy effects on hypersonic boundary layer transition in T5 hypervelocity shock tunnel. This series concerns transition of the attachment line boundary layer on a swept cylinder. The observed trend of transition Reynolds number with total enthalpy shows strong transition delay at a larger sweep angle for carbon dioxide, while no significant effect is observed in nitrogen., 資料番号: AA0045947028, レポート番号: NAL SP-56
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- 2002
58. CFD analysis and wind tunnel experiments of hypersonic shock-shock interaction heating for TSTO two body problem and proposal of new CFD workshop problem
- Author
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Yamamoto, Yukimitsu, Hozumi, Koichi, Tsuda, Shoichi, Koyama, Tadao, and Hirabayashi, Noriaki
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衝撃波相互作用 ,hypersonic wind tunnel ,two body problem ,hypersonic flow ,numerical analysis ,空力加熱 ,極超音速風洞 ,数値解析 ,計算流体力学 ,computational fluid dynamics ,Navier-Stokes方程式 ,Navier-Stokes equation ,aerodynamic heating ,2体問題 ,shock wave interaction ,極超音速流 - Abstract
Hypersonic aerodynamic interactions for two hemisphere-cylinders have been investigated numerically and experimentally for future TSTO space transport problems. Two hemisphere models with a diameter of 3 cm and 6 cm are placed parallel or with the inclined angle from 13 to 16 deg and complicated shock-shock interactions which generates severe heating on the body surface are studied by using NAL Mach 10 Hypersonic Wind Tunnel and CFD analysis. The purpose of the present study is to understand the complicated flow phenomena and to predict the related severe peak heating rate in the interaction area. Finally, proposals of CFD workshop are made for these two body shock/shock interaction problems. These works contribute to future TSTO aerodynamic design problems in both cruising and separation stages., 資料番号: AA0032819007, レポート番号: NAL SP-53
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- 2002
59. Analysis of real flow phenomena and application for the aerospace design problems by CFD
- Author
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Yamamoto, Yukimitsu
- Subjects
信頼性 ,reliability ,空力加熱 ,計算グリッド ,computational grid ,風洞 ,wind tunnel ,計算流体力学 ,computational fluid dynamics ,aerodynamic heating ,飛行実験 ,航空機設計 ,spacecraft design ,flight experiment - Abstract
CFD has become one of the main tools for the aerodynamic design problems with the wind tunnel experiments. At present, the reliability of CFD results is not 100 percent, however, its application area is enlarged. The following reasons are considered: (1) Aerospace vehicle design becomes more sophisticated and simple theory can not be applied to understand the real flow phenomena. (2) If geometry design and related grid generations can be done smoothly and fast, a large number of parametric design studies becomes possible by the progress of recent computer hardwares. Before doing the costly experimental works, CFD can achieve the optimum design purposes with the reduction of the necessary cost and the shortening of the term for developments. (3) CFD oriented Multi-Disciplinary Simulation (MDS) offers new ability for the highly aculate systems of the design process and evaluations. MDS tools are in general use for the pre-flight and post-flight evaluations of the aerospace flight experiments. In this report, typical examples of these CFD efforts are introduced and future prospects are overviewed., 資料番号: AA0032819008, レポート番号: NAL SP-53
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- 2002
60. HOPE熱荷重推定のための空力/熱伝導連成シミュレーション
- Author
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Otake, Kunihiko, Yamamoto, Yukimitsu, and Haneji, Kazuhiko
- Subjects
reentry vehicle ,numerical analysis ,空力加熱 ,数値解析 ,finite element method ,heat flux ,計算流体力学 ,熱解析 ,computational fluid dynamics ,再突入機 ,有限要素法 ,aerodynamic heating ,HOPE ,熱流束 ,thermal analysis ,ComputingMethodologies_COMPUTERGRAPHICS - Abstract
This paper discusses the development of a CFD/FEM coupling thermal simulation system, with its application to the thermal analysis of re-entry vehicle HOPE. The modified method is applied to improve the smooth interpolation of data generated by different grid systems, and works well. In addition, the information of computer resource for this large simulation work is obtained., 資料番号: AA0032819010, レポート番号: NAL SP-53
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- 2002
61. Uncertainty evaluation of hypersonic aerodynamic heating in tunnel to tunnel tests using flat plate with a compression ramp
- Author
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Hozumi, Koichi and Koyama, Tadao
- Subjects
衝撃波相互作用 ,hypersonic wind tunnel ,flat plate ,空力加熱 ,平板 ,極超音速風洞 ,赤外カメラ ,infrared camera ,計算流体力学 ,computational fluid dynamics ,極超音速熱伝達 ,aerodynamic heating ,shock wave interaction ,hypersonic heat transfer - Abstract
To evaluate the data uncertainty attributed to hypersonic heat transfer measurement technique, cooperative heat flux measurement tests on the flat plates with compression ramps using Infra Red (IR) cameras are conducted in the NAL 1.27 m and ONERA/S4MA hypersonic wind tunnel at Mach number 10. Efforts to examine the main factors affecting data accuracy in IR thermography tests and to evaluate and minimize IR heat flux data uncertainty during the cooperative test campaign were described. The final tunnel-to-tunnel comparison results and comparisons of the heat flux with the flux obtained from other sensors showed that the test data are high quality of within 3 to 5 percent uncertainty. This result shows the adequacy of tunnel flow quality and testing techniques in both tunnels. Examination study in the present cooperation for the initial discrepancy between experimental and computational results showed the importance of understanding of flow phenomena or appropriate modeling of the physics, i.e., importance of interaction between computational and experimental fluid dynamics in CFD code validation study., 資料番号: AA0032819003, レポート番号: NAL SP-53
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- 2002
62. Thermal analysis of the HYFLEX vehicle using a complete three-dimensional FEM model
- Author
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Kai, Takashi, Yamamoto, Yukimitsu, Kamita, Toru, and Hirabayashi, Toshiyuki
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carbon carbon composite ,numerical analysis ,空力加熱 ,数値解析 ,極超音速飛行 ,計算流体力学 ,熱解析 ,3次元モデル ,computational fluid dynamics ,Navier-Stokes方程式 ,three dimensional model ,Navier-Stokes equation ,炭素炭素複合材 ,aerodynamic heating ,hypersonic flight ,thermal analysis - Abstract
