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Thor Able
Part of Thor Family
Thor Able
Thor Able
Credit: © Thomas Kladiva - Thomas Kladiva
American orbital launch vehicle. Thor with Able stage derived from Vanguard second stage.

Status: Retired 1958. First Launch: 1958-04-24. Last Launch: 1958-07-23. Number: 3 . Payload: 120 kg (260 lb). Thrust: 667.20 kN (149,993 lbf). Gross mass: 51,608 kg (113,776 lb). Height: 30.00 m (98.00 ft). Diameter: 2.44 m (8.00 ft). Apogee: 640 km (390 mi).

In October 1957, Paul Degarabedian, an Associate Manager at Space Technology Laboratories (later TRW), proposed an American lunar/interplanetary launch vehicle combining the Air Force Thor IRBM; with the second and third stages of the Navy's Vanguard satellite launcher. This idea didn't make it past his management, but a month later he proposed a two stage Thor Vanguard, which he called the Thor A or Able, for test of subscale models of ICBM warheads. This was of interest, and within a month an order was placed with Aerojet for several Vanguard second stages. The STL team used the Thor's own guidance system, and built the payload interface compartment and ejection actuators in-house. It was also necessary to add 84 kg of ballast to prevent the two-stage missile's payload from overshooting its south Atlantic impact area and hitting Africa. STL Electronic Laboratory's George Mueller, later a key NASA manager in the Apollo program, was made project manager of the $1.55 million classified program. The first tests of the Aerojet Able stage began on February 21, 1958. The first Thor stage arrived on March 4. It was decided that the nosecones would carry an instrumented mouse to see if it could survive boost, sustained zero-G, and re-entry. Three weeks later the integrated tests were completed and the booster was declared ready for flight - only four months after it was conceived!

The first launch attempt on April 23 ended at T+146 when the Thor exploded due to a turbopump main bearing failure, and mouse Mia (inauspiciously named 'Missing In Action') perished. The same problem had occurred on other Thors and it took a while to identify the cause, take corrective action, and fix the turbopumps in the field. The second launch on July 9, with a ballistic nosecone and the Mouse Mia II aboard, was successful, although the nosecone could not be located by the recovery ship before it sank.

On the third launch, on July 23, telemetry indicated that mouse Wickie survived the flight into space through splashdown. But again the nosecone was not located. This completed the nosecone tests. In February it had been suggested that the configuration could be converted into a low-cost ICBM, dubbed Thoric (Thor Inter-Continental). This was an obvious threat to the Atlas program and got nowhere.

Thor B or Thor Baker was to use the three-stage combination originally proposed in October 1957 to allow the Air Force to send the first space probe to the moon. It was renamed Thor Able-I and the first launch attempt on August 17 was thwarted when the first stage failed at T+70 seconds. The next month NASA took over the program, and the Thor Able-I's payloads became the first of NASA's long series of Pioneer deep-space probes. The USAF used an upgraded version of the Aerojet Able stage for another series of reentry vehicle tests in 1959, while NASA and DARPA continued to use developed versions of the rocket for launch of Explorer, Transit, and Tiros satellites. Finally the addition of solid rocket boosters allowed larger upper stages to be carried and payload to be increased in the Delta series of rockets. The evolutionary descendant of the Thor Able, the Delta 7000, was still flying in the 21st Century. Payload had increased from 100 kg to over 5 metric tons, and the Delta was the most reliable and economical launch vehicle ever produced in the United States.

LEO Payload: 120 kg (260 lb) to a 640 km orbit at 48.00 degrees. Flyaway Unit Cost 1985$: 8.930 million.

Stage Data - Thor Able

  • Stage 1. 1 x Thor DM-19. Gross Mass: 49,340 kg (108,770 lb). Empty Mass: 3,125 kg (6,889 lb). Thrust (vac): 758.711 kN (170,565 lbf). Isp: 282 sec. Burn time: 165 sec. Isp(sl): 248 sec. Diameter: 2.44 m (8.00 ft). Span: 2.44 m (8.00 ft). Length: 18.42 m (60.43 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: LR-79-7. Status: Out of Production.
  • Stage 2. 1 x Able. Gross Mass: 2,268 kg (5,000 lb). Empty Mass: 816 kg (1,798 lb). Thrust (vac): 34.300 kN (7,711 lbf). Isp: 270 sec. Burn time: 115 sec. Isp(sl): 240 sec. Diameter: 0.84 m (2.75 ft). Span: 0.84 m (2.75 ft). Length: 6.57 m (21.55 ft). Propellants: Nitric acid/UDMH. No Engines: 1. Engine: AJ10-101. Status: Out of Production.


More at: Thor Able.

Family: orbital launch vehicle. Country: USA. Engines: LR79-7, AJ10-101. Spacecraft: Pioneer 0-1-2, S-2, Transit, Pioneer 5, TIROS. Launch Sites: Cape Canaveral, Cape Canaveral LC17A. Stages: Able, Thor DM-19. Agency: Douglas.
Photo Gallery

Thor Able 2Thor Able 2
Credit: © Thomas Kladiva - Thomas Kladiva


Thor-AbleThor-Able
Credit: US Air Force


Thor Able Thor Able
Thor Able - COSPAR 1959-004


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Thor Able-Star - COSPAR 1960-013


Thor Able Thor Able
Thor Able - 58


Thor AbleThor Able
Credit: © Mark Wade



1958 February 11 - . LV Family: Thor, Atlas, Titan, Navaho. Launch Vehicle: Thor Able, Thor Agena A.
  • The ballistic missile division informed command headquarters that as many as 14 Thor boosters would be available during the calendar year for special purpose flights. - . Spacecraft: Man-In-Space-Soonest.

