文献一覧: 一般社団法人日本航空宇宙学会 (出版者)

5 0 0 0 OA 單葉機の主翼に前進或は後退角を附けたる時の揚力及抗力に及ぼす影響に就て

著者: 小谷寛之亮
出版者: 一般社団法人日本航空宇宙学会
雑誌: 日本航空學會誌 (ISSN:18835422)
巻号頁・発行日: vol.2, no.3, pp.23-37, 1935-01-04 (Released:2009-07-09)

Wenn man einmal einen positiven oder negativen Pfeinform dem TragFlügel gegeben hatte, so wurde es sich hauptsachlich um die Stabilitat handeln. Der EinFlüss des Winkels auf den Auftrieb und Widerstand, mit Ausnahme von einigen besonderen Fallen, wurde noch nicht geklart.Also versuchte ich eine approximative Berechnung zu vervollstandigen, um die wegen des mit beiden Winkeln versehenen Flügels entstehende, allgemeine Tendenz von Auftrieb und Widerstand klar zu machen, indem ich einen Versuch an den rechtwinkeligen, mit einer positiven oder negativen Pfeinform versehenen Flügel von Clark-Y Profil, in einem Einmeterkanal machte.Nach meiner Betrachtung wird die Verteilung der Zirkulation unbedingt um die Gestalt des ebenen Flügels bei der Berechnung sich handeln, weil er mit einer positiven oder negativen Pfeinform versehen ist. Folglich berucksichtigte ich die in der Flügelsbreiterichtung sowohl als in der Flügelssehnerichtung entstehende Verteilung und ich bemuhte mich daraus eine Berechnungsmethode zu verwirklichen.

2023-01-02 23:50:16
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5 0 0 0 太陽光圧によるソーラーセイルの姿勢制御に向けた形状記憶合金ワイヤを用いた膜形状制御

著者: 高橋秀幸松下将典高尾勇輝森治角田博明
出版者: 一般社団法人日本航空宇宙学会
雑誌: 航空宇宙技術 (ISSN:18840477)
巻号頁・発行日: vol.21, pp.21-30, 2022 (Released:2022-05-10)
参考文献数: 14

This study proposes a new method for shape control of non-spinning solar sails, in which Shape Memory Alloy (SMA) wires are exploited. An SMA wire is one of soft actuators that contracts at temperatures above its design value. In the proposed framework, the whole shape of a solar sail membrane is deformed via the contraction of SMA wires distributed over the membrane. The deformation results in the change in solar radiation pressure (SRP) torque acting on the solar sail-craft, which is applicable to fuel-free attitude control. In this paper, we investigate the theory of shape control using SMA wires. It is shown that a membrane under shape control behaves similarly both in a ground experiment and in a finite element method (FEM) analysis, demonstrating the validity of numerical modeling. With this result, the performance of shape control for a large membrane in a space environment is simulated by another FEM analysis. Results demonstrate that the proposed method is capable of producing SRP torque at an effective level for attitude control.

2022-05-18 18:58:32
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5 0 0 0 OA 滑空機の距離最大飛行に関する研究

著者: 原田正範別府護郎東昭
出版者: 一般社団法人日本航空宇宙学会
雑誌: 日本航空宇宙学会誌 (ISSN:00214663)
巻号頁・発行日: vol.44, no.513, pp.582-587, 1996-10-05 (Released:2010-12-16)
参考文献数: 9

By using of the optimal control theory, the optimal controls of the lift coefficient and the related flight paths of gliders are obtained to find the maximum flight range for given initial and final conditions. The results show that without ground effect the steady gliding flight at the maximum lift-to-drag ratio occupies a greater part of the flight path, but with the ground effect, the unsteady horizontal flight at the minimum allowable height takes the place of the steady gliding flight.

