Gulfstream Aerospace Corporation

Kristopher Lynch

Mike Lucas

Michael Eugene Lucas

Tongan Wang

Allen Davis

John Willett Maxon, Jr

Tyler Relf

Michael Brinley

Andrew Gorton

Benjamin Frank Wilson

Adam White

Jeffrey Jonas

J R Grovenstein

Randy Hull

Charles Roberts, Ii

A finished floor assembly covers a floor area of an aircraft and includes a subfloor, a padding assembly, and a finish flooring layer. Noise radiates from the subfloor due to vibrations transmitted by an aircraft structure. The padding assembly attenuates the noise and includes a first pad layer, a second pad layer, and a plurality of discontinuous couplings. The first pad layer abuts the subfloor. The second pad layer is adjacent to the first pad layer. The plurality of discontinuous couplings are laterally separated from each other along the floor area by void portions. The discontinuous couplings secure the first pad layer to the second pad layer and the first pad layer and the second pad layer are in contact at the void portions. The finish flooring layer disposed overtop the padding assembly.

Aircraft floor assemblies with discontinuous coupling between layers

A method of repairing an over-frame blanket assembly in an aircraft includes identifying an aperture in an over-frame blanket piece having an exposed sound barrier layer. The method further includes cutting an acoustic barrier patch to a size that is larger than the aperture. The method includes adhering a sound barrier layer of the acoustic barrier patch to the exposed sound barrier layer of the over-frame blanket piece around the aperture to cover the aperture.

Repair of over-frame blanket assemblies in aircraft

Ventilation systems, aircraft, and silencers are disclosed herein. An aircraft includes a ventilation system. A ventilation system includes first and second air flow sources configured to generate first and second air flows, a silencer, a first conditioning vent, and a second conditioning vent. A divider spans an interior dimension of the housing to define a first cavity and a second cavity, where the divider restricts substantially all mass flow between the first cavity and the second cavity in the housing. First and second silencer tubes have porous portions disposed in the respective cavity and are operatively coupled with the respective air flow source to receive the respective air flow. First and second conditioning vents are operatively coupled with the respective silencer tubes to direct the respective air flows to a conditioned volume.

Dual tube silencer for separate gas flows

Aircraft, vibration isolation assemblies, and methods of assembling vibration isolation assemblies are provided. An aircraft includes a vibration isolation assembly. The vibration isolation assembly includes a mounting track, a plate, a clamp block, a vibration isolator, and a support fitting. The mounting track defines a cavity and includes flanges that define an opening to the cavity. The plate is configured to be positioned on the flanges outside of the cavity. The clamp block is configured to be fastened to the plate under the flanges of the mounting track within the cavity. The vibration isolator is configured to be laterally constrained by the clamp block within the cavity. The support fitting is configured to be secured to the vibration isolator outside of the cavity.

Seat track assemblies for vibration isolation of floor mounted components

A ventilation system for ventilating a passenger compartment of an aircraft, an aircraft, and a method of operating the ventilation system are disclosed herein. The ventilation system includes, but is not limited to, a bezel, a fluid vent, an electronic sensor, and a valve. The bezel defines a bezel aperture and the fluid vent defines an axis that passes through the bezel aperture to direct a stream of air through the bezel into the passenger compartment. The electronic sensor is associated with the bezel and is configured to generate a bezel position signal. The valve is configured to vary a flow rate of the stream of air through the fluid vent based on the bezel position signal.

Coaxial fluid vent and electronic control for a fluid valve for aircraft

Fuselage assemblies, over-frame blanket assemblies, and methods of installing over-frame blanket assemblies are provided. A fuselage assembly for an aircraft includes a fuselage skin, a cabin liner, and an over-frame blanket assembly. The cabin liner has an outer side facing the fuselage skin. The over-frame blanket assembly is disposed between the fuselage skin and the cabin liner and has a first blanket piece. The first blanket piece includes a first sound barrier layer that defines a first outer surface of the over-frame blanket assembly and a first sound absorbing layer that defines a second outer surface of the over-frame blanket assembly facing the fuselage skin. A method of installing the over-frame blanket assembly includes positioning the first blanket piece in an orientation such that the first sound barrier layer is directly adjacent the cabin liner.

Over-frame blanket assemblies and methods of installation in fuselage assemblies

Aircraft, wing-to-body fairing assemblies, and air exchange systems are provided. An aircraft includes a fuselage, a wing secured to the fuselage, an outer skin panel, and an air exchange system. The outer skin panel is secured to the wing and/or the fuselage and at least partially defines a cavity. The air exchange system is secured to the outer skin panel and exchanges air between the cavity and an external environment. The air exchange system includes an air inlet, a diffuser, and a silencer. The air inlet is disposed in the outer skin panel and accommodates an air flow between the cavity and the external environment. The diffuser is attached to the air inlet and has a varying cross sectional area to change the speed of the air flow. The silencer is attached to the diffuser and communicates the air flow between the diffuser and the cavity and reduces noise.

Aircraft and air exchange systems for ventilated cavities of aircraft

Aircraft, aircraft exterior speaker systems, and methods of projecting sound waves from an exterior of an aircraft are provided. An aircraft includes an outer skin membrane, a vibration actuator, and a controller. The outer skin membrane has an exterior surface that defines an exterior boundary of the aircraft. The vibration actuator is coupled for common vibration with the outer skin membrane. The controller is operatively coupled with the vibration actuator and is configured to generate a command for the vibration actuator based on audible content to be projected from the exterior surface. The controller is further configured to transmit the command to the vibration actuator. The vibration actuator is configured to vibrate in response to receiving the command.

Aircraft and exterior speaker systems for aircraft

A ventilation system for ventilating a passenger compartment of an aircraft is disclosed herein. The ventilation system includes, but is not limited to, a nozzle that is adapted to be mounted proximate an interior of the aircraft and that is configured to direct a stream of air into the passenger compartment. The ventilation system further includes a valve that is spaced apart from the nozzle and positioned upstream of the nozzle, the valve configured to control a flow of air to the nozzle. The ventilation system still further includes a conduit that fluidly couples the valve to the nozzle. The conduit is configured to convey the flow of air from the valve to the nozzle.

Growing community of inventors

Savannah, GA, United States of America

Kristopher Lynch