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Abstract
Charl E Janeke
Asonic Aerospike Protocol -- US Patent #6213431, 4/01
A linear aerospike rocket engine has a tapered body, a slanted or curved reaction plane, a
leading end, and a trailing end. A first fuel injector is located at the leading end and
directs a first fuel towards the reaction plane. A second fuel injector is located in
between the leading end and trailing end and directs a second fuel towards the reaction plane.
The second fuel injector helps to increase propulsive pressure across the reaction plane and
inhibits boundary layer separation. A vortex may be induced parallel to the reaction plane to
help increase propulsive pressure across the reaction plane. The vortex is induced using a
flap or spoiler, a rotatable turbine, or at least two fuel injectors that direct fuel
in counter current directions across the reaction plane.
The reaction plane may be corrugated, dimpled, grooved, or coated with a special material
to inhibit boundary layer separation from the reaction plane. Alternatively, Wheeler vortex
generators may be attached to the leading end and/or to the reaction plane to inhibit
separation of the boundary layer.
Engines having different length reaction planes may be used for different flight regimes
to optimize the thrust and/or engine efficiency. The engines may use a dual-fuel combination
of a H2 fuel and a hydrocarbon fuel to increase the payload capacity of the space plane.
A bell engine may be used in conjunction with the linear aerospike engine in outer space
for optimal engine efficiency.
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