Sprint (missile)

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Sprint
Sprint-i-box.jpg
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 3,500 kilograms (7,700 lb)
Length 8.20 metres (26.9 ft)
Diameter 1.35 metres (53 in)
Warhead W66 nuclear low kt

Engine 1st Stage: Hercules X-265 (2,900 kilonewtons (650,000 lbf);
2nd Stage: Hercules X-271
Operational
range
40 kilometres (25 mi)
Flight ceiling 30 kilometres (19 mi)
Speed Mach Mach 10 (12,250 km/h; 7,610 mph; 3.403 km/s)
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.[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 2,900 kN (650,000 lbf) of thrust. 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[edit]

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]

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 & Propellant[edit]

The first stage, 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]

Survivors[edit]

See also[edit]

References[edit]

External links[edit]