1kW级肼电弧加热发动机工程样机研究

Development of the 1kW class hydrazine arcjet

关键词:  电推进  电弧加热发动机  肼

Key words:  Electrical propulsion  Arcjet  Hydrazine

摘要:

为了满足静止轨道卫星及中低轨道卫星降低重量、延长寿命的需要,北京控制工程研究所近年来开展了电弧加热发动机的研究工作,目前正在进行1kW级肼电弧加热发动机工程样机的研制。介绍了1kW级肼电弧加热发动机工程样机研制工作的进展情况。该项研制工作的目标是:完成电弧加热发动机的设计、加工和500h寿命试验。预期发动机功耗为1kW左右,比冲为4.5～5.5N·s/g,推力为75～150mN。目前已经完成了第一轮的发动机设计、加工和性能测试工作。出于安全性的考虑,目前的测试暂时是用N₂和NH₃的混合气体模拟肼进行的,测试获得了发动机的比冲、推力、效率等数据。在模拟肼的流量为18～30mg时,发动机的推力为100～150mN,比冲在5N·s/g左右,满足设计指标要求。预期采用单组元肼作为推进剂后,比冲将有所提高。

Abstract:

Arcjet propulsion system offers significant propellant savings for satellite because of its relatively high specific impulse compare with traditional chemical propulsion system. To satisfy the requirement of orbit control for LEO satellite and NSSK for GEO satellite, an engineering model of 1kW hydrazine arcjet system is under developing in BICE (Beijing Institute of Control Engineering). The development program includes design and fabricating of a hydrazine arcjet system and its 500 hours endurance test, which will be complete in December, 2009. According to mission analysis results, performance of arcjet system is specified, which includes thrust of 75~150mN and specific impulse of 4.5~5.5N·s/g.On the basis of previous research in BICE, the 1kW arcjet thruster has been designed and fabricated. The first round of design, fabricate and performance test has completed. For the security consideration, simulated hydrazine (mixture of Nitrogen and ammonia) is used as propellant in currently experiments. Some important parameter, such as specific impulse, thrust and efficiency of the thrust, are obtained. With the mass flow rate of 18mg/s to 30mg/s, thrust is in the range of 100mN to 150mN and specific impulse is around 5N·s/g. And the performance is expected to be improved in the next round experiment with anhydrous hydrazine as propellant, for its heat producing in decomposition reaction. 