Titan II GLV

Titan II GLV
	Launch of Gemini 11 on a Titan II GLV from LC-19
Function	Human-rated launch vehicle for Gemini spacecraft
Manufacturer	Martin
Country of origin	United States
Size
Height	109 feet (33.2 m)
Diameter	10 feet (3.05 m)
Mass	340,000 pounds (154,200 kg)
Stages	2
Capacity
Payload to LEO
Mass	7,900 pounds (3,580 kg)
Associated rockets
Family	Titan
Launch history
Status	Retired
Launch sites	Cape Canaveral LC-19
Total launches	12
Success(es)	12
First flight	April 8, 1964
Last flight	November 11, 1966
Type of passengers/cargo	Gemini
First stage
Powered by	1 LR87-AJ-7
Maximum thrust	430,000 pounds-force (1,913 kN)
Specific impulse	258 sec
Burn time	156 seconds
Propellant	Aerozine 50/N2O4
Second stage
Powered by	1 LR91-AJ-7
Maximum thrust	100,000 pounds-force (445 kN)
Specific impulse	316 sec
Burn time	180 seconds
Propellant	Aerozine 50/N2O4
	[edit on Wikidata]

The Titan II GLV (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 unmanned launches followed by ten manned 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 a single set of turbomachinery), and the second stage was propelled by an LR-91 engine.

Modifications from the Titan II missile

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.

Several modifications were made to the Titan missile to man-rate it for Project Gemini:^[2]

A Gemini Malfunction Detection System was installed to inform the crew of the rocket's status, and improve response in an emergency.
Redundant systems were fitted to reduce the chances of launch failures.
The inertial guidance system was replaced by a lighter weight radio ground guidance system
The avionics truss in the second stage was modified slightly
To help guard against the possibility of a guidance malfunction causing the engine nozzles to gimbal hard right or left, an extra backup guidance system was added.
The second stage propellant tanks were lengthened for longer burn time and unnecessary vernier engines and retro-rockets were removed. Because the second stage engine had had issues with combustion instability, it was equipped with baffled injectors.
The first stage was loaded with 13,000 pounds (5896 kilograms) more propellant than the Titan ICBM although tank size remained unchanged.
Modifications were made to the tracking, electrical and hydraulics systems in the interest of improved reliability.
The propellants were chilled to slightly improve vehicle performance.
First stage engine thrust was reduced slightly to cut down on vibration and G loads.
First stage engine burn would go until propellant depletion unlike Titan ICBMs which were designed to cut off when propellant flow/pressure and engine thrust started dropping as the tanks emptied. This was to prevent the possibility of a malfunctioning pressure sensor triggering an abort condition. Also running until depletion would slightly boost the Titan's lift capacity.

Modifications were overseen by the Air Force Systems Command. Aerojet, the manufacturer of the Titan's engines, had released a revised model during mid-1963 due to deficiencies in the original design and also attempting to improve manufacturing procedures.

Film footage of Gemini 10's launch revealed that the first stage oxidizer tank ruptured shortly after staging and released a cloud of N2O2. 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.

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 it did not appear to pose any safety risk to the astronauts, NASA decided it was not a concern.

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, only static firing tests, but it was considered critical to fix. Aerojet developed a totally redesigned gearbox and all Gemini launch vehicles except Gemini 1 used it.

There was also a potentially serious problem with the turbopump bearings which led to more design changes, however the odds of failing on a Gemini launch were slim to nil since GLV boosters used specially selected and tested bearings, in addition the turbopumps would be "hot fired" as part of prelaunch checks.

Combustion instability in the second stage engine was also a concern although that too had only been witnessed in static firing runs. A new injector with improved baffling was developed for the engine and flight-tested on a Titan IIIC launch; all GLVs from Gemini 8 onward incorporated it.

After a Titan II propellant feed line was found to have damage to it during factory inspections, NASA put out the requirement that all GLV propellant lines had to be X-rayed in order to prevent a potentially disastrous fuel leak during launch. X-ray tests later found several more damaged propellant lines, most likely due to careless handling.

