Date of Award


Degree Name

Master of Science


Mechanical Engineering


John F. Chessa

Second Advisor

Ahsan Choudhuri


One of the many goals for the Center of Space Exploration and Technology Research is the design and testing of liquid methane and liquid oxygen propulsion systems that is done by the students in charge of the projects. The reaction control engine is one of the few projects that is developed by the students and has been iterated since the proposed design. The current iteration of the engine has been designed and tested out in the Fabens [8] facility which characterized parts of the engine. To advance in its purpose, a flight configuration setup has been proposed in this Thesis that will go onto the proposed designed reaction control system. The Thesis presents how the RCS has been proposed, basing it off the objectives the system will carry out. Branching from the objectives are requirements needed from the thrusters that will be verified through proposed testing. This proposed testing is to characterize the flight configuration engine that will go onto the system and based on the results will guide for any modifications with the design. What can be done right now to verify the performance of the engine is run a Simulink model that a senior design student help propose which characterizes the engine and system and can optimize the design of the engine for future iterations.




Received from ProQuest

File Size

77 pages

File Format


Rights Holder

Gerardo Javier Ramirez Marquez

Available for download on Monday, February 24, 2121