Power cartridges are designed and developed for use in military aircraft in association with High Energy Materials Research Laboratory, Pune. During development, the cartridge is fired in a closed vessel to generate basic design parameters. When the cartridge is fired, the heat is lost to the walls of the vessel due to conduction, convection, radiation, and to some extent, by expansion of the vessel. An attempt has been made to estimate the heat loss from the vessel and the surrounding. The aim of this study was to lay down the technical results theoretically and their validation through experiments.
Surface area of the vessel Co-volume of gas Charge weight of propellant Specific heat at constant volume Specific heat at constant pressure Mean molar heat capacities of gaseous products Internal dia of vessel Force constant of propellant Overall heat transfer coefficient Heat loss by propellant Thermal conductivity Length of closed vessel Molecular weight Mass of gaseous products Number of moles of gas per unit mass Maximum pressure obtained from Absolute pressure of gas Amount of heat generated by propellant Gas constant for products of combustion Temperature of propellant gas Ambient temperature Adiabatic flame temperature of propellant Time when propellant burns Temperature difference Volume of gas Specific volume of gas Constant, 3.147 Ratio of specific heat for propellant gases
Closed vessel, heat transfer, heat loss, heat generation
