Whittier-
23-08-2004, 06:20
Rockets:
Delta
http://img78.photobucket.com/albums/v245/vetobob/Deltarocket.jpg
began boosting remaining GPS satellites on 26 November 1990. The Delta II 7920 has a 12-foot longer first stage than previous Delta vehicles. Nine Hercules Aerospace strap-on Graphite-Epoxy Motors (GEMs) surround the first stage for augmented lift-off with a thrust of 45,000 kiloNewtons. Containing a more powerful propellant mixture than did its predecessor, the motors are built in a composite material called graphite-epoxy which is lighter but as strong as the steel cases they replaced. The new motors are 6 feet longer and provide 40 percent more thrust. Thrust is aided by the unsegmented solid-rocket motors as six ignite at lift-off and the remaining three are ignited in flight.
The first stage includes one Rocketdyne RS-27 and two LR-101-NA-11 vernier engines; both use RP-1 (refined kerosene) and LO2 (liquid oxygen) as its propellants, with a thrust of 101,250 kiloNewtons. The second stage is a restartable Aerojet AJ10-110K motor using N2O4 (nitrogen tetroxide) and A50 (Aerozine 50) propellants with a thrust of 4,050 kiloNewtons. The payload assist module, if used, is a Star-48B solid-fuel rocket with a 6,750 kiloNewton thrust.
Height in position is 125 feet (37.5 meters), and the diameter is 8 feet (2.4 meters). With a gross lift-off mass of 227,700 kilograms, the Delta II can carry payloads into near-earth orbits (approximately 160 kilometers in space). It can lift up to 4,995 kilograms into a 28-degree circular near-earth orbit and up to 3,789 kilograms into a 90-degree polar near-earth orbit. The Delta II also can carry up to 1,805 kilograms into geo-transfer orbit (approximately 19,200 kilometers) and up to 900 kilograms into geosynchronous orbit (approximately 35,200 kilometers). Payloads include the Navstar Global Positioning System as well as NASA's MELV, Radarsat and Lageos, and commercial tasks such as Inmarsat, Palapa, ASC-2, and NATO communications satellites. The guidance System is the Delta redundant inertial measurement system and a Delco guidance computer.
850 million
Atlas II Commercial Launch Vehicle
http://img78.photobucket.com/albums/v245/vetobob/Atlas_II.jpg
. The Atlas IIA booster has been stretched nine feet, and the Centaur upper stage is three feet longer than an Atlas I vehicle. Atlas IIA uses a Rocketdyne MA-5A stage-and-a-half propulsion system with two booster engines and one sustainer engine burning a combination of liquid oxygen and RP-I propellant. The Atlas IIA provides total thrust of 474,000 pounds.
capable of lifting payloads in the 7,000 to 8,000-pound class range to geosynchronous transfer orbit. Four strap-on solid rocket motor boosters have been added to the booster stage to increase liftoff thrust and payload lift capability.
booster uses a Rocketdyne MA-5A stage-and-a-half propulsion system with two booster engines and one sustainer engine burning a combination of liquid oxygen and RP-1 propellant. The MA-5A system provides a total liftoff thrust of 423,500 pounds. The four solid strap-ons are Castor IVA solid rocket boosters, each 37 feet long and 40 inches in diameter. providing an average thrust of 97,500 pounds. Two of the four solid rocket boosters ignite at liftoff, contributing an additional 197,000 pounds of thrust. Total thrust at liftoff is 620,500 pounds. The second pair of solid rocket boosters fires during flight after the first pair burns out, to control acceleration forces. The IIAS Centaur upper stage, is identical to the Centaur flown on IIA.
500 million
Titan 4
http://img78.photobucket.com/albums/v245/vetobob/Titan4.jpg
the newest and largest unmanned space booster
The Titan IV is a heavy lift rocket booster that will assure continued access to space for the nation's highest priority space systems, such as Defense Support Program and Milstar satellites
the first and second stages have been stretched, and an additional one and a half segments have been added to each of the strap-on solid rocket motors. The 16.7-foot-wide payload fairing will enclose both the satellite and upper stage.