A precise three-dimensional HYFLEX thermal model has been developed. It is intended to be a standard model used in the evaluation of candidate methods making simple re-entry vehicles' FEM models suitable for early design phases. The model consists of about 30,000 elements and includes various types of TPS ranging from carbon/carbon hot structures to ceramic tiles and aluminum structural parts in rather realistic shapes fundamentally using hexahedral elements. On-board equipments such as actuators, propulsion system, parachute, and floating bag are modeled as simple shapes having equivalent thermal capacities. Electronic equipments are neglected because they were placed on instrument panels which were thermally isolated from fuselage by means of insulating rubbers. Aerodynamic heat load for the analysis was obtained fundamentally through CFD calculations not taking account of turbulence transition. Results of an analysis using the model do not show good agreements with flight data of HYFLEX. There are some reasons: (1) the inner radiation heat change within elevon is not included because of the workstation's ability; (2) tentative heat rates are set for areas where CFD did not give; and (3) bolts are neglected in the models of metal fittings of nose cap. These items must be included to improve the model., 資料番号: AA0032819009, レポート番号: NAL SP-53
- Published
- 2002
63. Effect of surface catalysis on aerodynamic heating in high enthalpy shock tunnel
- Author
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Ueda, Shuichi, Sato, Kazuo, Komuro, Tomoyuki, Tanno, Hideyuki, Ito, Katsuhiro, Kurotaki, Takuji, Shiromizu, Masao, Tsujimoto, Takeshi, and Miho, Kazuyuki
- Subjects
空力加熱 ,表面反応 ,打ち上げ機 ,heat flux ,計算流体力学 ,surface reaction ,computational fluid dynamics ,風洞試験 ,launch vehicle ,enthalpy ,aerodynamic heating ,熱流速 ,エンタルピー ,shock tunnel ,wind tunnel test ,衝撃風洞 - Abstract
宇宙往還機の大気圏再突入時には、機体まわりの強い衝撃波により窒素、酸素分子の解離が起こる。解離原子の再結合特性は機体表面の触媒性に大きく依存し、機体への熱伝達に大きく影響する。しかしながら、表面触媒効果による流れ場や空力加熱への影響についての実験的研究は少なく、触媒効果のモデル化およびその検証も進んでいない。本報告では高温衝撃風洞における平板模型の空力加熱に対する触媒性の影響の研究について述べる。風洞試験には金属およびSiO2をコーディングした平板模型を使用し、供試体表面温度の触媒効果に対する影響を調べるため、ヒーターによる予熱機構を採用した。, 資料番号: AA0032235015, レポート番号: NAL SP-51
- Published
- 2001
64. Aerodynamic heating measurement by infrared camera system
- Author
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Koyama, Tadao, Hirabayashi, Noriaki, Tsuda, Shoichi, Sekine, Hideo, Nagai, Shinji, and Hozumi, Koichi
- Subjects
温度測定 ,空力加熱 ,infrared camera ,熱伝達係数 ,計算流体力学 ,熱電対 ,computational fluid dynamics ,赤外線カメラ ,heat transfer coefficient ,thermocouple ,超音波風洞 ,aerodynamic heating ,temperature measurement ,supersonic wind tunnel - Abstract
航空宇宙技術研究所の大型極超音速風洞では、空力加熱測定を赤外線カメラを用いて行っている。この赤外線カメラによる空力加熱測定法は、従来の離散的なセンサによる測定法に比べ、機体全体にわたる空力加熱を2次元的な面情報として捉えられるため、局所的なピーク加熱も捕捉できる点で優れている。また、これまで定量測定精度の問題が指摘されていたが、誤差量の見積もり、補正方法の確立、3次元マッピングソフトウェアの開発、従来型のセンサとの比較試験などを行い、総合的な測定精度として10%以内の測定が可能であることを確認した。赤外線カメラによる空力加熱測定法は、極超音速風洞における空力加熱測定の実用的なシステムとしてほぼ確立した。ここでは、赤外線カメラによる空力加熱測定法の概要と定量測定精度を高めるために行った誤差の検討と補正法、センサとの比較試験などについて報告する。, 資料番号: AA0032235012, レポート番号: NAL SP-51
- Published
- 2001
65. Preliminary study of thermal protection system of single-stage-to-obit plane
- Author
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Kudo, Kenji and Kanda, Takeshi
- Subjects
空力加熱 ,airframe cooling ,ceramic tile insulation ,極超音速飛行 ,飛行シミュレーション ,single stage to orbit plane ,水素強制冷却 ,hydrogen cooled panel ,thermal protection system ,hydrogen active cooling ,熱防護システム ,セラミックタイル断熱 ,aerodynamic heating ,水素冷却パネル ,hypersonic flight ,単段式スペースプレーン ,機体冷却 ,飛行動圧 ,flight dynamic pressure ,flight simulation - Abstract
スペースブレーンは低軌道に達するまでに空気中に約15分以上飛行する。この間、特にスクラムジェットを使用する極超音速飛行時に、スペースプレーンは強い空力加熱を受ける。そこで今回、簡単なモデルを使って加速上昇中の単段スペースプレーン(SSTO)熱防護システムの特性について検討した。タイルによる熱防護材と水素による強制冷却を検討対象とした。飛行経路に沿ったシミュレーションを行い、タイル内温度分布あるいは水素冷却パネルの冷却要求について検討を行った。その結果、以下のことが明らかになった。タイルを用いた熱防護システムの場合、タイル裏面の最高温度は軌道到達後に現れた。従ってタイル設計には、軌道到達後のタイルの状態も考慮する必要がある。今回の検討ではタイル裏面の温度が内部断熱材許容上限温度480Kを越えない場合のタイルの最小厚さは、機体上面で50mm、下面で60mmであった。タイル表面温度を使用限界温度1,500K以下にするためには、飛行動圧を100kPa以下にする必要があった。タイル裏面最高温度は、飛行動圧の低下による飛行時間の増加と共に上昇した。機体の能動冷却に必要な水素質量は燃料水素質量の約20%であった。水素冷却パネル表面にタイルを張り合わせることで、機体の冷却に要する水素質量を減らすことができた。, This paper discusses the Thermal Protection System (TPS) of an airframe of the Single Stage To Orbit (SSTO) with a scramjet engine. There is aerodynamic heating to the airframe during flight through the air, especially during hypersonic flight, and this paper examines ceramic tile insulation and hydrogen active cooling. The transient nature of each system was simulated along the ascent trajectory of the SSTO to the low earth orbit of 100 km. When ceramic tiling was used, a tile thickness of around 60 mm was required to protect the inside of the airframe. The highest temperature on the inside surface of the tile occurred after arrival to the orbit. The temperature on the inside surface increased with the decrease of the flight dynamic pressure. In the active cooling system, around 20 percent of fuel were used for airframe-cooling. Attaching thin ceramic tiling on the surface of the cooling panel reduced the cooling requirement., 資料番号: AA0028665000, レポート番号: NAL TR-1420
- Published
- 2000
66. A comparison test on aerodynamic heating around 09HOPE in NAL hypersonic wind tunnel
- Author
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Fujii, Keisuke, Hozumi, Koichi, Tsuda, Shoichi, Koyama, Tadao, and Wakamatsu, Itsuo
- Subjects
空力加熱 ,極超音速風洞試験 ,09HOPE ,大気圏再突入 ,HOPE X ,Von Karman gas dynamics Facility ,迎角効果 ,H 2 Orbiting Plane ,Arnold Engineering Development Center ,宇宙往還技術試験機 ,アーノルド工学開発センター ,AEDC ,H 2 Orbiting Plane Experimental ,hypersonic wind tunnel ,HOPE-X ,極超音速風洞 ,atmosphere reentry ,attack angle ,VKF ,hypersonic wind tunnel test ,comparison test ,加熱率センサ ,フォン・カルマン空気力学施設 ,aerodynamic heating ,HOPE ,対応風試 ,heating rate sensor - Abstract
21-22 May 1998 (60th). 26-27 Nov. 1998 (61st), 現在設計が進められている有翼宇宙往還機HOPE-Xの空力加熱データ取得の目的でNASDA発注により1996年および1997年にAEDC(アーノルド工学開発センター)VKF(フォン・カルマン空気力学施設)風洞B、Cにおいて試験が実施されていた。今回これらとの対応風試を航技研極超音速風洞において行ったのでそれらの結果の比較について報告する。模型は基準長576mmの3.6%HOPE(H-2ロケット打ち上げ型有翼回収機)であって、今回の風試では表面上のおよそ400個所に埋め込まれた加熱率センサの一部を用いて空力加熱を計測した。AEDCにおいて行われたケースに完全に対応したデータは必ずしも得られていないが、14Run、43ケースの試験を行った。, To obtain the aerodynamic heating data of HOPE-X (H-2 Orbiting Plane Experimental), the design of which is now in progress, experiments placed by NASDA were performed at AEDC (Arnold Engineering Development Center) VKF (Von Karman gas dynamics Facility) tunnel B, C in 1996 and 1997. A comparison test has been performed at the NAL hypersonic wind tunnel and the results are reported here. The model is a 3.6 percent HOPE (H-2 Orbiting Plane) of the reference length 576 mm. In the experiment, the aerodynamic heating is measured by about 400 heating rate sensors embedded on the surface of the model. Although the data are not completely corresponding to the AEDC case, 14 runs of 43 cases of experiments have been performed., 資料番号: AA0001959008, レポート番号: NAL SP-42
- Published
- 1999
67. Aerodynamic heating experiment on a HOPE-X model in the high enthalpy shock tunnel
- Author
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Tanno, Hideyuki, Komuro, Tomoyuki, Sato, Kazuo, Ito, Katsuhiro, Takahashi, Masahiro, Ueda, Shuichi, Maehara, Takuya, Narita, Tomoaki, and Suito, Takanobu
- Subjects
同軸型熱電対 ,heat flux fluctuation ,HOPE-X ,自由ピストン型衝撃風洞 ,空力加熱 ,熱流束分布 ,熱流束の変動 ,coaxial thermocouple ,翼前縁 ,free piston shock tunnel ,leading edge ,HOPE X ,high enthalpy shock tunnel ,heat flux distribution ,aerodynamic heating ,高温衝撃風洞 ,宇宙往還技術試験機 ,H 2 Orbiting Plane Experimental - Abstract
