Physical Phenomena of Electric Thrusters in Space

太空电动推进器的物理现象

• 批准号: 09044168
• 负责人: YOSHIKAWA Takao
• 金额: $ 6.14万
• 依托单位: Osaka University
• 依托单位国家: 日本
• 项目类别: Grant-in-Aid for international Scientific Research
• 财政年份: 1997
• 资助国家: 日本
• 起止时间: 1997 至 1998
• 项目状态: 已结题
• 来源: https://kaken.nii.ac.jp/grant/KAKENHI-PROJECT-09044168/
• 关键词: Electric Propulsion; Arcjet Thruster; Magnetoplasmadynamic Thruster; Ion Thruster; Hall Thruster; Plasma Diagnostics; Thruster Performance; Spacecraft Environment; ホール型推進機

A joint study among Japan, Russia and USA was carried out in order to understand physical phenomena on electric thrusters in space. Direct-current (DC) arcjet thrusters, magnetoplasmadynamic (MPD) thrusters, ablative pulsed plasma thrusters, ion thrusters and Hall thrusters were investigated. Physical plasma properties, such as electron temperature and electron number density, in their thrusters were measured by means of electrostatic probe method and spectroscopic technique, and plasma features and acceleration processes were examined. In Japan, the Institute of Space and Astronautical Science is promoting the sample and return space mission from an asteroid, the MUSES-C, which is scheduled to be launched in 2002 and to bring back some specimens to the Earth in 2006 from an extra-terrestrial object. In the MUSES-C mission, the cathode-less microwave discharge ion thruster system is ready as a primary propulsion in the interplanetary space. The 400 W microwave discharge ion thruster was studied to improve the thrust performance. 30-cm-diam. ring-cusped, 20-cm-diam. microwave discharge and CィイD260ィエD2-propellant ion thrusters, 0.3-1kW DC arcjet thrusters, 10-100kW steady-state and 1kW quasi-steady MPD thrusters, 0.5-5kW Hall thrusters, and their plasma plumes-spacecraft interactions were investigated aiming at applications to practical near-earth and interplanetary missions. Non-propulsive applications of electric thrusters to material processing were also conducted.

日本、俄罗斯和美国进行了一项联合研究，以了解空间电推进器的物理现象。研究了直流电弧喷射推力器、磁等离子体推力器、烧蚀脉冲等离子体推力器、离子推力器和霍尔推力器。采用静电探针法和光谱技术测量了它们的推力器等离子体的电子温度和电子数密度等物理特性，研究了等离子体的特性和加速过程。在日本，空间和宇宙航行科学研究所正在推动从小行星MUSES-C取样和返回空间的使命，该使命定于2002年发射，并于2006年从一个外星物体带回一些标本到地球。在MUSES-C使命中，无阴极微波放电离子推进器系统已准备好作为行星际空间的主要推进器。为提高微波放电离子推力器的推力性能，对400 W微波放电离子推力器进行了研究.直径30厘米。环尖，直径20厘米。针对实际近地和行星际飞行任务的应用，研究了微波放电和C_（60）D_2D_2推进剂离子推力器、0.3- 1 kW直流电弧喷射推力器、10- 100 kW稳态和1 kW准稳态MPD推力器、0.5- 5 kW霍尔推力器及其等离子体羽流-航天器相互作用。还进行了电推进器在材料加工方面的非推进应用。

项目成果

N.Antropov etal.: "Pulsed Plasma Thrusters for Space Craft Attitude and Orbit Control System"Proc. 26th Int. Electric Propulsion Conf.. 99-192. 1-10 (1999)

N.Antropov 等人：“用于航天器姿态和轨道控制系统的脉冲等离子推进器”Proc。

V.B.Tikhonov etal.: "Own Magnetic Field Impact on MPD Thrusters Performance with External Magnetic Field"Proc. 26th Int. Electric Propulsion Conf.. 99-176. 1-10 (1999)

V.B.Tikhonov 等人：“自身磁场对外部磁场对 MPD 推进器性能的影响”Proc。

M.Martinez-Sanchez etal.: "Linear 1-D Analysis of Oscillation Instabilities in Hall Thrusters"Proc. 26th Int. Electric Propulsion Conf.. 99-105. 1-10 (1999)

M.Martinez-Sanchez 等人：“霍尔推进器振荡不稳定性的线性一维分析”Proc。

Hirokazu Tahara et al.: "Performance and Acceleration Process of Quasisteady Magnetoplasmadynacmic Arcjets with Applied Magnetic Fields" J.Propulsion and Power. 13・5. 651-658 (1997)

Hirokazu Tahara 等人：“应用磁场的准稳态磁等离子动力电弧射流的性能和加速过程”J.Propulsion and Power。13・5 (1997)。

Kyoichiro Toki etal.: "Development Status of a Microwave Ion Engine System for the MLISES-C Mission"Proc. 26th Int. Electric Propulsion Conf.. 99-139. 1-10 (1999)

Kyoichiro Toki 等人：“MLISES-C 任务微波离子发动机系统的开发现状”Proc.