Yay, another Soyuz launch, another one out of the Amazon jungle (actually a bit north of that, but it's still pretty close to reality :lol

! Today's launch will see the second of two Pleiades high-resolution Earth observation satellites owned by CNES (the French space agency) lifted into space by the fourth Soyuz rocket launching from French Guiana. The 1 tonne satellite will join Pleiades-1A (
launched just less than a year ago from exactly the same place) 700 km above the Earth, providing imagery services to five different European space agencies (France, Austria, Belgium, Spain and Sweden) and three countries' defense ministries (France, Italy and Spain), as well as commercial customers.
Launch location:
Kourou ELS 5°18'18"N 52°50'02"W
Launch dates and times:
[table="head"]{colsp=7}Launch times (updated)
Time Zone|
Australia - Sydney/AEST|
Moscow / MSK/ UTC+4|
CET UTC+1|
Universal / UTC|
Washington / EST|
French Guiana
Launch time:|13:02:50|06:02:50|03:02:50|02:02:50|21:02:50|23:02:50
on:|
Dec. 2, 2012|
Dec. 2, 2012|
Dec. 2, 2012|
Dec. 2, 2012|
Dec. 1, 2012|
Dec. 1, 2012
{colsp=7}[highlight][eventTimer]2012-12-02 02:02:50?before|after;%dd% Days %hh% Hours %mm% Minutes %ss% Seconds %c%[/eventTimer] Pleiades 1B Launch[/highlight][/table]
Live Coverage
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Pleiades 1B Earth observation satellite
Pleiades 1B is the second of two dual-use, very-high-resolution satellites in the Pleiades Earth observation system. Both are built by Astrium Satellites in Toulouse for French space agency CNES. The satellite will joined its twin brother Pleiades 1A launched about a year ago.
[table="head"]Characteristics|Values
Orbit|sun-synchronous, 695 km altitude
Weight at launch|970 kg
Electrical power|1,500 W
Design life|5 years
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Two Pleiades satellites are supposed to work together with SPOT-5 optical observation satellite.
The SPOT-5 optical Earth observation satellite combines the advantages of a relatively wide imaging swath and sub-3-metre resolution. Today, new and evolving civil and military challenges facing Europe call for different levels of image resolution.
The Pleiades optical satellites will provide imagery covering a smaller area but with a resolution of 0.70 m.
Together, SPOT and Pleiades will offer a broader range of complementary data better able to meet the diverse requirements of civil users—for example, cartographers, volcanologists, geophysicists, hydrologists and urban planners—and military users.
The Pleiades optical system is being developed under CNES supervision as part of a joint effort with Italy, alongside the Cosmo-Skymed radar imaging system that is under the responsibility of the Italian space agency (ASI).
This French-Italian cooperation will bring users a richer variety of large and small-area optical and radar imagery than ever before, at high and low resolutions.
The main design drivers for the satellite architecture are the image quality, the agility and the image location accuracy. The image quality drives the instrument size. A high agility requires a very compact design, with a few stiff appendages. As a consequence, the instrument is integrated inside the bus. A high image location accuracy is achieved by minimizing the interface between the instrument and the bus. The star trackers and the gyroscope heads are directly supported by the instrument to avoid any thermal distortion that could be induced by the bus.
The bus structure is build on an hexagonal shape, with three solar arrays at 120 deg, and three star trackers in a quasi tetrahedron configuration, optimizing the attitude determination accuracy. This configuration authorizes accommodation of the instrument focal plane radiator for maximum heat dissipation. An antenna support structure is used to carry the Earth-pointing antennas and for the instrument baffle.
The solar arrays are mounted directly on the bus structure without any drive mechanism to ensure a maximum stability. Their first flexion mode frequency is increased by the use of stiffeners when deployed. Moreover the high compacity and low mass of the satellite (<1000 kg) make it compatible with a large series of low cost small launchers (among them Soyouz and Rockot). The two Pleiades satellites will be launched by Soyouz from Europe's spaceport in Kourou, French Guiana.
