Sirius 4 launch coverage | |
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| Site administrator Join Date: 26-07-2003 Location: Scottish Borders
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My System: Sky UK family pack. FTA analogue & digital satellite from 5 fixed dishes (4.6E/5E/13E/16E/19E/23E/28E) Pace MSS100, Echostar IP3000VA (with dragon cam), Coship CDVB 2300A, Fortecstar Lifetime Ultra, Technomate TM-1000D, Dreambox 7020S, 2250kb ![]() The last noble sat warrior to fly the olden flag of Analogue |
Payload: SIRIUS 4, A2100 AX platform Separated mass: 4,385 kg (9,667 lbs) Launch Vehicle: Proton M/Breeze M Weight at liftoff: 691,272 kg (1.5 million lbs) including payload Height: 56.2 m (184 ft) Launch Time: 04:39 Nov. 18 Baikonur; 23:39 Nov. 17 CET; 22:39 Nov. 17 GMT; 17:39; Nov. 17 EST Launch Site: Baikonur Cosmodrome, Kazakhstan Launch Pad 39 End User: SES SIRIUS, Solna, Sweden Satellite Manufacturer: Lockheed Martin Commercial Space Systems,Newtown, PA Launch Vehicle Manufacturer: Khrunichev State Research and Production Space Center, Moscow Launch Services Provider: International Launch Services, McLean, Va. Satellite Use: Multi-mission satellite that will provide a wide range of telecommunications services, providing coverage over Europe, Africa and the Baltic/Nordic region. Satellite Statistics: 52 active Ku-band transponders 2 active Ka-band transponders Anticipated service life of 15 years Mission Profile: The Proton launch vehicle will use a 4-burn Breeze M mission design to inject the satellite into a geosynchronous transfer orbit. The first three stages of the Proton will use a standard ascent trajectory to place the Breeze M fourth stage, with the satellite, into a suborbital trajectory, from which the Breeze M will place itself and the spacecraft into a circular parking orbit of 173 km (107.5 miles) inclined at 51.5 degrees. Once the upper stage and SIRIUS 4 are in the parking orbit, the unit will then be propelled into its transfer orbit by a series of additional burns of the Breeze M. Following separation from the Breeze M, the spacecraft will perform a series of liquid apogee burns to raise perigee, lower inclination, and circularize the orbit at the geostationary altitude of 35,786 km (22,236 miles). Target Orbit at Separation: Apogee: 35,786 km (22,236 miles); Perigee: 7,030 km (4,368 miles); Inclination: 17.3 degrees Spacecraft Separation: Approximately 9 hours, 13 minutes after liftoff Coverage will be carried on Sirius 2 5E 12265H 27500 3/4. The test card is already running on the tp :
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| | #2 | ||
| Regular Member Join Date: 25-04-2005 Location: Austria
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My System: 1,25 Fibostop Jäger Smr 1224 Dual Axsis Echostar Dvr 7000 Monterey 140 Tagra 2,20 M Fullsize Dish Echostar 2,40m Mesch for cband! | very good,we must wait ,very long,for this launch,now lets see,how strong ,this special spotbeam would be,thor 5 ,will be also launched,on februry 8 i think sirius 4 ,has also 3 stearable beams,one for central europe,the other for the middle east,and the last,for scandinavian nordic region! that,could means,that very big antennas,are needed,to catch all beams ![]() | ||
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