Neutral Pressure Measurement of Ion Thruster

2014 Fiscal Year Final Research Report

• Project/Area Number: 24560983
• Research Category: Grant-in-Aid for Scientific Research (C)
• Allocation Type: Multi-year Fund
• Section: 一般
• Research Field: Aerospace engineering
• Research Institution: 防衛大学校(総合教育学群、人文社会科学群、応用科学群、電気情報学群及びシステム工学群)
• Principal Investigator: NAKAYAMA Yoshinori 防衛大学校(総合教育学群、人文社会科学群、応用科学群、電気情報学群及びシステム工, その他部局等, 准教授 (80532770)
• Project Period (FY): 2012-04-01 – 2015-03-31
• Keywords: 航空宇宙工学 / ロケット / イオンエンジン / 希薄気体 / 圧力計測 / 推進剤 / 流れ / 真空装置

Outline of Final Research Achievements

Investigation of propellant flow of ion thruster is required to improve ion thruster performance. Since few measurement systems can detect the pressure because the propellant pressure is rarefied, in this research, a low pressure measurement system with a precise differential pressure gauge had been developed. Through the evaluations with a thruster, it had been confirmed that the accuracy of this measurement system was enough to discuss the influence of the rarefied propellant flows, for the researches on account of not only ion thruster but also the other electric propulsion and test facility effect.

Free Research Field

宇宙推進工学