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Delta III  
Initial Operational Capability (IOC): 1998
Total Production: 3
Origin: United States of America
Corporations: Boeing
Parent System: Delta
Initial Operational Capability (IOC): 1960
Total Production: 304
Family Members: Delta II and Delta IV
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Description: The Delta expendable launch vehicle program started in 1959 to meet the requirements of NASA. The Delta I launch vehicle propulsion system took its first stage from the USAF's Thor Intermediate Range Ballistic Missile (IRBM) and the second stage from the US Navy's Vanguard ballistic missile. In 1960 the first Delta I vehicle was capable of delivery a 100-pound payload into the GTO (Geosynchronous Transfer Orbit).

The Delta III launch vehicle program started in 1995 in response to market needs for space rockets capable of loading larger and heavier commercial satellites. The first Delta III was launched in 1998. Its propulsion system consists of RS-27 motor for the first stage and RL10B-2 for the second stage, as well as up to 9 GEM 46 strap-on boosters.

The Delta III can carry up to 8,400 lb (3,800 kg) of payload to GTO.

Delta III Specifications

Crew: 0
Number of Stages: 2
Weight
Payload to GTO: 3,800 kilogram (8,377 pound)
CEP: Circular Error Probable
Meters (m)   Kilometers (km)   Nautic Miles (nm)   Inch (in)   Yard (yd)   Foot (ft)   Millimeter (mm)
Pound (lb)   Kilogram (kg)   kN (KiloNewton)   Ton (t)
Meters per Second (mps)   Kilometers per Hour (kph)   Knot (kt)   Miles per Hour (mph)
Liter (l)   Galon (gl)
Year (yr)   Minutes (min)   Second (sec)
Shaft-Horse-Power (shp)

Operators & Related Equipment


OperatorsItems

Grand Total ?1
Propulsion Systems
GEM 46x9
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