LIPS-100电推进高精度宽范围连续可调电源测试验证  

Test and Verification of High-precision Wide-range Continuously Throttled Power Processing and Control Unit for LIPS-100

作　　者：王成飞 杨福全[1] 赵勇 孙明明[1] 张兴民 施凯敏 WANG Chengfei;YANG Fuquan;ZHAO Yong;SUN Mingming;ZHANG Xingmin;SHI Kaimin(Science and Technology on Vacuum Technology and Physics Laboratory,Lanzhou Institute of Physics,Lanzhou 730000,China;Shenzhen Aerospace New Power Technology Ltd,Shenzhen 518000,Guangdong,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,兰州730000 [2]深圳航天新源科技有限公司,广东深圳518000

出　　处：《真空与低温》2022年第1期122-127,共6页Vacuum and Cryogenics

基　　金：民用航天预先研究项目(D010509)。

摘　　要：低地球轨道具有轨道周期短、信号传输延时小等特点,在该轨道开展遥感侦察、地球环境探测、互联网星座部署等具有显著优势。但由于低轨道高度处的大气阻力会对卫星轨道造成摄动,因此须采用推进系统进行阻力补偿,而离子电推进因寿命长、比冲高、参数可调节范围宽等优点成为优选方案。针对地球重力场反演和低轨卫星应用对离子电推进的需求,结合LIPS-100推力器试验结果,研究确定了配套PPCU的关键指标体系、关键电源方案,并对PPCU原理样机的指标符合性和与推力器的匹配性进行了试验验证。结果表明,PPCU关键电源指标——屏栅电压实测输出为1200.76~1201.35 V,稳定度和准确度均优于0.1%,带载能力覆盖1~20.0 mN(对应屏栅电流18.0~367.0 mA)需求;阳极电流调节范围可达0.1000~3.0000 A,分辨率为1.0 mA;励磁电流在0.0150~1.0000 A的范围内,分辨率可达0.50 mA;与推力器联试可实现1~20.0 mN推力调节,分辨率优于15μN。验证了指标体系的正确性和推力调节方案的合理性,可以为阻力补偿用电推进系统的工程应用提供技术支持。Low orbit has the characteristic of short orbital period and small signal transmission delay.It has signifi‐cant advantages for remote imaging,earth environmental detection,and communication constellation.The orbit perturba‐tion of satellite caused by atmosphere drag must be compensated by propulsion system.Ion electric propulsion system has become the preferred solution due to the characteristic of long endurance,high specific impulse,and wide range thrust.Aimed to the earth’s filed model recovery and the low orbit satellite application requirements for ion electric propulsion,combing with the test result of LIPS-100 thruster,the key index decomposition of PPCU is conformed,and the correspon-ding key modules of PPCU is briefly described.Meanwhile performance test activities are applied to thruster and PPCU as the demonstration of prototype product technology.Data analysis result shows that the screen voltage output range of PPCU is 1200.76 to 1201.35 V.The stability and accuracy is better than 0.1%in 1 to 20.0 mN(the range of beam current is 18.0 to 367.0 mA)loading range.Anode current can be adjusted in the range of 0.1000 to 3.0000 A with a resolution of 1.0 mA,the magnet current resolution is better than 0.50 mA in the range of 0.01500 to 1.0000 A.The thrust range reaches 1 to 20.0 mN and thrust resolution is better than 15μN.Meanwhile,the correctness of establishing PPCU index and thrust throttling scheme are verified.The relative technology can be used in the engineering application.

关 键 词：LIPS-100电推进 可调电源 测试验证 

分 类 号：V439.4[航空宇航科学与技术—航空宇航推进理论与工程]