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4. Experimental Parameter Identification and an Evaluation of the Impact of Tire Models on the Dynamics of Fixed-Wing Unmanned Aerial Vehicles.

Author

Eguchi, Hikaru and Nakata, Daisuke

Subjects
DRONE aircraft, PARAMETER identification, MODEL airplanes, AERODYNAMICS, LATERAL loads
Abstract

Because fixed-wing unmanned aerial vehicles (UAVs) require high-speed taxiing for takeoff and landing, the aircraft's stability during taxiing is critical. However, despite research on the taxiing stability of fixed-wing UAVs conducted in taxiing motion simulations employing various tire models, the applicability of the models to fixed-wing UAV taxiing simulations remains unclear, as does the rationale behind the parameter settings in the models. Therefore, in our study, we measured the forces acting on the tires of a fixed-wing UAV under various conditions, including tire loads of 1.6–3.6 kg and tire slip angles of 0–40 deg. Based on the results, we modified conventional tire models and assessed their applicability in taxiing simulations. Among our findings, the parameter values of the models significantly differed from those used in crewed aircraft taxiing simulations, and the presence or absence of load parameters in the lateral force tire models significantly affected the dynamics. Furthermore, the aerodynamics acting on the aircraft enhanced the straight-line stability during taxiing, resulting in reduced forces on the tires. [ABSTRACT FROM AUTHOR]

Published
2024
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6. Cerebral Venous Sinus Thrombosis with Bilateral Optic Disc Swelling and Bilateral Sixth Nerve Palsies in the Absence of Headache: A Case Report.

Author

Nakata, Daisuke, Okada, Hiroshi, Ueoka, Koji, Shimada, Yoshiaki, Tanikawa, Atsuhiro, Horiguchi, Masayuki, and Ito, Yasuki

Subjects
*OPTIC disc, *CRANIAL sinuses, *VENOUS thrombosis, *SINUS thrombosis, *PARALYSIS, *NERVES
Abstract

Introduction: We report a case of cerebral venous sinus thrombosis (CVST) that presented with bilateral optic disc swelling and diplopia in the absence of headaches. Case Presentation: A 54-year-old woman with no relevant medical history presented with a 2-week history of diplopia and no loss of visual acuity in each eye. Eye movements revealed bilateral abduction deficits, and fundoscopic examination revealed bilateral optic disc swelling. Non-contrast computed tomography of the head showed no abnormalities. Magnetic resonance venography revealed the absence of flow in the superior sagittal and left transverse sinuses as a consequence of thrombosis. The patient was diagnosed with intracranial hypertension associated with abducens nerve palsies secondary to CVST and was initiated on anticoagulant therapy. CVST can lead to stroke even in younger individuals. Conclusion: CVST should be considered in differential diagnosis when bilateral papilledema and abducens nerve palsies are present, even in the absence of headache or other neurological findings. [ABSTRACT FROM AUTHOR]

Published
2024
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10. Flight Demonstration Experiment of Liquid Propellant Detonation Engine System Using Sounding Rocket S-520-34

Author

KASAHARA, Jiro, MATSUYAMA, Koichi, MATSUOKA, Ken, KAWASAKI, Akira, ITOUYAMA, Noboru, ISHIHARA, Kazuki, ITO, Shiro, NAKATA, Kotaro, SATO, Tomoki, MATSUO, Akiko, FUNAKI, Ikkoh, NAKATA, Daisuke, UCHIUMI, Masaharu, EGUCHI, Hikaru, HABU, Hiroto, ARAKAWA, Satoshi, MASUDA, Junichi, MAEHARA, Kenji, USUKI, Tomoaki, YAMADA, Kazuhiko, and NAKAO, Tatsuro

Subjects
Sounding Rocket Flight Experiment, Detonation, Rotating Detonation Engine, Pulse Detonation Engine
Abstract

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

Published
2023

11. 自己加圧式ハイブリッドロケットの推力一定制御

Author

OKANO, Hiro, NAKATA, Daisuke, TADA, Takuya, EGUCHI, Hikaru, and UCHIUMI, Masaharu

