the application of a fluxgate magnetometer for mars space environment exploration in china · 2016....
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The application of a fluxgate magnetometer for Mars space
environment exploration in CHINA
Jindong Wang, Bin Zhou, Xin Zhang, Hua Zhao
Center for Space Science and Applied Research, Chinese Academy of Science, Beijing, China
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contents
Magnetic field of Martian Space Environment
Introduction of the fluxgate magnetometer (FGM)
Calibration & EM tests
Spacecraft residual magnetic field
Summary
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Orbit & Martian space environment
orbit:elliptical, periapsis (nearest point) 800km,apoapsis (furthest point) 76,000km, period 72hours.
“YH-1” orbiter will pass through bow shock, magnetosheath, magnetic pileup boundary, magnetic pileup region, and magnetic tail.
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Martian magnetic field Mars lacks an appreciable global magnetic field (<0.5 nT equatorial
surface field) Based on the Mars Global Surveyor (MGS), magnetic field at 800km
altitude is dominated by external fields arising from the interaction of the solar wind with Mars.
This external field is highly variable, ranging from a few nT to as much as (rarely) ∼100 nT.
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Design parameters Measurement range: ±256nT Resolution: 0.01nT Noise: <0.01nT/√Hz@1Hz Operating temperature range:-120~+70 ℃ Mass: <2.5kg
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Block diagram of FGM
FMG sensor A
FGM sensor B
PCB of FGM ACPU
ofspacecraft
PCB of FGM B
On the Boom Electronic box of FGM
F1/2
ClockDrive
16bitA/D
8bitD/A
DPUWith
DigitalFilter
3-Axis Sensor Analogue Fluxgate Magnetometer Electronics Digital Part
Feed Back
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Operating modes Default mode
Acquires vector magnetic field measurements up to 10 samples/s in orbit;
Measurement range: -256~+256nT, resolution 0.01nT
Compensation mode Only used in ground testing; Measurement range: +/-65000nT
Self-calibration mode Every time starting FGM Self-calibration every 18 hours
0 2 4 6 8 10 12 14 16 18 20-200
-150
-100
-50
0
50
100
150
200
时间(s)
磁场
强度
(
nT)
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Instrument design Integrate 3 fluxgate sensors
into a small casing;
Can be divided into two independent instruments.
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Simulation of structure stress
20℃15g acceleration
X Y Z
Max stress (MPa) 3.17 1.77 9.26
Displacement (μm) 6.21 0.353 12.5
-180℃15g acceleration
X Y Z
Max stress (MPa) 8.18 3.79 15.2
Displacement (μm) 12.6 2.16 21.3
75℃15g acceleration
X Y Z
Max stress (MPa) 7.62 2.28 13.2
Displacement (μm) 9.34 1.15 18.4
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Performance Measurement range
-256nT~+256nT -65000nT~+65000nT
Resolution 0.01nT
Noise <0.01nT/√Hz@1Hz
Sample rate 10 Hz
Mass 2.5kg
Power consumption 6W YH-1 FGM, flight model
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Calibration & Test
Linearity and resolution Noise Stability Thermal stability
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Linearity and resolution Laboratory for calibration:
National Institute of Metrology, Beijing, China; 3-axis criterion coil system; magnetic clean and thermostatic
test room.
Linearity(%)
Range(nT)
Sensitivity(nT)
X 0.041 >±256 0.098
Y 0.031 >±256 0.097
Z 0.116 >±256 0.099
-400 -300 -200 -100 0 100 200 300 400-3
-2
-1
0
1
2
3x 10
4
磁场强度 (nT)
磁强计读数
Linearity, sensitivity and resolution of FGM ALinearity of FGM A, axis X
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Calibration for FGM sensor——National Institute of Metrology, Beijing, China
FGMsensor
Turntable
Coilsystem
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Linearity, sensitivity and resolution of FGM, flight mode
Axis Sensitivity(1/nT) Resolution (nT/1) Linearity(%)
A
X 101.58 0.0098 0.041
Y 103.32 0.0097 0.031
Z 103.80 0.0098 0.116
B
X 103.06 0.0097 0.052
Y 104.19 0.0096 0.083
Z 101.23 0.0099 0.045
-300 -200 -100 0 100 200 300
-30000
-20000
-10000
0
10000
20000
30000
正样A机 Y轴线性度及偏差
磁场强度(nT)
磁场
测量
值
-240 -210 -180 -150 -120 120 150 180 210 240-50
0
50
磁场强度(nT)
线性
偏差
参考点
拟合点
拟合直线
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Noise
0 1 2 3 4 50
0.5
1
1.5
2
2.5
3
3.5
4
4.5
5
频率(H z)
功率
谱密
度(
1/√Hz)
正 样件A机功率谱密度
X 方向
Y方向
Z方向
Laboratory for noise test Ming-Tombs Geomagnetic Station, Institute of Geology and Geophysics,
China Academy of Sciences, Beijing, China Space Research Institute, Austrian Academy of Sciences, Graz, Austria
PSD noise of FGM sensor, CAS, Beijng & IWF, Graz
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Stability
Stability of FGM, flight mode
FGM Axis stability(nT/24hours)
A
X 0.035
Y 0.116
Z 0.096
B
X 0.057
Y 0.105
Z 0.110
Laboratory for stability test CSSAR, Beijing, China Space Research Institute,
Austrian Academy of Sciences, Graz, Austria
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Thermal stability
Sensitivity VS Temperature
Temperature(℃) -80 -60 -40 64
Axis Y, FGM A flight mode
Measurement 13276 13253 13238 13279Error 0.11% 0.06% 0.18% 0.13%
During eclipses, temperature of FGM sensors could drop to about -210℃;
Temperature drift must be calibrated so that we could fix the data measured in orbit.
-100 -80 -60 -40 -20 0 20 40 60 80-15000
-10000
-5000
0
5000
10000
15000
温度 ( ℃ )磁
场测
量值
X方向测量数据
X方向拟合曲线
Y方向测量数据
Y方向拟合曲线
Z方向测量数据
Z方向拟合曲线
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Thermal test devices
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Block diagram of thermal test equipment
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Spacecraft residual magnetic field In case of limited boom length, the spacecraft residual magnetic field
could be simplified as a dipole; Use gradient magnetic data by two sensors, we can eliminate the
influence of residual magnetic field of the spacecraft; Multi-pole magnetic field can be ignored because it weaken by 5-th
power of distance.
Sensor A
LBLA
33
33
BA
BBAAM LL
BLBLB−−
=
Sensor B
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Current of Solar Wing Current on the solar wing
generates electromagnetic interference;
An analyses model was established in order to remove these interference;
Typical case: W1=W3=0.2A W2=0.1A,
Result: 1.97nT at Sensor A 8.38nT at Sensor B
SensorA
SensorB
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Summary Time and Space Resolution
Time resolution: 0.1s Space resolution: better than 0.3 km
The speed of YH-1 spacecraft is about 3km/s at perimartian (nearest point ), so in most case space resolution will be better than 0.3 km.
Performance
Hz/ HznT /008.0
Performances Design specifications Measured indicators
Range -256nT~256nT -270~270nTResolution 0.01nT 0.0099nTPSD noise 0.01nT @1Hz @1HzRMS noise <0.1nT <0.03nTAccuracy <0.125nT <0.09nT
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Thank you