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

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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

佐原 宏典 小林 悠也 中村 健二郎 尾又 由佳乃 阿部 圭典 染谷 昴 西尾 勘汰 飯塚 俊明

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.67, no.6, pp.205-210, 2019 (Released:2019-12-05)

参考文献数

20

被引用文献数

2

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Microsatellites are now in vogue and a lot of and a variety of missions using them are progressed in the world, some of them require propulsion system to realize a highly precise attitude control or orbit transfer. In order to satisfy the requirements, we are developing Microsatellite-Friendly Multi-Purpose Propulsion System, MFMP-PROP, with capabilities of both mono-propellant and bi-propellant modes to provide both of small impulse bit and large delta-V, under the policies of Safety First, Border Free, Effective COTS, and Easy Scalability, based on the techniques of 60wt% Hydrogen Peroxide. We conducted captive tests of a thruster for mono-propellant mode under bi-propellant mode to confirm its stable ignition and continuous operation, and obtained performances under its pre-heating temperature and mixing ratio of hydrogen peroxide and ethanol, of 160 seconds of specific impulse at the highest.

著者

岡野 仁庸 古本 政博 大島 草太 竹中 秀樹 佐原 宏典

出版者

特定非営利活動法人 学習分析学会

雑誌

学習分析学 (ISSN:24366862)

巻号頁・発行日

vol.5, pp.1-12, 2022-04-07 (Released:2022-11-09)

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PBL型授業はチーム教育の手法として広く導入されているが、チームの迷走によって実施側も参加者も今ひとつPBLの効果を感じられないもので終わることがある。本学が提供する「研究プロジェクト演習(4)」の2年度間について、チームによるプロジェクト活動の活性化と評価を作業時間とその一定進捗からの乖離、及びチーム余裕の指標を以って分析した。その結果、前年度の最終報告書のレビューを行うことを導入することと報告会を複数回実施することによって、スムースなプロジェクト開始と作業時間の増加が見られた。また、チームの活性化を評価する指標としてジニ係数を導入し、初年度と第2年度のチームとチーム内メンバーの作業時間に適用した結果、いずれも初年度に比べて第2年度は一定進捗に近付き、チーム作業時間及びメンバー作業時間のばらつきが有意に縮小していることが分かった。本論文の手法によってチーム及びチーム内メンバーの活性化を評価することができ、顕著な活性化が見られないチームやチームメンバーを定量的に顕在化させ、テコ入れの必要性を判断することができる。

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

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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

佐原 宏典 荒井 康雄

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.64, no.3, pp.145-152, 2016 (Released:2016-06-05)

参考文献数

24

被引用文献数

1

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This paper proposes a way of quantitative evaluation for a system with design complexity defined by cyclomatic number, coupling, cohesion, scales of system and subsystems, and the number of interface and communication. Though the design complexity would eventually apply to the calculation of reliableness, it essentially enables a comparison between systems. Here, we adopted the design complexity to Japanese microsatellites, and obtained their characteristics and a guideline to improve them. Furthermore, we found a relation between the design complexity and success level of missions accomplished by the microsatellites, i.e. we should have an option to reduce the design complexity in order to increase the success level of a satellite. Thus, the design complexity affects the reliableness in reliability assessment or resource allocation in a project, so that it would establish an applicable reliability assessment specialized for microsatellite, so-called Hodoyoshi Reliability Assessment.

著者

清水 盛生 内藤 均 佐原 宏典 Shimizu Morio Naito Hitoshi Sahara Hironori

出版者

航空宇宙技術研究所

雑誌

航空宇宙技術研究所資料 = Technical Memorandum of National Aerospace Laboratory (ISSN:1347460X)

巻号頁・発行日

vol.769, 2003-03

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本資料では、当所において1985年頃から実施された太陽熱スラスタの試作研究について述べる。当初はステンレス鋼を材料とした習作スラスタであり、加熱・噴射試験結果も平凡で、比推力500〜600秒級であった。次段階では物質・材料研究機構が日本および米国の特許を有する単結晶モリブデン材を採用して、超小型(外径約6mm)から大型(外径65mm)までの各種サイズのスラスタの試作・太陽集光加熱・推進剤噴射試験を実施した。この材料では推進剤温度2,300K、比推力800秒が期待できる。これが本資料の主要部である。さらに究極の材料として単結晶タングステンを採用して、比推力1,000秒級に対応可能なスラスタを試作して予備実験を実施した。このスラスタはアポジおよびペリジでの噴射が可能な対向型で、この型の試作・実験結果の発表は世界初と思われる。

著者

勝部 駿 佐原 宏典

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.70, no.1, pp.1-6, 2022 (Released:2022-02-05)

参考文献数

5

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In spacecraft systems, it is important to quickly detect and deal with anomalies. However, the increasing complexity of spacecraft systems makes it difficult to avoid failures using previous anomaly detection methods. In recent years, anomaly detection methods based on machine learning have been studied. But it is difficult for a spacecraft to detect anomalies autonomously in orbit. In this study, we propose an anomaly detection method that defines and monitors a single variable representing the health status of a spacecraft system, instead of monitoring a huge amount of telemetry data. We have confirmed that the single variable can represent the health status of a spacecraft system and can be applied to the anomaly detection method.