The most significant issue in man-rating the Titan II was resolving problems with resonant vibration known as "pogo" (since the action was said to resemble that of a pogo stick) that could produce g-forces sufficient to incapacitate astronauts,^{[citation needed]} but the Air Force were not interested in helping NASA with a problem that did not affect the ICBM program and could potentially delay it or require major modifications to the Titan design. However, Martin-Marietta argued that the pogo problem could be fixed fairly easily and also the Air Force began to develop more of an interest in man-rating the Titan II due to the proposed Manned Orbiting Laboratory program. The primary changes made to resolve pogo were adding oxidizer standpipes, increasing the pressure in the propellant tanks, and adding a mechanical accumulator to the fuel suction side.^[3]

Another nuisance problem that occurred during the Gemini program was code-named "Green Man" and involved momentary pitch oscillations of the Titan second stage following engine cutoff. This phenomenon had happened on both Gemini and unmanned Titan II/III flights and had resulted in failure of the ablative skirt on the second stage at least twice (those instances were dubbed "Brown Man"). Investigation following skirt failure on a Titan IIIC launch concluded that pressure buildup in the ablative skirt caused the pitch oscillations, but NASA decided that there was probably little chance of loose debris from the skirt contacting the Gemini spacecraft, so no corrective action had to be taken and in any case, the Titan IIIC incident was found to be the result of poor quality control that would not affect the more tightly supervised Gemini program.

Assembly was done at Martin-Marietta's Baltimore plant so as not to interfere with missile work at the Denver facility, although it also saved the former from a planned shutdown. As with the Mercury-Atlas launch vehicles, a high degree of workmanship was stressed as well as more thorough testing of components and improved handling procedures compared with Titans designed for unmanned flight.^[4]

Flights

Mission	LV Serial N^o	Launch date	Crew
GT-1	GLV-1 12556	April 8, 1964	Unmanned orbital test flight
GT-2	GLV-2 12557	January 19, 1965	Unmanned suborbital test of Gemini heat shield
GT-3	GLV-3 12558	March 23, 1965	Gus Grissom and John Young
GT-IV	GLV-4 12559	June 3, 1965	James McDivitt and Edward H. White
GT-V	GLV-5 12560	August 21, 1965	Gordon Cooper and Charles P. Conrad
GT-VII	GLV-7 12562	December 4, 1965	Frank Borman and James Lovell
GT-VI A	GLV-6 12561	December 15, 1965	Wally Schirra and Thomas P. Stafford
GT-VIII	GLV-8 12563	March 16, 1966	Neil Armstrong and David Scott
GT-IX A	GLV-9 12564	June 3, 1966	Thomas P. Stafford and Eugene Cernan
GT-X	GLV-10 12565	July 18, 1966	John Young and Michael Collins
GT-XI	GLV-11 12566	September 12, 1966	Charles P. Conrad and Richard F. Gordon
GT-XII	GLV-12 12567	November 11, 1966	James Lovell and Edwin "Buzz" Aldrin

Notes

^ Gatland, Kenneth (1976), Manned Spacecraft (2nd revision ed.), New York: MacMilan, p. 37, ISBN 0-02-542820-9
^ Simplicity, Duplication Will Give Titan 2 Manned Flight Capability, Aviation Week & Space Technology, September 3, 1962 pages 38-45
^ Hacker and Grimwood, p. 105
^ http://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19780012208_1978012208.pdf

References

Krebs, Gunter. "Titan-2-GLV". Gunter's Space Page. Retrieved April 29, 2009.
Wade, Mark. "Titan". Encyclopedia Astronautica. Retrieved April 29, 2009.

External links

Media related to Titan II Gemini at Wikimedia Commons

[1] Gatland, Kenneth (1976), Manned Spacecraft (2nd revision ed.), New York: MacMilan, p. 37, ISBN 0-02-542820-9

[2] Simplicity, Duplication Will Give Titan 2 Manned Flight Capability, Aviation Week & Space Technology, September 3, 1962 pages 38-45

[3] Hacker and Grimwood, p. 105

[4] ttp://ntrs.nasa.gov/archive/nasa/casi.ntrs.nasa.gov/19780012208_1978012208.pdf

