VENµS MISSION STATUS
VENµS users meeting – Jan 2010Pierric FERRIER, CNES
VENµS users meeting – Jan 2010 2
1- Camera status
2- Bus status
3- Ground segment status
4- Launcher status
5- Summary
Content
VENµS users meeting – Jan 2010 3
CEU
DETECTORSASSEMBLY
BEZEL
TUBE
SUNSHIELD
THERMAL CONTROLSHIELD
SMA PMA CORRECTIONLENSES
Camera longitudinal section
1- Camera status
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Tube equipped with both mirrors
1- Camera status
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Correction lens assembly
1- Camera status
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Thermal control shield (external cylinder)
1- Camera status
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Camera status synthesis
~1.4 mm 2.0 mm
8.0 mm 10 mm
Blocking Filter
Narrow-band Filters
1- Camera status
BARR filters= the weakest link of the chain, so far...
•18 months needed to obtain the ITAR approval
•13 months delay in manufacturing due to technical issues (delivery expected in March)
The current schedule shows a camera delivery at end of Aug 2011
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-Mass: 250kg -Power: 800w
-Overall stowed dim: 1.6x1.2 m
-2xSTR - 2 X-band - 1xIHET redunded , 16 Kg Xenon - 4x1N redunded thrusters, 7 Kg hydrazine
2– Bus status
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2– Bus status
VENµS users meeting – Jan 2010 10
2– Bus status
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2– Bus status
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Bus status synthesis
2– Bus status
• Base plate to be delivered this quarter (from RAFAEL to IAI)
• Other parts of the bus are stored and ready for final bus assembly (solar pannel, satellites pannels - 6 of them, and all bus internal subsystems)
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SMIGSIsraeli Ground Control Station
GCS
Israeli Technological Mission
Ground CenterTMC
IHET Telemetry
ProgrammingMessages
Catalogue&
Products
VENµSProducts Distribution
DownloadMessages
& Image TM
S band
X band
VENµS Image Qualityunit
VENµS scientific mission programing & Image Processing
unit
Browsing
& Products by network
KIRUNAX Band Receiving
Station
Scientific mission FRANCE
Satellite command & control and technological mission ISRAEL
3– Ground segment status
Ready end of 2010 Ready end of
2010
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4– Launcher status
The foreseen launcher for Venµs is PSLV so far.
Unfortunately this scenario faces 2 issues • at the INDIAN government level• as Venµs would be the co-passenger, the risk exist to be injected in a non optimal orbit (i.e. 666 km – 3days instead of 720 km -2 days)
•Nevertheless, other scenarios exist, the main one being a launch with PLEIADES 2 on SOYOUZ
•Current engineering practice calls for a final launcher selection 2 years ahead of the foreseen launch date. In other words the launcher will be selected in 2010.
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Mission timeline
last quarter
2009 2011
CAMERA
MISSION GROUND SEGMENT
IHET
SATELLITE
GROUND CONTROL SEGMENT
2012 2015
mid year
MISSION
……
5- Summary
2010