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形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA2230017000, レポート番号: JAXA-RR-22-006

Ammonium dinitramide (ADN) based energetic ionic liquids (EILs) has been expected as a next HEMs. Since ADN-based EILs are thermally stable, it is difficult to control ignition phenomena using thermal ignition methods. Our research group focused on an ignition method of the EILs by applying a voltage. Previous Studies have theoretically reported the possibility of ignition of ADN-based EILs and experimentally demonstrated the ignition. However, appropriate operational conditions have not been established due to a lack of understanding of the ignition process and phenomena. Therefore, the objective of this study was understanding the ignition process and phenomena based on the results of voltage applied experiments (image, temperature and current measurement). In this experiment, a voltage was applied to a droplet of ADN-based EILs, and the behavior of droplet was filmed by a high-speed camera, while temperature and current measurements were made simultaneously. The voltageapplication process is divided into four phases based on current behavior. It was revealed that the amount of power required for the transition from Phase 1 to Phase 3 remained constant under different experimental conditions. Established a method for measuring ignition delay time. Furthermore, it became clear that the ignition delay time could be reduced by lowering the resistivity of the sample., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA2230017003, レポート番号: JAXA-RR-22-006

Ammonium dinitramide-based ionic liquid propellants (ADN-EILPs) are expected the candidates with high-performance and low toxicity for next-generation chemical thrusters in small satellites. Through past studies, authors have investigated the laser radiant heating ignition of ADN-EILPs to solve technical problems for thruster applications and proposed a thruster concept using ADN-EILPs by utilizing the new propellant supply method as well as such the ignition mechanism. From a new hot-fire test following the previous ones, this paper describes the recent result and discussion about the operational properties of composed thruster based on the concept., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA2230017002, レポート番号: JAXA-RR-22-006

第5回観測ロケットシンポジウム(2023年2月28日-3月1日. オンライン開催), 5th Sounding Rocket Symposium(February 28-March 1, 2023. Online Meeting), 著者人数: 21名, 資料番号: SA6000185021, レポート番号: Ⅲ-6

形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA2130019000, レポート番号: JAXA-RR-21-002

高エネルギー物質研究会では，アンモニウムジニトラミド（ADN）を基剤とした高エネルギーイオン液体（ADN系EILs）を推進剤とした衛星用化学推進系の研究開発を進めている．ADN系EILsは固体エネルギー物質の混合のみで調製可能であり，低蒸気圧，高エネルギー密度という特性から，高性能かつ安全な推進剤となることが期待される．数年以内の軌道上実証を目指し，合成から運用までの一貫した研究開発を進めている．本年度は，小型連続反応器を用いたADNの合成，これまでに見出された手法に基づくEILs組成のデザイン，レーザーおよび電解を用いたEILsの新規点火方式の実現可能性評価，EILsの安全利用に向けた化学安定性と材料適合性試験を進め，実用化に向けた技術の高度化がなされた．今後はスラスタの試作および推進性能の実証を行い，化学推進系としての成立性を明らかにする．, We have been conducting research and development on chemical propellants using high-energy ionic liquids based on ammonium dinitramide (ADN-based EILs) for micro chemical propulsion system. ADN-based EILs can be prepared only by mixing solid energetic materials, and are expected to be high-performance and safe propellants due to their characteristics of low vapor pressure and high energy density. To realize the on-orbit demonstration of propulsion systems using EILs within several years, we are advancing researches of component technologies, consistent research from synthesis to operation. This year, we have made advances in these technologies; synthesis of ADN using a flow reactor, the design of EILs, the feasibility evaluation of a new ignition method of EILs using laser and electrolysis, and the chemical stability test for safe use of EILs. In the future, we will make a prototype of the thruster and demonstrate the propulsion performance to clarify its feasibility as a chemical propulsion system., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA2130019001, レポート番号: JAXA-RR-21-002

