著者

豊田 実 石堂 正弘 飯野 博司

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.24, no.265, pp.85-94, 1976-02-05 (Released:2009-05-25)

参考文献数

5

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The attitude of a rocket is determined by two kinds of angle which are formed between the axis of a rocket and two standard lines. The one is a pitch angle, and the other is a yaw angle.In this paper, the method of the design of a horizon sensor device to determine a pitch angle, the observed results using it and the discussion on them are reported.The output of this device is remarkably affected by the several factors such as the time constant of a sensor, the altitude and the attitude of a rocket and the setting angle of a sensor for a rocket. So that, making these factors as parameters, the method of the design for the optical system and the amplifier of this device were studied.Two horizon sensor devices designed based on these results were boarded on the rocket L-3H7 and the rocket K-10-10 respectively. The observed results by these two devices gave not only the pitch angles of two rockets, but also the temperature distribution of the earth from which the yaw angles were gained.

著者

北田 尚夫

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.381, pp.561-568, 1985-10-05 (Released:2009-05-25)

参考文献数

4

著者

長友 信人

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.24, no.270, pp.323-332, 1976-07-05 (Released:2009-05-25)

参考文献数

21

著者

植村 益次

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.22, no.244, pp.229-239, 1974 (Released:2009-05-25)

参考文献数

10

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)

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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.

著者

安東 茂典 梶田 弘

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.40, no.456, pp.14-22, 1992

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Static longitudinal stability of tailless airplane is evaluated theoretically with two methods. One is quasi (or modified)-strip method and the other is a lifting surface theory—DLM. Computation is made on the basis of available data of Northrop XB-35. The both methods agree each other only qualitatively; of course results of DLM should be much more reliable. Allowable limit of longitudinal CG position may be almost comparable with that of conventional airplanes. The airplane efficiency factor, e concerning with induced drag, is computed which is also satisfactory at least for cruising configuration.

著者

小松 敬治 佐野 政明 角田 義秋

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.51, no.591, pp.158-163, 2003 (Released:2003-09-16)

参考文献数

10

被引用文献数

3 2

---

Progress in materials technology has produced a much more durable synthetic fabric envelope for the non-rigid airship. Flexible materials are required to form airship envelopes, ballonets, load curtains, gas bags and covering rigid structures. Polybenzoxazole fiber (Zylon) and polyalirate fiber (Vectran) show high specific tensile strength, so that we developed membrane using these high specific tensile strength fibers as a load carrier. The main material developed is a Zylon or Vectran load carrier sealed internally with a polyurethane bonded inner gas retention film (EVOH). The external surface provides weather protecting with, for instance, a titanium oxide integrated polyurethane or Tedlar film. The mechanical test results show that tensile strength 1,000 N/cm is attained with weight less than 230g/m2. In addition to the mechanical properties, temperature dependence of the joint strength and solar absorptivity and emissivity of the surface are measured.

著者

坂田 東一

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 = Journal of the Japan Society for Aeronautical and Space Sciences (ISSN:00214663)

巻号頁・発行日

vol.43, no.498, pp.387-389, 1995-07-05

著者

河原 淳人 岩堀 太紀 山川 宏 佐藤 亨 山本 衛 橋口 浩之

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会論文集 (ISSN:13446460)

巻号頁・発行日

vol.64, no.3, pp.189-199, 2016 (Released:2016-06-05)

参考文献数

18

---

Shape estimation of space debris is an important task in evaluating its trajectory evolution and collision probability with resident objects in space. This paper shows the magnitude and rotation of space debris can be estimated by investigating the Doppler shift with a Single Range Doppler Interferometry (SRDI) method. The theory of SRDI method is discussed and its usefulness is confirmed by numerical simulations. Furthermore, fluctuation of Doppler shift of known space debris were successfully observed by the MU radar of Kyoto University and the size and spin rate of some space debris were successfully estimated.

著者

杉浦 綾 横関 智弘 平野 義鎭

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.61, no.5, pp.133-140, 2013 (Released:2013-10-25)

参考文献数

24

---

This paper describes the development and the wind tunnel test of a variable geometry morphing airfoil using corrugated structures. Feasibility of a morphing wing with corrugated flexible seamless flap-like structure is verified by the finite element analysis, and a prototype is manufactured using carbon fiber reinforced plastics. For the actuation system, two servomotors are installed inside the prototype wing to control the airfoil shape by the chord-wise tension of the connected wires. Successful actuation of the prototype wing is demonstrated under the air speed up to 30m/s in the wind tunnel test. Basic aerodynamic properties are also evaluated in comparison to traditional airfoil with a hinged control surface. Lift increase of variable corrugated wing is recognized when the flap angle increases.

著者

元田 敏和

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.55, no.638, pp.117-124, 2007 (Released:2007-04-20)

参考文献数

15

---

In aerospace projects preflight evaluation is crucial for mission success, because flight testing in a real environment is often difficult or impossible. Monte Carlo simulation is a powerful tool for the preflight evaluation because a nonlinear system incorporating various uncertain parameters can be evaluated directly. Monte Carlo simulation has been used in various aerospace projects throughout the world as the computer power increases. After the system evaluation, it is important to detect influential uncertain parameters which cause significant performance degradation so that measures for the system improvement can be studied. However, detecting those parameters is often uneasy because various uncertain parameters are incorporated simultaneously and their magnitudes are randomly generated in Monte Carlo simulation. An interaction of more than two uncertain parameters might be affected. This paper presents a simple approach to detect influential uncertain parameters applying a statistical test to the Monte Carlo results.