Subjects
Throttling, Self pressurization, PID control, Hybrid rocket
Abstract

第5回ハイブリッドロケットシンポジウム(2023年2月14日. オンライン開催), 5th Hybrid Rocket Symposium(February 14, 2023. Online Meeting), 資料番号: SA6000186009, HR-2022-09

Published
2023

12. Development of Landing Experiment System using Rocket Sled

Author

EGUCHI, Hikaru, OKANO, Hiro, SHIBATA, Takuma, and NAKATA, Daisuke

Subjects
Landing, Reusable Rocket, Rocket Sled
Abstract

令和4年度宇宙輸送シンポジウム（2023年1月12日-13日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)) , 相模原市, 神奈川県, Space Transportation Symposium FY2022 (January 12-13, 2023. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, The flight demonstration of reusable rockets requires landing technologies such as deceleration and descent by engine throttling and shock absorption by landing legs. To achieve these landing technologies, this study aims to create a landing and descent environment using a rocket sled for reusable rockets. In this paper, we describe the landing and descent environment that can be achieved with the proposed experimental system, and also describe its current development status., 資料番号: SA6000184018, STCP-2022-018

Published
2023

13. The Study on High-Precision Flow Rate Prediction for LOX/Ethanol Gas Generator

Author

NAMERA, Mio, FUJIURA, Akitomo, NAKAMURA, Yuta, NAKATA, Daisuke, EGUCHI, Hikaru, and UCHIUMI, Masaharu

Subjects
Throttling, Pressure Loss, Gas Generator, Flow Rate
Abstract

令和4年度宇宙輸送シンポジウム（2023年1月12日-13日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)) , 相模原市, 神奈川県, Space Transportation Symposium FY2022 (January 12-13, 2023. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, In this paper, describe a method of prediction for gas generator throttled combustion tests. In addition to the conventional method, the injector Cd was set small based on past test results. As a result, the LOX flow rate error at 70% throttle was improved from 10% to 1.3%. In addition, for flight operation, the propellant orifice diameter was examined for the feed-line resistance of the control valves., 資料番号: SA6000184027, STCP-2022-027

Published
2023

14. Operational Characteristics and Performance Enhancement of DC Arcjet Thrusters: Use of Carbon Dioxide, Methane, Ammonia, Hydrogen, Helium, Air and Ice/Water etc. in Planets and Satellites in the Solar System to Propellants

Author

FURUTANI, Fuma, SASAI, Yui, IIBOSHI, Soma, SAWABE, Ataru, IKEMOTO, Ryo, TAHARA, Hirokazu, MOMOZAWA, Ai, NAKATA, Daisuke, TAKAO, Yoshiyuki, IKEDA, Tomoyuki, NOGAWA, Yuichiro, WAKIZONO, Takashi, and TOYAMA, Masaya

Abstract

令和4年度宇宙輸送シンポジウム（2023年1月12日-13日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)) , 相模原市, 神奈川県, Space Transportation Symposium FY2022 (January 12-13, 2023. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, The direct-current (DC) arcjet thruster is one of electric propulsion for satellite attitude control and orbital transfer. Hydrazine is mainly used as the propellant because it can be used together with chemical thrusters. In this study, performance characteristics of a low-power (0.1-2.0 kW) anode-radiation-cooled arcjet thruster were measured using special gases of carbon dioxide, methane, ammonia and water as original materials in planets and satellites in the Solar System; that is, propellant can be supplied just on the planets and satellites of Moon, Mars and Jupiter Moons, although light gases of hydrazine and hydrogen are normally used with higher performance; argon and nitrogen are also used in basic experiments. Because the performances with carbon dioxide and methane were lower than that with the light gas of ammonia, the structure and operational condition should be examined to design a thruster suitable with acceptable performance for transportation in the Solar System. As for water propellant, steady-state operation was achieved with stable supply of vapor using a metal glow-plug heater or a new water-vaporing system, which was developed with a long, narrow passage and a large sheet-type heater., 著者人数: 13名, 資料番号: SA6000184067, STEP-2022-015