The Titan IV consists of a liquid propellant core of two stages with a pair of large solid rocket motors (SRM) attached to the core to provide the initial stage of boost from liftoff. Stage 0 currently consists of two solid-rocket motors which provide 1.5 million pounds (675,000 kilograms) per motor at liftoff. The Titan IV'S first stage consists of an LR-87 liquid-propellant rocket that features structurally independent tanks for its fuel (Aerozine 50) and oxidizer (Nitrogen Tetroxide). This minimizes the hazard of the two mixing if a leak should develop in either tank. Additionally, the engines' propellant can be stored in a launch-ready state for extended periods. The use of propellants stored at normal temperature and pressure eliminates delays and gives the Titan IV the capability to meet critical launch windows. The Stage 1 LR-87 engines have an average of 548,000 pounds (246,600 kilograms). Stage 2 uses the LR-91 liquid-propellant engine with an average of 105,000 pounds (47,250 kilograms).
325 million
America Class Launch Vehicle
http://img78.photobucket.com/albums/v245/vetobob/Americaclass.gif
# Pop up and deliver 20 to 30 klbs of mission assets (does not include boost stage, aeroshell, guidance or propellant) to any terrestrial destination
# Pop up and deliver 45 klbs of orbital assets (does not include upperstage) due east to a 100 x 100 NM orbit
# Launch due east, carrying a 20-klb payload, orbit at 100 x 100 NM and return to base
# Launch polar, carrying 5-klb payload and return to base
# Payload bay size 45' x 15' x 15', weight capacity 60 klbs
345 million
CZ-2D Space Launch Vehicle
http://img78.photobucket.com/albums/v245/vetobob/CZ2D2.jpg
Flight Rate:
2-3 per year
Capability:
2,750 lb to GTO
Description
* Three-stage liquid fueled vehicle (including PAM-D upper stage)
* Stage 1 consists of four YF-20 motors burning UDMH/N2O4 providing a total thrust of 626,000 lb
* Stage 2 uses one YF-22 engine and four YF-23 verniers burning UDMH/N2O4 for a total thrust of 171,300 lb
* Stage 3 is a McDonnell Douglas PAM-D upper stage providing 66,700 lb of thrust
Profile
Length:
131 ft
Launch Weight:
421,000 lb
Diameter:
11 ft
Liftoff Thrust:
626,000 lb
Payload Fairing:
31.0 ft x 11.0 ft
Delta
http://img78.photobucket.com/albums/v245/vetobob/Deltarocket.jpg
began boosting remaining GPS satellites on 26 November 1990. The Delta II 7920 has a 12-foot longer first stage than previous Delta vehicles. Nine Hercules Aerospace strap-on Graphite-Epoxy Motors (GEMs) surround the first stage for augmented lift-off with a thrust of 45,000 kiloNewtons. Containing a more powerful propellant mixture than did its predecessor, the motors are built in a composite material called graphite-epoxy which is lighter but as strong as the steel cases they replaced. The new motors are 6 feet longer and provide 40 percent more thrust. Thrust is aided by the unsegmented solid-rocket motors as six ignite at lift-off and the remaining three are ignited in flight.
The first stage includes one Rocketdyne RS-27 and two LR-101-NA-11 vernier engines; both use RP-1 (refined kerosene) and LO2 (liquid oxygen) as its propellants, with a thrust of 101,250 kiloNewtons. The second stage is a restartable Aerojet AJ10-110K motor using N2O4 (nitrogen tetroxide) and A50 (Aerozine 50) propellants with a thrust of 4,050 kiloNewtons. The payload assist module, if used, is a Star-48B solid-fuel rocket with a 6,750 kiloNewton thrust.
Height in position is 125 feet (37.5 meters), and the diameter is 8 feet (2.4 meters). With a gross lift-off mass of 227,700 kilograms, the Delta II can carry payloads into near-earth orbits (approximately 160 kilometers in space). It can lift up to 4,995 kilograms into a 28-degree circular near-earth orbit and up to 3,789 kilograms into a 90-degree polar near-earth orbit. The Delta II also can carry up to 1,805 kilograms into geo-transfer orbit (approximately 19,200 kilometers) and up to 900 kilograms into geosynchronous orbit (approximately 35,200 kilometers). Payloads include the Navstar Global Positioning System as well as NASA's MELV, Radarsat and Lageos, and commercial tasks such as Inmarsat, Palapa, ASC-2, and NATO communications satellites. The guidance System is the Delta redundant inertial measurement system and a Delco guidance computer.
