著者
中道 達也 松岡 健 笠原 次郎 松尾 亜紀子 船木 一幸
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.10, pp.107-112, 2011 (Released:2012-01-17)
参考文献数
23

We conducted multi-cycle combustion experiments of a coaxial-rotary-valve pulse detonation engine (PDE) system. This PDE system showed a stable operation at the valve rotating frequencies of 5.0, 10, 15, 20, and 33 Hz. We successfully measured propellant mass flow rates, thrusts, and specific impulses in the 2-sec operation duration. The maximum thrust was 32 N at the operation frequency of 33 Hz and at the supply pressure of 0.98 MPa. The maximum specific impulse was 250 sec at the operation frequency of 33 Hz and at the supply pressure of 0.69 MPa. The partial fill ratio was varied from 0.07 to 1.14. The partial fill effect was almost identical to the previous model calculations.
著者
能見 公博 大井 克己 詫間 哲 苧側 正明
出版者
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
雑誌
航空宇宙技術 (ISSN:18840477)
巻号頁・発行日
vol.9, pp.37-42, 2010
被引用文献数
1 1

This paper describes solar paddle antenna proposed in the development of Kagawa Satellite "KUKAI." KUKAI is a mother-daughter pico-satellite for technical verification of a tethered space robot. The mother and the daughter satellites communicate respectively with the ground station by amateur radio frequencies. For the purpose of simple deployment system on orbit and antenna directivity suitable for KUKAI, solar paddle antenna mounted at the edge of a solar paddle is employed. After sufficient antenna adjustment on the ground, KUKAI was launched on 23 January 2009 by the H-IIA rocket from Tanegashima Space Center. The solar paddles were successfully deployed, and communication by the solar paddle antenna was successful.
著者
北村 圭一 葛生 和人 入門 朋子 野中 聡 藤本 圭一郎 福添 森康 嶋 英志
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.10, pp.43-50, 2011 (Released:2011-06-14)
参考文献数
23
被引用文献数
1 1

The Epsilon Launch Vehicle, scheduled to be launched in 2013, is currently under the development by JAXA (Japan Aerospace Exploration Agency). In this study, aerodynamic characteristics of the Epsilon Launch Vehicle are investigated by conducting both wind tunnel tests and numerical analyses at Mach 0.7. In order to examine accuracy of the measured drag, we probed the cavity pressure in addition to the base pressure, in contrast to our earlier work for Mach 1.5. The measured data indicated that the cavity pressure can be substituted by the base pressure or the static pressure within 3% error, which accounts for 1% error in the fore drag estimation. Then, the fore drag, calculated based on the static pressure, was used for CFD validation. Our CFD results of attack angles of 0 and 5 degrees showed fair agreement with the wind tunnel results, including the surface flow pattern, the fore drag and the normal force. Finally, aerodynamic characteristics of Epsilon Launch Vehicle at Mach 0.7 are extracted from the CFD results: 1) contribution to total forces was clarified for each part (e.g., flanges and attitude control units), 2) the normal force profile at Mach 0.7 showed comparable peaks with the Mach 1.5 case, in spite of the smaller separation regions near protuberant parts, and 3) the Reynolds number effect turned out to be minor within the range of the wind-tunnel and flight conditions.
著者
上野 和之 鷲見 裕太 田坂 昂大 内山 順史
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.12, pp.25-30, 2013 (Released:2013-02-20)
参考文献数
15

Airships with small horizontal cross-section and tall height are proposed. Such vertical airships have a remarkable advantage with respect to available locations for landing and mooring. Flight tests and wind tunnel tests of vertical airships were carried out using scale models. Drag coefficient of vertical airships is discussed.
著者
羽生 宏人 和田 英一 丹羽 崇博 近藤 靖雄 川村 尚史 丸山 信也 岡村 彩乃 山科 早英良 永井 康仁 中道 達也 上道 茜 田中 成明 小林 直樹 笠原 次郎 森田 泰弘
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.9, pp.15-21, 2010 (Released:2010-05-14)
参考文献数
6
被引用文献数
1

The educational hybrid-rocket was successfully launched and it also landed within the predicted area. Aerodynamic characteristics of the rocket designed by students of Tsukuba University were evaluated by the wind tunnel testing with the support of Tokai University. The flight path affected by the environmental condition, especially wind direction and velocity, was simulated with the original calculation program. The altitude of the rocket was measured with the optical equipment and the apex was 123 m although the calculation indicated 198 m. We expected that the insufficient filling or the volatilization of Nitrous oxide as an oxidizer led to this result. And then, the apex was verified with a function of the oxidizer filling ratio. The results showed that 81.2 % of the oxidizer volume in comparison with the firing test condition was accumulated in the tank at the launch.
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
2

