Book Description

A FORTRAN digital computer program was developed which is generally applicable for preliminary design tradeoff analyses of solid-propellant rocket motors for a variety of applications. The program computes rocket motor length, propellant and inert component weights, mass fraction, burn time, specific impulse, ideal stage burnout velocity, and other performance parameters as a function of input motor diameter, chamber pressure, thrust, payload mass, propellant ballistic properties, propellant web fraction, port-to-throat area ratio, and other required parameters. Either conical or contoured nozzle exit geometries may be analyzed. Options are available for considering a head-end propellant web and inert residual slivers.