21-22 May 1998 (60th). 26-27 Nov. 1998 (61st), HOPE-X(宇宙往還技術試験機)模型の空力加熱試験を航空宇宙技術研究所角田研究センターの自由ピストン型衝撃風洞(HIEST)で実施した。70個の同軸型熱電対を模型の風上側に装備した。模型は実物の1/40スケールである。気流条件は、同じ自由ピストンドライバー条件の下で、ノズルスロート径を変えることにより変化させた。この条件の下で測定された模型の周りの熱流束分布を報告した。模型の翼前縁の熱流束の変動についても言及した。, Aerodynamic heating experiment on a HOPE-X (H-2 Orbiting Plane Experimental) reentry vehicle model was carried out in the free piston shock tunnel HIEST (High Enthalpy Shock Tunnel) at National Aerospace Laboratory Kakuda Research Center. Seventy coaxial thermocouples were instrumented on the windward of the model, which is 1/40 scale of the actual vehicle. Flow condition was varied with different diameter nozzle throats under same free piston driver condition. Measured heat flux distribution around the model under the condition was reported. Heat flux fluctuation on the leading edge of the model was also mentioned., 資料番号: AA0001959007, レポート番号: NAL SP-42
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- 1999
68. 空力加熱を受けるHYFLEX構造の非定常熱解析
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Otake, Kunihiko, Ogawa, Satoru, Kai, Takashi, Haneji, Kazuhiko, 大竹 邦彦, 小川 哲, 甲斐 高志, 羽地 和彦, Otake, Kunihiko, Ogawa, Satoru, Kai, Takashi, Haneji, Kazuhiko, 大竹 邦彦, 小川 哲, 甲斐 高志, and 羽地 和彦
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Transient thermal response behavior of hypersonic reentry flight test vehicle HYFLEX (Hypersonic Flight Experiment) was investigated. The iterative CFD (Computational Fluid Dynamics)/FEM (Finite Element Method) coupling analysis was carried out. In this study, flow field around the body is computed by the finite volume Navier-Stokes equation solver FIVAD. On the other hand, heat conduction behavior is calculated by the finite element solver THAP. The NWT (Numerical Wind Tunnel) system and CMS (Common work Station) system of NAL are used for simulation, with the data file transfer by LAN (Local Area Network)., 極超音速で大気圏に再突入する実験機HYFLEX(極超音速飛行実験)について、空力加熱解析と構造熱伝導解析を連成させて、非定常熱応答の数値シミュレーションを試みた。対象をHYFLEX機体前胴部とし、空力解析は有限体積法コードFIVADを用い、熱伝導解析は有限要素法コードTHAPを用いた。計算には航空宇宙技術研究所の大規模並列ベクトルコンピュータシステムである数値風洞(NWT)と構造計算用ワークステーションシステム(CMS)を用い、データファイル転送による分散処理を行った。
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- 2015
69. 高マッハ数で伝播する衝撃波背後のCARS法による気体分子振動・回転温度計測
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Maeno, Kazuo, Toyoda, Kazuhiro, Ando, Hiroyuki, Miyazaki, Katsumi, 前野 一夫, 豊田 和弘, 安藤 広行, 宮崎 勝巳, Maeno, Kazuo, Toyoda, Kazuhiro, Ando, Hiroyuki, Miyazaki, Katsumi, 前野 一夫, 豊田 和弘, 安藤 広行, and 宮崎 勝巳
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When a space vehicle reenters onto the atmosphere with high velocity, radiative heating from the shocked air ahead of the vehicle plays an important role on the heat flux to the wall surface as well as convective heating. In the laboratory, the spectroscopic system has been developed for temperature measurement of radiation behind strong shock waves. In this paper, CARS method (Coherent Anti-Stokes Raman Spectroscopy) for radiative flow behind strong shock waves of high Mach number has been developed. The CARS measurement system consists of a YAG laser, a dye laser, optical system, and high-sensitivity I.I.-CCD camera systems with spectroscopy. The preliminary tests have been performed for the purpose of detecting CARS signal from strong shock waves with velocity range over 5 km/s. Finally, both vibrational and rotational temperatures could be estimated by fitting of the CARS spectra obtained from experiment and analytical calculation over Mach 15.
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- 2015
70. Utilization of expansion tube for MUSES-C reentry simulation
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Saso, Akihiro, Otsu, Hirotaka, Abe, Takashi, Sawada, Keisuke, Mizuno, Hiroyasu, 佐宗 章弘, 大津 広敬, 安部 隆士, 澤田 恵介, 水野 裕保, Saso, Akihiro, Otsu, Hirotaka, Abe, Takashi, Sawada, Keisuke, Mizuno, Hiroyasu, 佐宗 章弘, 大津 広敬, 安部 隆士, 澤田 恵介, and 水野 裕保
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An expansion tube has a unique capability of generating a hypervelocity flow without experiencing a stagnation condition of the test gas. Related to MUSES-C superorbital reentry flow condition, experimental and numerical simulations were conducted in domestic institutions as well as in University of Queensland, Australia. This paper summarizes the characteristics of the facility and results of their investigations., The Institute of Space and Astronautical Science Report SP
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- 2015
71. Transient heat conduction simulation of HYFLEX under aerodynamic heating
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Otake, Kunihiko, Ogawa, Satoru, Kai, Takashi, Haneji, Kazuhiko, 大竹 邦彦, 小川 哲, 甲斐 高志, 羽地 和彦, Otake, Kunihiko, Ogawa, Satoru, Kai, Takashi, Haneji, Kazuhiko, 大竹 邦彦, 小川 哲, 甲斐 高志, and 羽地 和彦
- Abstract
Transient thermal response behavior of hypersonic reentry flight test vehicle HYFLEX (Hypersonic Flight Experiment) was investigated. The iterative CFD (Computational Fluid Dynamics)/FEM (Finite Element Method) coupling analysis was carried out. In this study, flow field around the body was computed using the finite volume Navier-Stokes equation solver FIVAD. On the other hand, heat conduction behavior was calculated using the finite element solver THAP. The NWT (Numerical Wind Tunnel) system and CMS (Common Work Station) system of NAL were used for simulation, with the data file transfer by LAN (Local Area Network)., 極超音速で大気圏に再突入するHYFLEX(極超音速飛行実験)実験機について、過渡熱応答挙動を研究した。ここでは反復CFD/FEM(計算流体力学/有限要素法)結合解析を実施した。本研究では機体周りの流れ場をナビエ・ストークス方程式有限体積法コードFIVADを用いて計算した。熱伝導挙動は有限要素法コードTHAPを用いて計算した。シミュレーション計算には航空宇宙技術研究所の数値風洞(NWT)と共通ワークステーションシステム(CMS)を用い、データファイル転送は局地ネットワーク(LAN)を使用した。
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- 2015
72. Comparative force/heat flux measurements between JAXA hypersonic test facilities using standard model HB-2
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Kuchiishi, Shigeru, Watanabe, Shigeya, Ueda, Shuichi, Tanno, Hideyuki, Komuro, Tomoyuki, Sato, Kazuo, Ito, Katsuhiro, 口石 茂, 渡辺 重哉, 植田 修一, 丹野 英幸, 小室 智幸, 佐藤 和雄, 伊藤 勝宏, Kuchiishi, Shigeru, Watanabe, Shigeya, Ueda, Shuichi, Tanno, Hideyuki, Komuro, Tomoyuki, Sato, Kazuo, Ito, Katsuhiro, 口石 茂, 渡辺 重哉, 植田 修一, 丹野 英幸, 小室 智幸, 佐藤 和雄, and 伊藤 勝宏
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This report presents a detailed description and results of force and heat flux measurements conducted at the High-Enthalpy Shock Tunnel (HIEST) of the Japan Aerospace Exploration Agency (JAXA). The HB-2 standard hypersonic ballistic configuration was employed as a model. The force measurement tests used an aluminum alloy model and a three-component aerodynamic balance. An acceleration compensation technique was used to remove vibration components from the original data. Heat flux measurement tests used a chromel model with a total of 28 co-axial thermocouples press-fitted onto the surface. Time histories of temperature data were numerically integrated to determine the surface heat flux by applying one-dimensional heat conduction theory. Both force and heat tests used a conical nozzle, and a total of three enthalpy levels of 4, 8, and 11 MJ/kg and two levels of 4 and 8 MJ/kg were set for the force and heat tests, respectively. Although much higher stagnation enthalpy can be attained, relatively lower enthalpy levels were selected to compare with a blow-down type hypersonic wind tunnel and to alleviate uncertainties inherent in high-enthalpy facilities. The force test results correlated well with other hypersonic wind-tunnel data for the axial force coefficient at the enthalpy level of 4 MJ/kg, while a notable discrepancy was observed at the higher enthalpy levels of 8 and 11 MJ/kg. The real gas effects on aerodynamic characteristics are examined and discussed. In the heat test, a comparison of the heat flux distribution along the surface with data obtained in a blow-down type hypersonic wind tunnel showed good agreement in the nose part, typically within several percent. The present experiment was conducted as a series of comparative test campaigns between two hypersonic facilities in JAXA. Since the tunnel stagnation conditions and the corresponding data are tabulated in detail for each shot, the present test data are believed to serve as a complete database for eva, 本報告は、JAXA高エンタルピ衝撃風洞(HIEST)において実施された、HB-2形状バリスティック標準模型を用いた空気力/空力加熱率測定試験結果に関するものである。