    These were tentatively allocated as follows: three were assigned to Phase I "Able" series flights, six were assigned to the program for recoverable satellites, and five were assigned to Phase II "Able" for continued development leading to a Thor ICBM capability. (For a time Thor plus a second stage and warhead was considered as a means of acquiring an early emergency ICBM inventory well ahead of Atlas and Titan.) However, only eight additional launchings could be scheduled through 1958--three for Phase I "Able", three for recoverable satellites to be launched one a month beginning in October, and two in support of Phase II "Able" precisely guided reentry vehicles. Thus this appeared to be the maximum effort possible in the category of space related experimental flights essential to a more advance program. If a greater effort was desirable it would be necessary to obtain additional launching facilities, a problem that might be quickly and easily solved by modifying Navaho launch stands to accept Thor vehicles. (Msg, WDT 2-7E, AFBMD to ARDC, 11 Feb 58.)


1958 April 24 - . 00:10 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Able. FAILURE: Thor turbopump gearbox failed T+150 sec.. Failed Stage: 1.
  • Able RTV re-entry vehicle test flight - . Nation: USA. Agency: USAF. Spacecraft: Man-In-Space-Soonest. Apogee: 80 km (49 mi).

    Mouse 'Mia' not recovered. The Air Force launched a research test rocket which carried a mouse in the re-entry vehicle. This was the first small beginning of a research program to determine the requirements of a space life support system. (Msg SAFIS-3C 47151, SAF to AFBMD, 29 Apr 58.)


1958 April 25 - . LV Family: Thor, Titan. Launch Vehicle: Thor Able, Titan C.
  • The Air Force Ballistic Missile Division published the development plan for an Air Force Manned Military Space Systems Program. - . Spacecraft: Man-In-Space-Soonest, Lunex.

    The objective was to ". achieve an early capability to land a man on the moon and return him safely to earth. The program represented a reasonable level of accomplishment with a minimum of time and money and called for start of a high priority program (similar to that enjoyed by ballistic missiles) characterized by "concurrency" and single Air Force agency management. The complete program would be carried out in four phases: first, "Man-In-Space-Soonest," was to determine functional capabilities and limitations of man in space by means of earth orbital flights--beginning with an instrumented 2,900 pound re-entry body, then a primate passenger and, finally, a manned capsule. The second, designated "Man-In-Space-Sophisticated," would use a drag type 3, 200 pound re-entry vehicle, capable of a 14 day manned space flight. This device would be used for earth orbital flight only but it would perform experiments essential to the final phase of the lunar program. The third phase, "Lunar Reconnaissance," would explore the moon by television camera and by means of a soft landing of an instrumented package on the moonIs surface. The final phase of the projected program was "Manned Lunar Landing and Return, " which would first test equipment by circumlunar flights returning to earth with instrumented capsules containing animals. At this stage of project development payload capacity would be increased to 9,000 pounds. The spacecraft would then undertake a full scale flight to the moon and safe return to earth with an animal passenger. The climax of the entire project would then be a manned lunar landing, brief surface exploration, and return to earth. This would be followed by other circumlunar flights to fully explore the moon's surface and gather additional physical data. The program was scheduled for completion in December of 1965 at a total estimated cost of $1.5 billion. Program cost estimates were based on use of Air Force rocket hardware and available ground facilities thus eliminating much new development and construction funding. However, new launch vehicle combinations would have to be developed progressing in performance as follows: a Thor-Vanguard second stage, a Thor-fluorine second stage, a "super" Titan with a fluorine-hydrazine second and third stages. Methods of landing involved use of retrorockets to insure a soft landing on the moon and return to earth through re-entry to a predetermined landing area. (USAF Manned Military Space Syst.em Development Plan, 25 Apr 58, prep by AFBMD.)


1958 July 10 - . 02:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Able.
  • Able RTV re-entry vehicle test flight - . Nation: USA. Agency: USAF. Apogee: 1,600 km (900 mi). Mouse 'Mia II' reached 1600 km altitude, flew 9600 km range, but re-entry vehicle not recovered..

1958 July 23 - . 22:13 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Thor. Launch Vehicle: Thor Able.
  • Able RTV re-entry vehicle test flight - . Nation: USA. Agency: USAF. Apogee: 1,600 km (900 mi).

    In its second successful flight test, the Thor/Able (Number 1.19) advanced reentry test vehicle demonstrated proper reentry of the advanced General Electric ablative nose cone during a 5,300-mile test flight. Two successful tests established the two-stage Thor/Able as a reliable vehicle for further special test programs. This allowed the Air Force and other government agencies to complete plans for more advanced space programs. Mouse 'Wickie' not recovered; nose cone lost.



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