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

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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

飯塚 俊明 西尾 勘汰 阿部 圭典 川村 壮司 加藤 岳仁 賀来 将大 伴野 眞優 松島 純 小林 悠也 中村 健二郎 佐原 宏典

出版者

独立行政法人 国立高等専門学校機構 小山工業高等専門学校

雑誌

小山工業高等専門学校研究紀要 (ISSN:02882825)

巻号頁・発行日

vol.50, pp.63-68, 2017-12-25 (Released:2019-01-28)

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This paper reports fundamental study on performance degradation, caused by solid catalyst, of 60wt% hydrogen peroxide thruster for small satellites. The chemical in-space propulsion system, with 60wt% hydrogen peroxide, has been proposed and developed based on three policies, safety first, border free, and effective COTS. Platinum based metal honeycomb solid catalyst has been installed to BBM of thruster, and the solid catalyst is one of cause to limit lifetime of the thruster. In this study, to understand degradation, comparison between observation results of solid catalyst surface by FE-SEM/EDS and thruster performance has been conducted. Small cracks have been observed on upstream surface. The evident growth of cracks has not been found; however, instability of response time has been confirmed.

著者

岡野 仁庸 佐原 宏典

出版者

公益社団法人 日本設計工学会

雑誌

設計工学 (ISSN:09192948)

巻号頁・発行日

vol.57, no.5, pp.237-250, 2022 (Released:2022-05-05)

参考文献数

13

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Satellites are utilized in a wide range of fields, such as scientific research, remote sensing, communication, and defense. Unlike ground-based systems, a satellite system has certain special features in terms of system design, usage environment, and life cycle. Therefore, it is difficult for engineers to pass on the system design documents and experiences of the satellite to the next generation. Engineers often design, develop, and validate satellite systems according to their individual competence. In general, if the experience and competence of the engineer are insufficient, regressions and design defects can occur in the later stages of development. In the past, satellites have been affected by problems such as unexpected resource inputs and in-orbit failures, which have reduced quality, cost, and delivery (QCD). We consider that the large gap between the highest standards for satellite design and the actual standards met by the engineers is the most significant factor that causes the QCD to deteriorate. To address this issue, we aim to develop a systems-engineering method that can serve as a guideline for satellite development. Herein, we present the results of our study, along with an evaluation of one of the research themes that we are focusing on to address the aforementioned issue, that is, “Establishing a quantitative systems engineering (SE)-evaluation method by modeling the SE approach.” This is a method for quantitatively visualizing the SE approach and evaluating the validity of satellite development guidelines as a systems-engineering method. This method was validated based on the results of an actual project, i.e., the CanSat project, which involves developing a microsatellite as small as a canned drink.

著者

岡野 仁庸 佐原 宏典

出版者

公益社団法人 日本設計工学会

雑誌

設計工学 (ISSN:09192948)

巻号頁・発行日

pp.2021.2939, (Released:2021-12-16)

参考文献数

13

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Satellites are utilized in a wide range of fields, such as scientific research, remote sensing, communication, and defense. Unlike ground-based systems, a satellite system has certain special features in terms of system design, usage environment, and life cycle. Therefore, it is difficult for engineers to pass on the system design documents and experiences of the satellite to the next generation. Engineers often design, develop, and validate satellite systems according to their individual competence. In general, if the experience and competence of the engineer are insufficient, regressions and design defects can occur in the later stages of development. In the past, satellites have been affected by problems such as unexpected resource inputs and in-orbit failures, which have reduced quality, cost, and delivery (QCD). We consider that the large gap between the highest standards for satellite design and the actual standards met by the engineers is the most significant factor that causes the QCD to deteriorate. To address this issue, we aim to develop a systems-engineering method that can serve as a guideline for satellite development. Herein, we present the results of our study, along with an evaluation of one of the research themes that we are focusing on to address the aforementioned issue, that is, “Establishing a quantitative systems engineering (SE)-evaluation method by modeling the SE approach.” This is a method for quantitatively visualizing the SE approach and evaluating the validity of satellite development guidelines as a systems-engineering method. This method was validated based on the results of an actual project, i.e., the CanSat project, which involves developing a microsatellite as small as a canned drink.

著者

川島 レイ 趙 孟佑 宮崎 康行 佐原 宏典 安藤 恵美子

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 = Aeronautical and space sciences Japan (ISSN:00214663)

巻号頁・発行日

vol.62, no.10, pp.331-336, 2014-10

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大学宇宙工学コンソーシアム(University Space Engineering Consortium:UNISEC)は10年余にわたる国内高専・大学への実践的宇宙開発の支援を経て,宇宙ハンズオントレーニングの有用性・有効性を確信し,活動を宇宙開発新興国を含む他地域に広げるべく,2011年に国際委員会を組織した.国際向けの活動としては,超小型衛星のミッションアイディア国際コンテスト開催,海外の新興国への衛星開発教育の実践,超小型衛星シンポジウムの事務局運営などがある.UNISECでは,2020年までに100以上の国で大学生が実践的宇宙開発に参加できるような世界を作ろうという「VISION 2020-100」を発表し,世界各地にUNISECのような大学連携組織を作り,それらの組織を横断的につなぐUNISEC-Globalを設立しようという提案を国連の会議等で行い,2013年11月には,第1回UNISEC世界大会(The 1st UNISEC-Global Meeting)を実施し,UNISEC-Globalの設立が宣言された.本稿では,UNISEC国際展開の経緯と成果およびその将来展望,課題について考察する.