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Sparta (rocket)

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This is an old revision of this page, as edited by Stepho-wrs (talk | contribs) at 04:17, 27 February 2015 (Delinked BE-3. Obviously the 2014 BE-3 engine is not the third stage used on a 1960s rocket.). The present address (URL) is a permanent link to this revision, which may differ significantly from the current revision.

Sparta
FunctionSounding rocket
Launch system
ManufacturerABMA/Chrysler
Country of origin Vereinigte Staaten
Size
Height21.8 metres (72 ft)
Diameter1.78 metres (5 ft 10 in)
Mass30,000 kilograms (66,000 lb)
Stages3
Capacity
Payload to LEO
Mass45 kilograms (99 lb)
Associated rockets
FamilyRedstone
ComparableJupiter-C
Juno I
Launch history
StatusRetired
Launch sitesWoomera Test Range LA-8
Total launches10
Success(es)9
Failure(s)1
First flight28 November 1966
Last flight29 November 1967
Type of passengers/cargoWRESAT
First stage – Redstone
Powered by1 A-7
Maximum thrust416 kilonewtons (94,000 lbf)
Specific impulse265 sec
Burn time155 seconds
PropellantLOX/Hydyne
Second stage – Antares-2
Powered by1 X-259
Maximum thrust93 kilonewtons (21,000 lbf)
Specific impulse293 sec
Burn time36 seconds
PropellantSolid
Third stage – BE-3
Powered by1 solid
Maximum thrust34
Burn time9 seconds
PropellantSolid

The Sparta was a three-stage rocket that launched Australia's first Earth satellite, WRESAT, on 29 November 1967.

Sparta on the pad at Woomera

Sparta used a surplus American Redstone as its first stage, an Antares-2 as a second stage, and a BE-3 as a third stage. Several Spartas were launched from 1966–67 from Woomera Test Range in Woomera, South Australia as part of a joint United States–United Kingdom–Australian research program aimed at understanding re-entry phenomena, and the U.S. donated a spare for the scientific satellite launch into polar orbit.

References

  • Wade, Mark. "Redstone". Encyclopedia Astronautica. Retrieved 2009-04-07.