The Boeing Company

Alan Edgar Landmann

Mark Alan Negley

Marc Rollo Matsen

Richard Henry Bossi

Kay Youngdahl Blohowiak

Marc Joel Piehl

Stephen G Moore

Geoffrey Allen Butler

Robert A Anderson

Gregory Alan Foltz

Bret A Voss

Liam S Cavanaugh Pingree

Robert L Carlsen

Jaffar Sher Iqbal

John Mark Gardner

Justin David Kearns

Justin C Christenson

Herbert Louis Hoffman

Mark M Gmerek

Hugh Poling

Juhn-Shyue Lin

Adrian Viisoreanu

Gary R Chewning

Jason Alexander Gordon

Balamurugan R Annamalai

Liam S Pingree

Giacomo Licciardi

Jason A Gordon

Jaffar S Iqbal

A panel includes a structural substrate and a damping element including a viscoelastic material (VEM) layer coupleable to the structural substrate of the aircraft, and a constraining layer coupled to the VEM layer. The VEM layer is configured to dampen a vibration of the structural substrate. The constraining layer is configured to apply a shear force to the VEM layer.

Methods and systems for damping a cabin air compressor inlet

A method of forming a molybdenum composite hybrid laminate is disclosed. The method includes treating a surface of each of a plurality of molybdenum foil layers. The method further includes interweaving the surface treated molybdenum foil layers with a plurality of composite material layers. The method further includes bonding with an adhesive layer each of the surface treated molybdenum foil layers to adjacent composite material layers to form a molybdenum composite hybrid laminate having improved yield strength.

Molybdenum composite hybrid laminates and methods

A computer system enables a noise level associated with a structural substrate to be reduced. The computer system includes a memory device for storing data, and a processor in communication with the memory device. The processor is programmed to define a modulus of elasticity, a thickness, and/or a distribution associated with one or more damping elements coupleable to the structural substrate, define at least one operating parameter associated with the structural substrate and the one or more damping elements, simulate a first performance of the structural substrate and/or the one or more damping elements to generate a first performance data set; and determine whether the first performance data set satisfies a predetermined threshold. The first performance data set is associated with the at least one operating parameter and the modulus of elasticity, the thickness, and/or the distribution associated with the one or more damping elements.

Methods and systems for determining a structural parameter for noise and vibration control

In an embodiment of the disclosure, there is provided a molybdenum composite hybrid laminate. The laminate has a plurality of composite material layers. The laminate further has a plurality of surface treated molybdenum foil layers interweaved between the composite material layers. The laminate further has a plurality of adhesive layers disposed between and bonding adjacent layers of the composite material layers and the molybdenum foil layers.

Vibration-damping blankets are attached to the back surfaces of fairing panels of a flight vehicle (e.g., an aircraft or spacecraft) to reduce vibration, fatigue, structure and airborne transmitted energy, and cabin noise. In one case, the flight vehicle fairing has an exterior comprising exterior surfaces of a multiplicity of removable panels. A method of retrofitting the flight vehicle with vibration-damping blankets comprises: removing a panel from the flight vehicle exterior; attaching a vibration-damping blanket to a back surface of the removed panel; and installing the panel with attached vibration-damping blanket on the flight vehicle with the exterior surface of the panel forming part of the flight vehicle exterior. In one embodiment, the vibration-damping blanket comprises polymeric (e.g., aromatic polyamide) fibers in a nonwoven structure.

Flight vehicle fairing having vibration-damping blankets

A method is disclosed for reducing noise and vibration within a structure of a mobile platform, wherein the noise and vibration are at least in part caused by airflow over an outer skin of the mobile platform parallel to a longitudinal line extending fore to aft along the structure. The method may involve forming the structure such that a fundamental panel vibration mode shape of the structure is not parallel to the longitudinal line.

Structural mode shape alignment

Apparatus and method for controlling the orientation of a fundamental panel vibration mode shape of a structure, such as a skin panel of a fuselage of an aircraft, relative to the direction of a turbulent boundary layer flow over the fuselage, and in a manner to achieve a level of noise reduction within the fuselage. The fuselage is constructed either through orientating stringers and/or frame members, or by using stiffening members placed diagonally between the stringers and frame members, in a manner that produces a fundamental panel vibration mode shape that extends at an angle of between about 30&#xb0;-45&#xb0; relative to the direction of the turbulent boundary layer flow over the fuselage. Aligning the fundamental panel vibration mode shape at an angle of between about 30&#xb0;-45&#xb0; relative to the direction of the turbulent boundary layer flow results in a reduction of the vibration response of the skin panel, and thus a reduction in the noise level within the fuselage.

Growing community of inventors

Woodinville, WA, United States of America

Alan Edgar Landmann