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Delta II (7925)

Background Information
First Launch:
February 1989
Flight Rate:
6-12 per year
Launch Site:
SLC-17A & SLC-17B (CCAS), SLC-2 (VAFB)
Capability:
11,110 lb to LEO (28.5)

History

  • NASA ELV program started in the late 1950s
  • Used Thor and Vanguard components
  • Delta II is enhanced version of Delta 3920/PAM

Description

  • Four-stage vehicle
  • Stage 0 consists of nine Alliant Techsystems Graphite Epoxy Motors (GEMs) providing 98,870 lb of thrust each (three are air lit)
  • Stage 1 uses one Rocketdyne RS-27A engine that burns LO2/RP-1, generating 201,000 lb of thrust
  • Stage 2 uses one Aerojet ITIP engine that burns N2O4/A-50, generating 9,645 lb of thrust
  • Stage 3 uses one Thiokol Star 48B solid rocket motor that burns HTPB, generating 15,100 lb of thrust

Profile

Length:
125.2 ft
Launch Weight:
506,470 lb
Diameter:
8.0 ft
Liftoff Thrust:
794,200 lb
Payload Fairing:
15.3 ft x 9.5 ft

Other Resources


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