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Background Information
- First Launch:
- July 1960
- Flight Rate:
- 1-2 per year
- Launch Site:
- Wallops Island and VAFB, USA; San Marco, Kenya
- Capability:
- 560 lb to LEO (37.5 degrees);
- 455 lb to LEO polar
History
-
Start of full scale development in 1958
- Full operational capability in December 1963
Description
-
Four-stage solid propellant vehicle
- Stage 1 uses one Algol IIIA motor (United Technologies) providing 104,400 lb of thrust
- Stage 2 uses one castor IIA motor (Thiokol) providing 60,100 lb of thrust
- Stage 3 uses one Antares IIIA motor (Thiokol) providing 18,200 lb of thrust
- Stage 4 uses one Altair IIA motor (Thiokol) providing 5,800 lb of thrust
Profile
-
Length:
- 75.1 ft
- Launch Weight:
- 47,950 lb
- Diameter
- 3.8 ft (stage 1)
- Liftoff Thrust:
- 104,400 lb
- Payload Fairing
- 6.6 ft x 3.5 ft
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