Hybrid Rocket Engine Ignition and Control

Author

Benjamin Letourneau, University of New HampshireFollow
Trevor Blampied, University of New Hampshire
Megan Johnson, University of New Hampshire
Thomas Pham, University of New Hampshire

Date of Award

Spring 2020

Project Type

Senior Honors Thesis

College or School

CEPS

Department

Electrical & Computer Engineering

Program or Major

Electrical Engineering

Degree Name

Bachelor of Science

First Advisor

Kent Chamberlin

Abstract

Control of a hybrid rocket engine is dependent upon a robust system capable of executing commands at precise times. In order to accomplish this, hardware systems must be in place to control the flow of a pressurized gas and provide feedback to launch site personnel. Through the use of solenoid valves and wireless transceivers, control over the thrust of a rocket can be accomplished. In order to understand this information and provide a user-friendly interface to complete this, a launch control module is used. Through the combined capabilities of the two system it becomes possible to test and launch a hybrid engine rocket in a safe and efficient manner.

Recommended Citation

Letourneau, Benjamin; Blampied, Trevor; Johnson, Megan; and Pham, Thomas, "Hybrid Rocket Engine Ignition and Control" (2020). Honors Theses and Capstones. 481.
https://scholars.unh.edu/honors/481