Why we are exploring hybrid rocket technology.
A brief explanation of the hybrid rocket's combustion process.
Project: Prometheus
Project Prometheus is a joint project between the Illini Space Development Society and the University of Illinois Aerospace Engineering Department to build an operate a lab scale hybrid rocket motor. The project is currently in the construction phase with a planned first firing later this year. There are two primary goals of the project. The first is to build a test motor capable of being used to test and verify current theories on the nature of hybrid rocket combustion processes, and the second is to provide a combustion lab where the students at the U of I can gain experience in the techniques used in testing rocket engines.
The current plans for the hybrid rocket engine are to use Plexiglas (tm) as the solid fuel and gaseous oxygen as the oxidizer. The motor will be approximately 2 feet long with an outer diameter of 3.25 inches. The rocket will produce around 200 lbs of thrust at chamber pressure of about 500 psia.
Team Members
Some drawings of the current rocket design
- The Outer Casing
- The Injector System
- The Front Injector Flange
- The Nozzle
- The Flow System
- The Fuel Grain
- The Test Stand
For more information on the project contact Jeff Norr at j-norr@uiuc.edu
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