Published
2023

15. Operational Characteristics and Performance Enhancement of Steady-State MPD Thrusters by Using Original Materials in Planets and Satellites in the Solar System to Propellants

Author

MORI, Daiki, NANRI, Yuta, SHIBAIKE, Yuki, NITTA, Naoyuki, YOSHIDA, Ayano, TAHARA, Hirokazu, MOMOZAWA, Ai, NAKATA, Daisuke, TAKAO, Yoshiyuki, IKEDA, Tomoyuki, WAKIZONO, Takashi, and TOYAMA, Masaya

Abstract

令和4年度宇宙輸送シンポジウム（2023年1月12日-13日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)) , 相模原市, 神奈川県, Space Transportation Symposium FY2022 (January 12-13, 2023. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, Magneto-Plasma-Dynamic (MPD) thrusters have been investigated in Osaka Sangyo University. The purpose of this study is to develop a practical MPD thruster system for future transportation among planets and satellites in the Solar System, especially for manned Mars exploration as one of the In-Space Transportation & Propulsion Project in collaboration with the Japan Aerospace eXploration Agency (JAXA). A magnetic field is applied to an MPD thruster by using permanent magnets of samarium cobalt (SmCo) magnets. In this study, performance characteristics were measured using special gases of carbon dioxide, methane and ammonia as original materials in planets and satellites in the Solar System; that is, propellant can be supplied just on the planets and satellites of Moon, Mars and Jupiter Moons; argon and nitrogen also used in basic experiments. Because operations with carbon dioxide and methane were slightly unstable compared with cases with other gases, the structure and operational condition should be examined to design a thruster suitable for transportation in the Solar System. Accordingly, the highest specific impulses of 444 and 560 sec, respectively, were obtain with CO2 and CH4 with 0.157 T although deposition of carbon was observed on the surface of the anode constrictor. Furthermore, a high performance with 5 mg/s of NH3 at 1.0 kW was a thrust of 60 mN, a specific impulse of 1,500 s and a thrust efficiency of 30.0% with 0.157 T. In high-power operation, a performance with 60 mg/s of NH3 at 6.75 kW was a thrust of 478 mN, a specific impulse of 810 s and a thrust efficiency of 19.0% with 0.157 T., 著者の誤記: Daisuke Tanaka, 著者人数: 12名, 資料番号: SA6000184075, STEP-2022-023

Published
2023

16. Combustion chamber temperature distribution of Gas Generator for GG-ATR engine

Author

FUJIURA, Akitomo, NAMERA, Mio, NAKAMURA, Yuta, NAKATA, Daisuke, EGUCHI, Hikaru, and UCHIUMI, Masaharu

Subjects
Temperature Distribution, GG-ATR Engine, Gas Generator (GG), Temperature Equalization
Abstract

令和4年度宇宙輸送シンポジウム（2023年1月12日-13日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)) , 相模原市, 神奈川県, Space Transportation Symposium FY2022 (January 12-13, 2023. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, Muroran Institute of Technology is conducting research and development of a Gas Generator Cycle Air Turbo Ramjet (GG-ATR) Engine as a propulsion system for small unmanned supersonic aircraft. A temperature deviation exists inside the combustion chamber of the gas generator installed in this engine. Therefore, we installed elbows, which are known to be effective in improving temperature distribution to confirm the temperature uniformity effect of the elbows. As a result, it was confirmed that the elbow improved the combustion gas temperature by 630K., 資料番号: SA6000184028, STCP-2022-028

