PGM-17 Thor

File:Thor IRBM.jpg

A Thor intermediate-range ballistic missile.

Thor was the first operational ballistic missile in the arsenal of the United States. Thor was Template:Ft to m in height and Template:Ft to m in diameter. Named after the Norse god of Thunder, it was deployed in the UK between 1959 and September 1963 as an Intermediate Range Ballistic Missile (IRBM) with thermonuclear warheads. It was later augmented in the U.S. IRBM arsenal by the PGM-19 Jupiter.

A large family of space launch vehicles — the Delta rockets — were derived from the Thor design. A modified version is still in use today at the first stage of the Delta II.

Design and development

Fearful that the Soviet Union would deploy a long-range ballistic missile before the United States, in January 1956 the Air Force began developing the Thor, a 1,500 mile (2,400 km) intermediate-range ballistic missile (IRBM). The Thor program unfolded with amazing speed, and within 3 years of the program’s inception the first Thor squadron became operational in the UK. One of the perks of the design was that, unlike the Jupiter IRBM, the Thor was able to be carried by the USAF's cargo aircraft of the time, which made its deployment more rapid, although the launch facilities were not transportable, and had to be built on site. The Thor was a stop-gap measure, however, and once the first generation of ICBMs based in the United States became operational, the Thor missiles were quickly retired. The last of the missiles was withdrawn from operational alert in 1963.

A small number of Thors, converted to "Thrust Augumented Delta" launchers remained operational in the Anti-Satellite missile role as Project 637 until April 1975. These missiles were based on Johnston Island in the Pacific and had the ability to destroy satellites in low Earth orbit. With prior warning of an impending launch, they could destroy a Soviet spy satellite soon after orbital insertion.

These missiles remain in storage, and could be reactivated, though the W-49 Mod 6 warheads were all dismantled by June 1976.

Initial development as an IRBM

Development of the Thor was initiated by the US Air Force in 1954 as a Tactical Ballistic Missile. The goal was a missile system that could deliver a nuclear warhead over a distance of 1150 to 2300 miles (1900 to 3700 km) with a CEP of 2 miles (3 km). This range would allow Moscow to be hit from a launch site in the UK.

The initial design studies were headed by Cmdr. Robert Truax (US. Navy) and Dr. Adolph K. Thiel (Ramo-Wooldridge Corp, formerly of Redstone Arsenal). They refined the specs to an IRBM with:

• A 1750 mile (2,820 km) range
• 8 ft (2.4 m) diameter, 65 ft (20 m) long (so it could be carried by Douglas C-124 Globemaster)
• A gross takeoff weight of 110,000 lb (50,000 kg)
• Propulsion provided by half of the Navaho-derived Atlas booster engine (due, largely, to the lack of any alternatives at this early date)
• 10,000 mph (4.5 km/s) maximum speed during warhead reentry
• AC Spark Plug inertial guidance system with radio backup (for low susceptibility to enemy disruption)

On November 30, 1955 three companies were given one week to bid on the project: Douglas, Lockheed, and North American Aviation. They were asked to create "a management team that could pull together existing technology, skills, abilities, and techniques in 'an unprecedented time.'" On December 27, 1955 Douglas Aircraft Corporation was awarded the prime contract for the airframe and integration. The Rocketdyne division of North American Aviation was awarded the engine contract, AC Spark Plug the primary inertial guidance system, Bell Labs the backup radio guidance system, and General Electric the nose cone/reentry vehicle.

Douglas further refined the design by choosing bolted tank bulkheads (as opposed to the initially suggested welded ones) and a tapered fuel tank for improved aerodynamics. The engine was developed as a direct descendant of the Atlas MA-3 booster engine. Changes involved removal of one thrust chamber and a rerouting of the plumbing to allow the engine to fit within the smaller Thor boat-tail. Engine tests were being performed as of March 1956. The first engineering model engine was available in June, followed by the first flight engine in September. Engine development was complicated by serious turbopump problems. Early Thor engines suffered from what was known as "Bearing Walking", whereby the turbopump bearings shift axially within their housing, causing rapid wear and the bearings to seize.

