Gulfstream Aerospace Corporation

Renaelc, Inc.

Michael Knight

Jeffrey Hausmann

James R Grieco

Timothy Raymond Conners

Scott Bohanan

John Louis

Jim Jordan

Kristin Medin

Brian G Cook

Thomas Van De Ven

Robert M Vieito

Gary Palfreyman

Bethany Davis

Charles Michaels

Ozan Ates

Patrick C Gehm

Robert Cowart

Gary Freeman

Pedro R Carleial

Timothy Burns

Douglas Klutzke

A throttle quadrant system for an aircraft includes: a first throttle handle to control a first engine of the aircraft, the first throttle handle having a first activatable visual indicator integrated therein; a second throttle handle to control a second engine of the aircraft, the second throttle handle comprising a second activatable visual indicator integrated therein; and at least one controller to control activation and operation of the first activatable visual indicator and the second activatable visual indicator. The at least one controller responds to first engine data related to operating status of the first engine to selectively activate the first activatable visual indicator. The at least one controller also responds to second engine data related to operating status of the second engine to selectively activate the second activatable visual indicator.

Aircraft throttle quadrant assembly with integrated visual indicator feature

The disclosed embodiments describe cover detection systems, controllers, and aircraft. The aircraft includes the controller and parts of the cover detection systems. A cover detection system includes an engine, a first sensor, a second sensor, an engine cover, and a controller. The engine has moving parts and defines a fluid opening. The fluid opening exposes the moving parts to an ambient environment. The first sensor component is located proximate to the engine and the second sensor component is configured to interact with the first sensor component. The engine cover assembly includes an engine cover and a second sensor. The engine cover is configured to cover the fluid opening. The controller is configured to determine whether the engine cover is installed on the engine based on an interaction between the first sensor component and the second sensor component.

Engine inlet cover detection system and method

An aircraft includes an engine, a thrust reverser, landing gear, a brake system, a pilot input device, and a control system. The engine is configured to generate thrust directed to move the aircraft in a forward direction. The landing gear includes wheels. The brake system is configured to generate a braking force on the wheels. The pilot input device is positioned for use by a pilot of the aircraft. The control system is programmed to: determine whether the taxi operations are allowed; receive a request to achieve and hold a taxi speed at a desired taxi speed from the pilot input device; and command the engine, the thrust reverser, and the brake system to achieve and maintain the desired taxi speed in response to receiving the request to hold taxi speed only when the taxi operations are allowed.

Aircraft taxi assistance avionics

An aircraft, a control surface arrangement, and a method of assembling an aircraft are disclosed herein. In an exemplary embodiment, the aircraft includes, but is not limited to, an airframe, a control surface, and a rotary actuator. The rotary actuator rotatably mounts the control surface to the airframe. The rotary actuator supports the control surface on the airframe and is configured to rotate the control surface with respect to the airframe when the rotary actuator is actuated. The rotary actuator is further configured to deliver torque to the control surface from a longitudinally intermediate portion of the rotary actuator.

Aircraft, control surface arrangements, and methods of assembling an aircraft

An aircraft seat assembly for supporting a seat occupant, and a method for fabricating an aircraft seat assembly for supporting a seat occupant are provided. In one non-limiting example, the aircraft seat assembly includes a seat cushion supported by the seat structure. A vibration producing apparatus configured to produce vibrations conducive for inducing drowsiness. The vibration producing apparatus is disposed adjacent to or within the seat structure for transferring the vibrations to the seat occupant.

Aircraft seat assembly including a vibration producing apparatus and method for fabricating the same

An aircraft seat assembly for supporting a seat occupant, and a method for fabricating an aircraft seat assembly for supporting a seat occupant are provided. In one non-limiting example, the aircraft seat assembly includes a seat structure and a seat cushion that is supported by the seat structure. A vibration mitigating apparatus is operatively coupled to the seat structure to prevent or reduce vibrations from transferring to the seat occupant.

Aircraft seat assembly including a vibration mitigating apparatus and method for fabricating the same

Aircraft, vision sensor systems, and methods of operating deployable vision systems are provided. An aircraft includes a fuselage and a vision sensor system. The fuselage defines an outer mold line and the vision sensor system includes a housing and a vision sensor package. The housing is selectively deployable between a retracted position and a deployed position and is disposed within the outer mold line in the retracted position and outside of the outer mold line in the deployed position. The vision sensor package is associated with the housing and is positioned to collect imaging information when the housing is in the deployed position.

