Patent ID: 6499696
Filing Date: 2002-12-31
Classification: B64G,F02K

Abstract:
A rocket, comprising:a spacecraft; an upper stage interconnected with said spacecraft and comprising an upper stage rocket engine; and an upper stage rocket engine vent system fluidly interconnected with said upper stage rocket engine and comprising a first rocket engine vent system conduit, wherein said first rocket engine vent system conduit comprises first and second vent apertures that extend entirely through a wall thickness of a first conduit section of said first rocket engine vent system conduit, as well as a first flow diverter that is disposed within said first conduit section, wherein said first flow diverter comprises first and second vanes that are disposed within said first conduit section and that project toward said first and second vent apertures, respectively. 2.The rocket of claim 1, wherein:said first and second vent apertures are disposed in opposing relation.