850 million
Atlas II Commercial Launch Vehicle
http://img78.photobucket.com/albums/v245/vetobob/Atlas_II.jpg
. The Atlas IIA booster has been stretched nine feet, and the Centaur upper stage is three feet longer than an Atlas I vehicle. Atlas IIA uses a Rocketdyne MA-5A stage-and-a-half propulsion system with two booster engines and one sustainer engine burning a combination of liquid oxygen and RP-I propellant. The Atlas IIA provides total thrust of 474,000 pounds.
capable of lifting payloads in the 7,000 to 8,000-pound class range to geosynchronous transfer orbit. Four strap-on solid rocket motor boosters have been added to the booster stage to increase liftoff thrust and payload lift capability.
booster uses a Rocketdyne MA-5A stage-and-a-half propulsion system with two booster engines and one sustainer engine burning a combination of liquid oxygen and RP-1 propellant. The MA-5A system provides a total liftoff thrust of 423,500 pounds. The four solid strap-ons are Castor IVA solid rocket boosters, each 37 feet long and 40 inches in diameter. providing an average thrust of 97,500 pounds. Two of the four solid rocket boosters ignite at liftoff, contributing an additional 197,000 pounds of thrust. Total thrust at liftoff is 620,500 pounds. The second pair of solid rocket boosters fires during flight after the first pair burns out, to control acceleration forces. The IIAS Centaur upper stage, is identical to the Centaur flown on IIA.
500 million
Titan 4
http://img78.photobucket.com/albums/v245/vetobob/Titan4.jpg
the newest and largest unmanned space booster
The Titan IV is a heavy lift rocket booster that will assure continued access to space for the nation's highest priority space systems, such as Defense Support Program and Milstar satellites
the first and second stages have been stretched, and an additional one and a half segments have been added to each of the strap-on solid rocket motors. The 16.7-foot-wide payload fairing will enclose both the satellite and upper stage.
The Titan IV consists of a liquid propellant core of two stages with a pair of large solid rocket motors (SRM) attached to the core to provide the initial stage of boost from liftoff. Stage 0 currently consists of two solid-rocket motors which provide 1.5 million pounds (675,000 kilograms) per motor at liftoff. The Titan IV'S first stage consists of an LR-87 liquid-propellant rocket that features structurally independent tanks for its fuel (Aerozine 50) and oxidizer (Nitrogen Tetroxide). This minimizes the hazard of the two mixing if a leak should develop in either tank. Additionally, the engines' propellant can be stored in a launch-ready state for extended periods. The use of propellants stored at normal temperature and pressure eliminates delays and gives the Titan IV the capability to meet critical launch windows. The Stage 1 LR-87 engines have an average of 548,000 pounds (246,600 kilograms). Stage 2 uses the LR-91 liquid-propellant engine with an average of 105,000 pounds (47,250 kilograms).
325 million
America Class Launch Vehicle
http://img78.photobucket.com/albums/v245/vetobob/Americaclass.gif
# Pop up and deliver 20 to 30 klbs of mission assets (does not include boost stage, aeroshell, guidance or propellant) to any terrestrial destination
# Pop up and deliver 45 klbs of orbital assets (does not include upperstage) due east to a 100 x 100 NM orbit
# Launch due east, carrying a 20-klb payload, orbit at 100 x 100 NM and return to base
# Launch polar, carrying 5-klb payload and return to base
# Payload bay size 45' x 15' x 15', weight capacity 60 klbs
345 million
CZ-2D Space Launch Vehicle
http://img78.photobucket.com/albums/v245/vetobob/CZ2D2.jpg
Flight Rate:
2-3 per year
Capability:
2,750 lb to GTO
Description
* Three-stage liquid fueled vehicle (including PAM-D upper stage)
* Stage 1 consists of four YF-20 motors burning UDMH/N2O4 providing a total thrust of 626,000 lb
* Stage 2 uses one YF-22 engine and four YF-23 verniers burning UDMH/N2O4 for a total thrust of 171,300 lb
* Stage 3 is a McDonnell Douglas PAM-D upper stage providing 66,700 lb of thrust
Profile
Length:
131 ft
Launch Weight:
421,000 lb
Diameter:
11 ft
Liftoff Thrust:
626,000 lb
Payload Fairing:
31.0 ft x 11.0 ft