Patent ID: 7909288
Filing Date: 2011-03-22
Classification: B64C,B64D,Y02T

Abstract:
1. A fuel tank positionable within a host aeronautical structure and having high energy absorption characteristics for aeronautical applications, the said fuel tank comprising: a substantially closed and substantially rigid main fuel tank comprising at least one lateral wall; at least one vent valve formed in the at least one lateral wall and which can be opened when a pressure exceeding a predetermined value is present within the substantially closed main fuel tank; a supplementary fuel tank configured to cooperate with the at least one lateral wall and adapted to receive fuel from said main fuel tank through said at least one vent valve when said at least one vent valve is open because of an overpressure within said main fuel tank; wherein said vent valve comprises a breakable membrane which is positioned to close a corresponding aperture, wherein said breakable membrane comprises a fragile material; and an aperture stiffener fixed to the at least one lateral wall, surrounding the at least one valve, and configured to provide rigidity reinforcement for the at least one lateral wall of the main fuel tank; wherein the aperture stiffener is in the form of a collar positioned around substantially only a circumference of the aperture of the vent valve.