Thor-Able

Thor-Able on display at the Air Force Space & Missile Museum
FunctionExpendable launch system
Sounding rocket
ManufacturerDouglas/Aerojet
Country of originUnited States
Size
Height26.9 metres (88 ft) – 27.8 metres (91 ft)
Diameter2.44 metres (8 ft 0 in)
Mass51,608 kilograms (113,776 lb)
Stages2–3
Capacity
Payload to 640km LEO
Mass120 kilograms (260 lb)
Associated rockets
FamilyThor
Derivative workThor-Ablestar
Delta
ComparableLuna
Launch history
Launch sitesLC-17A, Canaveral
Total launches9 suborbital
7 orbital
Success(es)7 suborbital
3 orbital
Failure(s)2 suborbital
4 orbital
First flight24 April 1958
Last flight1 April 1960
Type of passengers/cargoPioneer
Transit
Tiros
First stage – Thor
Powered by1 LR79-7
Maximum thrust758.71 kilonewtons (170,560 lbf)
Specific impulse282 seconds (2.77 km/s)
Burn time165 seconds
PropellantRP-1/LOX
Second stage – Able
Powered by1 AJ-10
Maximum thrust34.69 kilonewtons (7,800 lbf)
Specific impulse270 seconds (2.6 km/s)
Burn time115 seconds
PropellantHNO3/UDMH
Third stage (optional) – Altair
Powered by1 X-248
Maximum thrust12.45 kilonewtons (2,800 lbf)
Specific impulse256 seconds (2.51 km/s)
Burn time38 seconds
PropellantSolid

The Thor-Able was an American expendable launch system and sounding rocket used for a series of re-entry vehicle tests and satellite launches between 1958 and 1960.

It was a two-stage rocket, consisting of a Thor IRBM as a first stage and a Vanguard-derived Able second stage. On some flights, an Altair solid rocket motor was added as a third stage. It was a member of the Thor family and an early predecessor of the Delta.[1][2]

The Able upper stage name represents its place as the first in the series, from the Joint Army/Navy Phonetic Alphabet.[3]

  1. ^ Krebs, Gunter. "Thor Able". Gunter's Space Page. Retrieved 2008-11-10.
  2. ^ Wade, Mark. "Delta". Encyclopedia Astronautica. Archived from the original on 2013-08-17. Retrieved 2008-11-10.
  3. ^ Wells, Helen T.; Whiteley, Susan H. & Karegeannes, Carrie E. (1976). Origins of NASA Names. NASA Science and Technical Information Office. p. 5. NASA SP-4402.

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