Asonic aerospike engine
Patent 6213431 Issued on April 10, 2001. Estimated Expiration Date: 
September 29, 2018. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.
September 29, 2018. Estimated Expiration Date is calculated based on simple USPTO term provisions. It does not account for terminal disclaimers, term adjustments, failure to pay maintenance fees, or other factors which might affect the term of a patent.Patent References 3630449 Aerospace plane and engine therefor Dual-fuel, dual-mode rocket engine Aerospace plane and engine Integrated aerospike engine and aerobrake for a spacecraft Tip vortex generation technology for creating a lift enhancing and drag reducing upwash effect Mass producible launch system Patent #: 6036144 InventorApplicationNo. 162930 filed on 09/29/1998US Classes:60/204Method of operationExaminersPrimary: Poon, Peter M.Assistant: Palo, Francis T. Attorney, Agent or FirmInternational ClassB64G 001/40AbstractA 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.Other References
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