著者

海老沼 拓史 中須賀 真一

出版者

一般社団法人 日本航空宇宙学会

雑誌

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

巻号頁・発行日

vol.54, no.635, pp.542-548, 2006-12-05

被引用文献数

9 2 2

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An increasing number of small satellites and hybrid rockets are proposed for miscellaneous space applications, many of which assume the use of Global Positioning System (GPS) for positioning. Some of those platforms are designed and developed by university students and require very low power consumption and also low cost. This paper describes the adaptation of small GPS receivers and open source receiver firmware for space and high dynamics applications, including software performance validation using a GPS signal simulator.

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.19, no.207, pp.155-165, 1971 (Released:2009-05-25)

著者

三橋 清通 瀬尾 良三 横田 昌彦

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.36, no.408, pp.18-25, 1988-01-05 (Released:2010-12-16)

参考文献数

3

著者

長谷川 裕晃 塚本 義明 花田 忠之 田北 勝彦

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会論文集 (ISSN:13446460)

巻号頁・発行日

vol.50, no.581, pp.231-231, 2002 (Released:2003-09-02)

参考文献数

6

---

The application of ceramic components in gas turbine engines enables the improvement of the power output and the efficiency of gas turbines by increasing the turbine inlet temperature. The high temperature properties of the ceramic materials offer the potential of higher turbine operating temperatures with no cooling techniques and therefore the ceramic components with higher temperature limits are becoming more attractive. In this study, the ceramic turbine wheel is applied in the aircraft gas turbine engine and the engine testing is demonstrated under full load operating conditions. The successful testing of the ceramic turbine components in the aircraft gas turbine engine has been accomplished. The test results indicate that the ceramic turbine wheel is capable of operating under the high thermal shock condition of fast starting to full speed. Furthermore, the adoption of some new ceramic turbine design concepts is proposed in actual use for aircraft ceramic turbine engines.

著者

山根 秀公 松永 易 草川 剛

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.56, no.649, pp.80-87, 2008-02-05

被引用文献数

1 1

---

A flyable FADEC system engineering model incorporating Integrated Flight and Propulsion Control (IFPC) concept is developed for a highly maneuverable aircraft and a fighter-class engine. An overview of the FADEC system and functional assignments for its components such as the Engine Control Unit (ECU) and the Integrated Control Unit (ICU) are described. Overall system reliability analysis, convex analysis and multivariable controller design for the engine, fault detection/redundancy management, and response characteristics of a fuel system are addressed. The engine control performance of the FADEC is demonstrated by hardware-in-the-loop simulation for fast acceleration and thrust transient characteristics.

著者

小池 勝 石井 満

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.663, pp.166-174, 2009 (Released:2009-04-30)

参考文献数

7

被引用文献数

1

---

In recent years Micro Air Vehicles (MAV) for disaster aerial video are developed vigorously. In order to improve aerodynamic performance of MAV wing performance in low Reynolds numbers (Re) need to be improved, but research on the theme are very rare. In category of Hand Launch Glider, a kind of model aircraft, glide performance are competed, as a result high performance airfoils in Re is around 20,000 are developed. Therefore for MAV's aerodynamic performance improvement airfoils of Hand Launch Gliders should be referred and aerodynamic characteristics of the airfoils desired to be studied. So in this research, aerodynamic characteristics of the gliders are measured in wind tunnel. And also consistency between wind tunnel test and glide test in calm air is examined to confirm reliability of wind tunnel test. Comparison of different airfoils and flow visualization are also performed.

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.

著者

柴藤 羊二 秋元 敏男

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.26, no.298, pp.607-610, 1978-11-05 (Released:2009-07-09)

著者

加藤 修

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.25, no.279, pp.162-166, 1977-04-05 (Released:2009-05-25)

参考文献数

10

著者

秋葉 鐐二郎 青木 嘉範 加勇田 清勇 藤井 篤之 永田 晴紀 佐鳥 新

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.591, pp.141-150, 2003-04-05

参考文献数

11

被引用文献数

1 2

---

The staged combustion hybrid rocket is under development by our research group since 1999. This hybrid rocket engine consists of two combustion chambers. The primary combustion chamber is the fuel tank itself filled with granular solid fuels. The fuel rich gas generated by the first stage combustion flows into the secondary combustion chamber, which is located in the bottom of the primary combustion chamber. The additional oxidizer is injected to the secondary combustion chamber in order to attain an optimal specific impulse by completing combustion. There are two types of the primary combustion. One is nicknamed as the incinerator type; the other is called the multi-grain type. This new type engine is featured with a wide range throttling capability and an extensive freedom in selecting the fuel material. This paper deals with the incinerator type. Presented are preliminary experiments as well as the systems description.

