Structures for propulsion system: design and analysis of a hybrid rocket combustion chamber

The subsequent thesis aims to offer the theoretical basis on which the MATLAB code for the Start-Up HyImpulse Technologies has been written, concerning the design and analysis of combustion chamber behaviour in composite material for a hybrid mini-launcher. At first, it is provided with an overview of the socio-economic reasons for which investment in the design of such launchers stimulates promising expectations. Space-Works and Euroconsult economic forecasting predictions are examined. Subsequently, the reader is introduced to the types of materials available and adopted for combustion chambers. Specifically, the characteristics for polymer matrix materials with carbon fibre reinforcement, for the case, and glass fibre, for the insulation, are analyzed. Moreover, the theory used to predict the material fibre-reinforced materials’ properties and behaviour, in case the properties of the separate components, matrix and fibre, are known, is clarified. Regarding the geometry of a combustion chamber, an overview of the widespread theoretical basis for its design of combustion chambers is offered, comprehensive of usual simplifications such as associating the design to cylindrical pressure vessels with closing domes. Focusing on the geometry of the chamber, since the cylindrical section is dictated by the propulsive requirements of the launcher, as it hosts the solid fuel, different modalities to generate the dome’s end contour is outlined. The whole theoretical overview offers the basis on which the code has been written: it lets the user to input or choose the preferred characteristics and approach, such as the different options and subsequently theories available for the ending domes, and then perform stress analysis and lay-up optimization. In conclusion, it is offered a brief glimpse of the setting of the manufacturing process, its optimisation and the testing of CFRP pressure vessel with geodesic dome realized in house.