Abstract: Embodiments of the present invention provide a fuel tank communication system. The communication system includes a main body (30) used to connect two fuel bladder flanges (12, 20) to one another. The communication system provides two separate, independent locking features (42, 60) that can secure fuel bladders to one another.

Abstract: Embodiments of the present invention provide a fuel tank communication system. The communication system includes a main body (30) used to connect two fuel bladder flanges (12, 20) to one another. The communication system provides two separate, independent locking features (42, 60) that can secure fuel bladders to one another.

Abstract: Systems and methods for de-icing an aircraft surface. The systems create a shock pulse to create a shock activation. The shock pressure is designed to deform the surface of an erosion shield on the surface in order to expulse ice from the wing. The deformation may be between a negative to a positive shape. In one example, the de-icing occurs from a pulse delivered by pressurized fluid injected into and quickly removed from a recess between the aircraft surface and an erosion shield. A pulse of pressurized air or fluid may be injected into one or more cells formed in the recess, together or alternatively, according to the designed effect on the erosion shield surface.

Abstract: Embodiments of the present disclosure relate generally to systems and methods for de-icing an aircraft surface (14). The systems create a shock pulse to create a shock activation. The shock pressure is designed to deform the surface of an erosion shield (16) on the surface in order to expulse ice from the wing. The deformation may be between a negative to a positive shape. In one example, the de-icing occurs from a pulse delivered by pressurized fluid injected into and quickly removed from a recess (12) between the aircraft surface and an erosion shield. A pulse of pressurized air or fluid may be injected into one or more cells (32) formed in the recess, together or alternately, according to the desired effect on the erosion shield surface.

Abstract: A method of assembling a de-icing mat (3) on a piece of wing structure (1) includes shaping a shielding foil (2) so that the internal surface (5) thereof has a shape that complements the external surface (6) of the piece of wing structure (1). The method then includes securing the de-icing mat (3) to the internal surface (5) of said shielding foil (2), leaving a surface uncovered with the de-icing mat on the contour (8) of the shielding foil (2) to allow direct contact between the contour (8) of the shielding foil (2) and the piece of wing structure (1) in a contact region (7) thus created. The method then includes attaching the shielding foil (2) to the piece of wing structure (1) at the contact region (7), and injecting a filling resin (4) between the de-icing mat (3) and the piece of wing structure (1).

Abstract: Method for assembling de-icing matting (3) and an external protective metal shield (2), on a structure (1), such as an airfoil leading edge structure (1), comprising the following steps: manufacture of de-icing matting (3) independent of said structure (1), installation of the de-icing matting (3), between said structure (1) and the metal shield (2), said de-icing matting (3) covering only a portion (4) of the external surface of said structure (1), attachment of said metal shield (2), entirely covering said de-icing matting (3), to the portion (5) of the external surface of said structure (1) not covered by said de-icing matting (3).

Abstract: The invention concerns a laminate comprising a conductive fabric web (2) consisting essentially of electrically conductive material fibers, said web is provided with a terminal (2) designed to be connected to an electric current source, being sandwiched between an upper reinforcing layer (3) and a lower reinforcing layer (1) consisting each of an electrically insulating material. Said laminate is characterized in that said upper (3) and lower layers (1) comprise each an elastomer. The invention also concerns an electrothermal deicer comprising said laminate sandwiched between two protective coatings (5, 6), one of said coatings being optionally covered with a metal foil (8).