THE VEHICLE THE SATELLITE
Proton History Proton Description Lead designer was Vladimir Chelomei, who designed it Total Height with the intention of creating both a powerful rocket for 58.2 m (191 ft) military payloads and a high-performance ICBM. The program was changed, and the rocket was developed Gross Lift-off exclusively for launching spacecraft. Weight 705,000 kg First named UR-500, but adopted the name (1,554,000 lb) “Proton,” which also was the name of the first Propellant three payloads launched. UDMH and NTO
Proton launched Russian interplanetary mis- Initial Launch sions to the Moon, Venus, Mars, and Hal- 16 July 1965 ley’s Comet. Proton-1 Spacecraft Proton launched the Salyut space sta- Payload Fairings tions, the Mir core segment and both There are multiple payload fairing designs presently Satellite Operator the Zarya (Dawn) and Zvezda (Star) mod- qualified for flight, including ules for today’s International Space Station. Eutelsat Communications standard commercial payload www.eutelsat.com First commercial Proton launch — 9 April 1996. fairings developed specifically to meet the needs of our customers. Satellite Manufacturer First commercial Proton M Breeze M launch Breeze M Upper Stage Thales Alenia Space — 30 December 2002 The Breeze M is powered by one pump-fed www.thalesaleniaspace.com Mission Overview gimbaled main engine that develops thrust of 20 kN (4,500 lbf). It is composed of a central core and Platform an auxilliary propellant tank which is jettisoned in flight Spacebus 4000 following depletion. The Breeze M control system includes an on-board computer, a three-axis gyro stabilized platform, and a Separated Mass navigation system. The quantity of propellant carried is dependent 5470 kg on specific mission requirements and is varied to maximize mission Experience ILS: Achieve Your Mission performance. Satellite Mission Lifetime QUALITY | PERFORMANCE | EXPERIENCE | DEDICATION Proton Booster 15 Years The Proton booster is 4.1 m (13.5 ft) in diameter along its second and third stages, with a first stage diameter of 7.4 m (24.3 ft). Overall height Satellite Mission of the three stages of the Proton booster is 42.3 m (138.8 ft). EUTELSAT 3D will bring resources, reach and flexibility for www.ilslaunch.com high-growth professional video, data, telecom and broadband hird tage T S services at 3° East, an orbital position that sits at the crossroads Powered by one RD-0213 engine, this stage develops thrust of 583 kN of Europe, Africa and Asia. Through a configuration of Ku and (131,000 lbf), and a four-nozzle vernier engine that produces thrust of Ka transponders connected to three footprints, Eutelsat’s new 31 kN (7,000 lbf). Guidance, navigation, and control of the Proton M during satellite will serve customers in Europe, North Africa, the Middle EUTELSAT 3D operation of the first three stages is carried out by a triple redundant closed-loop East and Central Asia. A fourth footprint in the Ku-band will digital avionics system mounted in the Proton’s third stage. serve customers in sub-Saharan Africa. EUTELSAT 3D will be 3rd ILS Proton Launch in 2013 Second Stage located at 3° East until the launch in 2014 of EUTELSAT 3B Of conventional cylindrical design, this stage is powered by three RD-0210 engines that will further extend coverage to South America. It will 80th ILS Proton Launch Overall plus one RD-0211 engine and develops a vacuum thrust of 2.4 MN (540,000 lbf). subsequently continue service at 7° East. 7th Eutelsat Satellite Launched First Stage on Proton The first stage consists of a central tank containing the oxidizer surrounded by six out- board fuel tanks. Each fuel tank also carries one of the six RD-276 engines that provide 9th Thales Alenia Space Satellite first stage power. Total first stage vacuum-rated level thrust is 11.0 MN (2,500,000 lbf). Launched on ILS Proton The Proton and the Breeze M are built by Khrunichev State Research and Production Space Center. THE MISSION
Payload Fairing 3rd Stage/Breeze M 1st Burn = 00:04:39 2nd Burn = 00:17:41 3rd Burn = 00:13:03 4th Burn = 00:04:24 5th Burn = 00:07:48 Spacecraft (PLF) Separation Ignition Shutdown Ignition Shutdown Ignition Shutdown APT Jettison Ignition Shutdown Ignition Shutdown Separation Separation 00:09:42 00:11:16 00:15:55 01:07:33 01:25:14 03:28:34 03:41:37 03:42:27 03:43:54 03:48:18 08:51:50 08:59:38 09:13:00 00:05:47
MISSION DESCRIPTION GROUND TRACK
The Proton M launch vehicle, utilizing a 5-burn Breeze M 7UDQVIHU2UELW mission design, will lift off from Pad 39 at Baikonur Cosmodrome, Kazakhstan, with the EUTELSAT 3D satellite on board. The first three stages of the Proton /LIWRII will use a standard ascent profile to place the orbital unit (Breeze M upper stage and the EUTELSAT 3D satellite) 2nd/3rd Stage into a sub-orbital trajectory. From this point in the 3DUNLQJ2UELW Separation mission, the Breeze M will perform planned mission 00:05:27 maneuvers to advance the orbital unit first to a circular parking orbit, then to an intermediate orbit, followed
by a transfer orbit, and finally to a geosynchronous transfer orbit. Separation of the EUTELSAT 3D satellite /DWLWXGH GHJUHHV is scheduled to occur approximately 9 hours, 13 minutes ,QWHUPHGLDWH2UELW
after liftoff.
st nd 1 /2 Stage /RQJLWXGH GHJUHHV Separation 00:02:00
7UDQVIHU2UELW
+S NP
+D NP L
*HR7UDQVIHU2UELW *72
+S NP
+D NP Maximum Dynamic Pressure L 00:01:02
,QWHUPHGLDWH2UELW /9/LIWRII Command Stage 1 (100% Thrust) +S NP
-00:00:00.9 +D NP L Stage 1 Ignition (40% Thrust) -00:00:01.75 *HRVWDWLRQDU\ Ignition Start Sequence 2UELW *62 -00:00:02.5 3DUNLQJ2UELW
+S NP
+D NP LAUNCH PAD 39 L
ASCENT PROFILE PROTON ON PAD 39 FLIGHT DESIGN