SPACE LAUNCH SYSTEMS
Atlas V
_The Atlas launch vehicle family evolved from successful Atlas intercontinental ballistic missile (ICBM). It is suitable for launch payloads into low earth orbits, geosynchronous transfer orbit (GTO) and geosynchronous orbit.
The Atlas V launch vehicle takes Lockheed-Martin expertise gained with Atlas and Titan programs. It can lift greater payloads (19,114-lb/8670 kg to GTO) than its predecessors (Atlas II and Atlas III). It uses the single-stage RD-180 engine and the new solid rocket booster known as the Common Core Booster.
In its more than two dozen launches, starting with its maiden launch in August 2002, Atlas V has had a near-perfect success rate, giving it one of the highest success rates of all active launch systems. The sole failure of the Atlas V still was able to bring its payload into LEO.
The Atlas V launch vehicle takes Lockheed-Martin expertise gained with Atlas and Titan programs. It can lift greater payloads (19,114-lb/8670 kg to GTO) than its predecessors (Atlas II and Atlas III). It uses the single-stage RD-180 engine and the new solid rocket booster known as the Common Core Booster.
In its more than two dozen launches, starting with its maiden launch in August 2002, Atlas V has had a near-perfect success rate, giving it one of the highest success rates of all active launch systems. The sole failure of the Atlas V still was able to bring its payload into LEO.
Delta IV (family)
_The Delta IV launch vehicles have been designed to launch virtually any medium or heavy-sized commercial or military payload into space. The launch vehicle comprises five different models tailored to meet a wide range of payload and launch profiles requirements (4 models intended for medium and 1 for heavyweight payloads). The Delta IV along with Lockheed-Martin Atlas V were selected by the US Air Force for the Evolved Expendable Launch Vehicle (EELV) program.
The launch vehicle propulsion system consists of the RS-68 motor for the first stage and the RL10B-2 introduced by the Delta III for the second stage. In addition, ATK developed the GEM 60 boosters to be added according to launch needs.
The Delta IV can carry a 50,800 lb (23,040 kg) payload to a low earth orbit (LEO), or a 28,950 lb (13,130 kg) payload to GTO. The Delta IV launch system has failed only once in its carrier, giving it a success rate far above 90%.
The launch vehicle propulsion system consists of the RS-68 motor for the first stage and the RL10B-2 introduced by the Delta III for the second stage. In addition, ATK developed the GEM 60 boosters to be added according to launch needs.
The Delta IV can carry a 50,800 lb (23,040 kg) payload to a low earth orbit (LEO), or a 28,950 lb (13,130 kg) payload to GTO. The Delta IV launch system has failed only once in its carrier, giving it a success rate far above 90%.
Falcon (family)
_The Falcon space launch system family has been designed by SpaceX to provide breakthrough advances in reliability, cost, flight environment and time to launch. This privately-developed liquid fuel rocket family includes Falcon 1, Falcon 9 and Falcon 9 Heavy rocket designed to place a wide range of payloads into orbit for both civil and military customers.
The Falcon 1 rocket was introduced in September 2008 and consists of a two-stage layout, a liquid oxygen powered by SpaceX Merlin 1C engine and a rocket grade kerosene powered by SpaceX Kestrel engine. It is intended to carry payloads of 1,500-lb into low Earth orbits being mostly reusable launch system. The Falcon 1e is a larger version with increased fairing volume and higher liftoff mass and max liftoff thrust available starting in 2010. Falcon 1e is able to place a 1,010 kg payload into a circular Low Earth Orbit (LEO) at 185 km of altitude.
The Falcon 9 rocket was first launched on June 4, 2010. It is intended to carry a wide variety to payloads to Low Earth Orbits (LEO) and Geosynchronous Transfer Orbits (GTO). The Falcon 9 rocket is able to place a 10,450 kg payload into a circular LE orbit or a 4,680 kg payload into a GTO orbit.
The Falcon 9 Heavy is a heavy lift launch vehicle capable of lifting payloads of 32,000 kg into Low Earth Orbits (LEO) or 19,500 kg into Geosynchronous Transfer Orbits (GTO).
