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Titan II GLV
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Titan II GLV
The Titan II GLV (Titan II Gemini Launch Vehicle) or Gemini-Titan II was an American expendable launch system derived from the Titan II missile, which was used to launch twelve Gemini missions for NASA between 1964 and 1966. Two uncrewed launches followed by ten crewed ones were conducted from Launch Complex 19 at the Cape Canaveral Air Force Station, starting with Gemini 1 on April 8, 1964.
The Titan II was a two-stage liquid-fuel rocket, using a hypergolic propellant combination of Aerozine 50 fuel and nitrogen tetroxide oxidizer. The first stage was powered by an LR87 engine (with two combustion chambers and nozzles, fed by separate sets of turbomachinery), and the second stage was propelled by an LR91 engine.
In addition to greater payload capability, the Titan II promised greater reliability than the Atlas LV-3B, which had been selected for Project Mercury, because Titan's hypergolic-fueled engines contained far fewer components.[citation needed]
Several modifications were made to the Titan missile to human-rate it for Project Gemini:
Modifications were overseen by the Air Force Systems Command. The Aerojet company, the manufacturer of the Titan's engines, had released a revised model during mid-1963 due to deficiencies in the original design, and also to attempt to improve manufacturing procedures.[citation needed]
Film footage of Gemini 10's launch revealed that the first stage oxidizer tank ruptured shortly after staging and released a cloud of N2O4. As first stage telemetry had been terminated at staging, there was no data other than photographic/visual evidence to go by, however the conclusion was that either loose debris struck the oxidizer tank dome or else exhaust from the second stage engine had burned through it.[citation needed]
Gemini 12's launch vehicle also experienced a tank rupture after staging and film review of Titan II ICBM launches found several occurrences of this phenomenon. Since this did not appear to pose any safety risks to the astronauts, NASA decided that it was not a concern.[citation needed]
During Titan II ICBM development, it had been found that the first stage turbopump gearbox was prone to total failure caused by resonant vibration in the idler gear. This problem had not occurred on actual launches, but only static firing tests. This was considered to be a critical item to fix. Aerojet developed a totally redesigned gearbox, and all of Gemini launch vehicles except for the uncrewed Gemini 1 used it.[citation needed]
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Titan II GLV
The Titan II GLV (Titan II Gemini Launch Vehicle) or Gemini-Titan II was an American expendable launch system derived from the Titan II missile, which was used to launch twelve Gemini missions for NASA between 1964 and 1966. Two uncrewed launches followed by ten crewed ones were conducted from Launch Complex 19 at the Cape Canaveral Air Force Station, starting with Gemini 1 on April 8, 1964.
The Titan II was a two-stage liquid-fuel rocket, using a hypergolic propellant combination of Aerozine 50 fuel and nitrogen tetroxide oxidizer. The first stage was powered by an LR87 engine (with two combustion chambers and nozzles, fed by separate sets of turbomachinery), and the second stage was propelled by an LR91 engine.
In addition to greater payload capability, the Titan II promised greater reliability than the Atlas LV-3B, which had been selected for Project Mercury, because Titan's hypergolic-fueled engines contained far fewer components.[citation needed]
Several modifications were made to the Titan missile to human-rate it for Project Gemini:
Modifications were overseen by the Air Force Systems Command. The Aerojet company, the manufacturer of the Titan's engines, had released a revised model during mid-1963 due to deficiencies in the original design, and also to attempt to improve manufacturing procedures.[citation needed]
Film footage of Gemini 10's launch revealed that the first stage oxidizer tank ruptured shortly after staging and released a cloud of N2O4. As first stage telemetry had been terminated at staging, there was no data other than photographic/visual evidence to go by, however the conclusion was that either loose debris struck the oxidizer tank dome or else exhaust from the second stage engine had burned through it.[citation needed]
Gemini 12's launch vehicle also experienced a tank rupture after staging and film review of Titan II ICBM launches found several occurrences of this phenomenon. Since this did not appear to pose any safety risks to the astronauts, NASA decided that it was not a concern.[citation needed]
During Titan II ICBM development, it had been found that the first stage turbopump gearbox was prone to total failure caused by resonant vibration in the idler gear. This problem had not occurred on actual launches, but only static firing tests. This was considered to be a critical item to fix. Aerojet developed a totally redesigned gearbox, and all of Gemini launch vehicles except for the uncrewed Gemini 1 used it.[citation needed]
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