Space Shuttle Main Engine
Chemical Rocket Propulsion
Hybrid Rocket Motor Design Project: One of the main components
of this course is the semester design project in which each student team
designs, builds and tests an 10 lbf thrust hybrid rocket motor.
The thrust chambers are fabricated from aluminum and the nozzles are
fabricated from graphite. Solid fuel grains consisting of
HTPB and HTPB/Al are produced by each team. The oxidizer is gaseous
oxygen supplied at 500 SLPM. The chamber pressure is constrained
to 150 psig. Each rocket is tested on a thrust stand that enables
the measurement of instanteous oxygen mass flow rate, chamber pressure
and thrust. With these data, each team is able to measure
thrust (F), specific impulse
(Isp), characteristic exhaust velocity (C*), thrust coefficient (Cf) and
compare these measurements to their theoretical models, which predicted
instaneous O/F, C*, Pc, and thrust.
Instructor: Anthony J. Marchese
Instructions for the final design report can be downloaded here
Powerpoint presentation on "paper4" design project here.
IREC 2015 Team:
In parallel with the 2015 Rockets Class, we entered a team in the
2015 Intercollegiate Rocket Engineering Competition. The team
(John Whitmore, Joe Pointer, Shawn Nicholson and Geoff Pietz) built an
HTPB/paraffin/N2O hybrid rocket that generated 400 lb
thrust and launched a payload of 10 lbm to an altitude of 4,000
feet. Theirs was the only hybrid rocket to successfully launch
and retrieve in the past 2 years of the competition and the team was
awarded the Dr. Gil Moore Award for Innovation:
Team 0 (2005):
Is this valve open?
Rocket Motor Thrust Stand
University • Fort Collins, CO 80523 •
Phone / 970.491.2328