Proton-M Launch Overview:

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 of the three stages of the Proton booster is 42.3 m (138.8 ft).

The first stage consists of a central tank containing the oxidizer surrounded by six outboard fuel tanks. Each fuel tank also carries one of the six RD-276 engines that provide first stage power. Total first stage vacuum-rated level thrust is 11.0 MN (2,500,000 lbf).

Of conventional cylindrical design, the second stage is powered by three RD-0210 engines plus one RD-0211 engine and develops a vacuum thrust of 2.4 MN (540,000 lbf).

Powered by one RD-0213 engine, the third stage develops thrust of 583 kN (131,000 lbf), and a four-nozzle vernier engine that produces thrust of 31 kN (7,000 lbf). Guidance, navigation, and control of the Proton M during operation of the first three stages is carried out by a triple redundant closed-loop digital avionics system mounted in the Proton’s third stage.

The Breeze-M upper stage is the Phase III variant, a recent upgrade which utilizes two new high-pressure tanks (80 liters) to replace six smaller tanks, along with the relocation of command instruments towards the centre – in order to mitigate shock loads when the additional propellant tank is being jettisoned.

The Proton M launch vehicle, utilizing a 5-burn Breeze M mission design, will lift off from Pad 39 at Baikonur Cosmodrome, Kazakhstan, with the Telstar 14R/Estrela do Sul satellite on board. The first three stages of the Proton will use a standard ascent profile to place the orbital unit (Breeze M upper stage and the satellite) into a sub-orbital trajectory.

From this point in the mission, the Breeze M will perform planned mission 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 satellite is scheduled to occur approximately 9 hours, 13 minutes after liftoff.

Telstar 14R/Estrela do Sul 2 is a commercial communications satellite built by Space Systems/Loral for Telesat.

The satellite will utilize 46 high powered Ku-band transponders (58 36-MHz transponder equivalents) over five coverage beams consisting of: Brazil, the Continental United States (including the Gulf of Mexico and northern Caribbean), the Southern Cone of South America, the Andean region (including Central America and southern Caribbean), and the North and Mid-Atlantic Ocean.

Following its launch, Telstar 14R/Estrela do Sul 2 will be located at 63 degrees west longitude where it will replace and augment the communications capability currently supplied by Telesat’s Telstar 14/ Estrela do Sul. It is expected to be in service for 15 years.

The spacecraft has the following “Target Orbit at Separation”: Apogee: 35,786 km (22,236 miles), Perigee:  8,850 km (5,499 miles), Inclination: 13.8 degrees.

Friday’s launch will be the first of 2011, and the second in the latest series of Return To Flight missions after the December 5 failure of the Russian Federal mission which was utilizing a Proton M Block DM-03 vehicle, resulting in the loss of three GLONASS-M navigation satellites.

Overall, the launch is the seventh Telesat Satellite Launched on ILS Proton,the 17th Space Systems/Loral Satellite, the 65th ILS Proton Launch Overall and the 364th Proton mission since 1965.

Related posts:

1. ILS Proton M launches with ASTRA IM for long trip to orbit International Launch Services (ILS) have launched a Russian Proton M launch vehicle...
2. ILS launches Ciel-2 for Canada via Proton-M The last ILS mission of 2008 has launched from the...
3. ILS Proton-M launches with AsiaSat 5 International Launch Services (ILS) have launched the AsiaSat 5 telecommunications...

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 of the three stages of the Proton booster is 42.3 m (138.8 ft).

The first stage consists of a central tank containing the oxidizer surrounded by six outboard fuel tanks. Each fuel tank also carries one of the six RD-276 engines that provide first stage power. Total first stage vacuum-rated level thrust is 11.0 MN (2,500,000 lbf).

Of conventional cylindrical design, the second stage is powered by three RD-0210 engines plus one RD-0211 engine and develops a vacuum thrust of 2.4 MN (540,000 lbf).

Powered by one RD-0213 engine, the third stage develops thrust of 583 kN (131,000 lbf), and a four-nozzle vernier engine that produces thrust of 31 kN (7,000 lbf). Guidance, navigation, and control of the Proton M during operation of the first three stages is carried out by a triple redundant closed-loop digital avionics system mounted in the Proton’s third stage.

The Breeze M control system includes an on-board computer, a three-axis gyro stabilized platform, and a navigation system. The quantity of propellant carried is dependent on specific mission requirements and is varied to maximize mission performance.

Related posts:

1. ILS Proton M launches with ASTRA IM for long trip to orbit International Launch Services (ILS) have launched a Russian Proton M launch vehicle...
2. ILS launches Ciel-2 for Canada via Proton-M The last ILS mission of 2008 has launched from the...
3. ILS Proton-M launches with Telstar 14R International Launch Services (ILS) are in action on Friday, as...

The 8K82KM Proton-M will use a standard ascent trajectory to place the Breeze M fourth stage and the Ciel-2 satellite into a suborbital trajectory. From there the Breeze M will place itself and the spacecraft into a circular parking orbit.

From this orbit the Breeze M will make four more burns and the satellite will be injected into a geostationary transfer orbit. Target orbit at separation, that is schedule to occur at approximately L+9 hours, 12 minutes, is apogee 35,603 km (22,123 miles), perigee 5,597 km (3,478 miles) and inclination 19.5 degrees.