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v t e Orbital launch systems
List of orbital launch systems Comparison of orbital launch systems
Current	Angara 1.2 A5 Ariane 6 Atlas V Ceres 1 1S Chollima-1 Electron Falcon 9 Block 5 Falcon Heavy Firefly Alpha Gravity-1 GSLV H-IIA H3 Hyperbola-1 Jielong 1 3 KAIROS^† Kaituozhe 2 Kinetica 1 Kuaizhou 1 1A 11 Long March 2C 2D 2F 3A 3B/E 3C 4B 4C 5 5B 6 6A 7 7A 8 11 11H LVM3 Minotaur I IV V C Nuri OS-M1^† Pegasus XL Proton-M PSLV Qaem 100 Qased RS1^† Shavit 2 Simorgh SLS Block 1 Soyuz-2 2.1a / STA 2.1b / STB 2-1v SSLV Starship Tianlong-2 Unha Vega C Vulcan Centaur Zhuque 2
In development	Antares 330 Bloostar Cyclone-4M Deca Epsilon S Eris Gravity-2 Hyperbola-2 Irtysh Kuaizhou 21 31 Long March 9 10 12 Miura 5 MLV Neutron New Glenn New Line 1 NGLV Nova OS-M 2 4 Orbex Prime Pallas-1 Red Dwarf SLS Block 1B Block 2 Soyuz-7 Terran R Tianlong-3 VLM Vega E Zero Zhuque 3 Zuljanah
Retired	Antares 110 120 130^† 230 230+ Ariane 1 2 3 4 5 ASLV Athena I II Atlas B D E/F G H I II III LV-3B SLV-3 Able^† Agena Centaur Black Arrow Conestoga^† Delta A B C D E G J L M N 0100 1000 2000 3000 4000 5000 II III IV IV Heavy Diamant Dnepr Energia Epsilon Europa I^† II^† Falcon 1 Falcon 9 v1.0 v1.1 v1.2 "Full Thrust" Feng Bao 1 GSLV Mk I H-I H-II H-IIB Juno I Juno II Kaituozhe-1 Kosmos original 1 2/2I 3 3M Lambda 4S LauncherOne Long March 1 1D^† 2A 2E 3 3B 4A Mu 4S 3C 3H 3S 3SII V N1^† N-I N-II Naro-1 Paektusan^† Pilot-2^† R-7 Luna Molniya M L Polyot Soyuz original FG L M U U2 Soyuz/Vostok Sputnik Voskhod Vostok L K 2 2M R-29 Shtil' Volna^† Rocket 3 Safir 1 1A 1B Saturn I IB V Scout X-1 Blue Scout II^† X-2^† X-2M X-3 X-3M X-4 X-2B^† B A B-1 D-1 A-1 E-1 F-1 G-1 Shavit original 1 SLV Space Shuttle SPARK^† Sparta SS-520 Start-1 Terran 1^† Thor Able Ablestar 1 2 Agena A B D Burner 1 2 Delta DSV-2U Thorad-Agena SLV-2G SLV-2H Titan II GLV IIIA IIIB IIIC IIID IIIE 34D 23G CT-3 IV Tsyklon R-36-O original 2 3 Universal Rocket UR-500 Proton Proton-K Rokot Strela Vanguard Vega original VLS-1^† Zenit 2 2M 2FG 3SL 3SLB 3F Zhuque 1^†
Classes	Sounding rocket Small-lift launch vehicle Medium-lift launch vehicle Heavy-lift launch vehicle Super heavy-lift launch vehicle
This Template lists historical, current, and future space rockets that at least once attempted (but not necessarily succeeded in) an orbital launch or that are planned to attempt such a launch in the future Symbol ^† indicates past or current rockets that attempted orbital launches but never succeeded (never did or has yet to perform a successful orbital launch)

v t e Orbital launch systems developed in the United States
Active	Atlas V**^†† Electron Falcon 9 Block 5 Falcon Heavy Firefly Alpha Minotaur I IV V C Pegasus XL RS1^† SLS Block 1 Vulcan Centaur
In development	Antares 330 Daytona I MLV New Glenn Neutron Nova Red Dwarf SLS Block 1B Block 2 Starship Terran R
Retired	Antares 110/120/130/230/230+^††† Athena I II Atlas B D E/F G H I II III LV-3B SLV-3 Able Agena Centaur Conestoga Delta A B C D E G J L M N 0100 1000 2000 3000 4000 5000 II III IV IV Heavy Falcon 1 Falcon 9 v1.0 v1.1 v1.2 "Full Thrust" H-I* Juno I Juno II LauncherOne N-I* N-II* Pilot Rocket 3 Saturn I IB V Scout Space Shuttle SPARK Sparta Terran 1 Thor Able Ablestar Agena Burner Delta DSV-2U Thorad-Agena Titan II GLV IIIA IIIB IIIC IIID IIIE 34D 23G CT-3 IV Vanguard
* - Japanese projects using US rockets or stages ** - uses Russian engines ^† - never succeeded ^†† - no new orders accepted ^††† - used Ukrainian first stage

Modifications from the Titan II missile

Flights

See also

Notes

References

External links