Design of an Aerospike Rocket Nozzle for Integration with a Hybrid Rocket Motor

Authors

Jeffrey L. Smith, Brigham Young University
Dr. Paul F. Eastman, Brigham Young University

Keywords

aerospike rocket nozzle, hybrid rocket motor, bell shaped nozzles

College

Ira A. Fulton College of Engineering and Technology

Department

Mechanical Engineering

Abstract

Safe, reliable, technologies are needed to launch a new generation of astronauts and space tourists into space. The aerospike nozzle is more efficient than traditional bell shaped nozzles and is safer because of lower combustion chamber pressure. These excellent performance characteristics have never before been tested in conjunction with a hybrid rocket motor. This paper presents the design and testing method for an aerospike rocket.

Recommended Citation

Smith, Jeffrey L. and Eastman, Dr. Paul F. (2013) "Design of an Aerospike Rocket Nozzle for Integration with a Hybrid Rocket Motor," Journal of Undergraduate Research: Vol. 2013: Iss. 1, Article 1941.
Available at: https://scholarsarchive.byu.edu/jur/vol2013/iss1/1941