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El Titan IIIE o Titan 3E, también conocido como Titan III-Centaur era un vehículo de lanzamiento desechable estadounidense. Lanzado siete veces entre 1974 y 1977, permitió varias misiones de alto perfil de la NASA, incluidas las sondas planetarias Voyager y Viking y la nave espacial de Alemania del Oeste estadounidense Helios.
The Titan IIIE or Titan 3E, also known as the Titan III-Centaur, was an American expendable launch system. Launched seven times between 1974 and 1977, [4] it enabled several high-profile NASA missions, including the Voyager and Viking planetary probes and the joint West Germany-U.S. Helios spacecraft.
- February 11, 1974
- 7
- 3 with an option for 4
- Titan I Missile
- Titan II
- Titan III
- Titan IV
- Titan V Concept
- Launch Vehicle Retirement
- See Also
- References
- External Links
The HGM-25A Titan I, built by the Martin Company, was the first version of the Titan family of rockets. It began as a backup ICBM project in case the SM-65 Atlas was delayed. It was a two-stage rocket operational from early 1962 to mid-1965 whose LR-87 booster engine was powered by RP-1 (kerosene) and liquid oxygen (LOX). The ground guidance for th...
Titan II missile
Most of the Titan rockets were the Titan II ICBM and their civilian derivatives for NASA. The Titan II used the LR-87-5 engine, a modified version of the LR-87, that used a hypergolic propellant combination of nitrogen tetroxide (NTO) for its oxidizer and Aerozine 50 (a 50/50 mix of hydrazine and unsymmetrical dimethylhydrazine(UDMH) instead of the liquid oxygen and RP-1 propellant of the Titan I. The first Titan II guidance system was built by AC Spark Plug. It used an inertial measurement u...
Titan II launch vehicle
The most famous use of the civilian Titan II was in the NASA Gemini programof crewed space capsules in the mid-1960s. Twelve Titan II GLVs were used to launch two U.S. uncrewed Gemini test launches and ten crewed capsules with two-person crews. All of the launches were successful.
Titan 23G
Starting in the late 1980s, some of the deactivated Titan IIs were converted into space launch vehicles to be used for launching U.S. Government payloads. Titan 23G rockets consisted of two stages burning liquid propellant. The first stage was powered by one Aerojet LR87 engine with two combustion chambers and nozzles, and the second stage was propelled by an LR91. On some flights, the spacecraft included a kick motor, usually the Star-37XFP-ISS; however, the Star-37Swas also used. Thirteen w...
The Titan III was a modified Titan II with optional solid rocket boosters. It was developed on behalf of the United States Air Force (USAF) as a heavy-lift satellite launcher to be used mainly to launch American military payloads and civilian intelligence agency satellites such as the Vela Hotel nuclear-test-ban monitoring satellites, observation a...
The Titan IV was an extended length Titan III with solid rocket boosters on its sides. The Titan IV could be launched with a Centaur upper stage, the USAF Inertial Upper Stage (IUS), or no upper stage at all. This rocket was used almost exclusively to launch US military or Central Intelligence Agency payloads. However, it was also used for a purely...
The Titan V was a proposed development of the Titan IV, that saw several designs being suggested. One Titan V proposal was for an enlarged Titan IV, capable of lifting up to 90,000 pounds (41,000 kg) of payload. Another used a cryogenic first stage with LOX/LH2 propellants; however the Atlas V EELVwas selected for production instead.
Most of the decommissioned Titan II ICBMs were refurbished and used for Air Force space launch vehicles, with a perfect launch success record. For orbital launches, there were strong advantages to using higher-performance liquid hydrogen or RP-1 fueled vehicles with liquid oxygen; the high cost of using hydrazine and nitrogen tetroxide, along with ...
Bonds, Ray Editor. The Modern US War Machine: An encyclopedia of American military equipment and strategy. Crown Publishers, New York City 1989. ISBN 0-517-68802-6USAF Sheppard Technical Training Center. "Student Study Guide, Missile Launch/Missile Officer (LGM-25)." May 1967. pp. 61–65. Available at WikiMedia Commons: TitanII MGC.pdfLarson, Paul O. "Titan III Inertial Guidance System," in AIAA Second Annual Meeting, San Francisco, 26–29 July 1965, pp. 1–11.Liang, A.C. and Kleinbub, D.L. "Navigation of the Titan IIIC space launch vehicle using the Carousel VB IMU". AIAA Guidance and Control Conference, Key Biscayne, FL, 20–22 August 1973. AIAA Paper N...Titan III Research and Development – 1967 US Air Force Educational Documentary on YouTube(color; 13m33s)Titan I at fas.org (Federation of American Scientists)- 1958-12-20
- Glenn L. Martin Company
- 1959
- Expendable launch system with various applications
El Titan IIIE o Titan 3E, también conocido como Titan III-Centaur era un vehículo de lanzamiento desechable estadounidense. Lanzado siete veces entre 1974 y 1977, permitió varias misiones de alto perfil de la NASA, incluidas las sondas planetarias Voyager y Viking y la nave espacial de Alemania del Oeste estadounidense Helios.
The Titan IIIC was an expendable launch system used by the United States Air Force from 1965 until 1982. It was the first Titan booster to feature large solid rocket motors and was planned to be used as a launcher for the Dyna-Soar, though the spaceplane was cancelled before it could fly.
- 18 June 1965
- 36
- 2-3
La Voyager 2 fue lanzada el 20 de agosto de 1977 desde el Centro Espacial Kennedy de la NASA en Cabo Cañaveral a bordo de un cohete Titan IIIE.
Used by NASA for deep space missions in 1970's. AKA: SLV-5E;Titan 23E;Titan 3E. Status: Retired 1977. First Launch: 1974-02-11. Last Launch: 1977-09-05. Number: 7 . Payload: 15,400 kg (33,900 lb). Thrust: 10,586.80 kN (2,380,007 lbf). Gross mass: 632,970 kg (1,395,450 lb). Height: 48.00 m (157.00 ft). Diameter: 3.05 m (10.00 ft).