力試験はアルミ製模型に十字1列型3分力天秤を装着して実施され、データの振動成分を除去するために加速度補正が施された。熱試験で用いられた模型はクロメル製で計28個の同軸熱電対が装着されてあり、温度時間履歴データを1次元熱伝導の仮定の下で数値的に積分することにより加熱率を求めた。力/熱試験共にコニカルノズルを使用し、力試験についてはエンタルピ4、8、11MJ/kg、熱試験については4、8MJ/kgの試験条件でそれぞれ実施された。力試験結果はエンタルピ4MJ/kg条件の場合、軸力係数に関して他風洞の試験データと良好な傾向の一致を示している一方で、8、11MJ/kgの場合は系統的なずれが観測されており、実在気体効果の影響が可能性として示唆される。一方熱試験における無次元加熱率データは、ブローダウン式コールド極超音速風洞データと模型頭部において数%程度の範囲でよい一致を示した。本試験は、JAXA極超音速関連風洞対応風試の一環として実施されたものであり、また本試験データは高エンタルピ衝撃風洞における基礎データとしても有用である。, JAXA Research and Development Report, 宇宙航空研究開発機構研究開発報告
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- 2015
73. ONERA-NALマッハ10平板模型対応風試CFD解析
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Yamamoto, Yukimitsu, Hozumi, Koichi, Fujii, Keisuke, 山本 行光, 穂積 弘一, 藤井 啓介, Yamamoto, Yukimitsu, Hozumi, Koichi, Fujii, Keisuke, 山本 行光, 穂積 弘一, and 藤井 啓介
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Hypersonic CFD (Computational Fluid Dynamics) analysis is made for blunt nosed, ramped flat plates. Heat transfer and flow field around compression ramp have been investigated numerically. The present work correspond to the experimental study using the NAL 1.27 m and ONERA (Office National d'Etudes et de Recherches Aerospatiales) S4MA hypersonic wind tunnels, where the infrared thermography measurements are made at M(sub infinity) = 10.0 and angles of attack 0 deg, 20 deg, 30 deg and 35 deg. Heat transfer distributions and shock-shock interaction patterns are compared in detail, changing angles of attack and Reynolds numbers. Comparisons with CFD simulation using NAL and ONERA Navier-Stokes Codes were also made., 極超音速CFD(数値流体力学)解析を鈍頭ノーズ・ランプ平板について行った。圧縮ランプ周りの熱伝達および流れ場を数値的に調べた。本研究はNAL(航空宇宙技術研究所)の1.27m、ONERA(フランス国立航空宇宙技術研究所)のS4MA極超音速風洞を用いた実験研究に対応し、赤外サーモグラフィー計測を主流マッハ数10.0、迎え角0度、20度、30度および35度で行った。迎え角およびレイノルズ数を変えて、熱伝達分布および衝撃波間干渉パターンを詳細に比較した。NALおよびONERAナビエ・ストークスコードを用いたCFDシミュレーションとも比較した。
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- 2015
74. HYFLEX onboard measurement program
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Inoue, Yasutoshi, Shirouzu, Masao, 井上 安敏, 白水 正男, Inoue, Yasutoshi, Shirouzu, Masao, 井上 安敏, and 白水 正男
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In the HYFLEX (Hypersonic Flight Experiment), a consecutive hypersonic flight duration of some five minutes is secured. Therefore, it is expected to get the hypersonic aerodynamic/aerothermodynamic performance data good enough in both qualitative and quantitative sense for the region of M greater than 10, where best performance is crucial for the reusable space vehicles. Selection of the measurement items for the onboard measurement system was made among both aerodynamics and aerothermodynamics to get the real gas effects, thermostructural evaluation data, basic data for evaluation of lifting body technology (guidance, navigation and control) etc., consisting of some 250 channels in total. Grounds to select measurement items, the analysis and tests for design and confirmation, and specifications of each items are outlined and discussed in this paper. But mostly measurement mission items are discussed in this paper. Major objective of HYFLEX onboard measurement is to contribute to establishing reliable prediction/design methods for the winged space vehicles. To do this, the comparison between the flight data and the predictions made in advance based on ground tests and analyses is indispensable. For the meaningful comparison, the atmospheric condition along flight path must be known accurately enough. In HYFLEX, the utilization of the remotely sensed atmospheric data by NOAA meteorological satellite was planned to raise the inference accuracy. Data analysis program is briefly presented., 極超音速飛行実験においては、5分間程度の持続的な極超音速飛行時間が確保されるため、再使用型往還機に重要なM>10領域の極超音速空力、空力加熱特性データが質的および量的ともに充実したレベルで得られることが期待された。機上搭載計測系のための計測項目の選定において、極超音速領域の実在気体効果を得るための空力、空力加熱特性データ、熱構造特性評価用データ、および揚力飛行物体の基本データ(誘導、航法および軌道制御に関するデータ)などを抽出し、約250チャンネルの計測項目計画をたてた。ここでは各計測項目を選定した基準、設計とその確認のための解析・試験、各項目の仕様について概観し、特に具体的議論は主にデータ計測系に限った。HYFLEX機上搭載計測の主目的は有翼宇宙往還機に対する信頼度の高い予測手法や設計手法の確立に資することである。そのためには、地上での事前試験や解析に基づいた予測をフライトデータと比較することが不可欠となる。有意義な比較のためには、飛行経路に沿った大気状態を充分正確に把握する必要がある。NOAA気象衛星のリモートセンシング大気データを使用し、推定精度を上げることを試みている。データ解析計画の概略も述べてある。
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- 2015
75. 耐熱タイル表面黒色コーティングの放射率計測
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Ishida, Kiyomichi, Sano, Masaaki, Hamamura, Osamu, Sakuyama, Hideaki, 石田 清道, 佐野 政明, 濱村 修, 柵山 英明, Ishida, Kiyomichi, Sano, Masaaki, Hamamura, Osamu, Sakuyama, Hideaki, 石田 清道, 佐野 政明, 濱村 修, and 柵山 英明
- Abstract
The normal emittance of the Black High Emittance (BHE) coating for refractory tiles has been measured for surface temperatures of 473 to 1,473 K. The changes in emittance between new and exposed tiles were evaluated, and no distinct difference was found. The effects of thin metallic and ceramic coatings on BHE were also measured and discussed., OREX(軌道再突入実験機)軌道再突入実験の飛行実験データ解析のため、耐熱タイル黒色コーティングの放射率計測を行った。低温域(473K)での放射率計測には、放射率は同一温度の黒体試料を参照して求めるFT-IR(フーリエ変換赤外分光法)装置(波長範囲0.2〜25マイクロメートル)を使用し、高温域(1,073〜1,473K)では試料移動法により全垂直放射率(波長範囲0.2〜9マイクロメートル)を計測する高温放射率計測装置を使用した。耐熱タイル黒色コーティング供試体については、未使用品およびOREX飛行を模擬したアーク加熱風洞試験済み供試体を計測し、加熱による放射率の変化を観察した。その結果、低温域および高温域とも、両供試体の放射率に顕著な差異のないことが分った。また、耐熱タイル黒色コーティング表面に薄膜コーティングを施して、表面特性を改変した3種類の供試体(SiC、Au、Ir)の計測を行い、薄膜コーティングが計測結果に与える影響などについても討論した。
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- 2015
76. 第73回風洞研究会議論文集
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Japan Aerospace Exploration Agency, 宇宙航空研究開発機構, Japan Aerospace Exploration Agency, and 宇宙航空研究開発機構
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JAXA Special Publication, 宇宙航空研究開発機構特別資料
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- 2015
77. 解離再結合加熱とアブレータの飛行試験結果
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Watanabe, Yasuo, Wada, Yasuhiro, Ogawa, Satoru, Akimoto, Toshio, Maru, Masao, 渡辺 泰夫, 和田 安弘, 小川 哲, 秋元 敏男, 丸 正生, Watanabe, Yasuo, Wada, Yasuhiro, Ogawa, Satoru, Akimoto, Toshio, Maru, Masao, 渡辺 泰夫, 和田 安弘, 小川 哲, 秋元 敏男, and 丸 正生
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The outline of the mission and initial analysis of the flight data of the recombination heating and ablation sensors installed on the fourth row of the ceramic tile Thermal Protection System (TPS) of Orbit Reently Experiment (OREX) are described., 機体表面での再結合加熱にたいする表面触媒性の効果を観測することを目的とした再結合加熱センサとアブレータによる熱防護特性評価のためのアブレータセンサを製作しOREX第4列タイル上に搭載した。再結合加熱センサは3種類の表面(BHE,SiC,Au)の触媒効果の差異の観測を、アブレータセンサは深さ方向温度履歴データより熱ブロッキング効果を評価する。これらセンサで得られた飛行データの初期解析結果を述べる。
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- 2015
78. スペースシャトル及びHYFLEXまわりの高温実在気体解析
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Yamamoto, Yukimitsu, 山本 行光, Yamamoto, Yukimitsu, and 山本 行光
