This paper presents the first section of work carried out as part of a larger research investigation into the feasibility of engine type architecture for specific mission profiles, pertaining to next generational concepts of spacecraft propulsion. Significant work has been undertaken to improve the capability of an existing simulation code, HyPro, used to model all aspects of propulsion technologies, with a focus being given to developing gas turbine type components. The paper explores the implementation of an approach that circumvents the requirements for detailed component mapping and eliminates the need for a fixed, specified design point, presenting early stage validation data of the methodology selected for the modelling, which will go towards justifying its inclusion to the code library.

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