Gulfstream Aerospace Corporation

Jeffrey Hausmann

Scott Bohanan

Kristin Medin

Jim Jordan

Nicholas Kershaw

Michael Knight

Robert O'Dell

Frank Manochio

Andrew Martin

Bethany Davis

Jason Meade

Jimmy Lee Hancock, Jr

Christopher Watkins

Ozan Ates

Ray Slocum

Gary Freeman

An aircraft has a first principles takeoff processor (PCE), a predictive flight envelope protection processor (PFEP), and a maximum takeoff weight processor. The PCE is programmed to predict a liftoff location and an energy state of the aircraft at a liftoff on a runway. The PFEP is programmed to assess each of a plurality of potential trajectories for compliance with or violation of a predetermined flight envelope. The maximum weight processor is programmed to: indicate that the aircraft may takeoff at the aircraft weight when any one of the plurality of potential trajectories is in compliance with the predetermined flight envelope; iteratively reduce an input of the aircraft weight to the PCE until the PCE indicates that any one of the plurality of potential trajectories is in compliance with the predetermined flight envelope; and indicate that the input of the aircraft weight as reduced is a maximum allowable takeoff weight.

Maximum takeoff weight determination for aircraft

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

A flight guidance panel for an aircraft includes a subpanel display, a joystick, rotary encoders, a deflection sensor, and a processor. The subpanel display indicates autopilot modes and flight value goals and has a top-level state and a subpanel control state. The joystick is for user interaction with the subpanel display. The rotary encoder is coupled with the joystick to receive rotation inputs from a user of the joystick. The deflection sensor is coupled with the joystick to detect a deflection input from the user of the joystick. The processor is programmed to: change a state of the subpanel display to the subpanel control state corresponding to a selected subpanel in response to receiving the deflection input while the subpanel display is in the top-level state; and change the flight value goals in response to receiving the rotation inputs while the subpanel display is in the subpanel control state.

Flight guidance panels with joystick controls

An aircraft includes a fuselage, a main wing coupled with and extending outward from the fuselage, and a collision avoidance system coupled with the fuselage adjacent the main wing. The collision avoidance system includes first and second laser rangefinders and a detection circuit. The first and second laser rangefinders are configured to generate laser beams laterally outward of the fuselage and include diverging lenses spreading the laser beams in a vertical dimension. The detection circuit is coupled with the first laser rangefinder and the second laser rangefinder to: detect an object within a collision risk zone adjacent to the main wing based on input from at least one of the first laser rangefinder and the second laser rangefinder; and generate an alert that the object is at risk of colliding with the main wing.

Laser rangefinder systems with divergent lenses for aircraft wingtip collision avoidance systems

Flight control information systems, flight guidance display, and aircraft are provided. A navigational information system includes an input configured to receive a flight plan wherein the flight plan includes a first waypoint, a second waypoint, a third waypoint, and future waypoints, a user interface operative to generate a control signal in response to a user input, a display configured to display a graphical user interface, a processor operative to receive the flight plan from the input, to generate the graphical user interface to include to the first waypoint and the second waypoint and to couple the graphical user interface to the display, the processor being further operative to generate the graphical user interface in to include the first waypoint and the third waypoint in response to the control signal and to couple the graphical user interface to the display.

Advanced flight guidance panel with display of future waypoints and constraints

A flight guidance panel for an aircraft includes a first user input portion, a second user input portion, a display, and a controller. The display is disposed between the first user input portion and the second user input portion. The controller is configured for generating a first functional panel associated with a first flight parameter for presentation on the display. The controller is further configured for generating a second functional panel associated with a second flight parameter for presentation on the display.

Aircraft flight guidance panels with a display disposed between two input portions

An aircraft includes a display, a support system, and an avionics system. The support system includes at least one operable component, where at least one of the support system and the at least one operable component is configured to operate with an operating value falling within a predefined normal operating range. The avionics system is programmed to: calculate a rate of change of a value of at least one of the support system and the at least one operable component; determine whether the value will exit a predetermined normal operating range within a predetermined time based on the rate of change of the value; and indicate on the display that the value is expected to exit the predetermined normal operating range. The avionics system can leverage this function to declutter displays, and then present additional information to the crew when a value is trending out of range.

Trend indications for avionics systems

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, an engine cover assembly, 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. The engine cover assembly includes an engine cover and a second sensor. The engine cover is configured to cover the fluid opening. The second sensor component is attached to the engine cover and is configured to interact with the first sensor component. 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.

Display systems, controllers, and methods are provided. A display system for an aircraft includes a display unit, an input device, and a controller. The controller is communicatively coupled with the display and the input device and is configured to retrieve an electronic checklist that includes a plurality of tasks including an annotated task associated with at least one of a note, a warning, a caution, and task information. The controller is further configured to hide from view the at least one of the note, the warning, the caution, and the task information in an image of the electronic checklist based at least in part on viewing criteria. The controller is further configured to generate a signal that causes the display unit to visually present the image.

Electronic checklists with dynamic visibility of annotations

A system is provided that includes a detachable mounting apparatus. The detachable mounting apparatus is configured to be secured on an aircraft. The detachable mounting apparatus includes a detection system and a warning system. The detection system can detect objects in proximity to the aircraft and generate a detection signal when an object is detected in proximity to the aircraft. The warning system can generate at least one alarm signal that is perceptible outside the aircraft.

Growing community of inventors

Savannah, GA, United States of America

Jeffrey Hausmann