アンモニウムジニトラミドを基材とするイオン液体系推進剤 (ADN-EILPs) は，低毒・高密度比推力が期待される有望な一液推進剤の一つである．これまで筆者らは，ADN-EILPs が内包する点火・着火特性に関連する技術課題の克服に取り組んできた．昨今の研究により，新たな点火方式として，レーザ輻射加熱機構とレーザ吸光材の組み合わせを考案し， ADN-EILPs の効果的な点火の糸口を見出すまでに至った．本報告では，これら点火に関連する研究の展開として，当該点火機構に新たな推進剤供給機構を組み合わせた，ADN-EILPs を用いるスラスタの概念について紹介する．, Ammonium dinitramide-based ionic liquid propellants (ADN-EILPs) are expected the candidates with high-performance and low toxicity for next-generation chemical thruster in small satellites. Authors have investigated the ignition of ADN-EILPs to solve technical problems for thruster applications, e.g. ignitor or ignition mechanism of ADN-EILPs. Through the past studies, the combination of laser radiant heating and carbon-based laser absorbent was found out as a solution of expected ignition methods for ADN-EILPs. This paper introduces a thruster concept using ADN-EILPs by utilizing the new propellant supply method as well as such the ignition mechanism., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA2130019002, レポート番号: JAXA-RR-21-002

第4回観測ロケットシンポジウム（2022年3月14-15日. ハイブリッド開催（JAXA相模原キャンパス& オンライン）), 4th Sounding Rocket Symposium(March 14-15, 2022. Hybrid(in-person & online) Conference (Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 著者人数: 22名, 資料番号: SA6000175001, レポート番号: Ⅰ-1

第4回観測ロケットシンポジウム（2022年3月14-15日. ハイブリッド開催（JAXA相模原キャンパス& オンライン）), 4th Sounding Rocket Symposium(March 14-15, 2022. Hybrid(in-person & online) Conference (Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 著者人数: 22名, 資料番号: SA6000175011, レポート番号: Ⅱ-6

形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA2030017000, レポート番号: JAXA-RR-20-008

For the implementation of future space science missions at the father away from Earth, it is necessary to build the technological platforms for performing various challenging missions with high frequency and to mature the technology, and breakthrough of space propulsion technology is especially indispensable. In order to obtain the exploration flexibility by the propulsion control technology of the micro-spacecraft, our research group is working on the development and research of the high-thrust micro-propulsion systems, which is an important technical issue, and objective of this study is the feasibility of the propulsion technologies. In addition, as the platforms of propulsion technology, we propose the various future micro-spacecraft technology demonstration missions and technology demonstration missions of the propulsion system using micro-spacecraft, with hall-effect thruster propulsion system and high-energetic ionic liquid propulsion system as the representative of propulsion technologies. This paper presents the consideration status and further studies of innovative micro propulsion systems for the future deep space explorations., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA2030017001, レポート番号: JAXA-RR-20-008

形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA2030016000, レポート番号: JAXA-RR-20-007

The development of microsatellite is important for expansion of space utilization. The ''energetic ionic liquids (EILs)'', eutectic liquids of high energetic materials, are promising new liquid propellant replacing hydrazine because their unique properties, high energy density, low vapor pressure, enable miniaturization of system, easier handling, and reduction of explosion risks. The mixture of ammonium dinitramide (ADN), monomethylamine nitrate (MMAN), and urea forms EILs and it is one of the candidate for new propellant. To realize the on-orbit demonstration of propulsion systems using EILs within several years, we are advancing researches of component technology; synthesis with highly safety and low cost, propulsion system using laser ignition and electrical energy, and risk assessment for safety use from design to operation., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA2030016001, レポート番号: JAXA-RR-20-007

令和3年度宇宙輸送シンポジウム（2022年1月13日-14日. オンライン開催), Space Transportation Symposium FY2021 (January 13-14, 2022. Online Meeting), 著者人数: 21名, 資料番号: SA6000173021, STCP-2021-021

