Lockheed X-17

Infobox Weapon
is_missile=yes
name=Lockheed X-17


caption=
origin=
type=Atmospheric reentry testing
used_by=
manufacturer=Lockheed
unit_cost=
propellant=
production_date=
service=
engine=1st stage:1x Thiokol XM20 Sergeant solid-fuel rocket, 48,000 lbf (213 kN)
2nd stage:3x Thiokol XM19 Recruit solid-fuel rocket, 33,900 lbf (150 kN) (each)
3rd stage:1x Thiokol XM19E1 Recruit solid-fuel rocket, 35,950 lbf (160 kN)
engine_power=
weight=
length=40 ft 4 in (12.3 m)
height=
diameter=1st stage: 2 ft 7 in (0.79 m)
2nd stage: 2 ft 5 in (0.43 m)
3rd stage: 0 ft 9.7 in (0.25 m)
wingspan=7 ft 7 in (2.3 m)
speed=Mach 14.5
vehicle_range=135 miles (217 km)
ceiling=
altitude=250 mi (400 km)
filling=
guidance=
detonation=
launch_platform=
The Lockheed X-17 was a three stage solid-fuel research rocket to test the effects of high mach reentry. The first stage of the X-17 carried the rocket to a height of convert|17|mi|km before burning out. The rocket would then coast on momentum to about convert|100|mi 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 convert|9000|mph at Patrick AFB. [E. Emme, ed., "Aeronautics and Astronautics, 1915-1960", p. 85.] Ultimately the X-17 would be travelling 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. [cite web|url=http://nuclearweaponarchive.org/Usa/Tests/Argus.html|title=Operation Argus tests|author=Carey Sublette|publisher=Nuclear Weapon Archive|date=20 September 1997|accessdate=2008-01-11]

References

* [http://www.designation-systems.net/dusrm/app1/x-17.html X-17 History]
* [http://users.dbscorp.net/jmustain/x-17.htm X-17 Specs]


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