Conceptual Design and Optimization of Hybrid Rockets
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2021-01-14
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Abstract
A framework was developed to perform conceptual multi-disciplinary design parametric and optimization studies of single-stage sub-orbital flight vehicles, and two-stage-to-orbit flight vehicles, that employ hybrid rocket engines as the principal means of propulsion. The framework was written in the Python programming language and incorporates many sub-disciplines to generate vehicle designs, model the relevant physics, and analyze flight performance. The relative performance (payload fraction capability) of different vehicle masses and feed system/propellant configurations was found. The major findings include conceptually viable pressure-fed and electric pump-fed two-stage-to-orbit configurations taking advantage of relatively low combustion pressures in increasing overall performance. The smallest launch vehicles assessed had lower payload fractions compared to larger vehicles. The vehicle configurations resulting in the highest performance used liquid oxygen and paraffin wax propellants. The smallest viable orbital launch vehicle, the vehicle with the highest payload fraction for the smallest payload considered, was a liquid oxygen and paraffin-wax-based launcher. The highest payload fraction found for the smallest payload class was 0.60 % of gross mass for a 10 kg payload delivered to 500 km Sun-synchronous orbit. The highest payload fraction for the investigated 150 kg payload class for the same Sun-synchronous orbit was found to be 1.2 %.
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Messinger, T. L. (2021). Conceptual Design and Optimization of Hybrid Rockets (Master's thesis, University of Calgary, Calgary, Canada). Retrieved from https://prism.ucalgary.ca.