离子与霍尔电推进性能和质量的工程数据模型  

Engineering data models of performance and mass for ion and Hall electric propulsions

作　　者：张天平[1,2] 张雪儿 李璇 ZHANG Tianping;ZHANG Xueer;LI Xuan(Science and Technology on Vacuum Technology and Physics Laboratory,Lanzhou Institute of Physics,Lanzhou 730000,China;Key Laboratory of Space Electric Propulsion Technology of Gansu Province,Lanzhou 730000,China)

机构地区：[1]兰州空间技术物理研究所真空技术与物理重点实验室,甘肃兰州730000 [2]甘肃省空间电推进技术重点实验室,甘肃兰州730000

出　　处：《火箭推进》2022年第1期1-13,共13页Journal of Rocket Propulsion

基　　金：国家重点基础研究发展计划(613193)。

摘　　要：为了提供航天工程任务设计时优选离子或霍尔电推进的通用对比分析方法,基于工程数据建立了包括推力器、电源处理单元、推力器选择单元、控制单元、推进剂气瓶、调压单元、流率单元、推力器支架、电缆、管路等产品的电推进的性能和质量经验模型。在此基础上通过推导建立了电推进系统干质量通用模型,模型变量参数包括推力器功率、推力器数量和推进剂量等。应用电推进模型对两种电推进的性能和工程应用效益进行了对比分析,结果表明存在针对具体任务优选电推进类型的必要性。In order to provide a general comparative analysis method for selecting ion or Hall electric propulsion(EP)in the design of aerospace missions,empirical models of performance and mass were established for the EP components based on engineering data.The EP components include thrusters,power processing units,thruster selection units,control units,propellant tanks,pressure regulating units,flow rate units,thruster support mechanisms,cables,and pipelines.Based on these component models,an empirical model of dry mass for the EP system was established.The parameters for this system model include thruster power,the number of thrusters,and propellant mass.The performances and benefits of ion and Hall EP were compared using the system model.The results show the necessity of selecting the EP type with respect to a specific mission.

关 键 词：性能模型 质量模型 离子电推进 霍尔电推进 工程数据 

分 类 号：V439[航空宇航科学与技术—航空宇航推进理论与工程]