THE VEHICLE THE SATELLITE
www.ilslaunch.com Pr o t o n Hi s t o r y Pr o t o n Description Lead designer was Vladimir Chelomei, who To t a l He i g h t designed it with the intention of creating a 58.2 m (191 ft) powerful rocket for both military payloads and as a high-performance ICBM. The program was Gr oss Li f t o f f changed, and the rocket was developed We i g h t exclusively for launching spacecraft. 702,000 kg (1,547,000 lb)
First named UR-500, but adopted the name Pr o p e l l a n t
“Proton,” which also was the name of the UDMH and N2O4 first three payloads launched. In i t i a l La u n c h 16 July 1965 Proton launched Russian interplanetary Proton-1 Spacecraft missions to the Moon, Venus, Mars, and Halley’s Comet. Pa y l o a d Fa i r i n g s There are multiple pay- Proton launched the Salyut space sta- load fairing designs pres- ently qualified for flight, tions, the Mir core segment and both the including standard commer- Zarya (Dawn) and Zvezda (Star) modules cial payload fairings developed for today’s International Space Station. specifically to meet the needs of our Western customers. First commercial Proton launch — 9 April 1996, ASTRA 1F. Br e e z e M Up p e r St a g e The Breeze M is powered by one pump- fed gimbaled main engine that develops thrust of
19.6 kN (4,400 lbf). The Breeze M is composed of a September 2008 central core and a jettisonable additional propellant tank. Inert mass of the stage at liftoff is approximately Sa t e l l i t e Op e r a t o r 2,370 kg (5,225 lb). The quantity of propellant carried is Telesat dependent on specific mission requirements and is varied to Nimiq 4 www.telesat.com maximize mission performance. The Breeze M is controlled by a closed loop, triple-redundant guidance system. Sa t e l l i t e Manufacturer Mis sion Ov e r v i e w EADS Astrium Pr o t o n Boos t e r The Proton booster is 4.1 m (13.5 ft) in diameter along its second www.astrium.eads.net 4th ILS launch of 2008 and third stages, with a first stage diameter of 7.3 m (24.0 ft). Overall Pl a t f o r m height of the three stages of the Proton booster is 42.3 m (138.8 ft). 47th Proton launch for ILS Eurostar E3000 Th i r d St a g e 10th Eurostar satellite launched Powered by one RD-0213 engine, this stage develops thrust of 583 kN Se p a r a t e d Ma ss (131,000 lbf), and a four-nozzle vernier engine that produces thrust of 4,850 kg on Proton 31 kN (7,000 lbf). Sa t e l l i t e De s i g n Li f e 5th Telesat satellite launched with Se c o n d St a g e 15+ Years Of conventional cylindrical design, this stage is powered by three RD-0210 ILS Proton engines plus one RD-0211 engine and develops a vacuum thrust of 2.3 MN Mi ss i o n (517,000 lbf). Nimiq 4 is a commercial communications satellite built by Fi r s t St a g e EADS Astrium. The satellite has two payloads for Canadian The first stage consists of a central tank containing the oxidizer surrounded by six broadcast services. The main payload has 32 Ku-band channels outboard fuel tanks. Each fuel tank also carries one of the six RD-275 engines that providing specialty television and foreign language program- provide first stage power. Total first stage sea-level thrust is approximately 9.6 MN ming. The second, smaller payload has 8 Ka-band channels (2,158,000 lbf) with a vacuum-rated level thrust of 10.5 MN (2,360,000 lbf). spread over six beams covering Canada for advanced services such as high-definition television. The satellite will be located The Proton and the Breeze M are built by Khrunichev State Research and Production at 82° West longitude. Nimiq satellites are dedicated to the Space Center. provision of direct-to-home services for Bell TV. THE MISSION
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MISSION DESCRIPTION GROUND TRACK
The Proton Breeze M launch vehicle, utilizing a standard 5-burn mission profile, will lift off from 7UDQVIHU2UELW Launch Pad 39 (within Launch Complex 200) at the Baikonur Cosmodrome, Kazakhstan, with the Nimiq 4 satellite on board. The first three stages of the Proton /LIWRII will use a standard ascent profile to place the Ascent QGUG6WDJH Unit (Breeze M upper stage and the Nimiq 4 satellite) 6HSDUDWLRQ into a sub-orbital trajectory. From this point in the mission, the Breeze M will perform planned mission maneuvers to advance the Ascent Unit first to a circular 3DUNLQJ2UELW parking orbit, then to an intermediate orbit, followed ,QWHUPHGLDWH2UELW by a transfer orbit, and finally to geo-transfer orbit. /DWLWXGH GHJUHHV Separation of the Nimiq 4 satellite is scheduled to occur approximately 9 hours, 11 minutes after liftoff.
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