Dragon Space – Titan III E Rocket w/Launch Pad SLC-41 – Cape Canaveral Space Launch Complex 41
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-sběratelský model vesmírné rakety 1/400 -provedení: plastový model -model je v kvalitním provedení
Titan IIIC
Titan byly nosné rakety vesmírné agentury NASA a USAF, které se používaly od roku 1959 až do roku 2005. Projekt začal roku 1955 a měl sloužit jako doplněk nebo náhrada programu mezikontinentálních balistických střel SM-65 Atlas v případě jeho zpoždění nebo selhání. Na rozdíl od Atlasu, se jednalo o klasickou dvoustupňovou raketu. Prvním zástupcem rodiny raket byl Titan 1, značen též LGM-25 nebo SM-68, který spaloval v motorech obou stupňů kapalný kyslík a RP-1 a měl mít nosnost až 1800 kg na nízkou oběžnou dráhu.
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 and Manned Orbiting Laboratory, though both programs were cancelled before any astronauts flew. The majority of the launcher’s payloads were DoD satellites, for military communications and early warning, though one flight (ATS-6) was performed by NASA. The Titan IIIC was launched exclusively from Cape Canaveral while its sibling, the Titan IIID, was launched only from Vandenberg AFB.
Titan IIIC
- Primary Function: Space booster
- Builder: Martin Marietta
- Power Plant:
- Stage 0 consists of two solid rocket motors.
- Stage 1 uses two LR87 liquid propellant engines.
- Stage 2 uses one LR91 liquid propellant engine.
- Stage 3 uses two Aerojet AJ-10-138 liquid propellant engines.
- Length: 42 m
- Stage 0: 25.91 m
- Stage 1: 22.28 m
- Stage 2: 7.9 m
- Stage 3: 4.57 m
- Diameter:
- Stage 0: 3.05 m
- Stage 1: 3.05 m
- Stage 2: 3.05 m
- Stage 3: 3.05 m
- Mass:
- Stage 0: Empty 33,798 kg/ea; Full 226,233 kg/ea
- Stage 1: Empty 5,443 kg; Full 116,573 kg
- Stage 2: Empty 2,653 kg; Full 29,188 kg
- Stage 3: Empty 1,950 kg; Full 12,247 kg
- Lift capability:
- Up to 28,900 lb (13,100 kg) into a low Earth orbit with 28 degrees inclination.
- Up to 6,600 lb (3,000 kg) into a geosynchronous transfer orbit when launched from Cape Canaveral Air Force Station, FL.
- Maximum takeoff weight: 626,190 kg
- Cost:
- Date deployed: June 1965.
- Launch sites: Cape Canaveral Air Force Station, FL., and Vandenberg Air Force Base, CA.
