Lockheed X-17

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"X-17" redirects here. For other uses, see X17 (disambiguation).
Lockheed X-17
Lockheed X-17 horizontal.jpg
TypeAtmospheric reentry testing
Production history
ManufacturerLockheed Corporation
Specifications
Length40 ft 4 in (12.3 m)
Diameter1st stage: 2 ft 7 in (0.79 m)
2nd stage: 1 ft 5 in (0.43 m)
3rd stage: 0 ft 9.7 in (0.25 m)
Engine1st stage:1× Thiokol Sergeant solid-fuel rocket, 48,000 lbf (213 kN)
2nd stage: 3× Recruit solid-fuel rocket, 33,900 lbf (150 kN) (each)
3rd stage: 1× Recruit solid-fuel rocket, 35,950 lbf (160 kN)
Wingspan7 ft 7 in (2.3 m)
Operational
range
135 miles (217 km)
Flight altitude250 mi (400 km)
Maximum speed Mach 14.5

The Lockheed X-17 was a three-stage solid-fuel research rocket to test the effects of high mach atmospheric reentry. The first stage of the X-17 carried the rocket to a height of 17 miles (27 km) before burning out. The rocket would then coast on momentum to about 100 miles (160 km) before nosing down for reentry. The second stage engine would then fire before jettisoning and igniting the third and final stage. On April 24, 1957, an X-17 reached a speed of 9,000 miles per hour (14,000 km/h) at Patrick AFB.[1] Ultimately the X-17 would be traveling towards Earth at up to Mach 14.5.

The X-17 was also used as the booster for the Operation Argus series of three high-altitude nuclear tests conducted in the South Atlantic in 1958.[2]

The rocket engine used by the rocket is called 1.5KS35000, a solid propellant rocket engine designed by Thiokol. It was used in at least 23 launches.[3][4]

References[]

  1. ^ E. Emme, ed., Aeronautics and Astronautics, 1915–1960, p. 85.
  2. ^ Carey Sublette (20 September 1997). "Operation Argus tests". Nuclear Weapon Archive. Retrieved 2008-01-11.
  3. ^ McDowell, Jonathan (February 2007). "Stages". Retrieved 2010-03-02.[unreliable source?]
  4. ^ 1.5KS35000[unreliable source?]

External links[]

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