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.
著者
宮沢 与和 ビクラマシンハ ナビィンダ キトマル 原田 明徳 宮本 侑斗
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.12, pp.31-38, 2013 (Released:2013-03-06)
参考文献数
10
被引用文献数
3 5 2

In the future air transportation system, airspace will be efficiently used and each aircraft can optimize its own performance. Due to limited capacity of the airspace like terminal area, however, some sort of adjustment for each aircraft is necessary to maintain separation among multiple aircraft. Fixed arrival time is a basic solution to the problem. This paper studies the effect of arrival time assignment on the performance by assuming that each aircraft generates its own flight plan by minimizing its fuel consumption. Dynamic programming trajectory optimization is used to calculate the optimal flight profile composed of altitude and velocity. The result shows that the arrival time adjustment is efficiently performed in the descent phase, if the required amount of time to be adjusted is not large.
著者
蒋 理 大森 太加 柴田 寿一 今村 太郎 李家 賢一
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.14, pp.17-21, 2015 (Released:2015-02-13)
参考文献数
7
被引用文献数
1

Modified PARSEC (PARametric SECtion Method) is used as a parameterization method to describe airfoil shapes by few number of parameters, which is suitable for airfoil design optimization. To calculate these parameters, GA (Genetic Algorithm) is usually used. However, it has been observed that for some airfoils, Modified PARSEC method generates irregular shapes when GA is used. To overcome this issue, a new method using Pseudo-Inverse Matrix is developed. The proposed method is applied to various airfoils including the airfoil sections of the CRM (Common Research Model) wing, and a two-dimensional CFD code is used to carry out the aerodynamic analysis. Subsequently, the three-dimensional CRM wing is reproduced using the proposed method and its aerodynamic characteristics are analyzed with Euler equations. The results show that reproduced geometry is almost identical to that of the original CAD data in terms of aerodynamic characteristics, which shows the applicability and usefulness of the method.
著者
羽生 宏人 和田 英一 丹羽 崇博 近藤 靖雄 川村 尚史 丸山 信也 岡村 彩乃 山科 早英良 永井 康仁 中道 達也 上道 茜 田中 成明 小林 直樹 笠原 次郎 森田 泰弘
出版者
THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES
雑誌
航空宇宙技術 (ISSN:18840477)
巻号頁・発行日
vol.9, pp.15-21, 2010
被引用文献数
1

The educational hybrid-rocket was successfully launched and it also landed within the predicted area. Aerodynamic characteristics of the rocket designed by students of Tsukuba University were evaluated by the wind tunnel testing with the support of Tokai University. The flight path affected by the environmental condition, especially wind direction and velocity, was simulated with the original calculation program. The altitude of the rocket was measured with the optical equipment and the apex was 123 m although the calculation indicated 198 m. We expected that the insufficient filling or the volatilization of Nitrous oxide as an oxidizer led to this result. And then, the apex was verified with a function of the oxidizer filling ratio. The results showed that 81.2 % of the oxidizer volume in comparison with the firing test condition was accumulated in the tank at the launch.
著者
亀井 卓也 伊藤 那知 菅井 慎也 太田 諭志 佐鳥 新 千葉 一永
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.12, pp.111-117, 2013 (Released:2013-11-28)
参考文献数
16
被引用文献数
1 1

Precision agriculture has been being implemented in order environmentally friendly and efficiently to product and manage crops. The remote sensing by satellite and aircraft is employed in order to obtain the information regarding the growth of crops. Although the data from satellites can include wide-range image each time, it is insufficient due to the fixed orbital path of satellites. Therefore, fixed-point observations cannot be sufficiently performed. Moreover, the observations on fixed orbital path cannot be always carried out because of cloud. Although aircrafts are used for the interpolation of the insufficient data by satellites, manned aircrafts need high personnel expenses and maintenance costs. Therefore, unmanned aerial vehicle (UAV) is recently employed. The objective of the present study is the development of the system to generate the interpolated image data by normalized difference vegetation index (NDVI) map taken by small-type UAV (sUAV), which is low-priced and simple system to implement precision agriculture. The following three assignments have been concretely performed in the present study; 1) light-weight four-band multispectral camera carried in sUAV will be developed, 2) sUAV is managed and the image data will be taken, and 3) NDVI map will be generated from the image data by sUAV and interpolated image data will also be developed to contribute precision agriculture. Consequently, the lightest four-band multispectral camera in the world has been developed, and also sUAV has been able to be successfully managed and acquired image data could also generates NDVI maps.