Electric Propulsion Development Activity at MELCO
Electric Propulsion Development Activity at MELCO
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MELCO 的电力推进开发活动
DOI：
10.2514/6.2006-4321
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发表时间：
2006
期刊：
影响因子：
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通讯作者：
K. Matsui
中科院分区：
文献类型：
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作者：
T. Ozaki;Y. Kasai;Y. Inanaga;T. Nakagawa;H. Osuga;Takashi Itoh;K. Kajiwara;K. Matsui
MELCO在日本的一些国家项目下开发电力推进器已有约30年的历史。20 mN级氙离子发动机子系统（IES）已进入NSSK卫星推进的实用阶段。IES应用于将于2006财政年度发射的JAXA工程试验卫星的NSSK。此外，MELCO正在为下一代大功率卫星开发200 mN级霍尔推力器和功率处理单元。目标规格为推力水平超过250 mN，PPU输入功率5 kW下比冲超过1, 500 s，寿命超过3,000小时。到目前为止，开发状态是工程模型（EM）阶段后，评估的面包板模型（BBM）和开发模型（DM）。在4.56kW的推力器输入功率下，发动机EM显示出264 mN的推力水平和1, 721 s的比冲。在250 V和350 V电压下，阳极效率在93%以上，输出功率在1.75-4.5kW之间。在推进器和PPU EM之间的耦合测试之后，我们将从2006年中期开始推进器EM的耐久性测试。
MELCO has been developing electric propulsions for about 30 years under some national projects in Japan. The 20mN class xenon ion engine subsystem (IES) has arrived at the practical stage of a satellite NSSK propulsion. The IES is applied for NSSK of the engineering test satellite of JAXA, which will be launched in FY2006. Furthermore, now MELCO is developing 200mN class hall thruster and power processing unit for high power next generation satellite. The target specification is that the thrust level is over 250mN, the specific impulse is over 1,500s under the PPU input power of 5kW, and the lifetime is over 3,000 hours. To date, the development status is engineering model (EM) phase after the evaluation of breadboard model (BBM) and development model (DM). The thruster EM showed 264mN of the thrust level and 1,721s of the specific impulse under the thruster input power of 4.56kW. The PPU EM showed the anode efficiency was over 93% for 250V and 350V at output power between 1.75-4.5kW. We will start the endurance test of the thruster EM from the middle of 2006 after the coupling test between the thruster and PPU EM.