Abstract: A landing gear noise attenuator mitigates noise generated by airframe deployable landing gear. The noise attenuator can have a first position when the landing gear is in its deployed or down position, and a second position when the landing gear is in its up or stowed position. The noise attenuator may be an inflatable fairing that does not compromise limited space constraints associated with landing gear retraction and stowage. A truck fairing mounted under a truck beam can have a compliant edge to allow for non-destructive impingement of a deflected fire during certain conditions.

Abstract: An aircraft engine nacelle comprises: (a) an inlet lip and a skin having internal and external surfaces; (b) a noise abatement structure such as an acoustic panel located on the internal surface of the nacelle skin; and (c) an electrically powered de-icing system located on the external surface of the nacelle skin and in electrical connection to a power source. A method for de-icing and abating noise from an aircraft nacelle comprises: (a) providing a noise abatement structure such as an acoustic panel located on the internal surface of the nacelle skin; (b) providing an electrically powered de-icing system on the external surface of the nacelle skin; and (c) applying an electric current to the electrically powered de-icing system. The nacelle skin may be a perforated skin, and the de-icing system comprises a wire mesh bonded to the external surface of the perforated skin.

Abstract: An assembly useful in reducing aircraft engine noise such as turbofan engine noise (730) comprises: (1) at least one tube “H-Q” having an inlet end (738), an outlet end (740) and a central tube portion therebetween; an (ii) at least one actuator operatively interconnected to at least one tube, wherein the actuator is capable of causing dynamic response by the tube. The assembly of this invention may be used in a method for reducing noise, the method comprising: (a) providing means for generating non-uniform noise energy about an inner surface and within a disclosure having at least an inlet; (b) providing an assembly for reducing noise comprising; (i) at least one tube having an inlet end, an outlet end and a central tube portion therebetween, and (ii) at least one actuator operatively interconnected to at least one tube, wherein the actuator is capable of causing dynamic response by the tube; and (c) directing at least a portion of the non-uniform noise into the assembly.

Abstract: A landing gear noise attenuator mitigates noise generated by airframe deployable landing gear. The noise attenuator can have a first position when the landing gear is in its deployed or down position, and a second position when the landing gear is in its up or stowed position. The noise attenuator may be an inflatable fairing that does not compromise limited space constraints associated with landing gear retraction and stowage. A truck fairing mounted under a truck beam can have a compliant edge to allow for non-destructive impingement of a deflected fire during certain conditions.

Abstract: An assembly useful in reducing aircraft engine noise such as turbofan engine noise (730) comprises: (i) at least one tube “H-Q” having an inlet end (738), an outlet end (740) and a central tube portion therebetween; and (ii) at least one actuator operatively interconnected to at least one tube, wherein the actuator is capable of causing dynamic response by the tube. The assembly of this invention may be used in a method for reducing noise, the method comprising: (a) providing means for generating non-uniform noise energy about an inner surface and within a disclosure having at least an inlet; (b) providing an assembly for reducing noise comprising; (i) at least one having an inlet end, an outlet end and a central tube portion therebetween, and (ii) at least one actuator operatively interconnected to at least one tube, wherein the actuator is capable of causing dynamic response by the tube; and (c) directing at least a portion of the non-uniform noise into the assembly.

Abstract: An assembly useful in reducing aircraft engine noise such as turbofan engine noise comprises: (a) a core portion comprising at least one entrance end and at least one exit end for the passage of acoustic energy therethrough; (b) a first member having an exterior face and an interior face, wherein the first member is adjacent to at least a part of the core portion, and the first member has a plurality of openings therein to permit the passage of acoustic energy therethrough; and (c) a second member having an exterior face and an interior face, wherein the interior face of the second member is adjacent to the core portion. The core portion may be a honeycomb acoustic structure, and the first member may be perforated to permit the passage of acoustic energy into and out of the conduit portion.

Abstract: An assembly useful in reducing aircraft engine noise such as turbofan engine noise comprises: (a) a core portion comprising at least one entrance end and at least one exit end for the passage of acoustic energy therethrough; (b) a first member having an exterior face and an interior face, wherein the first member is adjacent to at least a part of the core portion, and the first member has a plurality of openings therein to permit the passage of acoustic energy therethrough; and (c) a second member having an exterior face and an interior face, wherein the interior face of the second member is adjacent to the core portion. The core portion may be a honeycomb acoustic structure, and the first member may be perforated to permit the passage of acoustic energy into and out of the conduit portion.

Abstract: An aircraft wing useful for reducing wing-generated noise comprises: (a) a main element having a leading edge and a trailing edge; (b) at least one slat having a leading edge and a trailing edge, wherein the slat acts cooperatively with the main element to provide lift to the aircraft, and the main edge leading edge and slat trailing edge define a cavity there between; and (c) at least one sound-absorbing structure located on at least a portion of the main element leading edge, at least a portion of the slat trailing edge, in the cavity, or combinations thereof. If located on the main element leading edge or slat-trailing edge, the sound-absorbing structure may be a honeycomb load-bearing structure such as a honeycomb load-bearing structure having a perforated skin or a machine grid structure having an outer skin which is bonded or perforated. If located in the cavity, the sound-absorbing structure may be a flow blocker.

Abstract: A strain compatible attachment arrangement for releasably securing a plurality of metallic thermal protection system (TPS) panels to a space vehicle substructure to provide an outer mold line of the aeroshell of the vehicle. The TPS panels are spaced from the substructure to support aerodynamic loading on the TPS outer panel surface while isolating the outer panel surface from strains in the substructure and to isolate the vehicle substructure from direct thermal energy conductance though the outer TPS panel surface of the space vehicle. The attachment arrangement provides for a stand-off leg member to be secured at an inner end to the substructure and at its outer end to be releasably secured to a corner of a TPS panel, such panels being arranged in an edge abutting relationship.

Abstract: A novel pivoting door thrust reverser which provides a nozzle for the exhaust of a bypass engine that ensures a smooth continuous flow path for the exhaust without leakage around the pivoted upper and lower reverser doors. The upper reverser door is provided with a pair of biased cooperating crescent shaped kicker members that are biased outwardly in a controlled movement when the doors are deployed to deflect the upper portion of the reversed exhaust efflux forwardly in a predetermined direction to avoid interference with the control surfaces of the aircraft. The lower reverser door is provided with pivoted splitter plates that are biased outwardly when the door is deployed to abut and form a unitary splitter element that divides the lower exhaust efflux into two portions that are directed forwardly and away from the inlet of the engine to preclude foreign object damage to the engine.