Published
2023

19. Flight Demonstration Experiment of Liquid Propellant Detonation Engine System Using Sounding Rocket S-520

Author

KASAHARA, Jiro, MATSUYAMA, Koichi, MATSUOKA, Ken, KAWASAKI, Akira, WATANABE, Hiroaki, ITOUYAMA, Noboru, GOTO, Keisuke, ISHIHARA, Kazuki, ITO, Shiro, NAKATA, Kotaro, SATO, Tomoki, MATSUO, Akiko, FUNAKI, Ikkoh, NAKATA, Daisuke, UCHIUMI, Masaharu, HABU, Hiroto, TAKEUCHI, Shinsuke, ARAKAWA, Satoshi, MASUDA, Junichi, MAEHARA, Kenji, YAMADA, Kazuhiko, and NAKAO, Tatsuro

Subjects
Sounding Rocket Flight Experiment, Detonation, Rotating Detonation Engine, Pulse Detonation Engine
Abstract

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

Published
2022

20. Development of Visualization System for Fuel Regression of Paraffin Wax in Acceleration Environments

Author

NEKI, Tomoya, OZAWA, Kohei, TSUBOI, Nobuyuki, NAKATA, Daisuke, UCHIUMI, Masaharu, and YASUDA, Kazuki

Subjects
Acceleration environment, Regression rate, Hybrid rocket, Wax fuel, Rocket sled
Abstract

第4回ハイブリッドロケットシンポジウム(2022年2月14日. オンライン開催), 4th Hybrid Rocket Symposium(February 14, 2022. Online Meeting), 資料番号: SA6000171015, HR-2021-15

Published
2022

21. PID Throttle Control of Self-pressurized Hybrid Rocket Engine

Author

YAMAGISHI, Kohki, NAKATA, Daisuke, YASUDA, Kazuki, SHIINA, Tatsuhiko, ANG, YiYong, TADA, Takuya, HASHIMOTO, Yuma, EGUCHI, Hikaru, and UCHIUMI, Masaharu

Subjects
PID controlle, Self-pressurization, Throttling, Hybrid Rocket, Thrust control
Abstract

第4回ハイブリッドロケットシンポジウム(2022年2月14日. オンライン開催), 4th Hybrid Rocket Symposium(February 14, 2022. Online Meeting), 資料番号: SA6000171010, HR-2021-10

Published
2022

22. Surface Temperature Distribution of LOX/LH2 Gas Generator for ATRIUM Engine

Author

FUJIURA, Akitomo, NAMERA, Mio, SUMIYOSHI, Masaya, NAKATA, Daisuke, UCHIUMI, Masaharu, EGUCHI, Hikaru, KONDO, Shoichiro, BANNO, Yuya, FUKUZAKI, Toshiya, KINEFUCHI, Kiyoshi, MANAKO, Hiroyasu, SAKAMOTO, Yuki, MARU, Yusuke, KOBAYASHI, Hiroaki, TOKUDOME, Shinichiro, and YAGISHITA, Tsuyoshi

Subjects
ATRIUM Engine, Thermography, Surface Temperature, Gas Generator (GG)
Abstract

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: 16名, 資料番号: SA6000173015, STCP-2021-015

Published
2022

23. Throttling Fire Test of a LOX/Ethanol Gas Generator for the GG-ATR Engine

Author

SUMIYOSHI, Masaya, NAMERA, Mio, FUJITA, Akitomo, NAKATA, Daisuke, EGUCHI, Hikaru, and UCHIUMI, Masaharu

Abstract

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), 資料番号: SA6000173017, STCP-2021-017

Published
2022

24. Throttling Firing Test of LOX/LH2 Gas Generator for ATRIUM Airbreathing Engine

Author

KONDO, Shoichiro, FUKUZAKI, Toshiya, BANNO, Yuya, KINEFUCHI, Kiyoshi, FUJIURA, Akitomo, NAMERA, Mio, NAKATA, Daisuke, MANAKO, Hiroyasu, TOKUDOME, Shinichiro, KOBAYASHI, Hiroaki, SAKAMOTO, Yuki, and MARU, Yusuke

Abstract

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: 12名, 資料番号: SA6000173016, STCP-2021-016

