火箭推进

射频离子推力器是空间电推进的一种,其推力性能是系统设计的核心问题。为获得推力特性随设计参数的变化规律,采用数值计算方法进行了研究,开展了1 mN射频离子推力器设计计算,对不同放电室尺寸、流量、射频功率、屏栅电压下的推力性能进行了分析并进行了工况优化。结果表明,模型能够正确地描述射频离子推力器性能变化规律,放电室内径25 mm的推力器即可以实现1 mN推力指标,在最优工况下,推力器推力1.176 mN,比冲2 503 s,效率53.13%,满足设计要求。根据该模型研制的推力器样机成功点火,验证了数值模型的有效性,可以利用该模型为射频离子推力器研制工作提供指导。

RF ion thruster(RIT)is a kind of electric propulsion, and the thrust performance is the core issuse of propulsion system design. Numerical calculation method was used to obtain the thrust characteristic with design parameters. The design of a 1 mN RIT was carried out, thrust performance of different discharge chambers, mass flowrates, rf power and screen voltage were analyzed and the working condition was optimized. The results show that the model can correctly describe the performance variation law of RIT, and thrust of the RIT with a discharge chamber of 25 mm inner diameter can reach 1 mN. Under the optimal working condition, thrust 1.176 mN, specific impulse 2 503 s and efficiency 53.13% can be achieved, which meets the design requirements. The thruster prototype developed according to the model was ignited successfully, which fully verified the effectiveness of the numerical model, the numerical model can be used to guide further research.

引言
1 性能计算模型
2 数值计算
3 结论

图1 射频离子推力器示意图<br/>Fig.1 Schematic diagram of RF ion thruster

图1 射频离子推力器示意图
Fig.1 Schematic diagram of RF ion thruster

图2 变压器器模型等效电路<br/>Fig.2 Transformer model equivalent circuit

图2 变压器器模型等效电路
Fig.2 Transformer model equivalent circuit

图3 离子引出示意图<br/>Fig.3 Schematic diagram of ion extraction

图3 离子引出示意图
Fig.3 Schematic diagram of ion extraction

图4 放电过程计算框图<br/>Fig.4 Block diagram for calculation of discharge

图4 放电过程计算框图
Fig.4 Block diagram for calculation of discharge

表1 射频离子推力器性能指标<br/>Tab.1 RIT thrust performance index

表1 射频离子推力器性能指标
Tab.1 RIT thrust performance index

图5 不同放电室内径、不同流量下的推力、比冲<br/>Fig.5 Thrust and specific impulse of different discharge chamber inner diameters and different flowrates

图5 不同放电室内径、不同流量下的推力、比冲
Fig.5 Thrust and specific impulse of different discharge chamber inner diameters and different flowrates

图6 不同放电室长度的推力、比冲<br/>Fig.6 Thrust and specific impulse of different discharge chamber lengths

图6 不同放电室长度的推力、比冲
Fig.6 Thrust and specific impulse of different discharge chamber lengths

图7 不同射频功率下的推力性能<br/>Fig.7 Thrust performance of different RF power

图7 不同射频功率下的推力性能
Fig.7 Thrust performance of different RF power

$图8 不同射频功率下的电离度与电子密度<br/>Fig.8 Ionization fraction and electron density of different RF power$

图8 不同射频功率下的电离度与电子密度
Fig.8 Ionization fraction and electron density of different RF power

图9 不同屏栅电压下的推力性能<br/>Fig.9 Thrust performance of different screen voltage

图9 不同屏栅电压下的推力性能
Fig.9 Thrust performance of different screen voltage

表2 射频离子推力器推力参数<br/>Tab.2 Thrust parameters of RIT

表2 射频离子推力器推力参数
Tab.2 Thrust parameters of RIT

表3 射频离子推力器等离子体参数<br/>Tab.3 Plasma parameters of RIT

表3 射频离子推力器等离子体参数
Tab.3 Plasma parameters of RIT

图10 射频离子推力器样机<br/>Fig.10 Prototype of RF ion thruster

图10 射频离子推力器样机
Fig.10 Prototype of RF ion thruster

图11 推力器放电图片<br/>Fig.11 Discharge picture of thruster

图11 推力器放电图片
Fig.11 Discharge picture of thruster

[1] 胡竟,蒋成保,张天平,等.星载永磁霍尔推力器磁场分实验研究[J/OL].推进技术. https://doi.org/10.13675/j.cnki.tjjs.190332.
[2] 康小录, 杭观荣, 朱智春. 霍尔电推进技术的发展与应用[J]. 火箭推进, 2017, 43(1): 8-17.

备注

引言

1 性能计算模型

2 数值计算

3 结论

期刊信息