Thermal Rocket Propulsion
Version 2.10
B.T.C. Zandbergen (TU Delft - Space Systems Egineering)
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Abstract
This document presents and details the basic theory and the associated methodology used at TU-Delft/AE to design thermal rocket propulsion systems. Focus is on the design of chemical rocket systems as well as cold and warm/hot gas propulsion systems. Theory presented starts with the fundamentals of (thermal) rocket propulsion assuming ideal motor conditions, followed by a discussion of rocket nozzle design, chemical and thermal rocket propellants and their attainable flame temperatures or the energy required to attain some temperature, the heat transfer that occurs in the motor. This is followed by a more in dept discussion/presentation of theory related to the design of the combustor for liquid, hybrid and solid rocket motors. Thirdly attention is paid to the means necessary to store and move the propellants from the storage to the combustor zone. Finally, attention is paid to igniting and controlling such rocket motors, including thrust vector control.
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