First launches

Thor test launches were to be from LC17 at Cape Canaveral. The development schedule was so compressed that plans for the Atlas bunker were used to allow the completion of the facility in time. Nevertheless pad LC17-B was just ready for the first test flight.

The first flight of the Thor IRBM was on 25 January 1957. The first airframe, number 101, was delivered in October of the previous year. The vehicle reached an apogee of 6 in (150 mm) whereupon contamination destroyed a LOX supply valve causing the engine to lose thrust. The Thor slid backwards through the launch ring and exploded on contact with the thrust deflector. Serious pad damage occurred.

The second Thor flight (102) lasted 35 seconds after an April 1957 launch. It was ended by a range safety officer who acted on faulty data from a readout which showed the missile heading inland over Florida.

Thor vehicle 103 (May 1957) exploded on the pad during tanking due to a faulty main fuel valve resulting in tank overpressurization leading to tank rupture.

Thor vehicle 104 (Aug 1957) broke up after 92 seconds due to a loss of guidance.

Thor vehicle 105 (20 September 1957), 21 months after the start of construction, flew 1,100 miles (1,800 km) downrange. Estimated range without the extra load of the R and D instrumentation was 1,500 miles (2,400 km).

1957 saw five more flights, the longest of which covered 2,700 miles (4,300 km).

Deployment

Thor was deployed to the UK starting in August 1958, operated by twenty squadrons of the Royal Air Force. The first active unit was No. 77 Squadron RAF at RAF Feltwell in 1958, with the remaining units becoming active in 1959. All were deactivated by September 1963.

All sixty of the Thor missiles deployed in the UK were based at above-ground launch sites. The missiles were stored horizontally on transporter-erector trailers and covered by a retractable missile shelter. To fire the weapon, the crew electronically rolled back the missile shelter and then, using a powerful hydraulic launcher-erector, lifted the missile to an upright position. Once it was standing on the launch mount, the missile was fueled and fired. The entire launch sequence took about 15 minutes. Main engine burn time was almost 2.5 minutes, boosting the missile to a speed of 14,400 ft/s (4.4 km/s). Ten minutes into its flight the missile reached an altitude of 280 miles (450 km), close to the apogee of its elliptical flight path. At that point the reentry vehicle separated from the fuselage and began its descent down toward the target. Total flight time from launch to impact was about 18 minutes.

The Thor was initially deployed with a very blunt conical G.E. Mk 2 'heat sink' re-entry vehicle. They were later converted to the slender G.E. Mk 3 ablative RV. Both RVs contained a W-49 thermonuclear bomb of 1.44 megatons yield.

Noteworthy Thor IRBM flights

• 4 June 1962, failed Starfish flight, Thor destroyed, nuclear device lost.
• 20 June 1962, failed Bluegill Prime flight, Thor destroyed, nuclear device lost.
• 9 July 1962, Thor missile 195 launched a Mk4 reentry vehicle containing a W49 thermonuclear warhead to an altitude of 250 miles (400 km). The warhead detonated with a yield of 1.45 Mt of TNT (6.07 PJ). This was the Starfish Prime event of nuclear test operation Dominic-Fishbowl.

Thor becomes a launch vehicle

The Thor rocket was also used as a space launch vehicle. It was the first in a large family of space launch vehicles -- the Delta rockets. Thor's descendants fly to this day as the Delta II and Delta IV.

