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(Fiches Galaxy 14 ARIANESPACE AND STARSEM TO ORBIT GALAXY 14 To meet the requirements of its customer, PanAmSat, Arianespace and Starsem have decided to orbit the Galaxy 14 satellite on a Soyuz launcher. The launch of Galaxy 14, originally planned on an Ariane launcher, will be performed by the Soyuz vehicle from the Baikonur Cosmodrome in Kazakhstan. This switch illustrates the launcher family policy developed by Arianespace and Starsem to best res- pond to their clients’ needs. Since the launch of PanAmSat’s first satellite on Ariane 4’s maiden mission in June 1988, Arianespace performed 18 launches for this global provider of satellite communications services and the Number 1 operator in the United States. The Galaxy 14 mission will mark the 13th flight performed by Starsem, which has been responsible for Soyuz commercialization and operation on the international marketplace since 1996. Starsem’s shareholders are Arianespace, EADS, the Russian Federal Space Agency and the Samara Space Center. The satellite, to be co-located with Galaxy 12 at 125 degrees west longitude, will enable PanAmSat to have two in-orbit spares for its U.S. fleet, giving the Company the highest fleet redundancy in the FSS industry. The powerful all C-band spacecraft is designed to deliver digital video programming, high-definition television (HDTV), VOD and IPTV service throughout the continental U.S. Built and custom-designed for PanAmSat by Orbital Sciences Corporation, Galaxy 14 is a 1790-kilogram Star 2 Bus model satel- lite with 24, 36-MHz C-band transponders. Galaxy 14 is the second in a series of three C-band satellites being constructed by Orbital Sciences for PanAmSat. The satellite will put out more than dou- ble the power of its predecessors, ready to play a pivotal role in the complete digital delivery of programming in the U.S. that is man- dated by the FCC. Visit us on www.arianespace.com www.starsem.com 1 MISSION DESCRIPTION The launch of Galaxy 14 will be performed from the Baikonur Cosmodrome, Launch Pad #6. The Galaxy 14 launch period is fixed from July 15th, 2005 to August 15th, 2005 (local time). The launch is pos- sible at any day inside the above launch period. The launch time for any launch date within the launch period slightly varies (around 1-12 sec slip each day). For example, for an August 5, 2005 (UTC) launch attempt, the launch time will be 11:29 p.m. UTC: 5:29 a.m. Baikonur local time on August 6, 2005 3:29 a.m. Moscow time on August 6, 2005 1:29 a.m. Paris time on August 6, 2005 7:29 p.m. EST on August 5, 2005 The launch window : ±1sec MISSION MAIN PHASES ➩ Lift-off ➩ End of vertical path, start of pitch turn ➩ Transition of the lateral boosters to the intermediate thrust level ➩ I-st stage control thrusters cut-off ➩ I-st stage engine cut-off and stage separation ➩ Fairing jettison ➩ III-rd stage ignition ➩ II-nd stage cut-off ➩ II-nd stage separation ➩ Separation of the III-rd stage tail section ➩ III-rd stage cut-off command ➩ Nose Module separation from the third stage ➩ Fregat upper stage’s pre-burn acceleration start ➩ Fregat first burn start (transfer to the circular parking orbit) ➩ Fregat first burn cut-off (transfer to the circular parking orbit) ➩ Coast phase on the parking orbit ➩ Fregat second pre-burn acceleration start ➩ Fregat second burn start (transfer to the super GTO separation orbit) ➩ Fregat second burn cut-off (transfer to the super GTO separation orbit) ➩ Fregat attitude maneuvers (orientation and three-axis stabilization) before S/C separation ➩ Fregat spin-up maneuver ➩ S/C separation The Russian ground-tracking network will be used to track the LV and to receive telemetry during the three- stage vehicle ascent phase and during Fregat flight leading to injection and separation of Galaxy 14. Visit us on www.arianespace.com www.starsem.com 2 MISSION DURATION: The nominal mission duration (from lift-off to spacecraft separation) is ~ 1 hour 37 minutes 19 seconds. SEPARATION ORBIT – ORBITAL PARAMETERS REQUIREMENTS: Osculated orbital parameters in the Greenwich system frozen at lift-off Time of osculation - S/C separation moment Unit Value Accuracy (3Σ) Perigee radius km 6,669 ± 10 Apogee radius km 72,401 ± 400 Inclination to equator deg 49.3 ± 0.067 Longitude of ascending node deg 9.56 ± 0.18 Argument of perigee deg 0.0 ± 0.17 Visit us on www.arianespace.com www.starsem.com 3 SOYUZ LAUNCH VEHICLE The Soyuz launch vehicle family has provided reliable and efficient launch services since the birth of the space program. Vehicles in this family, which launched both the first satellite and first man into space, have been credited with more than 1690 launches to this date. Today, this vehicle is used for manned and unmanned flights to the International Space Station and commercial launches managed by Starsem. The Soyuz configuration introduced