Asonic aerospike engine

Abstract

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 inhibit 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.

Dependencies are inferred from the claim text.