Patent ID: 8938972
Filing Date: 2015-01-27
Classification: B64G,F02K

Abstract:
1. An engine apparatus for a flying object, comprising: a combustion chamber having a throat region and a nozzle region, said nozzle region having a nozzle wall; wherein the nozzle region expands from the throat region towards an exit end relative to a combustion chamber axis; wherein the nozzle region has associated therewith a skirt and a gap between the exit end and the skirt for admitting ambient air; said skirt having a skirt wall, said skirt being positioned downstream relative to the exit end of the nozzle region and surrounding the exit end of the nozzle region; said skirt having a skirt exit end and a cross-sectional area of the skirt exit end being greater than a cross-sectional area of the nozzle at the exit end of the nozzle; wherein the skirt wall is at an acute angle away from the combustion chamber axis with respect to the nozzle wall, at least at the exit end of the nozzle region; and wherein the skirt is fixed to a holding area from where the flying object which is provided with the engine apparatus is launched.