The Boeing Company

David Daniel Leopold

Douglas Wilson

Matthew A Moser

Michael R Finn

Nikos D Mills

Nikos Damian Mills

Douglas Lee Wilson

A method, apparatus, and system for adjusting an operational flight envelope for an aircraft. An airspeed of the aircraft is received from a sensor system in the aircraft. An amount of change in the airspeed of the aircraft is determined. A current ceiling of the operational flight envelope for the aircraft is adjusted based on the amount of change in the airspeed of the aircraft.

Operational flight envelope management system

Integrated slat chine apparatus and methods are described. An example method comprises moving a slat relative to an airfoil between a stowed position and a deployed position. The slat is coupled to the airfoil. The slat is located adjacent a lateral surface of a chine. The chine is coupled to the airfoil. The slat is to expose the lateral surface of the chine when the slat is in the deployed position and to cover the lateral surface of the chine when the slat is in the stowed position.

Integrated slat chine apparatus and methods

A system for modifying a location of a water impingement limit on an airfoil of an aircraft includes a flight control computer configured to receive data representative of environmental parameters in an environment of a flight path of an aircraft, determine, based on the environmental parameters, an existence of icing conditions to which the aircraft is currently subjected or is predicted to be subjected, and generate, based on the existence of icing conditions, a command signal for actuating a movable surface of the aircraft. The system further includes a surface actuator configured to receive the command signal from the flight control computer and adjust the movable surface in a manner causing an increase in an angle of attack of the airfoil to thereby modify a water impingement limit on the airfoil.

System and method for modifying the location of water impingement limits on an airfoil

Integrated slat chine apparatus and methods are described. An example apparatus includes a chine and a slat. The chine is coupled to an airfoil. The chine includes a lateral surface. The slat is located adjacent the lateral surface of the chine and coupled to the airfoil. The slat is movable relative to the airfoil between a stowed position and a deployed position. The slat is to expose the lateral surface of the chine when the slat is in the deployed position and to cover the lateral surface of the chine when the slat is in the stowed position.

An aircraft stall protection system and method include calculating a first angle of attack and a second angle of attack based on aircraft configuration and environmental conditions, the first angle of attack being greater than the second angle of attack. The system and method limit the actual aircraft angle of attack to the first angle of attack for a predetermined period of time and thereafter the system and method limit the actual aircraft angle of attack to the second angle of attack. The system and method allow the aircraft operator or pilot to extract maximum performance from the aircraft for any given set of flight conditions, without the risk of stalling or remaining in a high drag state for a prolonged period of time. This system and method are suitable for use in conjunction with a stall warning system.

Aircraft stall protection system

A system for reducing a stopping distance of an aircraft may include an edge control system configured to control a leading edge device mounted to a wing of an aircraft. The edge control system may be configured to automatically command extension of the leading edge device from a first position to a second position in response to deployment of a spoiler if a ground speed of the aircraft is greater than a threshold ground speed.

Growing community of inventors

Seattle, WA, United States of America

David Daniel Leopold