著者

溝口 誠 麻生 茂

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.637, pp.74-81, 2007 (Released:2007-04-10)

参考文献数

12

被引用文献数

3 2

---

A numerical analysis of a piston motion in a free piston driver has been conducted including a diaphragm rupture. Quasi-one-dimensional flow is assumed in the driver. Various losses, which are generated in a compression process, are simplified. A process of the diaphragm rupture is assumed by Outa’s model. Experiments are also conducted by using a free piston shock tunnel. Calculated pressure histories show excellent agreements with experimental results. The numerical analysis shows that the piston motion is strongly affected by the diaphragm rupture. Especially, pressure histories in front of the piston change significantly with compact compression tubes. Diaphragm opening time is necessary to be considered to increase test time and to obtain soft landing conditions in compact free piston drivers.

著者

赤塚 純一 西島 寛典 渡辺 光則 永井 伸治

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会論文集 (ISSN:13446460)

巻号頁・発行日

vol.60, no.5, pp.197-202, 2012 (Released:2012-10-23)

参考文献数

8

---

This paper proposes a new method to predict an unstart of a supersonic wind tunnel. The pressure loss caused by both of a model and structures in the wind tunnel and cross-sectional area distribution are considered as well as blockage ratio in the conventional method. The prediction based on the proposed method was obtained by using quasi-1D numerical simulation. In order to validate the proposed method, a wind tunnel test was performed. The predicted maximum blockage ratios quite agreed with experimental ones except for a few cases in which strong shock wave-boundary layer interaction was observed. The method is expected to be available for various wind tunnels and it gives us more accurate prediction than that by conventional theory.

著者

秋葉 鐐二郎 松尾 弘毅

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.266, pp.103-113, 1976-03-05 (Released:2009-05-25)

著者

森 大吉郎

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.24, no.265, pp.58-66, 1976-02-05 (Released:2009-05-25)

参考文献数

18

著者

大屋 裕二 烏谷 隆 桜井 晃

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.50, no.587, pp.477-482, 2002-12-05

被引用文献数

6 13

---

We have developed a new wind turbine system that consists of a diffuser with a broad-ring brim at the exit periphery and a conventional wind turbine inside it. The new wind turbine has demonstrated power augmentation for a given turbine diameter and wind speed by a factor of about 2–3 compared with a bare wind turbine. This is because a very low-pressure region due to strong vortex formation behind the broad brim draws more mass flow to a turbine inside the diffuser.

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 = Journal of the Japan Society for Aeronautical and Space Sciences (ISSN:13446460)

巻号頁・発行日

vol.50, no.578, pp.95-102, 2002-03-05

被引用文献数

12 7

---

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 performed three RVD experiment flights, and verified all technical items. ETS–VII demonstrated first autonomous RVD between unmanned vehicles, and remote piloted rendezvous flight position accuracy at docking was about 1cm, and acceleration was less than 1.5mG (low impact docking). In the second RVD experiment flight, ETS–VII detected attitude anomaly and executed disable abort for safety insurance. We present the results and evaluation of three RVD experiment flights in this paper.

著者

大屋 裕二 烏谷 隆 桜井 晃

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.50, no.587, pp.477-482, 2002 (Released:2003-09-02)

参考文献数

11

被引用文献数

10 13

---

We have developed a new wind turbine system that consists of a diffuser with a broad-ring brim at the exit periphery and a conventional wind turbine inside it. The new wind turbine has demonstrated power augmentation for a given turbine diameter and wind speed by a factor of about 2–3 compared with a bare wind turbine. This is because a very low-pressure region due to strong vortex formation behind the broad brim draws more mass flow to a turbine inside the diffuser.

著者

鈴木 真之 内山 賢治 Derek J. BENNET Colin R. MCINNES

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.693, pp.259-265, 2011 (Released:2011-10-21)

参考文献数

16

---

This paper attempts to design a guidance law using bifurcating potential fields and velocity field for a swarm of autonomous Unmanned Aerial Vehicles (UAVs). We consider an autonomous flight system that can create different three-dimensional swarming patterns so as to guarantee obstacle and vehicle collision avoidance. The guidance law, which is derived from a steering and repulsive potential field, can express variable geometric patterns for a formation flight of UAVs. The system can transition between different formation patterns by way of a simple parameter change. We also describe the design method for potential field that is flexible enough to respond to a variety of UAV performance and mission. Numerical simulation is performed to verify the validity of the proposed guidance law.

著者

武田 和也 河島 信樹

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.393-396, 2003 (Released:2003-09-26)

参考文献数

7

被引用文献数

2 3

---

A full-size model of a lunar rover using a laser energy transportation to confirm directly the existence of ice on the moon has been fabricated and 100 m energy transportation test has been successfully performed. Problems to be solved to realize an actual lunar ice exploration mission are discussed.