基于挠性梁结构的电推进器推力测量方法研究  

Thrust measurement methods for electric propulsion based on flexible beam structure

作　　者：王洛麒 郑金星 刘海洋 李飞[3] 孟东东 陆玉东 杜宜凡 唐卓尧 吴涛[1,2] 史佳明[2] WANG Luoqi;ZHENG Jinxing;LIU Haiyang;LI Fei;MENG Dongdong;LU Yudong;DU Yifan;TANG Zhuoyao;WU Tao;SHI Jiaming(University of Science and Technology of China,Hefei 230026,China;Hefei Institutes of Physical Science,Chinese Academy of Sciences,Hefei 230031,China;State Key Laboratory of High Temperature Gas Dynamics,Institute of Mechanics,Chinese Academy of Sciences,Beijing 100190,China;School of Mechanical Engineering and Energy Engineering,Beijing University of Technology,Beijing 100124,China)

机构地区：[1]中国科学技术大学,合肥230026 [2]中国科学院合肥物质科学研究院,合肥230031 [3]中国科学院力学研究所高温气体动力学国家重点实验室,北京100190 [4]北京工业大学机械与能源工程学院,北京100124

出　　处：《核技术》2024年第5期91-101,共11页Nuclear Techniques

摘　　要：电推进系统在空间任务中相比于传统化学燃料推进工作寿命更长、燃料消耗更低,在近年来备受关注。但基于可控核聚变思想研发的高功率霍尔效应电推进器,其推力很难测量,原因在于这些电推进器需要在高温环境下电离推进剂,所以工作时会产生高温等离子体羽流,导致传统推力测试方法无法准确测量其推力。推进器推力的准确测量直接关系到航天器姿态以及轨道保持的控制精度,因此必须在地面测试中准确地测量推力。本文设计并搭建了一套基于挠性梁结构的推力测量平台,可以在高温环境下测量电推进器产生的推力。实验结果表明,以可变比冲磁等离子体火箭为例,在中心磁场强度0.2 T、质量流率为20 mg·s-1的工况下,实时测得电推进器推力为266.5 mN,证明了测量平台的可行性,为后续电推进器推力测量实验提供参考。[Background]Electric propulsion systems,compared to traditional chemical propulsion,offer longer operational lifespans and lower fuel consumption in space missions,garnering significant attention in recent years.However,for high-power Hall effect electric thrusters developed based on controlled fusion concepts,measuring thrust proves challenging due to the high-temperature environments required for ionizing propellants in electric thruster,resulting in the generation of hot plasma plumes during operation.As a result,traditional thrust measurement methods are unable to accurately measure the thrust.[Purpose]This study aims to accurately measure thrust during ground testing of electric thrusters for precise control of the spacecraft's attitude and orbit maintenance.[Methods]Firstly,a thrust measurement platform based on flexible beam structure was designed and implemented with capability of measuring the thrust generated by electric thrusters in high-temperature.Simultaneously,a calibration system was built to verify the stability and repeatability of the thrust measurement results.Then,simulation analysis was conducted on the structural mechanics and thermal coupling field of the thrust measurement system under different operating conditions.Finally,the variable specific impulse magnetoplasma rocket(VASIMR)was taken for experimental thrust measurement of its electric propulsion system.[Results]The experimental results of VASIMR indicate the thrust is 266.5 mN measured in real time at the central magnetic field intensity of 0.2 T with a mass flow rate of 20 mg∙s^(-1).[Conclusions]The thrust measurement platform based on the bending beam structure can meet the measurement requirements of VASIMR,providing valuable references for subsequent experiments.

关 键 词：电推进器 可控核聚变 等离子体 挠性梁 推力测量 

分 类 号：TH823[机械工程—仪器科学与技术]