Operators

Template:UK: Royal Air Force Template:USA: United States Air Force

Specifications

• Popular Name: Thor.
• Type: Intermediate range ballistic missile.
• IOC: 1958. Year: 1958.
• Family: Thor IRBM, Thor DM-18 (single stage LV); Thor DM-19 (rocket 1st stage), Thor DM-21 (rocket 1st stage), Thor DSV-2D,E,F,G (suborbital LV), Thor DSV-2J (anti-ballistic missile), Thor DSV-2U (orbital launch vehicle).
• Country: USA. Department of Defense
• Designation: PGM-17A.
• Alternate Designation: SM-75, PTM-17A, USM-75
• Manufacturer: Douglas Aircraft Company
• Thrust (vac): 760 kN
• Liftoff Thrust (sl): 670 kN (150,000 lbf)
• Isp: 282 s (2.77 kN·s/kg)
• Isp(sl): 248 s (2.43 kN·s/kg)
• Burn time: 165 s
• Core Diameter: 2.44 m
• Total Length: 19.82 m (65 ft)
• Span: 2.74 m (8 ft)
• Weight: 49,800 kg (110,000 lb)
• Empty Weight: 3,125 kg
• Standard warhead mass: 1,000 kg
• Maximum range: 2,400 km. (1,500 miles)
• Ceiling: 480 km (300 miles)
• Number Standard Warheads: 1.
• Standard RV: Mk. 2.
• Standard warhead: W49.
• Standard warhead yield: 1,440 kt of TNT (6.02 PJ)
• Standard warhead CEP: 1 km
• Boost Propulsion: Liquid rocket, Lox/Kerosene.
• Power plant:
  • Main: Rocketdyne LR79-NA-9 (Model S-3D); 666 kN (150000 lbf)
  • Vernier: 2x Rocketdyne LR101-NA; 4.5 kN (1000 lbf) each
  • Manufacturer Name: MB-1.
  • Government Designation: LR-79-7.
  • Designer: Rocketdyne.
  • Developed in: 1955.
  • Application:
  • Used on stages: Thor DM-19.
  • Used on launch vehicles: Delta, Thor, Thor Able, Thor Agena A, Thor Agena B, Thor Agena D, Thor Burner.
  • Propellants: Lox/Kerosene
  • Thrust (vac): 760 kN
  • Isp: 282 s (2.77 kN·s/kg)
  • Isp (sea level): 248 s (2.43 kN·s/kg)
  • Burn time: 165 s
  • Mass Engine: 643 kg
  • Diameter: 2.44 m
  • Chambers: 1
  • Chamber Pressure: 4.1 MPa
  • Area Ratio: 8.00
  • Thrust to Weight Ratio: 120.32
  • Country: USA
  • Status: Out of Production.
  • First Flight: 1958
  • Last Flight: 1980
  • Flown: 145.
  • Comments: Designed for booster applications. Gas generator, pump-fed
• Guidance: Inertial
• Maximum speed: 17,740 km/h (11,000 mph)
• Development Cost US dollars: $500 million
• Recurring Price US dollars: $6.25 million
• Total Number Built: 224
• Total Development Built: 64
• Total Production Built: 160
• Flyaway Unit Cost: US$750,000 in 1958 dollars
• Launches: 59
• Failures: 14
• Success Rate: 76.27%
• First Launch Date: 25 January 1957
• Last Launch Date: 5 November 1975

References

• Forsyth, Kevin S. (2002). Delta: The Ultimate Thor. In Roger Launius and Dennis Jenkins (Eds.), To Reach The High Frontier: A History of U.S. Launch Vehicles. Lexington: University Press of Kentucky. ISBN 0-8131-2245-7
• Boyes, John. Project Emily - Thor IRBM and the RAF, Tempus Publishing, 2008. ISBN 978 0 7524 4611 0. also: Project Emily. The Thor IRBM and the Royal Air Force 1959-1963. pub: Prospero No 4, Journal of the British Rocketry Oral History Programme (BROHP) Spring 2007.

External links

• Thor from Encyclopedia Astronautica
• Thor IRBM History site
• History of the Delta Launch Vehicle
• UK Thor missile launch sites on Secret Bases website
• UK Thor deployment in Lincolnshire
• Maxwell Hunter, "Father of the Thor Rocket"

See also

Comparable aircraft

• Jupiter IRBM

Designation sequence

• M- sequence: MIM-14 - RGM-15 - CGM-16/HGM-16 - PGM-17 - MGM-18 - PGM-19 - ADM-20

B- sequence: -	SR-71	- GAM-72 - XSM-73 - SM-75 - TM-76 - GAM-77 - SM-78
	XGAM-71

Related lists

• List of military aircraft of the United States
• List of missiles

See also

• Strategic Air Command

This article is licensed under the GNU Free Documentation License. It uses material from the Wikipedia article "PGM-17 Thor".