Published
2022

25. 太陽系惑星・衛星に存在する物資を推進剤に用いた定常作動型MPDスラスタの性能測定

Author

YOSHIDA, Ayano, IKEMOTO, Ryo, MORI, Daiki, NANRI, Yuta, TAHARA, Hirokazu, MOMOZAWA, Ai, NAKATA, Daisuke, TAKAO, Yoshiyuki, IKEDA, Tomoyuki, WAKIZONO, Takashi, and TOYAMA, Masaya

Abstract

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: 11名, 資料番号: SA6000173059, STEP-2021-020

Published
2022

27. Performance Measurement of DC Arcjet Thrusters -Use of Carbon Dioxide, Methane, Ammonia, Hydrogen, Helium, Air and Ice/Water etc. in Planets and Satellites in the Solar System to Propellants

Author

KAJI, Kentaro, SHIBUTANI, Kazuki, SASAI, Yui, FURUTANI, Fuma, TAHARA, Hirokazu, MOMOZAWA, Ai, NAKATA, Daisuke, TAKAO, Yoshiyuki, IKEDA, Tomoyuki, NOGAWA, Yuichiro, WAKIZONO, Takashi, and TOYAMA, Masaya

Abstract

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: 12名, 資料番号: SA6000173058, STEP-2021-019

Published
2022

29. Space Flight Demonstration of Detonation Kick Motor Using Sounding Rocket S-520

Author

KASAHARA, Jiro, MATSUYAMA, Koichi, MATSUOKA, Ken, KAWASAKI, Akira, WATANABE, Hiroaki, ITOUYAMA, Noboru, GOTO, Keisuke, ISHIHARA, Kazuki, MATSUO, Akiko, FUNAKI, Ikkoh, NAKATA, Daisuke, UCHIUMI, Masaharu, HABU, Hiroto, TAKEUCHI, Shinsuke, ARAKAWA, Satoshi, MASUDA, Junichi, MAEHARA, Kenji, WADA, Asato, and YAMADA, Kazuhiko

Abstract

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

Published
2021

30. 観測ロケット S-520 31号機プロジェクト：デトネーションエンジンシステムの宇宙実証

Author

MATSUOKA, Ken, KASAHARA, Jiro, Matsuyama, Koichi, KAWASAKI, Akira, ITOUYAMA, Noboru, WATANABE, Hiroaki, GOTO, Keisuke, BUYAKOFU, Valentin, ISHIHARA, Kazuki, NODA, Tomoyuki, MATSUO, Akiko, FUNAKI, Ikkoh, NAKATA, Daisuke, UCHIUMI, Masaharu, HABU, Hiroto, TAKEUCHI, Shinsuke, ARAKAWA, Satoshi, MASUDA, Junichi, MAEHARA, Kenji, YAMADA, Kazuhiko, and WADA, Asato

Subjects
pulse detonation engine, sounding rocket, rotating detonation engine, PDE, RDE
Abstract

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: 21名PDF再処理の為、2023年3月17日に差替, 資料番号: SA6000162001, レポート番号: Ⅰ-1

Published
2021

31. Ignition characteristics of hydrogen-air premixture in a ram combustor

Author

KAMIMURA, Kodai, FUKIBA, Katsuyoshi, NAKATA, Daisuke, KOBAYASHI, Hiroaki, and MARU, Yusuke

Abstract

令和二年度宇宙輸送シンポジウム（2021年1月14日-15日. オンライン開催), Space Transportation Symposium FY2020 (January 14-15, 2021. Online Meeting), PDF再処理の為、2023年2月27日に差替, 資料番号: SA6000160022, レポート番号: STCP-2020-022

Published
2021

32. Research and Development of DC/MPD Arcjet Thrusters Using HAN/Water and Hydrogen-Series Propellants: from Satellite Attitude Control to Orbital Transportation in the Solar System

Author

KAJI, Kentaro, SHIBUTANI, Kazuki, YOSHIDA, Ayano, IKEMOTO, Ryo, TAHARA, Hirokazu, MOMOZAWA, Ai, NAKATA, Daisuke, TAKAO, Yoshiyuki, IKEDA, Tomoyuki, NOGAWA, Yuichiro, WAKIZONO, Takashi, and TOYAMA, Masaya

