Development and Testing of a Hydrogen Peroxide Injected Thrust Augmenting Nozzle for a Hybrid Rocket
Date of Award:
12-2019
Document Type:
Thesis
Degree Name:
Master of Science (MS)
Department:
Mechanical and Aerospace Engineering
Committee Chair(s)
Stephen Whitmore
Committee
Stephen Whitmore
Committee
David Geller
Committee
Geordie Richards
Abstract
During a rocket launch, the point at which the most thrust is needed is at lift-off where the rocket is the heaviest since it is full of propellant. Unfortunately, this is also the point at which rocket engines perform the most poorly due to the relatively high atmospheric pressure at sea level. The Thrust Augmenting Nozzle (TAN) investigated in this paper provides a solution to this dilemma. By injecting extra propellant into the nozzle but downstream of the throat, the internal nozzle pressure is raised and the thrust is increased, and the nozzle efficiency, or specific impulse is potentially improved as well. Using this concept, the payload capacity of a launch vehicle can be increased and provides an excellent option for single stage to orbit vehicles.
Checksum
e4f269b8ce1bf76999488557650cd80f
Recommended Citation
Heiner, Mark C., "Development and Testing of a Hydrogen Peroxide Injected Thrust Augmenting Nozzle for a Hybrid Rocket" (2019). All Graduate Theses and Dissertations, Spring 1920 to Summer 2023. 7630.
https://digitalcommons.usu.edu/etd/7630
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