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In order to validate real gas CFD (Computational Fluid Dynamics) code and construct appropriate real gas models, analysis of HEK (High Enthalpy shock tunnel at Kakuda Research Center), high enthalpy shock tunnel experiment is made by using one temperature chemically nonequilibrium CFD code. Aerothermodynamic heating distributions on the windward surface of HYFLEX (Hypersonic Flight Experiment) six percent model are compared in detail. Four test conditions in HEK are selected to investigate enthalpy and binary scaling effects on heating characteristics and good agreements are obtained. To extrapolate data from ground to flight, real gas computations are also made for HYFLEX flight conditions at catalytic and non-catalytic wall assumptions. On the other hands, at high altitude and high mach numbers like HOPE-X (H-2 Orbiting Plane Experimental) reentry flight, trim capability of high angle attack is an important design factor. To investigate real gas effects of these aerodynamic characteristics, calculations are made around space shuttle configuration along its trajectory from mach number five to 26. Real gas effects on center of pressure locations are compared well with the shuttle OADB data., 実在気体CFD(数値流体力学)コードを確認して適切な実在気体モデルを構築するために、1温度で化学的に非平衡のCFDコードを使ってHEK(角田宇宙推進技術研究センター高エンタルピー衝撃風洞)実験を解析した。HYFLEX(極超音速飛行実験)6%モデルの風上表面における空力加熱分布を詳細に比較した。HEKについて4テスト条件を選択して、加熱特性に対するエンタルピーと2成分スケーリングの効果を研究し、良い一致を得た。データを地上から飛行へ補外するために、触媒および非触媒壁条件におけるHYFLEX飛行条件について実在気体計算を行った。一方、HOPE-X(宇宙往還技術試験機)再突入飛行のような高高度高マッハ数において、高角度アタックのトリム能力が重要な設計指標となる。これらの空力特性に対する実在気体の効果を研究するために、マッハ数が5から26までのスペースシャトルの軌道に沿った配置周囲で計算を行った。圧力位置の中心に対する実在気体の効果をシャトルのOADBデータと良く対比した。
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- 2015
79. HOPE誘導制御技術の課題
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Suzuki, Takahiro, 鈴木 崇弘, Suzuki, Takahiro, and 鈴木 崇弘
- Abstract
In the development of the HOPE (H-2 Orbiting Plane) guidance control subsystem, the following technical items are to be studied: Rendezvous-docking phase (RDV), orbital separation and reentry phase, Terminal Area Energy Management phase (TAEM), approaching and landing phase, redundancy techniques, and software. As for RDV, remote navigation RDV and automatic RDV should be combined and its safety and operability should be improved. As for the reentry phase, Lambert rule should be used. After the reentry interface, it would be desirable to use the closed form method, but a sufficient margin should be allowed for the constraints due to the aerodynamic heating rate of HOPE. The flight control system of the TAEM phase should be able to cope with large variations of the aerodynamic parameters in the transonic range. A Microwave Landing guidance System (MLS) should be used at the approaching and landing phase, but the adjustment between the nominal orbit and the flight performance should be very important and arranged to be made. Though the guidance control system had triple redundancy, it would be necessary to study the simplification of redundancy structure, the adequacy of redundancy control rule, and the efficient experimental method. As for software development, the quality assurance and task analysis should be discussed urgently., HOPE(H-2ロケット打上げ型有翼回収機)の誘導制御サブシステム開発には、軌道上・ランデブー(RDV)ドッキングフェーズ、軌道離脱・再突入フェーズ、最終エネルギー調整(TAEM)フェーズ、進入着陸フェーズ、冗長技術、ソフトウェア開発のそれぞれにおける技術課題がある。RDVについては、遠隔操縦RDVと自動RDVを組み合わせ、その安全性と運用性の向上について検討する必要がある。再突入フェーズでは、ランバート誘導則を用いる。再突入インタフェイス以降はクローズドフォーム法を用いるのが良いが、HOPEの場合、空力加熱率による制限が厳しいため、充分なマージンが得られることを検討しなければならない。TAEMフェーズの飛行条件は、主として遷音速の領域で空力パラメタの変化が大きいため、これに適合できるような飛行制御システムを構成する必要がある。進入着陸フェーズではマイクロ波着陸誘導システム(MLS)を使用するが、基準軌道と飛行性能などの調整が重要となり、その検討を行う必要がある。誘導制御システムは3重の冗長構成を基本としているが、冗長構成の簡素化、冗長管理則の妥当性、効率的な実験手法の検討が必要である。ソフトウェア開発については、品質保証の手法や作業分析を早急に検討する必要がある。
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- 2015
80. Development of the HYFLEX vehicle
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Sakurai, Hiroki, Tani, Shozo, Kosugi, Kenichi, Nakajima, Kazutaka, Yamada, Toshiyuki, Shirouzu, Masao, Shimoda, Takayuki, 櫻井 浩己, 谷 正三, 小杉 健一, 中嶋 一貴, 山田 敏之, 白水 正男, 下田 孝幸, Sakurai, Hiroki, Tani, Shozo, Kosugi, Kenichi, Nakajima, Kazutaka, Yamada, Toshiyuki, Shirouzu, Masao, Shimoda, Takayuki, 櫻井 浩己, 谷 正三, 小杉 健一, 中嶋 一貴, 山田 敏之, 白水 正男, and 下田 孝幸
- Abstract
Development of the Hypersonic Flight Experiment (HYFLEX) vehicle is described. The HYFLEX vehicle was launched by the first J-1 launch vehicle from Tanegashima Space Center (TNSC) on February 12, 1996. It splashed down in the Pacific Ocean, north east of Bonin Islands, bringing back memorable fruitful results. Here, the progress and the organization of the development, and the feature of the vehicle are described, introducing technological challenges and discussions in the areas of aerodynamics, aerothermodynamics, structures and flight controls which have been of central issues in the development., 極超音速飛行実験機(HYFLEX)の開発について報告する。1996年2月12日に種子島宇宙センターからJ-1ロケットの初号機によって打ち上げられた実験機が日本で初の極超音速揚力面飛行を実施した。小笠原諸島の北東で太平洋に着水した飛行は意義深く成果の多い飛行となった。ここでは開発の経過、開発体制、開発された機体の概要を述べると共に、実験機開発の重点であった空力/空力加熱、構造、飛行制御の分野での技術的な挑戦、議論を重ねた点を紹介する。
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- 2015
81. 大型衝撃風洞HIESTの設計の特徴
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Miyajima, Hiroshi, 宮島 博, Miyajima, Hiroshi, and 宮島 博
- Abstract
With the aim of testing the aerodynamic force and heating in reentry phase of a space transportation vehicle, NAL and NASDA are jointly constructing a large-sized free-position shock tunnel, HIEST (High Enthalpy Shock Tunnel). The concept of the design of this shock tunnel is to achieve efficient energy transport from high-pressure air generated by piston drive to test air. For realizing this shock tunnel, using relatively light piston was proposed and the concept to make piston speed faster when breaking a main diaphragm was developed. In this report, the design concept and the features of the mechanical design as a result of realizing the concept are described., 宇宙輸送機の再突入時の空気力および空力加熱の試験を当面の目的として、航空宇宙技術研究所と宇宙開発事業団は共同で大型の自由ピストン衝撃風洞HIEST(大型高温衝撃風洞)を建設中である。この衝撃風洞の設計思想はピストン駆動高圧空気から試験気体へのエネルギー輸送を効率的に行うことである。これを実現するために、比較的軽いピストンを用い、かつ、主隔膜の破膜時におけるピストン速度を高くする概念を開発した。ここでは、この設計概念とその結果としての機械設計の特徴を述べる。
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- 2015
82. HOPE開発における超高速流数値シミュレーション技術の応用とその役割
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Yamamoto, Yukimitsu, Wada, Yasuhiro, Yoshioka, Minako, 山本 行光, 和田 安弘, 吉岡 美菜子, Yamamoto, Yukimitsu, Wada, Yasuhiro, Yoshioka, Minako, 山本 行光, 和田 安弘, and 吉岡 美菜子
- Abstract
Numerical study of hypersonic flow around HOPE is performed, using flux-split and flux difference splitting upwind TVD (Total Variation Diminishing) Navier-Stokes codes. New parametric computations are made to determine the basic configuration from two type of HOPE candidate geometry designs. One type is the Double Delta type model (DD model) and the other is the Power Delta type one (PD model). Also, in order to investigate real gas effects, numerical calculations, corresponding to the flow conditions of high enthalpy wind tunnels of DLR, HEG (High Enthalpy Shock Tunnel Goettingen) and Caltech (California Institute of Technology) T-5, are made. In addition, hypersonic perfect gas flow calculations are made for the comparison with experimental data of AEDC (Arnold Engineering Development Center) and ONERA S4MA hypersonic wind tunnel and Calspan's shock Tunnel. Through the present numerical analysis, detailed aerodynamic and aerothermodynamic characteristics of HOPE are investigated. These works have been done as the joint research of NAL and NASDA., HOPE(H-2ロケット打ち上げ型有翼宇宙往環機)周りの極超音速流を流速分割および流速差分分割風上TVD Navier-Stokesコードを用いて数値解析した。2タイプの候補形状設計から基本形態を決めるために新しいパラメータ計算を行った。1つはダブルデルタタイプ(DDモデル)で、他の1つはパワーデルタタイプ(PDモデル)である。また、実在気体効果の調査研究のためDLR,HEG(Goettingenの高エンタルピー衝撃風洞)およびCaltech T-5の高エンタルピー風洞の流れ条件に対応した数値計算を行った。さらに、AEDCおよびONERA S4MAの極超音速風洞とCalspanの衝撃風洞の各試験との比較対応のための数値計算も行った。これらの数値解析を通じて、HOPEの空力・空力加熱特性の詳細を究明できた。本研究はNALとNASDAの共同で実施された。