The Ciel-2 satellite is based on the Thales Alenia Space Spacebus 4000 C4 and has a separated spacecraft mass of approximately 5,561 kg (12,260 lbs). The satellite will be used to provide Advanced Broadcast Satellite Service satellite delivering high-definition and other TV services throughout North America.

Anchor customer is DISH Network Corp. From its orbital position at 129 degrees West longitude, the high-powered Ku-band spacecraft will deliver a variety of communications services throughout Canada and the larger North American market.

Built by the Khrunichev State Research and Production Center, 8K82KM Proton-M is the largest Russian launch vehicle in operational service. The rocket launches all Russian geostationary and interplanetary missions under Khrunichev, establishing it as the principal workhorse of the Russian space program.

The Proton booster is 4.1 m (13.5 ft) in diameter along its second and third stages, with a first stage diameter of 7.3 m (24.0 ft). Overall height of the three stages of the Proton booster is 42.3 m (138.8 ft).

The first stage consists of a central tank containing the oxidizer surrounded by six outboard fuel tanks. Each fuel tank also carries one of the six RD-275 engines that provide first stage power. Total first stage sea-level thrust is approximately 9.6 MN (2,158,000 lbf) with a vacuum-rated level thrust of 10.5 MN (2,360,000 lbf).

The second stage is powered by three RD-0210 engines plus one RD-0211 engine and develops a vacuum thrust of 2.3 MN (517,000 lbf).

The third stage is powered by one RD-0213 engine, this stage develops thrust of 583 kN (131,000 lbf), and a four-nozzle vernier engine that produces thrust of 31 kN (7,000 lbf).

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 central core and a jettisonable additional propellant tank. Inert mass of the stage at lift-off is approximately 2,370 kg (5,225 lb).

The quantity of propellant carried is dependent on specific mission requirements and is varied to maximize mission performance. The Breeze M is controlled by a closed loop, triple-redundant guidance system.

This was the sixth ILS mission of the year, the 15th ILS Proton launch for SES AMERICON, 3rd Spacebus 4000 model to launch on Proton and the 49th ILS mission on Proton.

Related posts:

1. ILS Proton M launches with ASTRA IM for long trip to orbit International Launch Services (ILS) have launched a Russian Proton M launch vehicle...
2. ILS Proton-M launches with SIRIUS FM-5 International Launch Services (ILS) have launched the SIRIUS FM-5 communication...
3. ILS Proton-M successfully launches with QuetzSat-1 International Launch Services (ILS) have launched their Proton-M rocket on...

Click HERE FOR LAUNCH VIDEO AND LIVE COVERAGE

The first three stages of the Proton will use a standard ascent trajectory to place the Breeze-M fourth stage and the satellite into a suborbital trajectory from which the Breeze M Upper Stage will then place itself and the spacecraft into a low Earth circular parking orbit.

The Proton booster is 4.1 m (13.5 ft) in diameter along its second and third stages, with a first stage diameter of 7.3 m (24.0 ft). Overall height of the three stages of the Proton booster is 42.3 m (138.8 ft).

The first stage consists of a central tank containing the oxidizer surrounded by six outboard fuel tanks. Each fuel tank also carries one of the six RD-275 engines that provide first stage power. Total first stage sea-level thrust is approximately 9.6 MN (2,158,000 lbf) with a vacuum-rated level thrust of 10.5 MN (2,360,000 lbf).

The second stage is powered by three RD-0210 engines plus one RD-0211 engine and develops a vacuum thrust of 2.3 MN (517,000 lbf).

The third stage is powered by one RD-0213 engine, this stage develops thrust of 583 kN (131,000 lbf), and a four-nozzle vernier engine that produces thrust of 31 kN (7,000 lbf).

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 central core and a jettisonable additional propellant tank. Inert mass of the stage at lift-off is approximately 2,370 kg (5,225 lb).

The quantity of propellant carried is dependent on specific mission requirements and is varied to maximize mission performance. The Breeze M is controlled by a closed loop, triple-redundant guidance system.

The Proton M launch vehicle, utilizing a 5-burn Breeze M mission design to place the orbital unit (Breeze M upper stage and the ASTRA 1M satellite) into a sub-orbital trajectory.

From this point in the mission, the Breeze M will perform planned mission 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 ASTRA 1M satellite is scheduled to occur approximately 9 hours, 12 minutes into the mission.

ASTRA 1M will be positioned at 19.2 degrees East longitude, where it will provide pan-European coverage. It will primarily deliver direct-to-home services, including high-definition television.

The launch of the spacecraft will allow SES ASTRA to move capacity to its increasingly important orbital position 23.5 degrees East. ASTRA 1M will carry 36 transponders covering the FSS and BSS frequency bands.

Related posts:

1. ILS launches Ciel-2 for Canada via Proton-M The last ILS mission of 2008 has launched from the...
2. ILS Proton-M launches with AsiaSat 5 International Launch Services (ILS) have launched the AsiaSat 5 telecommunications...
3. ILS Proton-M launches AsiaSat 7 to its GEO destination International Launch Services (ILS) have launched their Proton-M rocket on...