in 1966 has been the workhorse of the Soviet/Russian space program. As the only manned launch vehicle in Russia and the former Soviet Union, the Soyuz benefits from exac- ting standards in both reliability and robustness. The addition of the restartable Ikar upper stage to the three-stage Soyuz in 1999 allowed Starsem to launch 24 satellites of the Globalstar constellation in 6 launches. Following this success, Starsem introduced the flexible, restartable Fregat upper stage with significantly more propellant capacity than the Ikar, thus opening up a full range of missions (LEO, SSO, MEO, GTO, GEO and escape). The inaugural flight of the Soyuz 2-1a launch vehicle performed on November 8, 2004 from the Plessetsk Cosmodrome represents a major step in the launch vehi- cle evolution program. This modernized version of Soyuz implements a digital control system providing additional mission flexibility and will enable control of the launch vehicle with the 4m ST fairing. It represents a necessary milestone towards the next generation evolved Soyuz 2-1b Fairing launcher as the latest step in a cooperative European/Russian evolution program. The decision of the European Space Agency to introduce the Fregat Soyuz launch capability at the Guiana Space Center (CSG) is a major Upper Stage step in widening the range of accessible missions. With the introduction of the Soyuz at CSG, this famed Russian launch vehicle becomes an integral part of the European launcher fleet, together with the heavy-lift Ariane 5 and the lightweight Vega. To be offered exclusively by Arianespace to the commercial market, the Stage III Soyuz at CSG is Europe’s reference medium-class launch vehicle for governmental and commercial missions. The Samara Space Center continues to mass-produce the Soyuz in Samara, Russia. As a result of continued demand from the Russian government, Stage II International Space Station activity, and Starsem’s commercial orders, the Soyuz is in uninterrupted production at an average rate of 10 to 15 launch vehicles per year with a capability to rapidly scale up to accommodate user’s needs. In fact, peak production of the Soyuz in the early 1980’s reached 60 vehicles per year. The Soyuz is a reliable, efficient, and cost-effective solution for a full range of missions from LEO to Mars. In its unequalled flight history, the Soyuz has already performed almost every mission profile, including orbiting satellites for telecommunications, Earth observation, weather monitoring, scientific missions and manned flights. It is a highly res- Stage I ponsive and flexible launch vehicle. Boosters The Soyuz currently offered by Starsem is a four-stage launch vehicle. The vehicles each consist of four boosters (first stage), a central core (second stage), a third stage, and the restartable Fregat upper stage (fourth stage). Each vehicle also includes a payload adapter/dispenser and fairing. Visit us on www.arianespace.com www.starsem.com 4 THE BOOSTERS (FIRST STAGE) The four boosters are assembled around the central core and are tapered cylinders with the oxidizer tank in the tapered portion and the kerosene tank in the cylindrical portion. The booster’s RD-107A engines are powered by liquid oxygen and kerosene, the same propellants which are used on each of the lower three stages. Each engine has four combustion chambers and nozzles. Three-axis flight control is carried out by aerofins (one per boos- ter) and movable vernier thrusters (two per booster). Following liftoff, the boosters burn for 118 seconds and are then discarded. The separation time is determined by comparing the velocity with a predefined value. Thrust is transferred through a ball joint located at the top of the cone-shaped structure of the booster, which is attached to the central core by two rear struts. CENTRAL CORE (SECOND STAGE) The central core is similar in construction to the four boosters, with a hammer-head shape to accommodate the boosters. A stiffening ring is located at the interface between the boosters and the core. This stage has a RD-108A engine with four combustion chambers and nozzles and four vernier thrusters. The verniers are used for three-axis flight control once the boosters have separated. The core stage nominally burns for 286 seconds. Ignition of the central core and boosters occurs at an intermediate level of thrust on the launch pad 20 seconds before liftoff in order to monitor engine health parameters before the engines are throttled up and the vehicle leaves the pad. Visit us on www.arianespace.com www.starsem.com 5 THIRD STAGE The third stage is linked to the central core by a lattice- work structure. Ignition of the third stage’s main engi- ne occurs approximately 2 seconds before shutdown of the central core. The third stage engine’s thrust directly separates the stage from the central core.
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