文献一覧: 一般社団法人日本航空宇宙学会 (出版者)

1 0 0 0 OA 超音速飛行機の安定性・操縦性

著者: 木村秀政
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.8, no.78, pp.189-194, 1960 (Released:2009-07-09)
参考文献数: 5

2020-08-31 09:10:31
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1 0 0 0 OA PARSEC翼型表現法の修正手法と表現性能検証

著者: 金崎雅博四谷智義奈良拓矢松島紀佐
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.59, no.684, pp.24-26, 2011 (Released:2011-03-03)
参考文献数: 4
被引用文献数: 1

The original PARSEC (PARametric SECtion) method can satisfactorily solve the optimization problems involving transonic airfoils by using a few design variables. However, it is difficult to apply this method to the design of airfoils under other conditions such as supersonic flow and low Reynolds number flow. To solve various airfoil design problems by using a few design variables and the PARSEC representation, a modified PARSEC representation is proposed. The capability of the proposed modified representation to solve unknown real-world design problems is investigated; the proposed representation is used along with multi-objective genetic algorithms to solve two types of problems. One is the design of a conventional transonic airfoil that is to be used in the Earth's atmosphere; the other is the design of an airfoil that is to be used in the Martian atmosphere. To evaluate the aerodynamic performance of the airfoils, the structured Navier-Stokes solver is used. The results indicate that better solutions can be obtained by using the proposed PARSEC modification than by using the original PARSEC representation, especially in the Martian atmosphere.

2020-08-30 22:58:46
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1 0 0 0 CFDを用いたブーメランの飛行シミュレーション

著者: 土井克則 Mohd FADHLI 川島渉中村佳朗
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 = Journal of the Japan Society for Aeronautical and Space Sciences (ISSN:13446460)
巻号頁・発行日: vol.59, no.693, pp.273-280, 2011-10-05
参考文献数: 14
被引用文献数: 3

A boomerang thrown properly into the air can fly in an elliptical path and return to the point of origin. In this study, such a motion of the boomerang was numerically simulated to clarify the mechanism of the motion. The simulation was conducted by the double CFD method which is the coupling method of the computational fluid dynamics and the computational flight dynamics. We considered the case that a small flat boomerang was thrown with a translational and a rotational velocity, an angle of the translational velocity from a horizontal plane, and no roll angle. Results showed that the boomerang lifted and traveled in a path with changing roll and pitch angles due to a pressure distribution on its surface, and returned to a point near the origin. Furthermore, an experiment was performed to confirm the validity of the computational results, and the experimental result was qualitatively corresponding to the computational results.

2020-08-23 16:46:40
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1 0 0 0 OA 航空機の空力騒音とその制御技術について

著者: 小林紘
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.43, no.493, pp.82-89, 1995-02-05 (Released:2010-12-16)
参考文献数: 19
被引用文献数: 1 1

2020-08-22 18:04:55
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1 0 0 0 佐藤信淵考案の自走火船:ロケット推進船

著者: 荒川秀俊
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.11, no.118, pp.364, 1963

2020-08-17 13:33:36
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1 0 0 0 OA ソニツク・ブーム(Sonic Boom)に関する研究の概況

著者: 河村龍馬
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.14, no.155, pp.423-432, 1966-12-05 (Released:2010-01-13)
参考文献数: 23

2020-08-05 11:32:05
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1 0 0 0 OA 地面効果翼艇 (WIG) の実用化に向けて

著者: 久保昇三松原武徳松岡利雄河村哲也
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.39, no.448, pp.236-242, 1991-05-05 (Released:2010-12-16)
参考文献数: 31

2020-08-01 16:09:35
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1 0 0 0 OA 飛行機

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.10, no.97, pp.365-379, 1943-05-05 (Released:2009-07-09)

2020-07-30 14:20:03
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1 0 0 0 OA れいめい(INDEX)衛星における統合化衛星制御

著者: 福田盛介水野貴秀坂井真一郎福島洋介齋藤宏文
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.57, no.660, pp.25-31, 2009 (Released:2009-02-17)
参考文献数: 7
被引用文献数: 1 2

REIMEI/INDEX (INnovative-technology Demonstration EXperiment) is a 70kg class small satellite which the Institute of Space and Astronautical Science, Japan Exploration Agency, ISAS/JAXA, has developed for observation of auroral small-scale dynamics as well as demonstration of advanced satellite technologies. An important engineering mission of REIMEI is integrated satellite control using commercial RISC CPUs with a triple voting system in order to ensure fault-tolerance against radiation hazards. Software modules concerning every satellite function, such as attitude control, data handling, and mission applications, work cooperatively so that highly sophisticated satellite control can be performed. In this paper, after a concept of the integrated satellite control is introduced, the Integrated Controller Unit (ICU) is described in detail. Also unique topics in developing the integrated control system are shown.

2020-07-17 12:57:54
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1 0 0 0 OA ヘリコプタの動力装置

著者: 小暮泰之
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.20, no.220, pp.284-297, 1972 (Released:2009-05-25)
参考文献数: 15

2020-07-07 23:07:11
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1 0 0 0 流體力學

著者: 糸川英夫岡本哲史谷一郎松川昌藏村上勇次郎
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
巻号頁・発行日: vol.4, no.30, pp.1071-1102, 1937

2020-06-29 15:40:33
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1 0 0 0 OA 月周回衛星「かぐや」の飛行計画

著者: 松本秀一滝澤悦貞小西久弘佐々木健小川美奈川勝康弘寺田博田中貴美恵加藤貴昭池上真悟宮田信岩本祥広山本昌幸
出版者: 一般社団法人日本航空宇宙学会
雑誌: 日本航空宇宙学会誌 (ISSN:00214663)
巻号頁・発行日: vol.56, no.657, pp.258-264, 2008-10-05 (Released:2019-04-22)
参考文献数: 13

2020-06-20 19:59:00
1 知恵袋

1 0 0 0 OA 45°デルタ翼の失速域におけるウイングロックの振動機構

著者: 松野隆横内滋中村佳朗
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.52, no.601, pp.80-86, 2004 (Released:2004-04-30)
参考文献数: 15
被引用文献数: 1 1

This paper describes the mechanism of the non-slender wing rock that occurs on a 45° delta wing, by focusing on its unsteady aerodynamic characteristics. In free-to-roll test the wing motions showed irregular oscillations the amplitude of which varied with time. In some cases, the wing suddenly changed its trajectory in the middle of the oscillation, and came to stop at roll angle φ=0°. The static rolling moment is quite nonlinear in characteristics, the profile of which has many critical states. The balance test for constant roll rate motion showed that the amount of time lag was not constant for roll angle, and that it is not linear for roll rate. The results of numerical simulation using the experimental data suggest that it is important to take into account the trajectory of the motion for a better understanding about the unsteady aerodynamic characteristics, associated with the non-slender wing rock.

2020-06-19 05:35:51
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1 0 0 0 サーモパイルセンサを利用した小型姿勢検出システムの開発

著者: 栗原真之望月俊希得竹浩
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
巻号頁・発行日: vol.14, pp.7-15, 2015
被引用文献数: 1

An attitude sensing system using thermopile sensors and inertial sensors was proposed. The output model of the thermopile sensor was constructed from the calibration experiment and the theoretical calculations. The estimation algorithm of the attitude angles was developed from the sensor output models using extended Kalman filter. Because thermopile sensor output correlates with attitude to the ground directly, the error of inertial sensors can be compensated. Additionally, the proposed system consists of commercial low-cost product. Numerical simulations and experiment were carried out and the performance was validated. Experimental result shows that the proposed system has precision of approximately 1.2°.