brief introduction of yinghuo-1 micro-satellite for mars environment exploration
DESCRIPTION
Brief introduction of YINGHUO-1 Micro-satellite for Mars environment exploration. J. Wu, G. Zhu, H. Zhao, C. Wang, L. Lei, Y. Sun, W. Guo and S. Huang Center for Space Science and Applied Research, CAS Shanghai Astronomical Observatory, CAS. Yinghuo-1 (YH-1) mission. - PowerPoint PPT PresentationTRANSCRIPT
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Brief introduction of YINGHUO-1 Micro-satellite for Mars environment
exploration
J. Wu, G. Zhu, H. Zhao, C. Wang, L. Lei, Y. Sun, W. Guo and S. HuangCenter for Space Science and Applied Research, CAS
Shanghai Astronomical Observatory, CAS
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Yinghuo (YH) -- Name of the mission
China has long history of astronomical observation of
Mars, the very first observation record was made during
475-221BC.
The mission is named after the ancient Chinese name
for Mars “YingHuo”
Ying --- Red
Huo --- unpredictable
Yinghuo-1 (YH-1) mission
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Fly opportunity with Phobos-Grunt
China and Russia signed the agreement in March
2007. The cooperation includes:
1) Piggy back launch of a Chinese Mars exploration
satellite YH-1 (~115kg)
2) Russia will provide ground TTC support to YH-1
3) Phobos-Grunt and YH-1 will carry out joint
measurements of Martian space environment
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Fly opportunity with Phobos-Grunt
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Overview of the spacecraftYH-1– 3 axis stabilized platform, with deployable solar panel– Mass: 110kg– Power: 90W (average) 180W (peak)– payload mass: 11 kg– payload power: 20 W – nominal life time: 1 year
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Overview of the spacecraftYH-1 orbit parameters:
apogee ~80,000 km perigee 800 km inclination 36
800km 80000kmOrbit of Phobos
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Scientific objectives of YH-1
This orbit will well cover the areas of solar wind, bow shock, magnetosheath, magnetic pileup region, and tail and plasma sheet.
Nagy et al.,2004
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Scientific Objectives
1 To study details of Martian space magnetosphere, ionosphere and the plasma distribution and their variations;
2 To study Martian ion escape mechanism, its implication for water loss.
3 To have moderate surveys of Martian surface topography, sandstorm and its influence on ionosphere;
4 To explore the Martian gravity field near equator by analyzing orbital data of YH-1.
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Instruments Goals
Flux gate magnetometer Space magnetic field measurement
Plasm
a pack
age
Electron analyzer Measuring plasma distribution : energy, mass, velocity
two ion analyzers
Two frequency occultation receiver
Ionosphere occultation
Photo-imager Sandstorm and Mars surface imaging
Scientific payloads of YH-1
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Magnetometer• Flux-gate magnetometer,
measures 3 components of magnetic field.
• 2 sensors– double redundant
– gradiometer to eliminate S/C remnance
Sensor A
Sensor B
Solar panel
YH-1 spacecraft
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Parameter Specifications Dynamic range 256nT
Noise 0.01 nT/√Hz@ 1Hz Resolution 0.01 nT
(RMS in 10 Hz bandwidth) Mass
2 sensors Electronics
2800g 500g (+cable & connector) 2300g
Size Sensor Electronics
102.2×58×50 (mm) 270×210×58 (mm)
Power 6.0 W
Magnetometer
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Plasma package• two identical ion analyzers• one electron analyzer• electronics
Plasma Package
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Plasma package• Ion analyzer
– Electrostatic analyzer + TOF scheme,
to resolve ion mass/direction/energy
• Specifications– Field of view: 360160, 8 angular sectors in polar
direction
– Energy range: 20eV-15keV
– Energy resolution: 7%, 96 bins
– Mass resolution: 1, 2, 4, 8, 16, >32 amu
• 2 identical ion sensors simultaneous measurements – Better angular coverage and resolving ability
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Plasma Package• Electron analyzer
– Electrostatic analyzer
– Electron direction/energy spectrum
• Specifications– Field of view: 9120 8 azimuth angular sectors
– Energy range: 20eV-15keV
– Energy resolution: 15%, 32 bins
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Occultation Receiver– Sensitivity: ≤-145 dBW;– Measuring accuracy of carrier phases: 1/100
cycle(0.02m);– Sampling rate: 10Hz;– Antenna polarization: linear polarization;– Operating frequencies: 833MHz, 416.5MHz
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• Receive signals at two frequencies from Phobos mission,
• Ionosphere Occultation between YH-1 and Phobos
• Focused on sub-solar and midnight ionosphere, never tapped by previous occultation due to limit of Sun-Earth-Mars geometry.
Occultation Receiver
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Optical Imager CMOS Imaging Sensor
Specifications
Wide FOV cameraNarrow FOV
camera
Pixels ≥ 4 million ≥ 4 million
SNR ≥30dB ≥30dB
Power < 3W < 3W
Weight 1.3±0.1kg 1.3±0.1kg
Resolution global images@ 10,000km
≤0.5Km at Perigee
≤ 0.3Km at Perigee
SDRAM 10 full resolution image
5 full resolution image
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Besides independent observation of the Martian environment, joint operations with Phobos mission are also planned:
1. Two-point measurements of the Mars space environment
2. S/C to S/S radio occultation measurements
3. Data archiving and exchange
Joint Operations
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1. Two-point measurements of the Martian space environment
Joint Operations
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Joint Operations
2. S/C to S/C radio occultation measurements
• Before/after FGSC landed on Phobos
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Start time (UTCG) Off time ( UTCG)
duration
backup
1 2010 10.10 17:53 :55.81 2010 10.10 18:04:21.23 11min
2 2010 10.13 17:24:41.59 2010 10.13 17:40:36.29 16min
3 2010 10.16 16:56:04.51 2010 10.16 17:16:16.68 20min
4 2010 10.19 16:27:46.32 2010 10.19 16:51:40.91 24min
5 2010 10.22 15:59:39.01 2010 10.22 16:26:56.70 27min
6 2010 10.25 15:31:39.53 2010 10.25 15:35:37.82 4min
7 2010 10.25 15:58:09.98 2010 10.25 16:02:6.84 4min
8 2010 10.28 15:03:45.99 2010 10.28 15:07:23.06 4min
9 2010 10.28 15:33:36.76 2010 10.28 15:37:12.91 4min
10 2010 10.31 15:12:58.21 2010 10.31 15:15:27.38 3min
11 2010 11.21 12:15:22.00 2010 11.21 12:17:54.69 2.5min Eclipse
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YH-1 and Phobos-Grunt are going to make
a series scientific break through in the area of
Mars space environment exploration.
We should get fully prepared for these
exciting events with good plans of joint
operation.
Summary
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Thank You!Thank You!
IEEE IEEE SpectrumSpectrum