Titan IV
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| Titan IVB | ||
|---|---|---|
| Image:Titan IV rocket.jpg Launch of a Titan IVB launch vehicle. (USAF) | ||
| Stages | 3 or 4 | |
| 0 - Solid Boosters | Engines | Solid Fuel |
| Thrust | 1,700,000 lbf (7.56 MN) X 2 = 3,400,000 lbf (15.12 MN) | |
| Burn time | 120 seconds | |
| Fuels | Solid Fuel | |
| 1 - 1st Stage | Engines | LR87 X 2 |
| Thrust | 548000 lbf (2.44 MN) | |
| Burn time | 164 seconds | |
| Fuels | A-50 hydrazine/N204 | |
| 2 - 2nd Stage | Engine | LR91 X 1 |
| Thrust | 105,000 lbf (467 kN) | |
| Burn time | 223 seconds | |
| Fuels | A-50 hydrazine/N204 | |
| 3 - 3rd Centaur Stage | Engine | RL-10 X 2 |
| Thrust | 33,100 lbf (147 kN) | |
| Burn time | 625 seconds | |
| Fuels | LOX/Liquid Hydrogen | |
| Launch Vehicle | 1st Launch June, 1989 | |
| Payload LEO 28-deg | 47,800 lb (21,680 kg) | |
| Payload LEO Polar orbit | 38,800 lb (17,600 kg) | |
| Payload Geo-sync orbit | 12,700 lb (5,760 kg) | |
| Payload Escape Velocity | 12,470 lb (5,660 kg) | |
The Titan IV family (including the IVA and IVB) of space boosters were used by the US Air Force. They were launched from Cape Canaveral Air Force Station, Florida, and Vandenberg Air Force Base, California.
The Titan IV was retired in 2005. The final launch (B-30) from Cape Canaveral AFS occurred on April 29, 2005, and the final launch from Vandenberg AFB occurred on October 19, 2005. [1]
Contents |
Features
The Titan IV was developed to provide assured capability to launch space shuttle-class payloads for the Air Force. The Titan IV could be launched with no upper stage, or either of two upper stages, the IUS (Inertial Upper Stage), and the Centaur Upper Stage.
The Titan IV is made up of two large solid fuel rocket boosters and a two stage liquid-fueled core. It was launched using the boosters alone, the first liquid core stage ignited about 2 minutes into flight.
The two storable liquid fuel core stages used aerozine 50 fuel and nitrogen tetroxide oxidizer. These propellants are hypergolic (ignite on contact at room temperature)and can be stored in a launch-ready state for extended periods.
The Titan IV could be launched from either coast. SLC-40 or 41 at Cape Canaveral Air Force Station near Cocoa Beach, FL and at SLC-4E, at Vandenberg Air Force Base near San Luis Obispo in California. Choice of launch site depended on mission parameters and mission goals.
Background
The Titan rocket family was established in October 1955 when the Air Force awarded Lockheed Martin (the former Glenn L. Martin Company) a contract to build an intercontinental ballistic missile (SM-68). It became known as the Titan I, the nation's first two-stage ICBM and replaced the Atlas ICBM as the second underground vertically stored, silo-based ICBM. Both stages of the Titan I used liquid oxygen and alcohol as propellants. A subsequent version of the Titan family, the Titan II, was similar to the Titan I, but was much more powerful. Designated as LGM-25C, the Titan II was the largest missile at the time, to be developed by the USAF. The Titan II had newly developed engines which used Aerozine 50 and Nitrogen Tetroxide as fuel and oxidizer.
Titan III development began in 1961 with the Titan IIIA. Years later, the Titan IVB evolved from the Titan III family and is similar to the Titan 34D. The last Titan IVA was launched in August 1998. The first Titan IVB flew on Feb. 23, 1997. The Titan IVB is an upgraded rocket having a new guidance system, flight termination system, ground checkout system, solid rocket motor upgrade and a 25 percent increase in thrust capability.
In the early 1980's, General Dynamics had a plan to use one Space Shuttle to lift a Lunar Module into orbit with one Titan IV Rocket to send an Apollo type Service Module into orbit to rendezvous and join the Lunar Module into making one moonship to land on the Moon. The plan required the Space Shuttle and Titan IV to use Lithium Fuel tanks instead of Aluminum to make a greater payload weight for takeoff. In the 1990's both Shuttle and Titan IV were converted to Lithium tanks to rendezvous with the highly inclined orbit of the Russian Mir Space Station. The Titan IVB became obsolete with the advent of the Atlas V rocket and the Delta IV Heavy rocket booster launch vehicles.
General characteristics
- Primary Function: Space booster
- Builder: Lockheed-Martin Astronautics
- Power Plant:
- Stage 0 consisted of two solid-rocket motors.
- Stage 1 used an LR87 liquid-propellant rocket engine.
- Stage 2 used the LR91 liquid-propellant engine.
- Optional upper stages included the Centaur and Inertial Upper Stage.
- Guidance System: A ring laser gyro guidance system manufactured by Honeywell.
- Thrust: Solid rocket motors provide 1.7 million pounds force (7.56 MN) per motor at liftoff.
- First stage provides an average of 548,000 pounds force (2.44 MN)
- second stage provides an average of 105,000 pounds force (467 kN).
- Optional Centaur upper stage provides 33,100 pounds force (147 kN) and the Inertial Upper Stage provides up to 41,500 pounds force (185 kN).
- Length: Up to 204 feet (62.17 m)
- Lift Capability:
- Can carry up to 47,800 pounds (21,680 kg) into a low-earth orbit
- up to 12,700 pounds (5,760 kg) into a geosynchronous orbit when launched from Cape Canaveral AFS, Fla.;
- and up to 38,800 pounds (17,600 kg) into a low-earth polar orbit when launched from Vandenberg AFB.
- into geosynchronous orbit:
- with Centaur upper stage 12,700 lb (5,760 kg)
- with Inertial Upper Stage 5,250 pounds (2,380 kg)
- Maximum Takeoff Weight: Approximately 2.2 million pounds (1,000,000 kg)
- Cost: Approximately $250-350 million, depending on launch configuration.
- Date deployed: June 1989
- Launch sites: Cape Canaveral AFS, Fla., and Vandenberg AFB, Calif.