College

College of Engineering and Polymer Science

Date of Last Revision

2022-05-04 16:52:17

Major

Aerospace Systems Engineering

Honors Course

4900 497-001

Number of Credits

2

Degree Name

Bachelor of Science

Date of Expected Graduation

Spring 2022

Abstract

The purpose of this project is to take the current liquid rocket engine test stand design and implement an external pressurant instead of utilizing the 2-phase oxidizer vapor to pressurize itself and the fuel. The purpose behind the design is because the team is limited with the current design concerning burn time due to the amount of propellant they can put in the tanks and the pressure it can reach. The initial pressure is currently not held since there is no external input of mass into the tanks, as the propellant is leaving. Adding an external pressurant allow for the tank pressures to remain steady throughout the burn, which helps the team accurately characterize the system along with having consistent mass flow rates. This research and design also helped jumpstart the R&D liquid engine team of the propulsion branch of the Akronauts in pursuing a modification to the current system for future projects. The solutions in this paper better prepare the Akronauts to grow and expand with industry-related projects, providing experiences for students to excel in their careers.

Research Sponsor

Dr. Manigandan Kannan

First Reader

Elizabeth Clifford

Second Reader

Blake Bowser

Honors Faculty Advisor

Dr. Scott Sawyer

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