著者

今度 史昭 平家 祐貴 木下 拓也

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.57, no.670, pp.437-444, 2009-11-05

参考文献数

4

---

A new point mass model of the air vehicle has been developed in our laboratory. This model employs angle-of-attack, side slip angle, bank angle and thrust, as four control variables. The existent three control variables point mass model cannot introduce the winds and active side slip angle control, while this new model can introduce them. This paper explains about the model at first. The model is applied to the YF-16 aircraft and simulations are conducted for two maneuvers as typical examples, which show the effectiveness and the preciseness of this model.

著者

山川 宏 小川 博之 藤田 和央 野中 聡 澤井 秀次郎 國中 均 船木 一幸 大津 広敬 中山 宜典

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.603, pp.148-152, 2004 (Released:2004-05-31)

参考文献数

4

被引用文献数

5 6

---

A magneto-plasma sail produces the propulsive force due to the interaction between the artificial magnetic field around a spacecraft inflated by the plasma and the solar wind erupted from the Sun. The inflation of the magnetic field by the plasma was proposed by a group of the University of Washington and the basic research has just started. This paper summarizes the characteristics of the magneto plasma sail by comparing with the other low-thrust propulsion systems, and investigates its potential application to near future planetary missions. Finally, an engineering satellite to demonstrate the magneto-plasma sail is proposed as a first step.

著者

山田 剛治 鈴木 俊之 高柳 大樹 藤田 和央

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.670, pp.426-436, 2009 (Released:2009-11-25)

参考文献数

22

被引用文献数

1 1

---

A free piston double diaphragm shock tube with 70 × 70mm cross-section at test section was newly developed for the purpose of investigating nonequilibrium phenomena behind a shock wave. This paper presents the performance of the shock tube and the measurement system newly developed. Experimental investigation to clarify its characteristics was conducted for various operational parameters, such a rupture pressure of the first diaphragm and initial pressures of the low pressure tube, the high pressure tube, and the compression tube. Based on the characteristics experiment, a performance map of the shock tube was obtained by changing the operation parameters. The result shows that the shock tube is capable of generating the shock layer corresponding to the super orbital reentry flight conditions. The newly developed measurement system enables us to obtain the spatial distribution of spectra behind a shock wave with high spatial and time resolution. A description of the measurement system and typical examples of the measured spectra are presented.

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 (ISSN:13446460)

巻号頁・発行日

vol.54, no.635, pp.542-548, 2006 (Released:2006-12-25)

参考文献数

9

被引用文献数

2 2

---

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.

著者

井藤 創 本田 博一

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 (ISSN:13446460)

巻号頁・発行日

vol.58, no.679, pp.226-232, 2010 (Released:2010-08-27)

参考文献数

19

---

This paper describes results of an exploratory study to investigate the capability of a passive approach for controlling the characteristic spanwise length of Görtler vortices generated in hypersonic flows: a serrated leading edge. Heat transfer, pressure measurements, encapsulated thermochromic liquid crystal, schlieren and glow spark visualizations were conducted with a flat plate/ramp model whose leading edge had a triangular wave shape in a gun tunnel at Mach number 10. Effect of wavelength Λ of the triangular waves on downstream flows was studied. Aerodynamic heating patterns observed with the liquid crystal confirmed that the vortex wavelength was equal to Λ. This was also supported by the spark results that filamentary bright lines perpendicular to an installed line-anode parallel to the spanwise direction at the ramp surface emerged at intervals of Λ. Phase lag was observed only between heat transfer data measured in the spanwise direction, which suggests that the vortex structure existed in the reattaching boundary layers. Pressure distribution in the streamwise direction was similar among all of the Λ tested. In contrast, the heat transfer data points exhibited a large scatter and the peak heating value for the finite Λ was somewhat larger than that for the infinite Λ. Schlieren results indicated that the appropriate Λ can mitigate flow separation.

著者

手塚 亜聖 砂田 保人 李家 賢一

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.57, no.665, pp.258-265, 2009-06-05

参考文献数

20

被引用文献数

5

---

In the Reynolds number region lower than approximately 1.0 × 105, which corresponds to the Reynolds number region of a Micro Air Vehicle, thinner and sharper leading edge airfoil performs better than thicker and blunter one. This research focuses on the difference in flowfields which are clarified by means of streamline calculation and surface pressure distribution measurement. Numerical studies were performed to the blunt type NACA0012 airfoil and both numerical and experimental studies were performed to the thinner type 4% cambered-plate airfoil. The performance of the NACA0012 airfoil is deteriorated with decreasing Reynolds number, whereas that of the 4% circular arc cambered-plate airfoil is not affected. The deterioration of the NACA0012 airfoil performance is mainly due to the laminar boundary layer separation near the trailing edge; such phenomena are not essential to the performance in the cambered-plate airfoil results. This paper also demonstrates that the flow separation at the trailing edge can be estimated from the temporal amplification factor of the oscillatory mode which is calculated by the global linear stability analysis.

