著者

加藤 寛一郎

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.35, no.399, pp.229-236, 1987-04-05 (Released:2010-12-16)

参考文献数

1

---

Flight path is calculated for the 1971 mid-air collision at Shizukuishi. The calculation is based on the flight-data-recorder records taken from the Government accident report. The crash point thus obtained shows fairly large discrepancy to the wreckage distribution. This paper reports about the contradiction and a new interpretation is given to the flight after the collision.

著者

鈴木 宏二郎 田辺 義慶 山田 和彦 越野 勝一郎 本郷 素行

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.48, no.561, pp.549-553, 2000-10-05 (Released:2019-04-11)

参考文献数

8

被引用文献数

1

---

The supersonic aerodynamic characteristics of lifting bodies with blunt thick delta configuration at high angles of attack are experimentally investigated by using the transonic and supersonic wind tunnels. The results show that the lift-to-drag ratio at the trimmed attack angle can be enhanced by the use of the bent nose and body flaps. Significant temporal nonperiodic fluctuation of the aerodynamic force is observed in the narrow freestream range around the Mach number 1. 5 and attack angle 25 deg. The high speed Schlieren pictures reveal that the intermittent breakdown of the leeward vortex pair causes such unsteadiness. This fluctuation can be abbreviated by the combination of the bent nose and the body flaps located on the upper surface of the body.

著者

内野 憲二

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.30, no.346, pp.613-620, 1982-11-05 (Released:2009-05-25)

著者

伊藤 献一 永田 晴紀 植松 努 ラウアー チャールズ

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.55, no.646, pp.292-295, 2007-11-05 (Released:2019-04-22)

参考文献数

6

著者

吉川 俊明 坂本 慎介 堀 琴乃 楠本 寛 山本 康 服部 高資 佐多 宏太

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.56, no.655, pp.391-395, 2008 (Released:2008-08-27)

参考文献数

7

被引用文献数

1 1

---

In this paper, we propose the method for the measurement of required power and the adjustment of optimum gear ratio in take-off ground running. To get the values of required power and speed, we measured torque of the left side and the right side of pedals, RPM of pedals, and speed of the cockpit frame. In order to improve the take-off speed, some drums were applied, and the optimum gear ratio of the front drum to the rear drum was determined.

著者

岩本 周平

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.5, no.41, pp.902-911, 1938-09-05 (Released:2009-07-09)

著者

辻 猛三

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.9, no.89, pp.1119-1124, 1942-09-05 (Released:2009-07-09)

著者

岩田 勉

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.36, no.416, pp.403-409, 1988-09-05 (Released:2010-12-16)

参考文献数

13

著者

上杉 邦憲

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.18, no.202, pp.418-425, 1970 (Released:2009-05-25)

参考文献数

11

著者

峯岸 正勝 熊倉 郁夫 岩崎 和夫 少路 宏和 吉本 周生 寺田 博之 指熊 裕史 磯江 暁 山岡 俊洋 片山 範明 林 徹 赤楚 哲也

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会論文集 (ISSN:13446460)

巻号頁・発行日

vol.51, no.594, pp.354-363, 2003 (Released:2003-09-26)

参考文献数

19

被引用文献数

1 2

---

The Structures and Materials Research Center of the National Aerospace Laboratory of Japan (NAL) and Kawasaki Heavy Industories, Ltd. (KHI) conducted a vertical drop test of a fuselage section cut from a NAMIC YS-11 transport airplane at NAL vertical drop test facility in December 2001. The main objectives of this program were to obtain background data for aircraft cabin safety by drop test of a full-scale fuselage section and to develop computational method for crash simulation. The test article including seats and anthropomorphic test dummies was dropped to a rigid impact surface at a velocity of 6.1 m/s (20 ft/s). The test condition and result were considered to be severe but potentially survivable. A finite element model of this test article was also developed using the explicit nonlinear transient-dynamic analysis code, LS-DYNA3D. An outline of analytical method and comparison of analysis result with drop test data are presented in this paper.

著者

山田 恵彦

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.225, pp.583-589, 1972 (Released:2009-05-25)

参考文献数

17

著者

辻 猛三

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.9, no.91, pp.1305-1312, 1942-11-05 (Released:2009-07-09)

著者

梶原 堅一 長野 寛 西田 英司 後藤 祥史 河内 宏道

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.530, pp.168-174, 1998-03-05 (Released:2010-12-16)

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.