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- 2015
83. CFD activity for future winged space transport system
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Yamamoto, Yukimitsu, Kurotaki, Takuji, 山本 行光, 黒滝 卓司, Yamamoto, Yukimitsu, Kurotaki, Takuji, 山本 行光, and 黒滝 卓司
- Abstract
Numerical Simulation for aerodynamic study of atmospheric space transport vehicles has been conducted at NAL (National Aerospace Laboratory) as the cooperative research work with NASDA (National Space Development Agency). CFD (Computational Fluid Dynamics) technology enlarges its application area with the progress of the computer hardware systems and now CFD has been developed as the strong aerodynamic design tool which covers flight range of space transport vehicle from the launching to the re-entry phase. Here, recent progress of numerical simulations at NAL are introduced., JAXA Special Publication, 宇宙航空研究開発機構特別資料
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- 2015
84. HYFLEX/HOPEシンポジウム講演論文集
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National Space Development Agency of Japan, National Aerospace Laboratory, 宇宙開発事業団, 航空宇宙技術研究所, National Space Development Agency of Japan, National Aerospace Laboratory, 宇宙開発事業団, and 航空宇宙技術研究所
- Abstract
The following topics were discussed: spaceplane development plan, H-2A rocket, HOPE-X (H-2 Orbiting Plane Experiment), ALFLEX (Automatic Landing Flight Experiment), J-1 rocket, and status of HYFLEX (Hypersonic Flight Experiment) development such as trajectory design, navigation system, flight control, electrical components, aerothermodynamic characteristics, aerodynamics, measurement program, aerodynamic heating, ADS (Air Data Sensor) measurement, gas jet interaction, and thermal protection system., 以下の主題を論じた。宇宙往還機開発計画、H-2Aロケット、HOPE-X(宇宙往還技術試験機)、ALFLEX(小型自動着陸実験)、J-1ロケット、飛行経路設計、航法系、姿勢制御、電気系、熱特性、空力特性、計測計画、空力加熱計測、ADS(大気データセンサ)計測、ガスジェット干渉、および熱防護系などのHYFLEX(極超音速飛行実験)の開発の現況。
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- 2015
85. Thermal protection system of the reentry capsule with superorbital velocity
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Yamada, Tetsuya, Ishii, Nobuaki, Inatani, Yoshifumi, Honda, Masahisa, 山田 哲哉, 石井 信明, 稲谷 芳文, 本田 雅久, Yamada, Tetsuya, Ishii, Nobuaki, Inatani, Yoshifumi, Honda, Masahisa, 山田 哲哉, 石井 信明, 稲谷 芳文, and 本田 雅久
- Abstract
In the final phase of the MUSES-C mission, a small capsule with asteroid sample conducts reentry flight directly from the interplanetary transfer orbit at the velocity over 12 km/s. The severe heat flux, the complicated functional requirements, and small weight budget impose several engineering challenges on the designing of the thermal protection system of the capsule. The heat shield is required to function not only as ablator but also as a structural component. The cloth-layered carbon-phenolic ablator, which has higher allowable stress, is developed in newly devised fabric method for avoiding delamination due to the high aerodynamic heating. The ablation analysis code, which takes into account of the effect of pyrolysis gas on the surface recession rate, has been developed and verified in the arc-heating tests in the facility environment of broad range of enthalpy level. The capsule was designed to be ventilated during the reentry flight up to about atmospheric pressure by the time of parachute deployment by being sealed with porous flow-restrict material. The designing of the thermal protection system, the hardware specifications, and the ground-based test programs of MUSES-C capsule are summarized and discussed here in this paper., The Institute of Space and Astronautical Science Report SP
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- 2015
86. 高エンタルピー流れワークショップまとめ
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Yamamoto, Yukimitsu, Hosaka, Yoko, Saito, Akiko, 山本 行光, 保阪 陽子, 斉藤 亜希子, Yamamoto, Yukimitsu, Hosaka, Yoko, Saito, Akiko, 山本 行光, 保阪 陽子, and 斉藤 亜希子
- Abstract
In the perspective of Japanese space projects, the knowledge of high enthalpy and high Mach number flow, occurring during the atmospheric reentry of space vehicles, has regained recently considerable interest. The need to support aerodynamic design of space vehicles under the environments where experiment is very difficult and costly, has driven the use of numerical simulation. Hence, high enthalpy flow workshop was held at NAL in June, 1995 for axisymmetric flow problems. This paper summarizes the computational results of OREX (Orbital Reentry Experiment) real gas flow problem and discusses the detailed comparison of each numerical results., 日本の宇宙プロジェクトを展望すると、宇宙飛行体の大気再突入の間に発生する高エンタルピー、高マッハ数流れに関する知識が最近かなりの関心を呼んできている。実験が極めて困難で費用の掛かる宇宙環境下の宇宙飛行体の空力設計を支援する必要性から、数値シミュレーションの利用が促された。このような状況から、軸対称流問題についての高エンタルピー流れワークショップを1995年6月にNALで開催した。OREX(軌道再突入実験機)実在気体流れ問題の計算結果を要約し、各数値結果の詳細な比較を論じた。
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- 2015
87. Capabilities and issues of unstructured-grid CFD for high-speed flight vehicles
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Lohner, Rainald, Cebral, Juan, Baum, Joseph D., Luo, Hong, Lohner, Rainald, Cebral, Juan, Baum, Joseph D., and Luo, Hong
- Abstract
A brief review of the current capabilities and outstanding issues for the efficient analysis, and design of high-speed flight vehicles using unstructured grids is given. It is concluded that all major areas required in the analysis cycle - grid generation, flow solvers and visualization - have seen major advances in recent years. This trend is expected to continue, leading us to believe that turnaround in a matter of hours or minutes for complex geometries and/or physics will become a reality sometime in the next decade., JAXA Special Publication, 宇宙航空研究開発機構特別資料
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- 2015
88. OREX再突入飛行体まわり極超音速流の化学非平衡粘性衝撃層解析
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Suzuki, Kojiro, Abe, Takashi, 鈴木 宏二郎, 安部 隆士, Suzuki, Kojiro, Abe, Takashi, 鈴木 宏二郎, and 安部 隆士
- Abstract
The forebody flow field of the Orbital Reentry Experiment (OREX) reentry vehicle at the flight condition of the maximum wall heating is studied by using the axisymmetric viscous shock-layer equations with the seven-air-species nonequilibrium chemistry. At this condition, the shock layer is in severe chemical nonequilibrium and the wall heating rate is significantly augmented due to the wall catalycity. The effects of the wall catalycity on the wall heating rate strongly depend on the extent of the chemical nonequilibrium in the shock layer. Consequently, the chemical nonequilibrium analysis is necessary for the prediction of the aerothermodynamic environment of the OREX reentry vehicle. The results show that the viscous shock-layer analysis has sufficient potential to be a useful tool not only for the estimation of the wall heating rate but also for the investigations on the physics of the real gas effects in the shock layer., OREX再突入物体の壁面加熱が最大となるような飛行条件における前面側の流れ場を、7種の化学種の間の非平衡化学反応を伴う軸対称衝撃層方程式によって調べた。この条件では、衝撃層は化学的に甚しく非平衡であり、壁面加熱率は壁面の触媒性によって著しく増大する。壁面触媒性が壁面加熱に与える影響は、衝撃層内における化学的非平衡の程度に強く依存する。したがって、OREX再突入物体の熱空気力学的環境を予測するためには化学的非平衡の解析が必要である。結果は、粘性衝撃層の解析が壁面加熱率の推定のみならず、衝撃層内における実在気体効果の物理に関する研究に役に立つ可能性が十分にあることを示す。
