Sprint (missile)

Sprint

Sprint missile in flight
Type Anti-ballistic missile
Place of origin United States
Service history
In service 1972
Production history
Manufacturer Martin Marietta
Specifications
Weight 7,700 pounds (3,500 kg)
Length 26.9 feet (8.20 m)
Diameter 53 inches (1.35 m)
Warhead W66 nuclear low kt
Engine 1st Stage: Hercules X-265 (650,000 pounds-force (2,900 kN);
2nd Stage: Hercules X-271
Operational
range
 25 miles (40 km)
Flight ceiling 19 miles (30 km)
Speed 12,250 kilometres per hour; 7,610 miles per hour; 3,403 metres per second (Mach 10)
Guidance
system
 Radio command guidance
Launch
platform
 Silo

The Sprint was a two-stage, solid-fuel anti-ballistic missile, armed with a W66 enhanced radiation thermonuclear warhead. It was designed as the short-range high-speed counterpart to the longer-range LIM-49 Spartan as part of the Sentinel program. Sentinel never became operational, but the technology was deployed briefly in a downsized version called the Safeguard program. The Sprint, like the Spartan, was in operational service for only a few months in the Safeguard program, from October 1975 to early 1976. Congressional opposition and high costs linked to its questionable economics and efficacy against the then emerging MIRV warheads of the Soviet Union, resulted in a very short operational period.

The Sprint accelerated at 100 g, reaching a speed of Mach 10 in 5 seconds. Such a high velocity at relatively low altitudes created skin temperatures up to 6200 °F (3400 °C), requiring an ablative shield to dissipate the heat.[1][2] It was designed for close-in defense against incoming nuclear weapons. As the last line of defense it was to intercept the reentry vehicles that had not been destroyed by the Spartan, with which it was deployed.

The conical Sprint was stored in and launched from a silo. To make the launch as quick as possible, the cover was blown off the silo by explosive charges; then the missile was ejected by an explosive-driven piston. As the missile cleared the silo, the first stage fired and the missile was tilted toward its target. The first stage was exhausted after only 1.2 seconds, but produced 650,000 lbf (2,900 kN) of thrust. On separation of the spent first stage, it disintegrated due to aerodynamic forces. The second stage fired within 1 – 2 seconds of launch. Interception at an altitude of 1,500 m to 30,000 m took at most 15 seconds.

The Sprint was controlled by ground-based radio command guidance, which tracked the incoming reentry vehicles with phased-array radar and guided the missile to its target.

The Sprint was armed with an enhanced radiation nuclear warhead with a yield reportedly of a few kilotons, though the exact number has not been declassified. The warhead was intended to destroy the incoming reentry vehicle primarily by neutron flux.

The first test of the Sprint missile took place at White Sands Missile Range on 17 November 1965.[3]

Design predecessors

See also: Nike Zeus
HIBEX rocket

The "HIBEX" (HIgh Boost EXperiment) missile is considered to be somewhat of a design predecessor and competitor to the Sprint missile, as it was a similar high acceleration missile in the early 1960s, with a technological transfer from that program to the Sprint development program occurring.[4] Both were tested at the White Sands Launch Complex 38. Although HIBEX's initial acceleration rate in G's was higher at near 400 G, its role was to intercept reentry vehicles at a much lower altitude than Sprint, 6,100 m, and it is considered to be a last ditch ABM missile "in a similar vein to Sprint".[5] HIBEX employed a star-grain "composite modified double-base propellant", known as FDN-80, created from the mixing of Ammonium perchlorate, Aluminum and Double Base powder with zirconium staples (0.125 inches in length) embedded or "randomly dispersed" throughout the matrix.[6]

The small "Thunderbird" rocket of 1947 produced an acceleration of 100 G with a polysulfide composite propellant, star-grained cross section solid rocket motor.[7]

Engines and propellant

The first stage's Hercules X-265 engine is believed to have contained alternating layers of zirconium "staples" embedded in nitrocellulose powder, followed by gelatinizing with nitroglycerine, thus forming a higher thrust double-base powder.[8][9]

Testing

The first test of the Sprint missile took place at White Sands Missile Range on 17 November 1965.[3]

By 1970, the Spartan had undergone 15 launch tests, achieving 11 successful, two partially successful and two failed missions using static points or simulated targets.[10] On August 28, 1970, a Spartan was launched from Kwajalein Atoll in the first intercept test against a live target, a Minuteman I ICBM launched from Vandenberg, in the first operational system test incorporating the prototype Missile Site Radar, MSR, and data center. Ground-based monitors determined that the interceptor passed within the kill distance of the target.[10]

Survivors

See also

References

  1. ↑ Sprint
  2. ↑ Designation-systems Directory of U.S. Military Rockets and Missiles. Martin Marietta Sprint
  3. 1 2 James Walker, Lewis Bernstein, Sharon Lang (2005). Seize the High Ground: The U.S. Army in Space and Missile Defense (PDF). Government Printing Office. ISBN 0160723086. 17 November 1965 First guided SPRINT flight test took place at WSMR
  4. ↑ III. HIBEX - UPSTAGE
  5. ↑ Sprint
  6. ↑ UpSTAGE TECHNOLOGY REPORT:SPECIAL MANUFACTURING AND FABRICATION 1972. McDonnell Douglas. pg 162-178, with impact sensitivity on G-24
  7. ↑ http://www.astronautix.com/articles/comlants.htm
  8. ↑ Up-ship. Sprint missile
  9. ↑ DTIC. by SB Moorhead - 1974
  10. 1 2 Sharon Watkins Lang, SMDC History: A Moment of Truth, August 28, 2014, USASMDC/ARSTRAT Historical Office (accessed 17 April 2016).
  11. ↑ http://www.city-data.com/articles/US-Army-Air-Defense-Artillery-Museum-El.html
  12. ↑ http://srmsc.org/mis2050.html
  13. ↑ ADA park (Fort Sill), photo journal of Daniel DeCristo

External links

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