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 56.2 m (184 ft) powerful rocket for both military payloads and 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. 705,000 kg (1,554,000 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 payload Proton launched the Salyut space sta- fairing designs presently qualified for flight, including tions, the Mir core segment and both the standard commercial payload Zarya (Dawn) and Zvezda (Star) modules fairings developed specifically to for today’s International Space Station. meet the needs of our customers. First commercial Proton launch — Br e e z e M Up p e r St a g e 9 April 1996, ASTRA 1F. The Breeze M is powered by one pump-fed gimbaled main engine that develops thrust of 20 kN (4,500 lbf). It is composed of a central core and an auxilliary propellant tank which is jettisoned in flight following depletion. The Breeze M control system includes an on-board computer, a three-axis gyro stabilized platform, and a Sa t e l l i t e Op e r a t o r navigation system. The quantity of propellant carried is dependent Telesat on specific mission requirements and is varied to maximize mission www.telesat.com performance. Nimiq 5 Pr o t o n Boos t e r Sa t e l l i t e Manufacturer is sion v e r v i e w The Proton booster is 4.1 m (13.5 ft) in diameter along its second and Space Systems/Loral M O third stages, with a first stage diameter of 7.4 m (24.3 ft). Overall height www.ssloral.com of the three stages of the Proton booster is 42.3 m (138.8 ft). 7th Proton Launch of 2009/ Pl a t f o r m 5th ILS Proton Launch of 2009 Th i r d St a g e Powered by one RD-0213 engine, this stage develops thrust of 583 kN 1300 Spacecraft Bus (131,000 lbf), and a four-nozzle vernier engine that produces thrust of 54th Proton Launch for ILS 31 kN (7,000 lbf). Guidance, navigation, and control of the Proton M during Se p a r a t e d Ma ss operation of the first three stages is carried out by a triple redundant closed-loop 4745 kg 6th Telesat satellite launch with digital avionics system mounted in the Proton’s third stage. ILS Proton Sa t e l l i t e De s i g n Li f e Se c o n d St a g e Of conventional cylindrical design, this stage is powered by three RD-0210 engines 15 Years 13th Space Systems/Loral Satellite plus one RD-0211 engine and develops a vacuum thrust of 2.4 MN (540,000 lbf). Launched on a Proton Sa t e l l i t e Mi ss i o n Fi r s t St a g e Nimiq 5 is a commercial communications satellite built by The first stage consists of a central tank containing the oxidizer surrounded by six out- Space Systems/Loral. The satellite has a 32 transponder board fuel tanks. Each fuel tank also carries one of the six RD-276 engines that provide Ku-Band payload with capability to switch capacity between first stage power. Total first stage vacuum-rated level thrust is 11.0 MN (2,500,000 lbf). Canada and the Continental United States coverage areas. The satellite will be located at 72.7° West longitude. This satellite The Proton and the Breeze M are built by Khrunichev State Research and Production will be dedicated to the provision of direct-to-home services as Space Center. part of Telesat’s DTH fleet THE MISSION
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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 Nimiq 5 satellite
on board. The first three stages of the Proton will /LIWRII use a standard ascent profile to place the Ascent Unit (payload fairing, Breeze M upper stage and the Nimiq 5 QGUG6WDJH satellite) into a sub-orbital trajectory. From this point in 6HSDUDWLRQ the mission, the Breeze M will perform planned mission 3DUNLQJ2UELW 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 geo-transfer orbit. Separation of the Nimiq 5 satellite is scheduled to occur /DWLWXGH GHJUHHV approximately 9 hours, 15 minutes after liftoff. ,QWHUPHGLDWH2UELW
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