The Boeing Company

Patrick M Fahey

Neal Van Huynh

John C Nicholas

Michael D Bills

Robert S Eick

Thomas G Heineman

Paul R Smith

Mark Steven Good

Bryan Gruner

Gen Matsui

Patrick Joseph McCormick

Mark William Lesyna

Kwan-Ho Bae

Barry D Hance

Matthew D Uhlman

Christopher P Beamis

Gregor William Dempster

Ali Abdelmagid

Rene T Nguyen

Frank L Wichman

John D Farmer

Drew M Thompson

Herbert Guttler

Robert J Hawk

Ellen A Pifer

Bryan J Gruner

Gregor W Dempster

A hydraulic system for a vehicle includes a hydraulic monitoring control unit configured to receive an operational signal from a sub-system of the vehicle and control flow of hydraulic fluid to actuators of components based on the operational signal. The hydraulic monitoring control unit is configured to bypass the flow of the hydraulic fluid in relation to a subset of the actuators in response to the operational signal indicating an altered operational state of the sub-system.

Hydraulic control systems and methods for components of an aircraft

Example methods and apparatus for mitigating aerodynamic flutter of aircraft wing flaps are disclosed. An example apparatus includes a fairing, an actuator, and a damper. The fairing is located on a bottom side of a wing of an aircraft. The actuator is disposed in the fairing. The actuator is coupled to and extends between the wing and a flap of the wing. The damper is disposed in the fairing. The damper is coupled to and extends between the fixed wing and the moveable flap.

Methods and apparatus for mitigating aerodynamic flutter of aircraft wing flaps

A hydraulic system (e.g., of an aircraft or other vehicle) includes a pump, a pressure line coupled to the pump and configured to distribute pressurized hydraulic fluid, and a return line configured to return hydraulic fluid to a reservoir. The hydraulic system also includes an auxiliary leakage valve coupled to the pressure line, to the return line, and to an actuator. The auxiliary leakage valve is configured to receive a control signal and, based on the control signal, selectively open a restricted fluid path. The restricted fluid path couples the pressure line to the return line to allow a restricted amount of the hydraulic fluid to flow from the pressure line to the return line.

Hydraulic fluid warming system and method

Methods and apparatus for operating flight control systems of aircrafts are disclosed. An example apparatus includes a flight control system including a processor to: based on data from first and second sensors, determine first and second values; based on the first and second values, determine a location of a jam in the flight control system, the location of the jam being determined based on a summation of the first and second values.

Methods and apparatus for operating flight control systems of aircrafts

Methods and apparatus for operating flight control systems of aircrafts are disclosed. An example apparatus includes a flight control system including a first sensor and a second sensor. The example apparatus also includes a processor to, based on data from the first and second sensors, determine first and second input values and, based the input values, determine an approximate location of a jam in the flight control system of an aircraft.

Growing community of inventors

Seattle, WA, United States of America

Patrick M Fahey