令和3年度宇宙輸送シンポジウム（2022年1月13日-14日. オンライン開催), Space Transportation Symposium FY2021 (January 13-14, 2022. Online Meeting), 著者人数: 21名, 資料番号: SA6000173022, STCP-2021-022

アンモニウムジニトラミドを基材とした共融型イオン液体は低毒・高エネルギー密度な一液推進薬と期待される反面，低揮発・高熱安定性故に従来の推進薬に比べ着火に技術課題を有する．これまで筆者では解決案としてカーボン材を吸光材として用いるCWレーザ吸光加熱着火を提案し，カーボン材の物理形状及び推進薬液中分散性が着火性に影響することを示した．本研究は蛍光顕微鏡を用いた光学観察から，カーボン材の物理形状と液中分散性の相関，及び既往研究より推定された着火原理の妥当性評価を行った．さらに吸光材を用いるCWレーザ吸光加熱着火における吸光材必要条件を提案した．, Deep eutectic solvents based on ammonium dinitramide (ADN-EILPs) are expected as one of green monopropellant, whereas they have the possibility of low ignitability due to low volatility and high thermal stability. The author had achieved to ignite ADN-EILPs by the combination of carbon absorbents and CW laser heating and proposed the correlation of carbons’ dispersibility and ADN-EILPs ignitability. Based on the study, this paper aimed at the evaluation of the prediction by a fluorescence microscope and proportion of requirements for absorbents on the CW laser heating ignition., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1930018004, レポート番号: JAXA-RR-19-003

我々は高エネルギーイオン液体推進剤（EILPs）を用いた新規宇宙推進系の研究開発を進めている．イオン性化合物特有の高密度・低蒸気圧は推進剤タンクの小型化，取扱性の向上，意図しない爆発リスク低減につながることが期待される．一方でEILPs 実用化のためには，低蒸気圧のEILPs を点火可能で，高温の燃焼にも耐え得るスラスタシステムが求められる．本年度は，高エネルギー物質研究会がこれまでに取扱ってきたアンモニウムジニトラミド（ADN）を基剤とした共融液体をターゲットとし，レーザーを用いた点火方式を中心に実現可能性の検討を進めた．今後は，以上の結果を基にスラスタの設計，燃焼試験を実施するとともに，電気化学反応への応用，推進剤の低コスト合成，安全利用に向けた研究を実施し，新規EILPs 開発指針を構築していく．, We have been developing new space propulsion system using high energetic ionic liquid propellants (EILPs). The unique properties of ionic liquids, high density, low vapor pressure, enable miniaturization of system, easier handling, and reduction of explosion risks. To realize the EILPs thruster, new ignition system and construction for EILPs with low vapor pressure and high combustion temperature. In this year, we developed the laser ignition system for ADN-based eutectic liquids. In future, design of thruster and combustion tests in thruster chamber will be carried out. In addition, we will also investigate the feasibility of electric propulsion with EILs, low-cost synthesis and safety use of EILPs. From them, we will establish guidelines for development of new EILPs., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1930018001, レポート番号: JAXA-RR-19-003

High energetic materials (HEMs) are useful substances for the engineering device with the requirement of high responsibility. HEMs release their high chemical energy through their decomposition and combustion. In order to achieve the safe treatment of HEMs, minimization of hazard risks is essential through the enough investigation of their chemical/physical characteristics. This paper focused on the detonation phenomena of HEMs on gas-phase zone and introduced the calculation methods of state quantity on CJ detonation which is a fundamental detonation mode., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA2030016008, レポート番号: JAXA-RR-20-007

第3回観測ロケットシンポジウム（2021年3月24-25日. オンライン開催), 3rd Sounding Rocket Symposium (March 24-25, 2021. Online Meeting), 著者人数: 19名PDF再処理の為、2023年3月17日に差替, 資料番号: SA6000162013, レポート番号: Ⅲ-6