火箭推进

针对一种微小卫星使用的超导磁悬浮储能及姿控飞轮结构,采用H方法(以磁场强度H作为独立变量)对飞轮的永磁结构转子与超导结构定子进行了耦合磁场分布和悬浮力的仿真分析。通过对比3种尺寸相同但构型不同的永磁结构,确定采用悬浮力最大且敏感元件区域磁场强度最小的Halbach构型作为飞轮转子的永磁结构。通过调整Halbach构型的中心磁体宽度和高度,并保持永磁结构的总体尺寸不变,以悬浮力最大为优化目标,兼顾敏感元件区域的磁场强度,获得了结构最优的Halbach构型永磁结构,计算悬浮力大小约1 084 N。

According to the requirement of micro satellite, a type of structure of HTS maglev energy storage and attitude control flywheel was proposed.Based the H-method, the magnetic field and levitation force of permanent magnetic(PM)structure coupled with HTS stator were analyzed through simulation calculation.Comparing three types of permanent magnetic structure, the Halbach configuration was adopted for its largest levitation force and lowest magnetic field in the sensitive component zone.By adjusting height and width of central magnet in Halbach configuration and keeping the size of the PM zone, aiming at largest levitation force and limiting external magnetic field, the optimal PM structure with levitation force about 1 084 N was obtained.

引言
1 计算模型
2 计算方法
3 计算结果与分析
4 结论

图1 超导磁悬浮储能及姿控飞轮地面试验装置示意图<br/>Fig.1 Schematic of ground test device for the HTS maglev energy storage and attitude control flywheel

图1 超导磁悬浮储能及姿控飞轮地面试验装置示意图
Fig.1 Schematic of ground test device for the HTS maglev energy storage and attitude control flywheel

图2 计算模型和网格划分<br/>Fig.2 Calculation model and mesh

图2 计算模型和网格划分
Fig.2 Calculation model and mesh

表1 永磁结构和超导阵列环的设计尺寸<br/>Tab.1 Design size of permanent magnetic structure and HTS array loop

表1 永磁结构和超导阵列环的设计尺寸
Tab.1 Design size of permanent magnetic structure and HTS array loop

图3 YBCO块材(Φ30 mm×H20 mm)与钕铁硼永磁体(Φ30×H30 mm)悬浮力试验与仿真结果<br/>Fig.3 Experimental and simulational levitation forces of the YBCO(Φ30 mm×H20 mm)and NdFeB permanent magnet(Φ30 mm×H30 mm)

图3 YBCO块材(Φ30 mm×H20 mm)与钕铁硼永磁体(Φ30×H30 mm)悬浮力试验与仿真结果
Fig.3 Experimental and simulational levitation forces of the YBCO(Φ30 mm×H20 mm)and NdFeB permanent magnet(Φ30 mm×H30 mm)

图4 3种相对于超导体轴向对称的永磁结构示意图<br/>Fig.4 Three permanent magnetic structures relative to HTS axial symmetry

图4 3种相对于超导体轴向对称的永磁结构示意图
Fig.4 Three permanent magnetic structures relative to HTS axial symmetry

图5 3种永磁构型耦合超导阵列环的磁场计算云图<br/>Fig.5 Calculated magnetic fields for the three permanent magnetic structures coupled with HTS array loop

图5 3种永磁构型耦合超导阵列环的磁场计算云图
Fig.5 Calculated magnetic fields for the three permanent magnetic structures coupled with HTS array loop

图6 构型Ⅲ Halbach永磁构型中超导阵列环内部的磁场密度和电流密度分布图<br/>Fig.6 Magnetic density distribution and electric current density distribution of the HTS array loop for Type-III Halbach permanent magnetic configuration

图6 构型Ⅲ Halbach永磁构型中超导阵列环内部的磁场密度和电流密度分布图
Fig.6 Magnetic density distribution and electric current density distribution of the HTS array loop for Type-III Halbach permanent magnetic configuration

图7 3种永磁构型的悬浮力计算结果和永磁结构上方20mm处的磁场分布<br/>Fig.7 Calculated levitation forces and magnetic fields(20mm above permanent magnetic structure) of the three configurations

图7 3种永磁构型的悬浮力计算结果和永磁结构上方20mm处的磁场分布
Fig.7 Calculated levitation forces and magnetic fields(20mm above permanent magnetic structure) of the three configurations

图8 永磁结构悬浮力及其上方20mm处的磁场峰值与中心磁体宽度的关系<br/>Fig.8 Relationship between the levitation force and magnetic peak(20 mm above permanent magnetic structure)with the center's width

图8 永磁结构悬浮力及其上方20mm处的磁场峰值与中心磁体宽度的关系
Fig.8 Relationship between the levitation force and magnetic peak(20 mm above permanent magnetic structure)with the center's width

图9 永磁结构悬浮力及其上方20 mm处的磁场峰值与中心磁体高度的关系<br/>Fig.9 Relationship between the levitation force and magnetic peak(20 mm above permanent magnetic structure)with the center's height

图9 永磁结构悬浮力及其上方20 mm处的磁场峰值与中心磁体高度的关系
Fig.9 Relationship between the levitation force and magnetic peak(20 mm above permanent magnetic structure)with the center's height

[1] 苏瑞丰,张科科,宋海伟.甚小型卫星发展综述[J].航天器工程,2013(6):104-111.
[2] 吴汉基,蒋远大,张志远,等.微小卫星的在轨推进技术[J].火箭推进,2006,32(3):40-43.
[3] PECZALSKI A, ELGERSMA M, DAN Q, et al.Micro-wheels for attitude control and energy storage in small satellites[J].IEEE Proceedings,2001,38(5):2483-2492.
[4] JANSEN R, DEVER T.G2 flywheel module design:AIAA2004-5603[R].[S.L.]:AIAA,2004.
[5] 韩邦成,房建成,吴一辉.单轴飞轮储能/姿态控制系统的仿真研究[J].系统仿真学报,2006,18(9):2511-2515.
[6] 白越,吴一辉,韩邦成.飞轮单轴姿态控制及储能系统[J].光学精密工程,2008,16(8):1446-1451.
[7] 程千兵,武俊峰,吴一辉,等.超导磁悬浮微飞轮系统设计与测试[J].低温物理学报,2011(6):422-426.
[8] 贾英宏,徐世杰.利用飞轮的航天器姿态跟踪与能量存储(英文)[J].航空学报,2005,18(1):1-7.
[9] 冯香枝.卫星储能/姿控两用飞轮在能量回馈状态下的姿态控制问题研究[D].上海:东华大学,2005.
[10] LEE E.A HTS/magnet flywheels with dual function of energy storage and attitude control[C]//International Energy Conversion Engineering Conference.Pasadena: California:[s.n.],2003.
[11] HONG Z, CAMPBELL A M, COOMBS T A.Numerical solution of critical state in superconductivity by finite element software[J].Superconductor Science & Technology, 2006, 19(12): 1246-1252.

备注

引言

1 计算模型

2 计算方法

3 计算结果与分析

4 结论

期刊信息