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

日本航空宇宙学会誌 (ISSN:00214663)

巻号頁・発行日

vol.17, no.184, pp.202-208, 1969 (Released:2009-05-25)

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)

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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.

著者

中谷 辰爾 笠原 希仁 芝 世弐 大坂 淳 津江 光洋 河野 通方

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.610, pp.487-493, 2004 (Released:2005-01-05)

参考文献数

46

---

Numerical analysis of O3 depletions by exhaust plume from stratospheric flight at the altitude of 25km was conducted. Expanding box method was employed to simulate a diffusion of exhaust plume in the stratosphere. Concentrations of chemical species and normarized sensitivities of O3 concentration for reactions were estimated by fifth-order BDF method. Chemical kinetics include NOx, HOx and Ox chemistry. As results, it takes over two days that O3 concentration within a plume becomes ambient lebel within 1ppb. O3 perturbations were changed by an effect of plume-emission time, and they are bigger in daytime than in nighttime. Distributions of sensitivities of O3 concentrations for reactions are also changed for the plume-emission time. O3 depletion is greater by NOx than by HOx in exhaust plume.

著者

平田 邦夫 上條 謙二郎 升谷 五郎

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会論文集 (ISSN:13446460)

巻号頁・発行日

vol.53, no.614, pp.123-129, 2005 (Released:2005-05-20)

参考文献数

3

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Idle spin phenomena were observed at rapid transient phase in liquid hydrogen pumps for rocket engines. Failure analyses were conducted and evaluation equations to estimate the shift of the operation point of the pump were derived in this paper. It was revealed that rapid fall of hydrogen flow rate resulted in decrease of pump efficiency which caused excessive temperature rise up to the saturation of the pump fluid.

著者

佐野 昇 木内 重基 山田 敏之

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.46, no.535, pp.449-452, 1998-08-05 (Released:2010-12-16)

被引用文献数

1 3

著者

前川 昭二 斉藤 勝也

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences (ISSN:13446460)

巻号頁・発行日

vol.51, no.595, pp.412-418, 2003-08-05

参考文献数

8

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An airship has usually two or three ballonets in its envelope in which air is contained. Its buoyancy and attitude control is performed by changing the air content of each ballonet. It is said that ballonet slosh may influence airship's stability or ride quality. However, no quantitative treatment has been performed so far to investigate this phenomenon. In this paper the coupled equations of an airship longitudinal motion are formulated by modeling the ballonets as cylindrical containers. Some numerical calculations are performed for a 25m class airship and it has been shown that the ballonet slosh may become a design issue when the shape of the ballonet is thinner or when the size becomes larger.

著者

水野 貴秀 津野 克彦 奥村 英輔 中山 通雄

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences (ISSN:13446460)

巻号頁・発行日

vol.54, no.634, pp.514-521, 2006-11-05

被引用文献数

2 1

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Hayabusa, launched May 2003, is the first Japanese spacecraft to explore the small asteroid Itokawa (1998SF36) and touched down on Itokawa twice to sample of the surface material. LIDAR (LIght Detection And Ranging) is an important navigation sensor for the asteroid explorer to measure distance between the spacecraft and the asteroid. Since it is carried in a planetary exploration spacecraft, the weight of LIDAR is very lightweight of 3.7kg. In the rendezvous and touchdown operation, LIDAR supplied the ranging data to the spacecraft navigation system to approach Itokawa down to 50m and its total shots number of laser pulse was more than 4 million. The composition and basic performance of LIDAR are explained and this paper also reports the ranging data at the time of landing to asteroid Itokawa of the autumn of 2005.

著者

小林 啓二

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.63, no.11, pp.350-354, 2015-11-05 (Released:2017-06-08)

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平成23年に発生した東日本大震災では,多数の航空機が救援活動に従事した.一方,一般に災害発生から72時間が経過すると被災者の生存率が激減すると言われているが,同震災においては救援航空機,特にヘリコプタによる初動時の迅速な救援活動を妨げる要因も顕在化した.宇宙航空研究開発機構(JAXA)は,総務省消防庁,自治体消防,災害派遣医療チーム(DMAT)等の災害対応機関と連携して大規模災害時における救援航空機の安全かつ効率的な運航管理を実現する技術の研究開発を進めており,消防防災ヘリやドクターヘリ等の実運用下での評価実験を実施してきた(「災害救援航空機情報共有ネットワーク(D-NET)」の研究開発).平成25年度からは,このD-NETを発展させ,航空宇宙機器(航空機・無人機・人工衛星)の統合的な運用による災害情報の収集・共有化,及び航空機による救援活動を支援する「災害救援航空機統合運用システム(以下,本システム)」の研究開発を進めている.本稿では,救援航空機の運用課題を整理し,安全かつ効率的な救援航空機の運用を実現する本システムの研究開発状況と今後の展望について紹介する.

著者

藤森 篤 呉 震宇

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.47, no.547, pp.138-143, 1999-08-05 (Released:2019-04-09)

参考文献数

18

被引用文献数

2