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AIMS: Several studies demonstrated that tricuspid regurgitation (TR) is associated with poor clinical outcomes. However, data on patients with TR who experienced acute heart failure (AHF) remains scarce. The purpose of this study is to evaluate the association between TR and clinical outcomes in patients admitted with AHF, using a large-scale Japanese AHF registry. METHODS AND RESULTS: The current study population consisted of 3735 hospitalized patients due to AHF in the Kyoto Congestive Heart Failure (KCHF) registry. TR grades were assessed according to the routine clinical practice at each participating centre. We compared the baseline characteristics and outcomes according to the severity of TR. The primary outcome was all-cause death. The secondary outcome was hospitalization for heart failure (HF). The median age of the entire study population was 80 (interquartile range: 72-86) years. One thousand two hundred five patients (32.3%) had no TR, while mild, moderate, and severe TR was found in 1537 patients (41.2%), 776 patients (20.8%), and 217 patients (5.8%), respectively. Pulmonary hypertension, significant mitral regurgitation, and atrial fibrillation/flutter were strongly associated with the development of moderate/severe of TR, while left ventricular ejection fraction

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, 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

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, 資料番号: SA6000184093, STEP-2022-041

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

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

Research and development of low-power Hall thruster system is important for the realization of space explorations using micro spacecrafts. In this paper, technical problems for the development of low-power Hall thruster system was discussed based on the previous experimental results of 100-W class Hall thruster., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA2030017002, 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: 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

Aims: Early aortic valve replacement (AVR) might be beneficial in selected high-risk asymptomatic patients with severe aortic stenosis (AS), considering their poor prognosis when managed conservatively. This study aimed to develop and validate a clinical scoring system to predict AS-related events within 1 year after diagnosis in asymptomatic severe AS patients. Methods and results: We analysed 1274 asymptomatic severe AS patients derived from a retrospective multicentre registry enrolling consecutive patients with severe AS in Japan (CURRENT AS registry), who were managed conservatively and completed 1-year follow-up without AVR. From a randomly assigned derivation set (N = 849), we developed CURRENT AS risk score for the AS-related event (a composite of AS-related death and heart failure hospitalization) within 1 year using a multivariable logistic regression model. The risk score comprised independent risk predictors including left ventricular ejection fraction

The emergence and prevalence of antimicrobial-resistant bacteria in wild animals are a great concern for public health. A total of 963 Escherichia coli isolates from 475 wild mammals (242 sika deers, 112 wild boars, 113 small mammals, 4 Japanese badger, 2 Tokara cows, and 2 Amani rabbits), collected between 2013 and 2017, were examined for antimicrobial susceptibility. Resistance to at least one antimicrobial was observed in 92 of 963 isolates (9.3%). No isolates exhibited resistance to carbapenem (meropenem). Resistance to third-generation cephalosporin (cefotaxime) and fluoroquinolone (ciprofloxacin) was observed in less than 1% of the isolates. Thus, low prevalence of bacterial antimicrobial resistance was observed in wild mammals between 2013 and 2017 in Japan.

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: SA6000173041, STEP-2021-002

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: SA6000173045, STEP-2021-006

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

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: SA6000173040, STEP-2021-001

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: SA6000173055, STEP-2021-016

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

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: SA6000173050, STEP-2021-011

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: SA6000160078, レポート番号: STEP-2020-042

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: SA6000160074, レポート番号: STEP-2020-037

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: SA6000160077, レポート番号: STEP-2020-041

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