Sprint (missile)


Sprint missile in flight
Type Anti-ballistic missile
Place of origin United States
Service history
In service 1972
Production history
Manufacturer Martin Marietta
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
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)
Radio command guidance

The Sprint was a two-stage, solid-fuel anti-ballistic missile (ABM), armed with a W66 enhanced radiation thermonuclear warhead. It was designed to intercept incoming reentry vehicles (RV) after they had descended below about 60 kilometres (37 mi) altitude, where the thickening air stripped away any decoys or radar reflectors and exposed the RV to observation by the radar. As the RV would be travelling at about 5 miles (8.0 km) per second, Sprint had to have phenomenal performance to perform an interception in the few seconds before the RV reached its target.

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] The high temperature caused a plasma to form around the missile, requiring extremely powerful radio signals to reach it for guidance.

Sprint was the centerpiece of the Nike-X system, which concentrated on placing bases around large cities to intercept Soviet warheads. As the cost of such a system quickly became untenable as the Soviets added more ICBMs to their fleet, Nike-X was abandoned. In its place came the Sentinel program which used Sprint as a last-ditch defense against RVs that evaded the much longer-ranged LIM-49 Spartan. Sentinel was itself changed to become the Safeguard program, which was operation only for a few months 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.

Some work on an improved Sprint II was carried out in the early 1970s, but cancelled as US ABM policy changed.


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 one to eighteen miles altitude (1.5 to 30 km) 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
White Sands Missile Range Museum HIBEX rocket display

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 anti-ballistic missile "in a similar vein to Sprint".[1] HIBEX employed a star-grain "composite modified double-base propellant", known as FDN-80, created from the mixing of ammonium perchlorate, aluminium, and Double Base powder, with zirconium staples (0.125 inches in length) embedded or "randomly dispersed" throughout the matrix.[5]

The small "Thunderbird" rocket of 1947 produced an acceleration of 100 G with a polysulfide composite propellant, star-grained cross section solid rocket motor.[6]

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.[7][8]


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


See also


Wikimedia Commons has media related to Sprint missiles.
This article is issued from Wikipedia - version of the 11/1/2016. The text is available under the Creative Commons Attribution/Share Alike but additional terms may apply for the media files.