Boring or penetrating the earth – Boring by directly applying heat to fluidize or comminute – Combustion is confined chamber having restricted discharge...
Patent
1989-06-28
1991-06-11
Kisliuk, Bruce M.
Boring or penetrating the earth
Boring by directly applying heat to fluidize or comminute
Combustion is confined chamber having restricted discharge...
175 17, 175 18, 299 14, 248171, 2481883, E21B 714, E21B 718
Patent
active
050224700
ABSTRACT:
An autonomous ice penetrator/payload delivery system is provided which, when once launched from its parent vehicle will, upon reaching the surface of the ice automatically right itself to proper orientation with respect to the ice surface for penetration. A modified solid propellant rocket engine is used as the heat source to penetrate the ice rapidly and automatically is ignited upon the ice pentrator/payload containment vessel attaining proper orientation with its longitudinal axis substantially normal to the ice surface. The hot gasses of combustion produced by the modified rocket engine impinge upon the ice thereby melting it. As the ice is melted and penetrated, the penetrator/payload containment vessel will follow the receding ice surface either by gravity, or by motive forces provided by the modified rocket engine, or both. In situations where the ice penetrator is launched below the surface of the ice, buoyancy built into the penetrator system containment vessel will cause it to penetrate the ice either due to its buoyancy alone or in conjunction with a motive force developed by the modified rocket engine. The penetrator system container in conjunction with the bore hole formed by the melting ice also functions as a guide to maintain verticality of the penetrator during the initial stages of penetration of the ice surface. The walls of the subsequent bore hole formed in the ice and the generally long, cylindrical shape of the penetrator/payload containment vessel body naturally coact to maintain the vertical penetration angle.
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K. W. Pearce "Some Thrust Control Methods for Solid Propellant Rockets" Journal of the Royal Aeronautical Society, vol. 65, Oct. 1961, p. 680.
Andersen James K.
White James W.
Helzer Charles W.
Kisliuk Bruce M.
Ocean Systems Research, Inc.
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