Aircraft and deployable vision systems for aircraft

A system is provided having a normal operational mode and a modulated operational mode. The system includes an input device configured to generate a command signal. The system further includes a brake controller configured to generate a brake actuation signal in response to the command signal. The system further includes a fluid source configured to provide fluid in response to the brake actuation signal. The fluid has a first portion and a second portion. The system further includes a return valve in fluid communication with the fluid source, and configured to return the first portion of the fluid to the fluid source when the system is in the modulated operational mode. The system further includes a wheel brake in fluid communication with the fluid source and configured to engage a wheel of the aircraft in response to at least the second portion of the fluid.

System for controlling a wheel brake of an aircraft

An integrated power distribution, data network, and control architecture for a vehicle is provided that includes nodes distributed throughout the vehicle. Each node includes power distribution (PD) and data collection and distribution (DCD) components. The PD components receive electrical power from a source external to the node and distribute and control the electrical power supplied to active and passive electrical loads that are external to the node. The PD components include an electrical power input interface configured to receive an electrical power input from a source external to the node, and one or more power control modules. Each power control module can control the electrical power supplied to one or more electrical power output interfaces that supply power to the active and passive electrical loads. The DCD components receive data from data sources external to the node and transmit data to data consumers external to the node.

Integrated power distribution, data network, and control architectures for a vehicle

A system for controlling a pressure field around an aircraft in flight is disclosed herein. In a non-limiting embodiment, the system includes, but is not limited to, a plurality of pressure sensors that are arranged on the aircraft to measure the pressure field. The system further includes, but is not limited to, a controller that is communicatively coupled with the plurality of pressure sensors. The controller is configured to receive information that is indicative of the pressure field from the plurality of pressure sensors. The controller is also configured to determine when the pressure field deviates from a desired pressure field based on the information. The controller is also configured to transmit an instruction to a movable component onboard the aircraft that will cause the movable component to move in a manner that reduces the deviation.

System and method for controlling a pressure field around an aircraft in flight

Aircraft landing gear assemblies and aircraft are provided. A landing gear assembly includes a main post and a light element cluster. The main post has a non-rotating portion and a rotatable steering portion. The light element cluster is associated with the non-rotating portion and includes at least two independently illuminating sections.

Aircraft landing gear assemblies with non-rotating light element clusters

An apparatus for controlling a hydraulically-actuated brake of an aircraft includes a brake control unit. The brake control unit is configured to receive a brake signal from an operator of the aircraft. A pump is in fluidic communication with a reservoir for holding hydraulic fluid and the brake for supplying the hydraulic fluid from the reservoir to the brake. An electric motor is in communication with the brake control unit and coupled to the pump to control pressure of the hydraulic fluid supplied by the pump in accordance with the brake signal.

Apparatus and method for controlling a hydraulic brake of an aircraft

A system is provided for engine and generator control. The system includes a compound AC generator, a generator control unit (GCU) module and an engine electronic controller (EEC) module. The compound AC generator includes a shaft, and a permanent magnet generator (PMG) configured to be driven by the shaft to generate an AC power signal. The GCU module is configured to control the compound AC generator. The PMG is coupled to the GCU module and the EEC module such that it is configured to simultaneously supply the AC power signal to the GCU module and to the EEC module.

Apparatus and systems for engine and generator control within an aircraft

The disclosed embodiments relate to methods and systems for avoiding a collision between an obstacle and a vehicle, such as an aircraft, on a ground surface. A processor receives a detection signal from one of a plurality of proximity sensors. The detection signal indicates that the obstacle has been detected. In response to receiving the detection signal, a video image signal is transmitted from the processor to a display in the cockpit of the aircraft. The video image signal corresponds to a particular video imager that is associated with the particular proximity sensor that detected the obstacle. A video image, of a particular region around the aircraft that includes the obstacle is displayed on a display. In response to receiving the detection signal, the processor can also transmit an alert signal, and a brake activation signal to activate a braking system to prevent the aircraft from colliding with the obstacle.

Growing community of inventors

Savannah, GA, United States of America

Michael Knight