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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 April 2020, Professor Tahara's group started a new nano-satellite/probe R&D project in Osaka Sangyo University (OSU) after the Project of OIT Electric-Rocket-Engine onboard Small Space Ship (PROITERES) was terminated. In the 1st PROITERES, a nano-satellite with an electrothermal pulsed plasma thruster (PPT) was launched by Indian PSLV C-21 rocket on September 9th in 2012. The main mission was to accurately measure thrust performance in space and to change orbital altitude with the PPT. Currently, the OSU-2 nano-satellite (modified PROITERES-2 satellite) is being developed in OSU for launching in 2024 or 2025. The mission is a long-distance powered flight 50-100 km in altitude by high-power electrothermal PPTs. If altitude control is successful, possibility of small/nano-satellites will be widened. In order to achieve the powered flight, a long-time PPT operation is needed for the system of the OSU-2 satellite. Therefore, a new PPT system with a Multi Discharge Room (MDR), called MDR-PPT, was developed and successfully operated. The weight of the OSU-2 satellite is 47 kg; the outside dimension is 470 x 470 x 450 mm, and the electric power is 60 W. The OSU-2 satellite mainly consists of five systems of thruster system, structure system, attitude control system, communication system and C & DH system. All systems were developed with technologies of 1st PROITERES R&D. The OSU-1 nano-satellite, cubesat 1U (1kg), which is provided with a very-low-power PPT system for orbital transfer and attitude control, is also being developed for launching in 2024-2025. Furthermore, the OSU-3 probe is under development for lunar exploration by Hall thruster. The 4th OSU satellite is planned as a nano-satellite to achieve a main mission that space debris makes deorbit by electric propulsion. The principle of deorbiting space debris is exposure of plasma flow exhausted from an electric thruster to space debris; that is, reaction impulse from the flow is given to debris, and after that debris decreases velocity and deorbits. Accordingly, the OSU-4 satellite can deorbit space debris with safety without contacting to space debris and the satellite. Now, the OSU-4 satellite is under development for launching in 2024-2026., 資料番号: SA6000184060, STEP-2022-008

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, Recently, there has been a growing interest in the use of satellites in very low Earth orbit (VLEO) at altitudes of 200 km or less. Satellites in VLEO has advantages in terms of resolution when observing the earth's surface, communication delay and power required for communication, and energy required for orbit insertion. However, in VLEO the effect of atmospheric drag is significant. In order to maintain flight of satellite in VLEO for a long period of time, deceleration must be prevented, and the use of air-breathing electric propulsion has been attracting attention. At Osaka Sangyo University (OSU), research and development of air-breathing-type electromagnetic-acceleration PPT, MPD thrusters, and Hall thrusters, which are considered as electric propulsion systems with sufficient atmospheric compensation due to their relatively high thrust and high specific impulse, are carried out. In this study, as a preliminary experiment for an air-breathing electric propulsion system, an operational test of an air-breathing-type electromagnetic-acceleration PPT was conducted. The air-breathing PPT was successfully operated with two gases of argon and air, and stable operation was confirmed for both gases., 資料番号: SA6000184071, STEP-2022-019

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 April 2020, nano-satellite/probe R&D project was started in Osaka Sangyo University (OSU) after PROITERES project was terminated at Osaka Institute of Technology (OIT). In PROITERES, a nano-satellite with electrothermal pulsed plasma thrusters (PPTs), the 1st PROITERES satellite, was successfully launched by the Indian PSLV C-21 launcher on September 9th, 2012. Currently, the 2nd PROITERES nano-satellite has been developed, and then the OSU-2 nano-satellite is being developed instead of the 2nd PROPITERES satellite. The main mission is to achieve long-distance powered flight of changing 50-100 km in altitude on near-earth orbit by high-power electrothermal PPTs. In this study, a high-power and long-operation PPT system with a multi-discharge room (MDR) of seven single discharge rooms, called the MDR-PPT, was developed. The single-discharge-room PPT head achieved a maximum impulse bit of 2.47 mNs and a total impulse of 92.0 Ns with a repetitive 110,000 shots at an input energy of 31.59 J. The total impulse means that a 50 kg nano-satellite with the MDR-PPT can be changed in altitude of approximately 25 km on LEO, although more improvement of thruster system is needed up to 50-100 km. The MDR-PPT system consists of MDR-PPT head, Power Processing Unit (PPU) and capacitors. Accordingly, the PPT-system test was successfully performed. Furthermore, a special onboard micro/nano PPT system was designed for orbital transfer and attitude control of 1-3U cubesates (OSU nano-satellite series). The 1J PPT system with 25-90 μNs/shot of measured impulse bit for 1U cubesates (specially OSU-1 cubesat) is successfully operated above 10,000 shots. Our OSU PPT systems can provide a total impulse of 5.0-105 Ns according to various main missions by changing the number of single PPT head and charging electric energy including structure. The OSU PPT systems are going to be marketed for micro/nano-satellites/probes all over the world., 著者人数: 12名, 資料番号: SA6000184061, STEP-2022-009

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 Hall thruster R&D, high thrust, high thrust efficiency and long operating lifetime are required for future space missions of In-Space & large-scale missions such as manned Mars exploration and 1 GW-class solar power satellite construction. The SPT-type Hall thruster THT-VI developed in Osaka Sangyo University achieved thrust efficiencies above 60% and specific impulses of 1,500-4,000 sec with a propellant of xenon at discharge voltages of 300-1,000 V. Furthermore, performance characteristics were measured using special gases of carbon dioxide, methane, ammonia, hydrogen, nitrogen, oxygen, helium, air and water/ice 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 only heavy gases of xenon and/or krypton are used with higher performance; argon is also used in basic experiments. Because the performances with carbon dioxide, methane and ammonia etc were lower than those with the heavy gases, the structure and operational condition are examined to design a thruster suitable for transportation in the Solar System. As for water propellant, a special., 資料番号: SA6000184091, STEP-2022-039