Abstract: A propellant configuration for a solid propellant rocket motor, comprising a generally cylindrical housing containing a generally cylindrical main grain having a central cavity, and an igniter assembly supported in the central cavity and having means therein for bringing about combustion. At the time of actuation of the igniter assembly, hot gases are directed along flutes formed in the interior of the main grain, to cause burning thereof to take place. Advantageously, the propellant utilized in the main grain is the same as utilized in the igniter assembly, with the burn surface area of the igniter grain being in a pre-established relationship to the burn surface area of the fluted main propellant grain, such that the igniter grain will be totally consumed at the time that the flutes of the main propellant are consumed.