著者

鶴 宏 古関 昌次

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.241, pp.107-113, 1974 (Released:2009-05-25)

著者

伊藤 隆 宮島 博

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.619, pp.351-357, 2005 (Released:2005-11-09)

参考文献数

16

被引用文献数

2 2

---

Performance of the methane fueled rocket nozzles are numerically investigated using computational fluid dynamics approach. A simple set of chemical reactions and kinetics for methane/oxygen nozzle flow is proposed. The chamber pressure, mixture ratio and size of the nozzle are parametrically changed to study the influence of characteristic rocket engine design parameters on nozzle losses. The amount of dissociation is high when the chamber pressure is low and the kinetic loss becomes dominant compared to the other nozzle losses. The peak specific impulse is achieved at a higher mixture ratio region as the chamber pressure increases. The chemical non-equilibrium flow appears mainly at down stream region of the nozzle throat. The influence of the chemical non-equilibrium effect decreases as the chamber pressure increases. Supersonic chemically reactive gas stays longer in the nozzle as the size of the nozzle become larger and the amount of recombination increases which decreases the kinetic loss. When the chamber pressure is high, the kinetic loss becomes small and the effect of the size of nozzle also becomes small.

著者

森 幹彦 大竹 邦彦 小松 敬治

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.29, no.325, pp.63-71, 1981-02-05 (Released:2009-05-25)

著者

太田 豊彦 福島 幸夫 上條 謙二郎

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会誌 (ISSN:00214663)

巻号頁・発行日

vol.46, no.539, pp.705-711, 1998-12-05 (Released:2010-12-16)

参考文献数

4

被引用文献数

2

---

National Space Development Agency of Japan (NASDA) started to develop H-II launch vehicle in 1983 and succeeded in the 1st flight on February in 1994. Meanwhile, several troubles were experienced in the development of LE-7 which is the 1st stage engine of H-II. The LE-7 is a staged combustion cycle engine with high pressure and high Isp like SSME. Therefore, high delivery pressure and high performance were required for LH2 turbopump, which is the main key component, and caused several troubles in the development. This paper describes the development of LH2 turbopump containing the design description, the contents of some troubles and their counterplans. In addition, some activities to solve turbopump life and endurance will be introduced.

著者

河野 功 杢野 正明 鈴木 孝 小山 浩 功刀 信

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.49, no.575, pp.432-437, 2001 (Released:2002-04-26)

参考文献数

6

被引用文献数

2 2

---

Engineering Test Satellite-VII (ETS-VII) is a test satellite to perform in-orbit demonstration of autonomous rendezvous docking (RVD) technology, which will be necessary for advanced space activities in the early 21st century. ETS-VII successfully performed the autonomous RVD by unmanned space vehicle for the first time in the world. For an unmanned space vehicle to perform rendezvous to a manned spacecraft, safe approach is needed. So we paid special attention to designing safe approach trajectory. There are other important points for approach trajectory design, for instance, coordination with guidance and control accuracy, performance of navigation sensors, and operability, etc. In this paper, we introduce the points, and show the result of ETS-VII RVD trajectory design.

著者

澤井 秀次郎 福田 盛介 坂井 真一郎 櫛木 賢一 荒川 哲人 佐藤 英一 冨木 淳史 道上 啓亮 河野 太郎 岡崎 峻 久木田 明夫 宮澤 優 植田 聡史 戸部 裕史 丸 祐介 下地 治彦 清水 康弘 芝崎 裕介 島田 貞則 横井 貴弘 藪下 剛 佐藤 賢一郎 中村 和行 久原 隆博 高見 剛史 田中 伸彦 古川 克己

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

pp.JSASS-D-16-00050, (Released:2017-08-03)

被引用文献数

8 7

---

SLIM (Smart Lander for Investigating Moon) is the Lunar Landing Demonstrator which is under development at ISAS/JAXA. SLIM demonstrates not only so-called Pin-Point Landing Technique to the lunar surface, but also demonstrates the design to make the explorer small and lightweight. Realizing the compact explorer is one of the key points to achieve the frequent lunar and planetary explorations. This paper summarizes the preliminary system design of SLIM, especially the way to reduce the size.