The Boeing Company

Heidi M Haugeberg

Nikos D Mills

Douglas Wilson

Kioumars Najmabadi

Kent Edmund Karnofski

David Paul Eggold

Tristan C Flanzer

Christopher M Hodges

Leonard J Inderhees

Uy-Loi Ly

Ryan L Pettit

Kevin Mark Johnsen

Steven Beland

Ryley Thies Ohlsen

Nikos Mills

Flap pressure shape biasing is disclosed. A disclosed example apparatus includes a flight monitor to determine a movement parameter of an aircraft, the movement parameter corresponding to at least one of a Mach number of the aircraft, an airspeed of the aircraft, or a vertical acceleration of the aircraft, and a spoiler controller to adjust a position of a spoiler of the aircraft to reduce pressure on a flap based on the movement parameter by moving a pressure transition away from the flap.

Flap pressure shape biasing

An example method of limiting an aircraft to a pitch axis envelope includes determining aircraft state limits associated with multiple pitch axis variables of an aircraft, determining predicted aircraft states, comparing the predicted aircraft states to the aircraft state limits to produce aircraft state errors, translating the aircraft state errors into a set of positive and negative limit elevator commands, selecting a highest priority positive limit elevator command, selecting a highest priority negative limit elevator command, limiting a primary pitch axis control law elevator command of the aircraft to a value that is less than or equal to the highest priority positive limit elevator command and greater than or equal to the highest priority negative limit elevator command, and controlling the aircraft according to the primary pitch axis control law elevator command limited to the value.

Systems and methods for pitch axis envelope limiting of an aircraft

In an example, method of controlling thrust produced by a plurality of engines on an aircraft for assisting with nose-down recovery of the aircraft is described. The method includes selecting a maximum value of an aircraft parameter, measuring a value of the aircraft parameter while the aircraft is in flight, based on a comparison of the maximum value and the measured value determining that the measured value exceeds the maximum value, and reducing a thrust produced by each of the engines of the plurality of engines to bring the measured value of the aircraft parameter below the maximum value of the aircraft parameter.

Methods and systems for controlling thrust produced by a plurality of engines on an aircraft for assisting with certain flight conditions

Growing community of inventors

Chicago, IL, United States of America

Heidi M Haugeberg