Abstract

令和二年度宇宙輸送シンポジウム（2021年1月14日-15日. オンライン開催), Space Transportation Symposium FY2020 (January 14-15, 2021. Online Meeting), 著者人数: 12名PDF再処理の為、2023年2月27日に差替, 資料番号: SA6000160050, レポート番号: STEP-2020-012

Published
2021

33. High Temperature Test of an Electro-thermal Thruster with Multi-wall Tungsten Heater

Author

CORAL, Giulio, KINEFUCHI, Kiyoshi, NAKATA, Daisuke, SUYA, LATU, SAKAI, Hitoshi, TSUKIZAKI, Ryudo, MARU, Yusuke, KOBAYASHI, Hiroaki, and NISHIYAMA, Kazutaka

Abstract

令和二年度宇宙輸送シンポジウム（2021年1月14日-15日. オンライン開催), Space Transportation Symposium FY2020 (January 14-15, 2021. Online Meeting), PDF再処理の為、2023年2月27日に差替, 資料番号: SA6000160080, レポート番号: STEP-2020-044

Published
2021

34. Progress Status of a Detonation Engine System for Sounding Rocket S-520 No. 31: Rotating Detonation Engine

Author

MATSUOKA, Ken, GOTO, Keisuke, BUYAKOFU, Valentin, ISHIHARA, Kazuki, NODA, Tomoyuki, ITOYAMA, Noboru, KAWASAKI, Akira, WATANABE, Hiroaki, MATSUYAMA, Koichi, KASAHARA, Jiro, MATSUO, Akiko, FUNAKI, Ikkoh, NAKATA, Daisuke, UCHIUMI, Masaharu, TAKEUCHI, Shinsuke, IWASAKI, Akihiro, WADA, Asato, MASUDA, Junichi, ARAKAWA, Satoshi, HABU, Hiroto, and YAMADA, Kazuhiko

Abstract

令和二年度宇宙輸送シンポジウム（2021年1月14日-15日. オンライン開催), Space Transportation Symposium FY2020 (January 14-15, 2021. Online Meeting), 著者人数: 21名PDF再処理の為、2023年2月27日に差替, 資料番号: SA6000160027, レポート番号: STCP-2020-027

Published
2021

35. 太陽系内軌道間航行用大推力・高比推力 MPD/DC スラスタの性能特性と熱設計

Author

TAHARA, Hirokazu, TAKAO, Yoshiyuki, IKEDA, Tomoyuki, MOMOSAWA, Ai, NAKATA, Daisuke, WAKIZONO, Takashi, and TOYAMA, Masaya

Abstract

令和元年度宇宙輸送シンポジウム（2020年1月16日-17日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, Space Transportation Symposium FY2019 (January 16-17, 2020. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000147055, レポート番号: STEP-2019-006

Published
2020

36. 観測ロケットSS520を用いたデトネーションキックモーター軌道投入実証実験

Author

Kasahara, Jiro, Matsuoka, Ken, Kawasaki, Akira, Matsuyama, Koichi, Goto, Keisuke, Matsuo, Akiko, Funaki, Ikkoh, Maru, Yusuke, Habu, Hiroto, Takeuchi, Shinsuke, Yamada, Kazuhiko, Kitagawa, Koki, Tobe, Hirobumi, Arakawa, Satoshi, Iwasaki, Akihiro, Wada, Asato, Nakata, Daisuke, Uchiumi, Masaharu, Endo, Takuma, Ishii, Kazuhiro, Tokudome, Shinichiro, Nonaka, Satoshi, Kojima, Takayuki, Kawashima, Hideto, and Shouji, Takeshi

Subjects
Sounding Rocket Flight Experiment, Detonation, Rotating Detonation Engine, Pulse Detonation Engine
Abstract

