Patent ID: 9688415
Date: 2017-06-27
CPC Classifications: B64C,B64D

Claim:
1. An aircraft hybrid fuel system, comprising: a main tank; a set of flexible bladders, the main tank and the set of flexible bladders defining a fuel containment space; and a set of pathways coupling the set of flexible bladders to the main tank, the set of pathways being constructed and arranged to vent gas out of the set of flexible bladders into the main tank while fuel from a fuel source is provided into the fuel containment space defined by the main tank and the set of flexible bladders; wherein each flexible bladder includes a venting end and a sealed end; wherein the set of pathways couples the venting end of each flexible bladder to the main tank; and wherein, when the aircraft is oriented at an angle in which the venting end of each flexible bladder is positioned above the sealed end of that flexible bladder, fuel provided into the fuel containment space fills the sealed end of each flexible bladder prior to filling the venting end of that flexible bladder.