AMC-14 MO final.qxp 2/29/2008 1:15 PM Page 1 THE VEHICLE THE SATELLITE PROTON HISTORY PROTON www.ilslaunch.com Lead designer was Vladimir Chelomei, DESCRIPTION who designed it with the intention of creating a powerful rocket for both TOTAL HEIGHT military payloads and as a high- 56.2 m (184 ft) performance ICBM. The program GROSS LIFTOFF was changed, and the rocket WEIGHT was developed exclusively for 691,272 kg launching spacecraft. (1,523,565 lbm) First named UR-500, but PROPELLANT UDMH and N O adopted the name 2 4 “Proton,” which also was INITIAL LAUNCH the name of the first July 16, 1965 three payloads Proton-1 Spacecraft launched. PAYLOAD FAIRINGS Proton launched Russian There are multiple payload fair- ing designs presently qualified for interplanetary missions to flight, including standard commer- the Moon, Venus, Mars, and cial payload fairings developed specif- Halley’s Comet. ically to meet the needs of our Western customers. Proton launched the Salyut space stations, the Mir BREEZE M UPPER STAGE SATELLITE OPERATOR core segment and both The Breeze M is powered by one pump-fed gim- SES AMERICOM baled main engine that develops thrust of 19.6 kN the Zarya and Zvezda www.ses-americom.com (4,400 lbf). The Breeze M is composed of a central core modules for today’s and a jettisonable additional propellant tank. Inert mass of the SATELLITE MANUFACTURER International Space stage at liftoff is approximately 2,370 kg (5,225 lbm). The quan- Lockheed Martin Commercial Space Systems Station. tity of propellant carried is dependent on specific mission require- www.lmcommercialspace.com ments and is varied to maximize mission performance. The Breeze M March 2008 First commercial is controlled by a closed loop, triple-redundant guidance system. PLATFORM Proton launch— A2100 PROTON BOOSTER April 9, 1996, The Proton booster is 4.1 m (13.5 ft) in diameter along its second and SEPARATED MASS ASTRA 1F. third stages, with a first stage diameter of 7.4 m (24.3 ft). Overall height of 4140 kg the three stages of the Proton booster is 42.3 m (138.8 ft). AMC-14 DESIGN LIFE Third Stage 15 years Powered by one RD-0213 engine, this stage develops thrust of 583 kN (131,000 MISSION OVERVIEW lbf), and a four-nozzle vernier engine that produces thrust of 31 kN (6,900 lbf). MISSION The AMC-14 satellite was developed and built for SES AMERI- 7th launch of a satellite for Second Stage COM, the leading supplier of satellite services in the USA. SES SES AMERICOM on a Proton Of conventional cylindrical design, this stage is powered by three RD-0210 engines AMERICOM, recognized as a major innovator of advanced plus one RD-0211 engine and develops a vacuum thrust of 2.3 MN (524,000 lbf). satellite communication services, operates a fleet of 15 space- craft in orbital positions predominantly providing a wide vari- 11th launch of a Lockheed Martin A2100 First Stage ety of services throughout the Americas. satellite model on a 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-275 engines that pro- AMC-14 is an advanced, high-powered Broadcast Satellite 2nd ILS launch of 2008 vide first stage power. Total first stage sea-level thrust is approximately 9.5 MN Service (BSS) satellite with 32 24-MHz Ku-band transponders, (2,140,000 lbf) with a vacuum-rated level thrust of 10.5 MN (2,360,000 lbf). and will operate at 61.5 degrees West longitude. As the third satellite dedicated to AMERICOM2HOME®, the spacecraft has 45th launch for ILS joint venture The Proton and the Breeze M are built by Khrunichev State Research and Production Space Center. been optimized to provide direct-to-home video services. The designated mission of AMC-14 is to expand the bandwidth resources needed to increase the number of high-definition and other services offered by the EchoStar Corporation. AMC-14 MO final.qxp 2/29/2008 1:16 PM Page 5 THE MISSION Payload Fairing 3rd Stage/Breeze M 1st Burn = 00:07:35 2nd Burn = 00:34:26 3rd Burn = 00:06:10 Spacecraft (PLF) Separation Ignition Shutdown Ignition Shutdown APT Jettison Ignition Shutdown Separation Separation 00:09:46 00:11:19 00:18:54 00:58:41 01:33:07 01:34:28 06:36:30 06:42:40 06:55:50 00:05:48 MISSION DESCRIPTION GROUND TRACK The Proton M launch vehicle, utilizing a 3-burn Breeze M 80 mission design, will lift off from Pad 39 at Baikonur Transfer Orbit Cosmodrome, Kazakhstan, with the AMC-14 satellite 60 on board. The first three stages of the Proton will use a standard ascent trajectory to place the Breeze M 40 Liftoff fourth stage and the AMC-14 satellite into a suborbital 2nd/3rd Stage trajectory from which the Breeze M will then place 20 Separation itself and the spacecraft into a low Earth circular park- 00:05:33 ing orbit. Once AMC-14 is in the parking orbit, it will 0 be injected into a geostationary-transfer orbit follow- Parking Orbit ing two additional burns of the Breeze M. Separation -20 will occur approximately 6 hours, 55 minutes and 50 seconds after liftoff. -40 -60 -80 1st/2nd Stage -180 -135 -90 -45 045 90 135 180 Separation 00:02:03 Transfer Orbit Hp = 890 km Ha = 35745 km SC Target Orbit i = 49.1° Hp = 6257 km APT Post-Separation Orbit Ha = 35786 km i = 19.7° e Maximum Dynamic Pressure 00:01:05 e Command Stage 1 (100% Thrust) -00:00:00.9 Parking Orbit Hcir = 173 km e Stage 1 Ignition (40% Thrust) i = 51.5° -00:00:01.6 e Ignition Start Sequence -00:00:02.5 Upper Stage Withdrawal Orbit LAUNCH PAD 39 Geosynchronous Orbit (GSO) ASCENT PROFILE PROTON M ON PAD 39 ORBIT INSERTION.