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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
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