著者

満武 勝嗣 東野 伸一郎

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会論文集 (ISSN:13446460)

巻号頁・発行日

vol.58, no.677, pp.153-163, 2010 (Released:2010-07-23)

参考文献数

10

被引用文献数

3 5

---

The authors have proposed the A*-EC hybrid path planning method which can generate a 3D flight path quickly considering terrain and obstacle avoidance. This paper proposes two methods to improve its calculation time in order to apply it to a larger scale problem in real time. Using the two methods, the calculation time reduces approximately from half to quarter. The authors measure the calculation times to examine the performance of the improved A*-EC method by changing the number of waypoints and ``nodes'' which are the apexes of the 3D cells expressing terrain and obstacles. Calculation time is about 10—100 seconds in case of 50—100 waypoints and 2000—7500 nodes. The authors apply the method to a large scale problem in which there are 61 waypoints and about 7000 nodes, and actual topological information and recorded weather information are used as obstacles. The simulation result shows the method can be used in real time.

著者

神永 晋 富岡 定毅 山岬 裕之

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.53, no.623, pp.554-561, 2005 (Released:2006-01-06)

参考文献数

16

被引用文献数

1

---

Flow behavior and thrust performance of MHD energy bypass scramjet engine was examined numerically. MHD generator was placed at the isolator to enhance the flow compression. Kinetic energy was converted to electrical energy in the MHD generator. Extracted electrical energy was consumed at the MHD accelerator placed at the downstream of the combustor. When MHD energy bypass system was used, the flow was decelerated and compressed in the MHD generator. Effect of velocity and Mach number on wall friction was analyzed and decrease of friction force was pointed out. Also, high pressure in the combustor resulted in increase of pressure contribution to net thrust. Despite of positive effects, decelerating Lorentz force in the MHD generator was comparably large and no significant difference in net thrust performance is observed.

著者

平川 美晴 中北 正人

出版者

一般社団法人 日本航空宇宙学会

雑誌

日本航空宇宙学会論文集 (ISSN:13446460)

巻号頁・発行日

vol.47, no.546, pp.267-271, 1999-07-05 (Released:2009-07-09)

参考文献数

6

---

The performance of the ion thruster depends on the discharge performance and the beam extraction, the former of which is significantly effected by the electron property such as density and energy, since ions are produced by ionization collisions between neutral atoms and electrons. In the microwave ion thruster, the discharge owes to the electron cyclotron resonance (ECR). Thus, the electron phenomenon in the microwave discharge chamber was numerically investigated by the particle simulation method. In our model, the electromagnetic wave is polarized circularly and propagates in the axial direction and electrons are moved in the microwave and static magnetic fields, colliding with neutral particles. Collision processes are taken into account by the Monte Carlo method. This simulation results show that some electrons can be heated enough to cause ionization collisions and that the density and energy distributions are peculiar to the microwave ion thrusters.

著者

佐藤 昌之 村岡 浩治

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.61, no.4, pp.110-118, 2013 (Released:2013-10-25)

参考文献数

15

被引用文献数

3 5

---

This paper is concerned with the flight controller design of Quad Tilt Wing (QTW) Unmanned Aerial Vehicle (UAV) which has Vertical Take-Off and Landing (VTOL) capability as well as high speed cruise performance. The flight controller is composed of Stability Augmentation System (SAS), which feedbacks angular velocity, and Control Augmentation System (CAS), which feedbacks the difference between attitude commands and current attitude angles. The gains of S/CAS are both scheduled by the tilt angle of the main wings of the QTWUAV since its airspeed and flight dynamics drastically change in accordance with the tilt angle. The S/CAS are designed by three steps; we first select several design points, then design the controller gains at those design points, and finally connect the gains by linear interpolation. In the design process of the controller gains, perturbed models are introduced in addition to the nominal models, and common gains for those models are designed to ensure robust control performance against modeling errors. Full transition flight from vertical take-off to horizontal cruise was successfully accomplished using our controllers.

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

---

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.

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

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

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

松井 信 小紫 公也 Georg Herdrich Monika Auweter-Kurtz

出版者

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.53, no.619, pp.379-384, 2005-08-05

被引用文献数

3 1

---

Absorption spectroscopy has been applied to the measurement of the arc-heater plumes. Number density distributions of atomic metastable oxygen were obtained from the measured absorption line profile at 777.19 nm in argon-oxygen plumes generated by arcjet type arc-heaters. As a result, it was found that the oxygen is localized off axis at the nozzle exit, and diffuses from outside toward the centerline in the plume. Moreover, numerical simulation was conducted to investigate the diffusion process of the oxygen in the arc-heater. The result indicates that the maximum degree of oxygen dissociation would be at the level of 0.01%.

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.