The Boeing Company

Terrence S Birchette

Akif O Bolukbasi

Ahmed A Hassan

Brian Koorosh Hamilton

Robert R Murrill

Douglas Reinhard Ludin

Matthew S Stauffer

Thomas A Zientek

Friedrich K Straub

Hieu Thien Ngo

Alan Douglas Stemple

Justin Johnson Schaub

Richard Karl Weisenburger

Controlled energy absorption of seats for impact is described herein. One disclosed example method includes determining a weight of an occupant of a seat of an aircraft, and calculating, using a processor, a stroke load of a seat energy absorber operatively coupled to the seat based on the weight of the occupant. The example method also includes setting the seat energy absorber to the calculated stroke load.

Controlled energy absorption of seats for impact

An active landing gear damping system and method for decelerating a vehicle during a terrain impact event, such as an aircraft landing or crash. The system monitors aircraft state data and terrain information to predict an impact of the vehicle with the terrain. The system can then determine a target damper force for each landing gear of the vehicle and a predicted damper velocity at the time of impact. Each landing gear can include an adjustable damper valve, wherein adjustment of the damper valves varies the damping coefficient of the respective dampers. The system can adjust valves of the respective dampers to provide the target force based on the predicted damper velocity. After an impact begins, the system can continuously monitor and adjust the valve to maintain the target force.

Active landing gear damper

An apparatus and method for a composite structural aircraft transmission support link having an integral energy-absorbing feature is disclosed. The link is a two-force member that can carry structural loads up an ultimate load. When loaded beyond ultimate load the design allows sections of the link to fail in a controlled and progressive manner, so that energy is absorbed over a defined stroking distance.

Energy absorbing link

A method and apparatus for moving a blade of a rotorcraft. The method comprises operating the rotorcraft and applying a torque to an elongate member connected to a tip portion of the blade during operation of the rotorcraft using a tip actuation mechanism that is external to the blade and associated with the elongate member such that the tip portion of the blade rotates about an axis through the blade.

Apparatus, system, and method for pitching and twisting a blade of a rotorcraft

An air pump positioned within a hollow space in an aerodynamic structure for controlling the flow over an aerodynamic surface thereof, includes a movable member linearly displaced by a very low friction piston mechanism and a compression chamber open to the exterior of the aerodynamic surface through an orifice. Reciprocal displacement of the very low friction movable member changes the volume of the compression chamber to alternately expel fluid (e.g., air) from and pull fluid into the compression chamber through the orifice. The movable member includes a piston oscillating within a piston housing each having an ultra-low friction coating for improved thermal performance and reduced maintenance. Fluid intake to the compression chamber may be increased through the use of a one-way valve located either in the aerodynamic surface, or in the piston. Multiple flapper valves may surround the orifice in the aerodynamic surface for increased fluid control.

Ultra-low friction air pump for creating oscillatory or pulsed jets

An airfoil member and an airfoil member altering system are provided for significantly modifying the shape and size of the airfoil member while simultaneously providing an airfoil member with increased adaptability to various flight conditions throughout a flight envelope. The airfoil member comprises at least one motor or actuator, a system controller, a plurality of vehicle performance sensors, at least one temperature controller and airfoil member comprising at least one geometric morphing device that is adjustable in both size and shape and one or more rigid members.

Composite material for geometric morphing wing

A piezoelectric actuator assembly allows maximization of the cross-sectional area of a piezoelectric driver assembly such that axial stiffness of the actuator assembly is substantially increased. The actuator assembly is coupled to an application structure and includes the piezoelectric driver assembly having a stack inboard end longitudinally extending in an inboard direction with respect to the application structure. The driver assembly also has a stack outboard end longitudinally extending in an outboard direction with respect to the application structure. The driver assembly further provides a longitudinal displacement in response to an applied voltage. The actuator assembly also includes an amplification arm having an arm outboard end coupled to a load. An outboard hinge mechanism rotatably couples an arm inboard end of the amplification arm to the stack outboard end such that the arm outboard end extends in the outboard direction. Voltage signals selectively applied to the driver assembly cause rotational displacement of the amplification arm.

Growing community of inventors

Chandler, AZ, United States of America

Terrence S Birchette