An engine device for a missile, missile, test stand or launch pad for a missile, and method for reducing a side load on an engine device

摘要

An engine device for a missile is provided which comprises a combustion chamber with a neck region and a nozzle region with a nozzle wall, the nozzle region expanding from the neck region towards an outlet end with respect to a combustion chamber axis, the apron wall having an apron wall is assigned, which is positioned downstream with respect to the outlet end and surrounds the outlet end of the nozzle region, and wherein the skirt wall to the nozzle wall lies at an acute angle away from the combustion chamber axis at least at the outlet end of the nozzle region.