著者

安平 浩義 小野 航大 平山 和樹 指田 春輝 池田 裕哉 飯島 拓人 吉岡 宙 佐原 宏典 飯塚 俊明 石井 宏宗 岡島 礼奈

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.22, pp.62-70, 2023 (Released:2023-09-20)

参考文献数

21

---

This paper introduces Microsatellite-Friendly Multi-Purpose Propulsion (MFMP-PROP) we proposed as a promising propulsion system using low-toxic propellant for microsatellite, clarifies the development policy and positioning of MFMP-PROP among a variety of propulsion system for microsatellites, and reports the current status of its systemization with the corresponding test results. In addition, the high scalability of MFMP-PROP also makes it suitable for a wide range of missions with microsatellites of 2U to 50kg class. Though the performance of MFMP-PROP is not up to the designed value at present because of too large propellant supply in a prototype of MFMP-1U, this will be solved by optimization of the piping or adding flow adjustment elements. We will continue to further systemize MFMP-PROP and conduct environmental tests to achieve an early space demonstration and utilization.

著者

片山 雅之 外本 伸治 麻生 茂 平山 寛

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.19, pp.47-55, 2020 (Released:2020-03-14)

参考文献数

16

---

The effect of aerodynamic drag on loss of the velocity of a microsatellite on LEO is investigated and compared with the on-orbit data of two microsatellites, Hodoyoshi-1 of the University of Tokyo and QSAT-EOS of Kyushu University, which were launched in 2014. A new model, which includes the influence of the solar activities on atmospheric density, is introduced in this paper. The results obtained from the model suggest that the effect of solar activity on the atmospheric density has to be considered with the deviation of F10.7 parameter due to the number of sunspots. The model is applied to a microsatellite composed of a cubic main body and a deorbit sail to estimate its altitude change due to aerodynamic drag. The rotation of the satellite is taken into consideration.

著者

高橋 秀幸 松下 将典 高尾 勇輝 森 治 角田 博明

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.21, pp.21-30, 2022 (Released:2022-05-10)

参考文献数

14

---

This study proposes a new method for shape control of non-spinning solar sails, in which Shape Memory Alloy (SMA) wires are exploited. An SMA wire is one of soft actuators that contracts at temperatures above its design value. In the proposed framework, the whole shape of a solar sail membrane is deformed via the contraction of SMA wires distributed over the membrane. The deformation results in the change in solar radiation pressure (SRP) torque acting on the solar sail-craft, which is applicable to fuel-free attitude control. In this paper, we investigate the theory of shape control using SMA wires. It is shown that a membrane under shape control behaves similarly both in a ground experiment and in a finite element method (FEM) analysis, demonstrating the validity of numerical modeling. With this result, the performance of shape control for a large membrane in a space environment is simulated by another FEM analysis. Results demonstrate that the proposed method is capable of producing SRP torque at an effective level for attitude control.

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

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

vol.17, pp.35-43, 2018 (Released:2018-03-02)

参考文献数

35

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.

著者

佐原 宏典 鈴木 信義

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.57-62, 2010 (Released:2010-10-21)

参考文献数

4

---

Microsatellites are now in vogue in the world and propulsion will be desired for the more complicated space mission with them. We have been devoting ourselves to develop a propulsion system based on hydrogen peroxide solution with middle-level concentration and tested it for several years, and are now working on price reduction of the propulsion system with the view of a budget of satellite development. One of the key elements of the propulsion for the price reduction is a bladder to pressure liquid propellant, and we confirmed a COTS bladder is practicable with respect to storage performance of hydrogen peroxide and application way of pressure in this study.

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.

著者

水野 貴秀 福田 盛介 坂井 智彦 岡田 祐 有井 基文 西村 健志 入部 紘一 長谷川 秀樹 片山 翔太 遠藤 勉 辻 雅生

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-17-00008, (Released:2017-08-03)

---

The landing radar employs a pulse-type radar using 4.3 GHz C-band microwave radiation. It has a wide beam for measuring the altitude in vertical direction, as well as four narrow tilted beams for measuring the velocity in horizontal direction. In this paper, development of the Bread Board Model (BBM), a field experiment, and the design of SLIM loading Flight Model (FM) are introduced. Furthermore, the radar simulator required for FM development of a radar is explained.

