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Ablation and deceleration of mass-driver launched projectiles for space disposal of nuclear wastesThe energy cost of launching a projectile containing nuclear waste is two orders of magnitude lower with a mass driver than with a typical rocket system. A mass driver scheme will be feasible, however, only if ablation and deceleration are within certain tolerable limits. It is shown that if a hemisphere-cylinder-shaped projectile protected thermally with a graphite nose is launched vertically to attain a velocity of 17 km/sec at an altitude of 40 km, the mass loss from ablation during atmospheric flight will be less than 0.1 ton, provided the radius of the projectile is under 20 cm and the projectile's mass is of the order of 1 ton. The velocity loss from drag will vary from 0.4 to 30 km/sec, depending on the mass and radius of the projectile, the smaller velocity loss corresponding to large mass and small radius. Ablation is always within a tolerable range for schemes using a mass driver launcher to dispose of nuclear wastes outside the solar system. Deceleration can also be held in the tolerable range if the mass and diameter of the projectile are properly chosen.
Document ID
19810036370
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Park, C.
(NASA Ames Research Center Moffett Field, Calif., United States)
Bowen, S. W.
(Beam Engineering Co. Sunnyvale, Calif., United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1981
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
AIAA PAPER 81-0355
Meeting Information
Meeting: Aerospace Sciences Meeting
Location: St. Louis, MO
Start Date: January 12, 1981
End Date: January 15, 1981
Sponsors: American Institute of Aeronautics and Astronautics
Accession Number
81A20774
Distribution Limits
Public
Copyright
Other

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