Minotaur I
ActiveOrbital Sciences Corporation (OSC)
Jan. 27, 2000
Description
The Minotaur I launch system is derived from converted Minuteman II ICBMs and is used to launch small satellites for the US Government. The first and second stages, taken directly from decommissioned Minuteman missiles, are mated to the Orion third and fourth stages taken from the Pegasus XL air-launched rocket family. An optional hydrazine-powered fifth stage called HAPS can be used.The Minotaur I launch system is derived from converted Minuteman II ICBMs and is used to launch small satellites for the US Government. An optional hydrazine-powered fifth stage called HAPS can be used.
Specifications
-
Minimum Stage
4 -
Max Stage
5 -
Length
19.21 m -
Diameter
1.67 m -
Fairing Diameter
― -
Launch Mass
36.0 T -
Thrust
935.0 kN
Family
-
Name
Minotaur I -
Family
― -
Variant
― -
Alias
Minotaur OSP-SLV -
Full Name
Minotaur I
Payload Capacity
-
Launch Cost
― -
Low Earth Orbit
580.0 kg -
Geostationary Transfer
Orbit
― -
Direct Geostationary
― -
Sun-Synchronous Capacity
331.0 kg
Orbital Sciences Corporation
Commercial
None
OSCNone
Flight Record
No spaceflights found for .
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