2022-03-03 06:43:18
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5 0 0 0 OA 電磁力による空力加熱低減法の超軌道速度飛行体への適用

著者: 大津広敬安部隆士船木一幸
出版者: 一般社団法人日本航空宇宙学会
雑誌: 日本航空宇宙学会論文集 (ISSN:13446460)
巻号頁・発行日: vol.54, no.628, pp.181-188, 2006 (Released:2006-06-30)
参考文献数: 17
被引用文献数: 3 2

An applicability of the electrodynamic heat shield system to super-orbital reentry vehicles was investigated. In the case of the super-orbital reentry flight, due to the strong ionization reactions inside the shock layer, the heat shield system which utilizes the electromagnetic force is expected to work well. In the present study, in order to evaluate the reentry heating reduction by this heat shield system, we performed a CFD analysis including thermochemical non-equilibrium effects and an electromagnetic force. The flight condition used for the present study is that the velocity is 11.6km/s at the altitude of 64km at which the stagnation point heat flux of the MUSES-C reentry capsule is considered to be the maximum value. From our CFD results, we found that the heat flux to the vehicle could be reduced by up to 50%. Additionally, it was also found that the drag coefficient increased with the magnetic field strength, and the maximum value of the drag coefficient was 2.0 with the magnetic field strength of 0.6[T].

2021-07-05 18:40:38
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5 0 0 0 OA 年間展望 (1995) 航空関係・字宙関係

著者: 会誌編集委員会
出版者: 一般社団法人日本航空宇宙学会
雑誌: 日本航空宇宙学会誌 (ISSN:00214663)
巻号頁・発行日: vol.44, no.506, pp.196-203, 1996-03-05 (Released:2010-12-16)

2021-05-10 23:15:44
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5 0 0 0 OA MU-300のDeep Stall特性

著者: 花井敏雄
出版者: 一般社団法人日本航空宇宙学会
雑誌: 日本航空宇宙学会誌 (ISSN:00214663)
巻号頁・発行日: vol.33, no.377, pp.322-325, 1985-06-05 (Released:2009-05-25)
参考文献数: 7

2021-05-01 00:13:38
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5 0 0 0 OA 寄書

出版者: 一般社団法人日本航空宇宙学会
雑誌: 日本航空宇宙学会誌 (ISSN:00214663)
巻号頁・発行日: vol.30, no.347, pp.698-714, 1982-12-05 (Released:2009-05-25)
参考文献数: 5

2021-02-15 23:27:09
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5 0 0 0 OA 小型無人機の防災活用

著者: 和田昭久
出版者: 一般社団法人日本航空宇宙学会
雑誌: 日本航空宇宙学会誌 (ISSN:00214663)
巻号頁・発行日: vol.54, no.625, pp.33-36, 2006-02-05 (Released:2019-04-19)
参考文献数: 5
被引用文献数: 1

2021-02-15 22:16:14
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5 0 0 0 OA 学生による学生のための「学生交流会」~鳥人間チーム~

著者: 丸山謙一郎
出版者: 一般社団法人日本航空宇宙学会
雑誌: 日本航空宇宙学会誌 (ISSN:00214663)
巻号頁・発行日: vol.54, no.632, pp.281-282, 2006-09-05 (Released:2019-04-19)

2021-02-13 23:26:20
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5 0 0 0 OA 先端ジェット駆動回転翼のオバーリングにおける最良ピッチ角について

著者: 橋本直輔
出版者: 一般社団法人日本航空宇宙学会
雑誌: 日本航空学会誌 (ISSN:00214663)
巻号頁・発行日: vol.9, no.93, pp.309-312, 1961-10-05 (Released:2009-05-25)
参考文献数: 3

As a result of some simple experiments on the characteristics of jet-reaction rotor blades, the author found the existence of the pitch angle which makes hovering thrust of rotor maximum regardless of the thrust of tip jet. By some analyses, he then confirmed its existence, and investigated how the lift slope and drag coefficient of wing section affect the value of optimum pitch angle. Comparing the results of analysis with those of experiment, there found some discrepancies, on which the ambiguous characteristics of the blade-root portion seem to have a great influence, and further investigations, especially the Practical method to estimate the effects of this blade-root portion on rotor thrust and torque must be studied.