Designing and Building a Hydrogen Peroxide-Kerosene Rocket Engine

摘要

Project Spartan Spear was composed of seven aerospace engineering undergraduates at San Jose State University that chose to design, build, and test a liquid bipropellant rocket engine for their senior design project. The mission of this rocket engine was designed to carry out was to be the propulsion system for an air launched, two stage launch vehicle capable of carrying CubeSats to Low Earth Orbit (LEO). An engine that featured regenerative cooling was designed and prototyped. Due to budget constraints an ablative model was instead designed, manufactured and tested. The purpose of this paper is to detail the combustor and injector design, analysis, fabrication, and test procedures, and test results.