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- 2015
89. Theoretical consideration on laminar-to-turbulent transitions over an ablating reentry capsule
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Komurasaki, Kimiya, Candler, Graham V., 小紫 公也, Komurasaki, Kimiya, Candler, Graham V., and 小紫 公也
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The mechanism of early transition phenomena over an ablating reentry capsule has been examined. A two-equation turbulence model (kappa-epsilon model) coupled with Reynolds averaged Navier-Stokes equations has been employed. Low-Reynolds-number effects on the solid wall were considered by modifying the Chien's correction. As a result, the transition occurred at lower Reynolds numbers with higher ablation rates. The predicted transition-point Reynolds number was 3 x 10(exp 4) at the surface-mass-injection rate of 100 g/sm(sup 2). The principal mechanism of this early transition is thought as follows; the viscosity damping effects are reduced and re-laminarization is prevented in the downstream of the capsule surface, due to the turbulence on the surface and due to the pushing out of near-surface stream-lines from the surface by successive mass injection., The Institute of Space and Astronautical Science Report SP
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- 2015
90. 宇宙輸送機の再突入飛行経路に沿った空力加熱解析:断面形状の相違による影響
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Kobayashi, Koji, Suzuki, Satoshi, Suzuki, Kazuyuki, Otsu, Hirotaka, Miyazawa, Masafumi, 小林 光司, 鈴木 悟史, 鈴木 和幸, 大津 広敬, 宮澤 政文, Kobayashi, Koji, Suzuki, Satoshi, Suzuki, Kazuyuki, Otsu, Hirotaka, Miyazawa, Masafumi, 小林 光司, 鈴木 悟史, 鈴木 和幸, 大津 広敬, and 宮澤 政文
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- 2015
91. 熱防護材触媒性評価試験:試験方法、試験結果
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Oguri, Kazuyuki, 小栗 和幸, Oguri, Kazuyuki, and 小栗 和幸
- Abstract
As a part of the HOPE-X (H-2 Orbiting Plane-Experimental) development, tests were carried out in order to evaluate quantitatively the catalytic activity of the surface of C/C (Carbon/Carbon composite material) thermal protection materials using a plasma wind channel. HF (High Frequency) Plasmatron U-13 at TsNIIMASH (Central Scientific Research Institute of Machine Building) in Russia was used as the plasma wind channel. The temperature of the test objects (thermocouples for the rear side and radiation thermometers for the front side), the gas flow rate, the pressure and the discharge power were obtained at the plasma heating tests under various conditions on different test objects. The important parameters such as the catalytic recombination rate constant, and the ratio of the heating rate of the test object to that of the Cu calorimeter which is the calibration catalyst of a unit, q/qFC were estimated. The value of q/qFC was in the range from 0.36 to 0.46 in both atmospheres of air and nitrogen. The type of the coating, which was used in OREX (Orbital Re-entry Experiment), has thus demonstrated a great effect on suppression of the heating rate against the reference catalyst. Values of the recombination rate constant were determined to be 0.7 to 1.8 m/s, 0.6 to 2.2 m/s, and 0.3 to 2.0 m/s for the air, nitrogen, and oxygen respectively. These low values demonstrate that the test objects have a sufficiently low catalytic activity. In conclusion, the OREX type coating is the material of low catalytic activity equivalent to the SiO2-B2O3 glass coating, which was evaluated as having low catalysts activity in USA and Russia., 本試験では、HOPE-X(宇宙往還技術試験機)の設計のための検討の一部として、C/C(カーボン/カーボン複合材)熱防護材の表面触媒性を定量的に評価するため、プラズマ風洞を用いて試験を実施した。プラズマ風洞には、ロシアTsNIIMASH(機械製作中央研究所)所有のHF(高周波)プラズマトロンU-13を使用した。各種条件で各種供試体のプラズマ加熱試験を実施し、供試体の温度(裏面は熱電対、表面は放射温度計で測定)、ガス流量、圧力、放電出力などを計測し、触媒再結合速度定数、供試体の加熱率と、校正用完全触媒材料であるCuの加熱率との比率q/qFCの見積もりを行った。q/qFCの値は、空気中と窒素中とでほとんど差がなく0.36〜0.46の範囲にあった。この結果、OREX(軌道再突入実験機)タイプコーティングは、完全触媒材料に対する加熱率低減効果が大きいことを示した。再結合の速度定数は、空気で0.7〜1.8m/s、窒素で0.6〜2.2m/s、および酸素で0.3〜2.0m/sとなって、いずれも小さい値を示し、供試体材料は低触媒性材料であることが示された。以上の結果、OREX用コーティングが、アメリカやロシアで評価されたSi2O3-B2O3系ガラス質コーティングと同等の低触媒性材料であることが確認できた。
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- 2015
92. Marco PoloカプセルとDASH-2計画
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Yamada, Tetsuya, Yoshikawa, Makoto, Kawaguchi, Junichiro, 山田 哲哉, 吉川 真, 川口 淳一郎, Yamada, Tetsuya, Yoshikawa, Makoto, Kawaguchi, Junichiro, 山田 哲哉, 吉川 真, and 川口 淳一郎
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- 2015
93. 航技研極超音速風洞における09HOPE熱対応風試について
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Fujii, Keisuke, Hozumi, Koichi, Tsuda, Shoichi, Koyama, Tadao, Wakamatsu, Itsuo, 藤井 啓介, 穂積 弘一, 津田 尚一, 小山 忠勇, 若松 逸雄, Fujii, Keisuke, Hozumi, Koichi, Tsuda, Shoichi, Koyama, Tadao, Wakamatsu, Itsuo, 藤井 啓介, 穂積 弘一, 津田 尚一, 小山 忠勇, and 若松 逸雄
- Abstract
To obtain the aerodynamic heating data of HOPE-X (H-2 Orbiting Plane Experimental), the design of which is now in progress, experiments placed by NASDA were performed at AEDC (Arnold Engineering Development Center) VKF (Von Karman gas dynamics Facility) tunnel B, C in 1996 and 1997. A comparison test has been performed at the NAL hypersonic wind tunnel and the results are reported here. The model is a 3.6 percent HOPE (H-2 Orbiting Plane) of the reference length 576 mm. In the experiment, the aerodynamic heating is measured by about 400 heating rate sensors embedded on the surface of the model. Although the data are not completely corresponding to the AEDC case, 14 runs of 43 cases of experiments have been performed., 現在設計が進められている有翼宇宙往還機HOPE-Xの空力加熱データ取得の目的でNASDA発注により1996年および1997年にAEDC(アーノルド工学開発センター)VKF(フォン・カルマン空気力学施設)風洞B、Cにおいて試験が実施されていた。今回これらとの対応風試を航技研極超音速風洞において行ったのでそれらの結果の比較について報告する。模型は基準長576mmの3.6%HOPE(H-2ロケット打ち上げ型有翼回収機)であって、今回の風試では表面上のおよそ400個所に埋め込まれた加熱率センサの一部を用いて空力加熱を計測した。AEDCにおいて行われたケースに完全に対応したデータは必ずしも得られていないが、14Run、43ケースの試験を行った。
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- 2015
94. An integrated numerical method for predicting aerodynamic heating environment for MUSES-C entry capsule with ablation
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Sawada, Keisuke, 澤田 恵介, Sawada, Keisuke, and 澤田 恵介
- Abstract
An integrated numerical method to obtain trajectory-based aerodynamic heating environment for entry probe vehicles with ablation is briefly described. In this method, a thermochemical nonequilibrium CFD code is loosely coupled with an ablation module along the entry trajectory. Radiative heating is estimated by the use of multi-band radiation module. The effect of earlier turbulent transition of the boundary layer due to ablation product gas is included. Calculated results for MUSES-C sample return capsule are shown and are compared with the results of existing analysis., The Institute of Space and Astronautical Science Report SP
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- 2015
95. REV熱防御系の設計と飛行後解析
- Author