第2回観測ロケットシンポジウム（2019年8月5日-6日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, 2nd Sounding Rocket Symposium (August 5-6, 2019. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 著者人数: 26名, 資料番号: SA6000142023, レポート番号: Ⅶ-2

Published
2019

37. Development of Space Flight Detonation Engine Demonstrator Using Sounding Rocket S520-31 and Its Evolution

Author

Kasahara, Jiro, Matsuoka, Ken, Kawasaki, Akira, Goto, Keisuke, Yokoo, Ryuya, Buyakofu, Valentin, Matsuo, Akiko, Funaki, Ikkoh, Nakata, Daisuke, Uchiumi, Masaharu, Habu, Hiroto, Takeuchi, Shinsuke, Yamada, Kazuhiko, Kitagawa, Koki, Tobe, Hirobumi, Iwasaki, Akihiro, and Wada, Asato

Subjects
Sounding Rocket Flight Experiment, Detonation, Rotating Detonation Engine, Pulse Detonation Engine
Abstract

第2回観測ロケットシンポジウム（2019年8月5日-6日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, 2nd Sounding Rocket Symposium (August 5-6, 2019. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 著者人数: 17名, 設計製造協力: NETS, 山本機械設計, 資料番号: SA6000142024, レポート番号: Ⅷ-1

Published
2019

38. Evaluation of Filling, Discharging and Flow Characteristics of Nitrous Oxide

Author

Yasuda, Kazuki, Nakata, Daisuke, and Uchiumi, Masaharu

Subjects
Self-pressurization, Nitrous oxide, Carbon dioxide, Hybrid rocket, Two-phase flow, Propellant supply system
Abstract

第2回ハイブリッドロケットシンポジウム（2019年7月11日-12日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, 2nd Hybrid Rocket Symposium (July 11-12, 2019. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000143011, レポート番号: HR-2019-010

Published
2019

39. Performance Characteristics of the 1kN-class Hybrid Rocket Engine

Author

Okada, Kugo, Nakata, Daisuke, Yasuda, Kazuki, and Uchiumi, Masaharu

Subjects
Rocket Noise, Nitrous Oxide, Hybrid Rocket, Rocket Sled
Abstract

平成30年度宇宙輸送シンポジウム（2019年1月17日-18日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, Space Transportation Symposium FY2018 (January 17-18, 2019. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000136028, レポート番号: STCP-2018-028

Published
2019

42. Flight Experiment Research of Detonation Engines Using Sounding Rocket

Author

Kasahara, Jiro, Matsuoka, Ken, Kawasaki, Akira, Matsuo, Akiko, Funaki, Ikkoh, Nakata, Daisuke, Uchiumi, Masaharu, and Higashino, Kazuyuki

Subjects
Sounding Rocket Flight Experiment, Detonation, Rotating Detonation Engine, Pulse Detonation Engine
Abstract

第1回観測ロケットシンポジウム（2018年7月17日-18日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, 1st Sounding Rocket Symposium (July 17-18, 2018. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000127017, レポート番号: V-3

Published
2018

43. Influence of Outside Temperature on Nitrous Oxide Self-Pressurized Discharging Characteristics

Author

Yasuda, Kazuki, Nakata, Daisuke, Uchiumi, Masaharu, Okada, Kugo, and Imai, Ryouji

Subjects
Self-pressurized tank, Nitrous oxide, Cold flow test, Hybrid rocket, Two-phase flow
Abstract

第1回ハイブリッドロケットシンポジウム（2018年6月28日-29日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, 1st Hybrid Rocket Symposium (June 28-29, 2018. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000126008, レポート番号: HR-2018-007

Published
2018

44. Operation of a Rocket Sled using Hybrid Rocket Engines

Author

Nakata, Daisuke, Yasuda, Kazuki, Okada, Kugo, Higuchi, Ken, Katsumata, Nobuhisa, and Uchiumi, Masaharu

