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.

Other References

• Rocketdyne, The X-33 on the Internet, An Annotated Arachniography About the Technology;.quadrature..quadrature.http://www.hq.nasa.gov/office/pao/ History/x-33/aerospik.htm.
• NASA, Reusable Launch Vehicle Program Fact Sheet, 1997, RLV Program Fact Sheet;.quadrature..quadrature.http://www.hq.nasa.gov/office/pao/History/ x-33/rlv_facts.htm.
• Ken Davidian, The Aerospike Nozzle Frequently Asked Questions List;.quadrature..quadrature.http://www.hq.nasa.gov/office/pao/History/ x-33/aero_faq.htm