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Kato, Sumio, Kanno, Yoshitsugu, Okuyama, Keiichi, Uegaki, Eiichi, Yamada, Tetsuya, Suzuki, Toshiyuki, 加藤 純郎, 菅野 義就, 奥山 圭一, 上垣 栄一, 山田 哲哉, 鈴木 俊之, Kato, Sumio, Kanno, Yoshitsugu, Okuyama, Keiichi, Uegaki, Eiichi, Yamada, Tetsuya, Suzuki, Toshiyuki, 加藤 純郎, 菅野 義就, 奥山 圭一, 上垣 栄一, 山田 哲哉, and 鈴木 俊之
- Abstract
The re-entry capsule USERS/REV was successfully recovered in May 2003. REV has a heat shield system to protect inner equipments against the severe heating environment during the re-entry. The heat shield system is mainly made of three kinds of layers, i.e., CFRP ablator, felt type insulation material with thermal anchor and an aluminum shell structure. In the design of the heat shield system, contradictory requirements of heat ejection in orbit and heat protection during the re-entry had to be satisfied. Thermal protection performance of the heat shield system was calculated using an ablation analysis code. Thermal stress analysis of the ablator during the reentry was carried out using a large deformation FEM that considers materials non-linearity. For the development of the heat shield system, various kinds of tests such as the arc-heated tests of the ablator and the strain survey test of the heat shield system were carried out. After the recovery of REV, evaluation of the recovered heat shield system was carried out. The temperature time histories in the ablator obtained during the re-entry and the damage of the heat shield system measured after the recovery were compared with the results of ablation analysis and structural analysis, from which the heating environment during the re-entry and the cause of the damage were estimated. The evaluation of the heat shield system design based on the flight results is also described., JAXA Research and Development Report, 宇宙航空研究開発機構研究開発報告
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- 2015
96. Advanced TPSについて
- Author
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Sakakibara, Toshio, Tanigawa, Eiji, Ando, Norio, Yamamoto, Mitsunori, Shimanuki, Masakazu, 榊原 俊夫, 谷川 栄治, 安藤 則雄, 山本 光紀, 嶋貫 雅一, Sakakibara, Toshio, Tanigawa, Eiji, Ando, Norio, Yamamoto, Mitsunori, Shimanuki, Masakazu, 榊原 俊夫, 谷川 栄治, 安藤 則雄, 山本 光紀, and 嶋貫 雅一
- Abstract
Thermal protection materials for HOPE (H-2 Orbiting Plane) must be developed by taking account of mechanical and heat resistance properties, light weight, acoustic resistance and chemical resistant properties as well as heat insulating properties against aerodynamic heating during atmospheric reentry. Titanium-base thermal protection materials were to be used in the sections from 300 C to 500 C. For these materials, manufacturing methods such as shaping and binding technologies were studied. By the performance evaluation of multi-wall shaped trial pieces, no problems of heat resistance, heat insulation and mechanical properties were found. Nickel-base thermal protection materials were to be used in the sections from 550 C to 1,100 C. On these materials, manufacturing problems such as bonding technologies and internal adiabatic materials technologies were studied. Trial pieces were evaluated for the density and adiabatic property, and the required performance level was found to be fulfilled. C/C thermal protection materials were to be used in the sections from 550 C to 1,300 C, and were to compose an ACC (Advanced C/C material) Thermal Protection System (TPS). Heat insulating properties of parts bonded by fasteners were studied. Ceramic thermal protection materials were to be used in the sections with temperatures below 1,300 C and in the antenna part. Properties of handling and environmental resistance were discussed., HOPE(H-2ロケット打ち上げ型有翼回収機)の熱防護材は再突入時の空力加熱からの断熱特性の他に、力学特性、耐熱特性、軽量化、耐音響性、および耐化学的特性も考慮に入れて開発されねばならない。チタン合金熱防護材は300度Cから500度Cまでの温度の部位に使用される材料である。この材料について、成型加工技術と接合技術という製造法上の課題を検討した。マルチウォール形状の試作品の性能評価の結果、耐熱性、断熱性および力学特性について問題のないことを確認した。ニッケル合金熱防護材は550度Cから1,100度Cまでの部位に使用される材料である。これについて内部断熱材料の選定、接合技術という製造上の課題を検討した。試作品について密度と断熱性の評価を行い、要求性能を満たすことを確認した。C/C熱防護材は550度Cから1,300度Cまでの部位に使用され、ACC(高性能C/C複合材料)熱防護システム(TPS)を構成するが、そのファスナ結合部の断熱構造を検討した。セラミック熱防護材は1,300度C以下の部位とアンテナ部位に使用される材料であるが、これについて取扱い性と耐環境性を検討した。
- Published
- 2015
97. HYFLEX飛行における空力加熱計測について
- Author
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Fujii, Keisuke, 藤井 啓介, Fujii, Keisuke, and 藤井 啓介
- Abstract
In HYFLEX (Hypersonic Flight Experiment) flight, aerodynamic heating to the region of C/C (Carbon/Carbon composite) hot structure and TPS (Thermal Protection System) ceramic tile are measured with some kind of temperature sensors. In this paper, aerodynamic heating measured in windward side will be noticed. In the region near symmetric plane in windward side, abrupt increase of heating rate caused by boundary layer transition are measured, and before the transition, good agreement between measured aerodynamic heating in HYFLEX flight and the value calculated by a simple engineering estimation using results of wind tunnel tests., HYFLEX(極超音速飛行実験)ではC/C(カーボン/カーボン複合材)ノーズキャップ、エレボン部およびタイル部に温度センサを配し、空力加熱計測を行った。ここでは、胴体下面タイル部で計測された加熱率について報告する。胴体下面中心線付近で境界層遷移によると考えられる加熱率の急激な増加が確認された。また境界層遷移以前では、測定された空力加熱は、設計用に取得した風洞試験結果と球淀み点加熱率の推算式とを用いた工学的簡易推算値と比較的良い一致をする事が確認できた。
- Published
- 2015
98. Trajectory-based coupled analysis of viscous shock layer and charring material ablation at stagnation point
- Author
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Suzuki, Kojiro, 鈴木 宏二郎, Suzuki, Kojiro, and 鈴木 宏二郎
- Abstract
To predict the characteristics of the ablation thermal protection for the MUSEE-C superorbital re-entry capsule, the trajectory-based analysis of the hypersonic shock layer flow and the ablator interior has been made on the stagnation line in a coupled manner. For the flow analysis, the Viscous Shock-Layer (VSL) equations with the nonequilibrium chemistry of C-O-H-N 26 species are solved. For the ablator, the in-depth thermal response is solved by the Charring Material Ablation (CMA) model. The boundary condition at the surface, which is necessary for both solutions, is determined by the mass and energy balance. Various surface reactions and the surface injection of the pyrolysis gas are considered. The results are compared with the experimental data obtained at the arc-heated wind tunnel. Analysis by using the empirical relations all along the re-entry trajectory is also made and the results are compared with those by the VSL/CMA coupled method. It is shown that such engineering prediction method provides reasonable prediction for the surface temperature and the mass loss of the ablator with sufficient safety margin. The effects of the initial ablator thickness on the ablator temperature are also discussed., The Institute of Space and Astronautical Science Report SP
- Published
- 2015
99. 磁場を利用した再突入飛行体の空力加熱低減法
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Otsu, Hirotaka, Matsushita, Kenji, Abe, Takashi, 大津 広敬, 松下 健治, 安部 隆士, Otsu, Hirotaka, Matsushita, Kenji, Abe, Takashi, 大津 広敬, 松下 健治, and 安部 隆士
- Published
- 2015
100. 航空宇宙数値シミュレーション技術シンポジウム2004論文集
- Author
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Japan Aerospace Exploration Agency, 宇宙航空研究開発機構, Japan Aerospace Exploration Agency, and 宇宙航空研究開発機構
- Abstract
JAXA Special Publication, 宇宙航空研究開発機構特別資料
- Published
- 2015
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