著者

松下 将典 高橋 秀幸 佐藤 泰貴 岩佐 貴史

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.21, pp.53-61, 2022 (Released:2022-09-29)

参考文献数

13

---

Membranes can be applied to deploy high-capacity, lightweight and large structures in space, such as solar sails, occulters, and sunshields. However, it is difficult to predict the shape of the membranes under low tension in orbit, mainly because gravity deflects the membrane on the ground experiments. We propose a ground-based experimental method to simulate the shape of the membrane in weightless conditions by placing the membrane in an aqueous solution. We developed a small experimental system and measured the shape of the curved membrane that floated in a sugar solution. The effectiveness of the experimental method was evaluated by comparing the experimental results with the results of geometrically nonlinear finite element analysis. In addition, these results were compared with the results of the suspended membrane without gravity compensation.

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

3 3

---

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

宮本 侑斗 原田 明徳 ビクラマシンハ ナヴィンダ キトマル 宮沢 与和 船曳 孝三

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.13, pp.1-10, 2014 (Released:2014-02-13)

参考文献数

11

被引用文献数

3 7

---

Fuel efficient flight is demanded due to air traffic increase, environmental concerns and skyrocketing fuel prices. To achieve an effective futuristic air traffic management system, realization of TBO (Trajectory Based Operations) optimized from departure to arrival is aimed in CARATS (Collaborative Actions for Renovation of Air Traffic Systems). In this paper, 4-D trajectory of passenger aircraft is optimized for fuel minimization on the assumption that aircraft is not bounded by any air traffic control constraints. BADA (Base of Aircraft Data) model is adopted for aircraft performance model, and dynamic programming is used to calculate the optimal trajectory. The optimal trajectory is compared with airliner’s flight trajectory by evaluating fuel consumption, flight time and flight range. Examples show that considerable amounts of reduction in fuel consumption could be achieved by trajectory optimization compared to the estimated values of actual flights.

著者

新井 和吉 高橋 秀明 浦澤 俊介 長谷川 直

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.11, pp.117-122, 2012 (Released:2012-10-10)

参考文献数

23

---

A space debris shield for use with spacecraft and satellites was designed. A space debris shield is required to have high defense performance and be lightweight. In this paper, the pressurized wall in the shield composition was made into a double wall structure, and we considered inserting a liquid layer into the shield between these walls. First, the numerical analysis conditions of aluminum alloys of shield composition materials were established from reverse analysis using the ballistic limit equation of a Whipple shield. Using the scaled-down liquid shield, the liquid layer thickness was investigated by comparing the numerical analysis and impact tests that used a two-stage light gas gun. Next, the ballistic limit curve of a real-size liquid shield was examined using the numerical analysis. From these results, it was found that the liquid layer in the debris shield substantially slowed the velocity of incoming debris fragments.

著者

森 治 櫛木 賢一 成尾 芳博 澤井 秀次郎 志田 真樹 丸 祐介 道上 啓亮 中塚 潤一 高見 剛史 浦町 光

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.18, pp.29-35, 2019 (Released:2019-02-01)

参考文献数

9

被引用文献数

1 1

---

The chemical propulsion system of Hayabusa-2 consists of 12 bipropellant thrusters whose thrust is 20N. The communication with Hayabusa was lost due to the fuel leakage just after touchdown in 2005. Akatsuki failed to enter orbit around Venus in 2010. The chemical propulsion system of Hayabusa-2 took measure to prevent these accidents. It satisfied the requirements of continuous injection for SCI (Small Carry-on Impactor) operation. The short injection impulse was estimated using flight data. It was changed by the thruster temperature and the frequency of use. The approximation of the long injection impulse was improved using TCM (Trajectory Correction Maneuver) data and VIC (Velocity Increment Cut) test data. This paper presents development and outward operation of the chemical propulsion system of Hayabusa-2.

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

中村 竣 岩本 雄馬 寺本 進 岡本 光司

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.22, pp.94-100, 2023 (Released:2023-12-06)

参考文献数

15

---

Incoming wakes can induce separated boundary layer instability, and cause performance losses in turbine cascades of a gas turbine. An efficient numerical method that can analyze unsteady incoming wake effects is desirable from practical point of view. In the present study, an extended harmonic balance method (Chebyshev-based harmonic balance, C-HB) is introduced to the analysis of the incoming wake effect on the separated boundary layer. Convection of a one-dimensional wake-like profile and the flow around the flat plate whose front part is replaced by the NACA0012 with the incoming wake at a Reynolds number Re = 92,000 are computed by the C-HB method. The result shows that the C-HB method can resolve the transient phenomenon of wake convection and the associated linear instability of the flow around the blade.

