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Airbreathing missiles enable increased range compared to rockets due to significantly higher specific impulse. One type of airbreathing engines, suitable for missile propulsion, is the so-called ramjet engine. Three solid hydrocarbon compounds with high heat of combustion have been studied as potential fuels for ramjet engines. Two of these; diazabicyclooctane (DABCO or triethylenediamine, TEDA) and azobisisobutyronitrile (AIBN) appear to be too thermally unstable for practical use. The third, hexamine, is significantly more promising. However, the method of producing hexamine-based fuels free from bubbles must be studied further. In order to study the combustion in a ramjet motor, an experimental setup is required that can provide the combustion chamber with an airflow with the temperature, mass flow and pressure required to represent the intended flight Mach number. A facility for this purpose is available at FOI Grindsjön which however must be upgraded and inspected before any tests can be performed. The design and architecture of the air intakes strongly influence the characteristics of a ramjet engine. Therefore, in continued work, air intakes should also be studied. This requires a study case missile to be defined.