The Falcon 1 rocket was introduced in September 2008 and consists of a two-stage layout, a liquid oxygen powered by SpaceX Merlin 1C engine and a rocket grade kerosene powered by SpaceX Kestrel engine. It is intended to carry payloads of 1,500-lb into low Earth orbits being mostly reusable launch system. The Falcon 1e is a larger version with increased fairing volume and higher liftoff mass and max liftoff thrust available starting in 2010. Falcon 1e is able to place a 1,010 kg payload into a circular Low Earth Orbit (LEO) at 185 km of altitude.
The Falcon 9 rocket was first launched on June 4, 2010. It is intended to carry a wide variety to payloads to Low Earth Orbits (LEO) and Geosynchronous Transfer Orbits (GTO). The Falcon 9 rocket is able to place a 10,450 kg payload into a circular LE orbit or a 4,680 kg payload into a GTO orbit.
The Falcon 9 Heavy is a heavy lift launch vehicle capable of lifting payloads of 32,000 kg into Low Earth Orbits (LEO) or 19,500 kg into Geosynchronous Transfer Orbits (GTO).
Minotaur (family)
_The Minotaur I is a launch system that couples components from retired Minuteman II Intercontinental Ballistic Missiles (ICBM) with upper stage components of commercial Pegasus rocket. This approach ensures Minotaur remains a low-cost launch vehicle which has demonstrated a 100 percent rate of success. Minotaur I are available only for United States government payloads.
Two variants of the Minotaur are currently in service. The Minotaur I is an orbital launch system used to launch small satellites into low Earth orbit (LEO). The Minotaur II, also known as Chimera and TLV, is used for suborbital flights, often as a target for tracking and anti-ballistic missile tests. The Minotaur IV is a more capable LEO launch system. Two more versions are also under development. These are the Minotaur III, which will also be used for suborbital flights, and the Minotaur V, which is designed to reach higher orbits, including GTO and trans-lunar trajectories. The Minotaur I and II are derived from the Minuteman missile, while the Minotaur III, IV and V are derived from the Peacekeeper.
Two variants of the Minotaur are currently in service. The Minotaur I is an orbital launch system used to launch small satellites into low Earth orbit (LEO). The Minotaur II, also known as Chimera and TLV, is used for suborbital flights, often as a target for tracking and anti-ballistic missile tests. The Minotaur IV is a more capable LEO launch system. Two more versions are also under development. These are the Minotaur III, which will also be used for suborbital flights, and the Minotaur V, which is designed to reach higher orbits, including GTO and trans-lunar trajectories. The Minotaur I and II are derived from the Minuteman missile, while the Minotaur III, IV and V are derived from the Peacekeeper.
Pegasus
_The Pegasus rocket is a winged space launch vehicle capable of carrying small, unmanned payloads (443 kilograms (980 lb)) into low Earth orbit. It is air-launched, as part of an expendable launch system developed by Orbital Sciences Corporation (Orbital). Three main stages burning solid propellant provide the thrust. It flies as a rocket-powered aircraft before leaving the atmosphere.
The Pegasus is carried aloft below a carrier aircraft and launched at approximately 40,000 ft (12,000 m). The carrier aircraft provides flexibility to launch the rocket from anywhere rather than just a fixed pad. A high-altitude, winged flight launch also allows the rocket to avoid flight in the densest part of the atmosphere where a larger launch vehicle, carrying much more fuel, would be needed to overcome air friction and gravity.
The Pegasus is carried aloft below a carrier aircraft and launched at approximately 40,000 ft (12,000 m). The carrier aircraft provides flexibility to launch the rocket from anywhere rather than just a fixed pad. A high-altitude, winged flight launch also allows the rocket to avoid flight in the densest part of the atmosphere where a larger launch vehicle, carrying much more fuel, would be needed to overcome air friction and gravity.
Taurus
_Taurus is a four stage, solid fuel launch vehicle built in the United States by Orbital Sciences Corporation. It is based on the air-launched Pegasus rocket from the same manufacturer. The Taurus rocket is able to carry a payload of around 1,350 kg into a low Earth orbit or up to 445 kg into a geostationary transfer orbit.