著者

佐原 宏典 渡部 武夫 渡邊 秋人 伊藤 裕明

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.11, pp.15-22, 2012 (Released:2012-01-31)

参考文献数

15

被引用文献数

2 2

---

This paper reports a development and demonstration of inflatable extension boom in the experiments of the ISAS/JAXA sounding rocket, S-520-25. The inflatable extension boom developed by the authors is the longest in ones with conductive part to work as an electrode for collection of electrons surrounding the rocket. S-520-25 sounding rocket was launched in August 31, 2010, and 5 experiments including an extension of the inflatable boom were conducted. The inflatable extension boom and its system worked very well with no problem to form 4-m-long electrode in space.

著者

菊池 隼仁 久原 隆博 中村 和行 森下 直樹 鳥居 航 徳永 翔 大槻 真嗣 橋本 樹明

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.20, pp.59-68, 2021 (Released:2021-06-23)

参考文献数

10

---

OMOTENASHI is a CubeSat that will be launched by NASA SLS rocket. Its mission is to demonstrate that a CubeSat can make a semi-hard landing on the Moon. The 6U-size spacecraft, which weighs 12.6kg, and consists of an orbiting module (OM), a rocket motor (RM) for deceleration on approach to the moon, and a surface probe (SP) as the landing module. Under tight resource constraints, a unique structure and separation mechanism is designed for a small space and a low mass. A validity of these designs has been verified through a vibration test. The margin of safety under the launch vibration is calculated by the structure analysis. In addition, to increase the impact resistance, all components of SP are filled with an epoxy resin. This performance had been evaluated by the drop impact test. As the result, this test model endured more than 16,158G with no function failure. In this paper, the design overview and test results are described.

著者

宮園 晃輝 中間 洸太 住友 佑樹 東野 伸一郎

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.19, pp.131-140, 2020 (Released:2020-12-05)

参考文献数

14

被引用文献数

1 1

---

A runway for the operation of a fixed-wind UAV cannot be always available in practical missions and there is no handy method for landing in confined space while a catapult can be used for launch. The purpose of this paper is to develop a new vertical landing method using the flat spin. Flat spin is the motion that an aircraft rotates horizontally while it is descending vertically. In order to control its touchdown position to a desired position, it is necessary to generate centripetal force to control UAV's descent path to target direction while descending vertically. This paper shows the method to change the path during vertical descent, as well as the result of flight tests and wind tunnel tests.

著者

山田 将史 仲瀬 寛輝 小木曽 望 南部 陽介

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.21, pp.31-39, 2022 (Released:2022-07-12)

参考文献数

29

---

Though our developed nano-satellite, HIROGARI released to orbit in March 2021 achieved the missions successfully until the end of 2021, the satellite encountered significant problems in the early operation stage. Because the satellite condition did not follow the expected behavior, the operation policy had to be decided with insufficient data. However, it was difficult to decide the operation policy rationally, since a nano-satellite has poor battery and communication margins. For the next nano-satellite development, this study constructed a resilient operation model for a nano-satellite using Systems-Theoretic Process Analysis (STPA) with lessons learned from operation experiences of HIROGARI. STPA is known as a new hazard analysis method that focuses on the interaction between a controller and the controlled object and that can be applied in conceptual design stage before detailed configurations are determined. The resilient operation model was constructed by considering the ground station as the controller and the satellite as the controlled target. Then, validity of adopting STPA to construct the operation model is discussed through comparing the unsafe control actions (UCA) and our lessons learned from operation of HIROGARI.

著者

横山 大知 原田 明徳

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.20, pp.154-165, 2021 (Released:2021-12-08)

参考文献数

25

---

Accurate and reliable flight data is indispensable for research and development to explore new findings which will be of assistance in establishing a new system of air traffic management (ATM). Although radar data called CARATS Open Data and Automatic Dependent Surveillance Broadcast (ADS-B) data are currently available, these data have limitations in accuracy and number of parameters; therefore, they are not so sufficient for the research in which detailed parameters such as airdata, take-off weight and cost index are required. The purpose of this study is to verify whether commercially available flight simulator software: X-Plane in which function of Flight Management System (FMS) is replicated, is usable for studies on ATM. To validate whether the flight simulator software can reproduce accurate flight profiles and aircraft parameters, mimicked flight data gained by the simulator is compared with calculated data and real data. In the flight simulation by X-Plane, weather data is input by a piece of software, FS Global Real Weather (FSGRW) which provides the simulator with weather data from National Ocean and Atmospheric Administration's (NOAA) server every 5 minutes.