[table="head"]{colsp=2}Characteristics
|[table="head"]{colsp=2}
Pleiades 1B
Prime contractor:
|EADS Astrium
Mass:
|1000 kg
Panchromatic resolution:
| 0.7 m at nadir
Multispectral resolution:
| 4 times panchromatic resolution
Swath:
| 20 km at nadir
Orbit:
| Sun-synchronous, quasi circular orbit at 694 km altitude
Acquisition capability:
| up to 450 images/day
Solar generator power:
| 1500 W
Instrument TM link rate:
| 450 Mbits/sec
On-board mass memory:
| 600 Gbits
Lifetime:
| 5 years
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Launch Vehicle:
[table="head"]{colsp=2}Characteristics
|[table="head"]{colsp=2}
Soyuz-2.1a
Prime contractor:
|
- Samara Space Sentre (Energia Holding enterprise)
GRAU Index:
|
Height:
| 51.1 m
Diameter:
| max 10.3 m
Liftoff mass:
| 313 metric tonnes
Payload mass:
| up to 6830 kg (a launch to LEO from Plesetsk)
1st stage (boosters B, V, G, D):
|
- 4 X RD-107 engines
- Propellants (T-1 Kerosene and LOX)
- Thrust/ISP in vacuum - / 320.2 s
- Thrust/ISP at sea level 85.6 tonnes / 263.3 s
2nd stage (core A):
|
- 1 X RD-108 engine
- Propellants (T-1 Kerosene and LOX)
- Thrust/ISP in vacuum 94 tonnes / 320.6 s
- Thrust/ISP at sea level 80.8 tonnes / 257.7 s
3rd stage (block I):
|
- 1 X RD-0110 engine
- Propellants (T-1 Kerosene and LOX)
- Thrust/ISP in vacuum 30.38 tonnes / 326 s
Upper Stage:
|
- GRAU Index: -
- Common Name: Fregat (meaning Frigate)
- Designer & Manufacturer: Lavochkin Association (NPO)
- Dimensions: Length 2.4 m, Diameter (max) 3.350 m
- Empty Mass 930 kg
- Propellants 5250 kg max
- Main Engine: 1 X S5.92
- Thrust in vacuum 2.0 tonnes of force (full power)
- Thrust in vacuum 1.4 tonnes of force (small power)
- ISP 333.2 s
Payload Fairing:
|
- Diameter 3.7 m
- Length 7.7 m
[/table]
[/table]
The launch vehicle's reliability standings (according to
http://www.spacelaunchreport.com/log2012.html#rate):
Code:
================================================================
Vehicle Successes/Tries Realzd Pred Consc. Last Dates
Rate Rate* Succes Fail
================================================================
Soyuz 2-1a/Fregt 10 11# .91 .85 8 5/21/09 2006-
# Does not include one successful suborbital Soyuz 2-1a test
flight performed in 2004.
Ascent profile
Weather Forecast for Sinnamary, French Guiana on November 30, 2012 (11 p.m.)
Overcast. Low of 23C. Breezy. Winds from the East at 10 to 20 km/h.
Time|Temps|Dew Point|Relative Humidity|Precip|Snow|Cloud cover|Pressure|Wind|Weather
11 PM|25°C|23°C|91%|0%|0%|68%|1009 hPa|11 km/h East|
Mostly Cloudy
References
http://www.esa.int
http://www.cnes.fr
http://www.arianespace.com
http://forum.nasaspaceflight.com
http://www.novosti-kosmonavtiki.ru
http://astronautique.actifforum.com
http://www.spacelaunchreport.com
www.russianspacweb.com
http://www.cnes.fr/web/CNES-en/3236-pleiades.php
http://smsc.cnes.fr/PLEIADES/
http://www.defense.gouv.fr/dga/actu...au-domaine-du-renseignement-spatial-militaire
http://www.samspace.ru
http://www.laspace.ru
http://english.wunderground.com/q/zmw:00000.3.81403