The Boeing Company

Adam Marshall Thoreen

Joshua Jay Baer

Matthew August Lassen

Matthew A Moser

Michael R Finn

Joseph Adam Sikora

Michael Edwin Foster

Mark John Gardner

Monte R Evans

Robert M Murphy

David Jeffrey Halaas

Timothy G Overton

Jonathan P Lee

Timothy Patrick Gallagher, Jr

Andrew J Peck

Timothy P Gallagher

Peter N Wyckoff

Robert E Buchholz

Monte R Evens

Joshua J Baer

Jr Gallagher Timothy Patrick

Mark J Gardner

Matthew A Lassen

Michael E Foster

A method and apparatus for a wingtip control system. The wingtip control system comprises a switch system for a flight deck of an aircraft and a controller. The switch system is configured to be placed into an armed state and generate an armed signal. The controller is in communication with the switch system. The controller is configured to receive the armed signal from the switch system, visually indicate a desired position for a wingtip of the aircraft in the switch system in response to an event occurring during operation of the aircraft, and generate a movement command to move the wingtip.

Wingtip control system

A system for controlling a high-lift device of an aircraft may include an interface for placement in a flight deck of an aircraft. The interface may include an edge control device for controlling a position of the high-lift device. The interface may be operable to select any of a plurality of control device positions. Each one of the plurality of control device positions may correspond to a different flight phase of the aircraft. The edge control device may be operable to engage, in response to a selection of a first control device position, a command mode for actuating the high-lift device in an automated manner based on the flight phase associated with the first control device position.

Control interface for leading and trailing edge devices

A system for optimizing performance of an aircraft may include a flight control computer for computing an optimum flap setting based on aircraft data. The system may further include a flap control system having a flap control device. The system may additionally include a flap actuation system coupled to the flap control system for positioning the trailing edge device at the optimum flap setting.

System and method for optimizing performance of an aircraft

A method for automatic rejection takeoff (RTO) of an aircraft monitors a plurality of sensors for an RTO event. Signals are sent to control systems of the aircraft to perform an RTO when the RTO event occurs.

Automatic rejected takeoff system

A system for displaying guidance aids to a crew for ground obstacle avoidance, particularly wingtip clearance. Perspective areas are drawn representing the current locations of the wingtips over the ground and predicted locations out into the future for a specified time or a specified distance. A flight crew may use these displayed guidance aids to determine the proximity of any perceived threat to the airplane. This capability addresses the costly problem of wingtip/airplane ground collisions. The graphical cue systems are specifically targeted toward aircraft that have a large wing span/size and/or folding wingtips.

Systems and methods for ground collision avoidance

The present invention provides a method of modifying the pitch attitude of an aircraft during landing, comprising: commanding the flaps to move to a landing setting; providing a current value for a flight condition parameter; providing a current flaps setting; comparing said current value to at least one threshold value; if said current value exceeds said threshold, determining a new flaps setting capable of producing an improvement in at least one of a selected aft body contact margin and a selected nose gear contact margin for the aircraft; and adjusting the flaps to said new flaps setting.

Quiet landing attitude modifier for airplane

A system for displaying pitch- and power-based guidance commands and flight path information for a variety of display modes (climb, cruise, descent, landing) to pilots in response to situations wherein the measured air data should not be relied upon. This information is presented in an intuitive and expedient manner exactly when and where it is needed on the primary flight display. The displayed information dynamically changes in response to airplane parameters.

Primary flight display pitch- and power-based unreliable airspeed symbology

Growing community of inventors

Lake Stevens, WA, United States of America

Adam Marshall Thoreen