Subjects
Hybrid Rocket, Rocket Sled, Ignition, Clustering
Abstract

第1回ハイブリッドロケットシンポジウム（2018年6月28日-29日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, 1st Hybrid Rocket Symposium (June 28-29, 2018. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000126011, レポート番号: HR-2018-010

Published
2018

45. Research and Development of a Low-Power DC Arcjet Thruster Using HAN series Propellant

Author

Okuda, Kazuyoshi, Mimura, Takefumi, Shimogaito, Katsuya, Okumura, Shunsuke, Tahara, Hirokazu, Takada, Kyoko, Momozawa, Ai, Nogawa, Yuichiro, and Nakata, Daisuke

Abstract

平成29年度宇宙輸送シンポジウム（2018年1月18日-19日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, Space Transportation Symposium FY2017 (January 18-19, 2018. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000210052, レポート番号: STCP-2017-052

Published
2018

46. High Performance and Low Cost Resistojet with 3D Additive Manufacturing

Author

Llanillo, Rodel, Kinefuchi, Kiyoshi, Matsunaga, Yoshiki, Fujii, Go, Ikeda, Hirohide, Nakata, Daisuke, and Sakai, Hitoshi

Abstract

平成28年度宇宙輸送シンポジウム（2017年1月19日-20日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, Space Transportation Symposium FY2016 (January 19-20, 2017. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000086040, レポート番号: STEP-2016-002

Published
2017

47. Performance Characteristics of Low-Power DC Arcjet Thrusters Using Low-Toxicity Propellants

Author

Mimura, Takefumi, Shiraki, Suguru, Fukutome, Yuki, Shimogaito, Katsuya, Okuda, Kazuyoshi, Tahara, Hirokazu, Takada, Kyoko, Momozawa, Ai, Nakata, Daisuke, and Nogawa, Yuichiro

Abstract

平成28年度宇宙輸送シンポジウム（2017年1月19日-20日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, Space Transportation Symposium FY2016 (January 19-20, 2017. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 資料番号: SA6000086039, レポート番号: STEP-2016-001

Published
2017

48. 複合材回転デトネーションエンジンの伝熱特性及び長秒時地上燃焼実験

Author

Kasahara, Jiro, Ishihara, Kazuki, Nishimura, Jyunpei, Nakagami, Soma, Matsuoka, Ken, Matsuo, Akiko, Funaki, Ikkoh, Mukae, Hiroto, Yasuda, Kazuki, Nakata, Daisuke, and Higashino, Kazuyuki

Subjects
Detonation Wave, Rotating Detonation Engine, Pulse Detonation Engine
Abstract

平成28年度宇宙輸送シンポジウム（2017年1月19日-20日. 宇宙航空研究開発機構宇宙科学研究所（JAXA)(ISAS)）, 相模原市, 神奈川県, Space Transportation Symposium FY2016 (January 19-20, 2017. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)), Sagamihara, Kanagawa Japan, 著者人数: 11名, 資料番号: SA6000086005, レポート番号: STCP-2016-005

Published
2017

49. Anti‐tumor efficacy of a novel CLK inhibitor via targeting RNA splicing and MYC‐dependent vulnerability

Author

Iwai, Kenichi, primary, Yaguchi, Masahiro, additional, Nishimura, Kazuho, additional, Yamamoto, Yukiko, additional, Tamura, Toshiya, additional, Nakata, Daisuke, additional, Dairiki, Ryo, additional, Kawakita, Yoichi, additional, Mizojiri, Ryo, additional, Ito, Yoshiteru, additional, Asano, Moriteru, additional, Maezaki, Hironobu, additional, Nakayama, Yusuke, additional, Kaishima, Misato, additional, Hayashi, Kozo, additional, Teratani, Mika, additional, Miyakawa, Shuichi, additional, Iwatani, Misa, additional, Miyamoto, Maki, additional, Klein, Michael G, additional, Lane, Wes, additional, Snell, Gyorgy, additional, Tjhen, Richard, additional, He, Xingyue, additional, Pulukuri, Sai, additional, and Nomura, Toshiyuki, additional

Published
2018
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