文献一覧: 日本航空学会誌 (雑誌)

3 0 0 0 OA 航空機に関係する突風について

著者: 竹内和之山根晧三郎
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.16, no.173, pp.191-197, 1968-06-05 (Released:2009-07-09)
参考文献数: 20

2023-10-18 04:44:15
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3 0 0 0 OA 有人飛行機の飛行性の改善への提案

著者: 堀越二郎
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.15, no.158, pp.78-90, 1967-03-05 (Released:2009-07-09)
参考文献数: 8

The author conceived that "control force vs. response" should be extended to "control force and displacement vs. response" in order to assure average pilots of safer, easier, and more precise flying of airplanes with wide speed range. Stick displacement per response varies inversely proportional to speed squared, unless dynamic pressure effect is compensated. The author tried to realize this concept by a deliberate reduction of elevator control system stiffness, which would almost ideally shift upward and flatten the curves of stick displacement per response vs. speed over a wide range of speed. Proper pilot-airplane matching is most seriously needed in longitudinal control. The concept and method proposed were verified by flight tests 27 years ago and applied to three models of airplanes, including the Zero Fighter. This paper describes how the afore-mentioned concept and idea were born and proved, and deals with the demonstration of their effects by theoretical analyses and by comparison of the results of numerical calculations with those of the flight tests, and with counterproofs against apprehensions for adverse effects. It is pointed out that the method is applicable to normally designed subsonic airplanes and is especially effective for those operated over wide ranges of speed and normal acceleration. Comparison is made with the results of recent research.

2015-11-19 17:25:01
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2 0 0 0 OA MU-2スポイラの空力特性

著者: 高田茂俊
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.14, no.153, pp.340-353, 1966-10-05 (Released:2010-01-13)
参考文献数: 13

2023-10-19 23:20:29
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2 0 0 0 OA ダグラスDC-8の開発

著者: Ivar L. Shogran 成井利行
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.85, pp.51-61, 1961-02-05 (Released:2009-05-25)

2022-05-21 20:02:03
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2 0 0 0 OA 航空用点火栓について

著者: 宮田応礼
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.13, no.138, pp.218-225, 1965 (Released:2009-07-09)

2019-09-24 02:42:24
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2 0 0 0 新航空機:グラマンC-2A"COD"

著者: 寺川徹
出版者: THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
雑誌: 日本航空学会誌 (ISSN:18835422)
巻号頁・発行日: vol.13, no.136, pp.163-164, 1965

2019-07-27 22:00:27
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2 0 0 0 OA 東洋航空工業株式会社製FD-25A機体強度試験について1)

著者: 疋田遼太郎武田峻市川輝雄田辺哲夫馬場敏治檜山斉雄得能健次郎
出版者: 一般社団法人日本航空宇宙学会
雑誌: 日本航空学会誌 (ISSN:00214663)
巻号頁・発行日: vol.2, no.10, pp.255-263, 1954-10-31 (Released:2009-07-09)

The aircraft Model FD-25 A is a trainer manufactured by the TOYO-KOKU-KOGYO Ltd., with the design of the Fletcher Aircraft Corp. To demonstrate the strength of this aircraft, the load was applied under a system of forces simulating as closely as possible those required in the regulation of C.A.A. of Japan. In this paper, the result of tests, the method of load calculation and the loading apparatus were reported and discussed.

2017-01-20 14:19:33
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2 0 0 0 グライダの安定性・操縱性

著者: 佐藤博
出版者: THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
雑誌: 日本航空学会誌 (ISSN:18835422)
巻号頁・発行日: vol.9, no.89, pp.184-190, 1961

2016-08-03 01:11:38
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2 0 0 0 ロッキードC-140ジェットスター輸送機

著者: 落合一夫
出版者: THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
雑誌: 日本航空学会誌 (ISSN:18835422)
巻号頁・発行日: vol.9, no.89, pp.201-202, 1961

2016-05-02 14:24:05
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2 0 0 0 OA ヘリコプターの高速化について

著者: 平木敏夫
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.12, no.125, pp.198-204, 1964 (Released:2009-05-25)

To improve helicopter performance, there are four problems to be solved, i.e. engine power-up, drag reduction, retreating blade stall prevention and prevention of compressibility phenomena on advancing blade.To solve above problems, in this paper, various methods with constant speed rotor are compared by analyses and wind tunnel tests.As the results, feasibility of 180 knot helicopter, a compound type helicopter withfixed-wing thrustpropeller, will be justified.

2014-12-23 23:42:41
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1 0 0 0 OA 化学ロケットについて

著者: 黒田泰弘
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.313-319, 1961-10-05 (Released:2009-05-25)

2023-11-11 17:15:50
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1 0 0 0 OA 人工衛星の軌道変化から求めた超高層大気の密度その他の特性

著者: 佐貫亦男
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.10, no.105, pp.334-338, 1962 (Released:2009-05-25)
参考文献数: 5

2023-08-03 08:43:04
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1 0 0 0 OA 傾斜ジャイロ式電気水平儀の試作研究

著者: 武田晋一郎
出版者: 一般社団法人日本航空宇宙学会
雑誌: 日本航空学会誌 (ISSN:00214663)
巻号頁・発行日: vol.4, no.32, pp.217-222, 1956-09-28 (Released:2009-05-25)
参考文献数: 1

A gyro horizon with laterally inclined axis can prevent the occurrence of the turning errors when the condition y0=αV/g is atisfied, y0 being the lateral inclination of the gyro axis, V the flyng speed of the airplane, α the precessional speed due to the pendulosity of the gyro system, g the acceleration of gravity. The electrically driven gyro horizon constructed by this principle was examined theoretically and tested in the laboratory and showed very small turning errors. The pendulosity of the gyro system was 60 gr-cm and 105 gr-cm, longitudinally and laterally respectively. y°=10', α=0.0234(rad/sec), v=73.1(m/s)=263(km/h) are the values satisfying the turning error preventhing condition for the inclined axis gyro horizon. The flying speed of the airplane could be increased indefinitely if the special alternating current generator whose frequency is proportional to the flying speed is used for the rotation of the gyro.