The Boeing Company

Mark John Gardner

Mark Steven Good

Michael E Renzelmann

Matthew August Lassen

Michael R Finn

Matthew A Moser

Jan A Kordel

Stephen John Fox

Stephen Roger Amorosi

Mark William Lesyna

Charles E Jokisch

Keith Townsend

George Moy

Robert M Murphy

Brian Curtis Hill

Nicholas Seth Tyler

Robert E Fisher

Jeffrey Lynn Duce

Kelly Thomas Jones

Joseph A Marshall

Adam P Malachowski

Otis Franklin Layton

Adam Marshall Thoreen

Dan Onu

Mark A Barr

Kwan-Ho Bae

Alan D Marx

Peter Angel Padilla

Christopher D Feet

Gary A Emch

Eric J Selby

William Suhail Hanna

Victoria L Garcia

Jen-Shen Liu

Gregory J Seehusen

Richard I Apfel

Monica E Thommen

Sarah A Jones

Jared Chung Houten

Michael Edward Renzelmann

Methods and systems according to one or more examples are provided for reducing chatter in a no-back brake during aiding load operations. In one example, an apparatus comprises a no-back brake, disposed within an actuator coupled to an aircraft, including a shaft, and a ball ramp plate, coupled to the shaft, to receive a force comprising an air loading force and is displaced responsive to the force. The apparatus further comprises a brake, coupled to the shaft and coupled to the ball ramp plate, and displaced by the ball ramp plate corresponding to a distance the ball ramp plate is displaced. The apparatus further comprises a modulating spring, coupled to the shaft and coupled to the brake, configured to compress in response to the brake being displaced, and the modulating spring is configured to apply a selective compressive force at the brake corresponding to a distance the brake is displaced.

Bi-directional no-back brake progressive modulation spring systems and methods

A system and method for a number of backup systems in an aircraft. The apparatus comprises a movement system; a latch system; a lock system; and at least one of a backup valve, a backup actuator, or a backup power source connected to at least one of the movement system, the latch system, or the lock system. The movement system has a first number of actuators and is connected to a hydraulic power source. The latch system has a second number of actuators and is connected to the hydraulic power source. The lock system has a third number of actuators and is connected to the hydraulic power source.

Backup system

An apparatus and method of a wing fold system may include a latch assembly rotating an unfixed portion of a wing, with respect to a fixed portion of the wing, between a flight position of the wing and a folded position of the wing. A first portion of the wing may hold a rotating portion of the latch assembly. A second portion of the wing may hold a secured portion of the latch assembly. The rotating portion of the latch assembly may rotate between an open position and a closed position. A slot in the rotating portion may receive the secured portion of the latch assembly. A securing portion of the rotating portion may secure a secured portion of the latch assembly. The latch assembly may prevent rotation of the second portion when the wing may be in the flight position.

Wing fold system rotating latch

Methods and apparatus to control movement of a component are disclosed herein. An example apparatus includes a housing defining a bore and a piston disposed inside the bore. The piston is to be coupled to a movable component disposed outside of the bore. The example apparatus further includes a fluid flowline in fluid communication with a first chamber of the bore and a second chamber of the bore. The first chamber is on a first side of the piston, and the second chamber on a second side of the piston. The example apparatus also includes a valve to control fluid flow through the fluid flowline. The valve is to be in a first state to enable the piston to dampen movement of the component, and the valve is to be in a second state to enable the piston to hold the component substantially stationary.

Methods and apparatus to control movement of a component

The disclosure provides in one embodiment an electrical conductor pathway system for diverting an electric charge. The electrical conductor pathway system includes a substrate having a first surface to be printed on and having one or more grounding points. The electrical conductor pathway system further includes a direct write conductive material pattern printed directly onto the first surface via a direct write printing process. The direct write conductive material pattern forms one or more electrical pathways interconnected with the one or more grounding points. The one or more electrical pathways interconnected with the one or more grounding points divert the electric charge from the first surface to the one or more grounding points.

Electrical conductor pathway system and method of making the same

A latch pin actuator comprises a primary lock, a spring, and a piston. The primary lock is attached to a primary lock cam and has a notch. The spring is biased to lock the primary lock. The piston is configured to unlock the primary lock.

Folding wing system

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 variable camber system for an aircraft may include a variable camber trim unit (VCTU) positioned between an inboard device and an outboard device. The inboard device and the outboard device may be mounted to at least one of a leading edge and a trailing edge of a wing. The VCTU may include a speed sum gearbox having an inboard shaft coupled to the inboard device and an outboard shaft coupled to the outboard device. The VCTU may additionally include a VCTU electric motor engaged to the speed sum gearbox. The VCTU electric motor may be selectively operable in conjunction with the speed sum gearbox to rotate the outboard shaft independent of the inboard shaft in a manner causing the outboard device to be actuated independent of the inboard device.

Variable camber flap system and method

A system for varying a wing camber of an aircraft wing may include a leading edge device coupled to the wing. The leading edge device may be configured to be actuated in an upward direction and a downward direction relative to a retracted position of the leading edge device.

Leading edge variable camber system and method

An apparatus comprises a sensor system, a flexible line, and a sensor. The sensor system is capable of detecting skew in at least some of a plurality of control surfaces for a vehicle. The flexible line extends across a number of interfaces for a portion of the plurality of control surfaces. The sensor is connected to the flexible line and is capable of detecting the skew in the portion of the plurality of control surfaces in response to a selected amount of movement of the flexible line.

Slat skew detection system

A method for detecting freewheeling skew failures in the wing flaps of an aircraft includes measuring the outputs of flap skew sensors when the aircraft is in flight (IF) and the flaps are extended to a selected position, and when the aircraft is next on the ground (OG) and the flaps are extended to the selected position. The respective differences between the IF and OG outputs of symmetrical pairs of the flap skew sensors are computed, and then the respective difference between the computed IF output difference and the computed OG output difference of each symmetrical pair of the sensors is computed. The computed IF and OG difference of each symmetrical pair of the sensors is then compared with each of predetermined maximum and minimum threshold value to determine whether a freewheeling skew failure exists in any of the flaps of the aircraft.

In-flight detection of wing flap free wheeling skew

A skewed-roller brake assembly is provided, including a first rotor disc and a second rotor disc . A stator disc , positioned between the first and second rotor discs , includes a plurality of skewed-roller slots formed through the stator disc . A pair of roller elements are positioned within each of the plurality of skewed-roller slots such that a first of the pair of roller elements protrudes from the stator disc in the direction of the first rotor disc and a second of said pair of roller elements protrudes from the stator disc in the direction of the second rotor disc . When the first and second rotor discs are moved towards the stator disc , the first of the pair of roller elements and the second of the pair of roller elements rotate in concert while transmitting frictional torque to the first rotor disc and the second rotor disc respectively.

Duplex skewed-roller brake disc

Growing community of inventors

Snohomish, WA, United States of America

Mark John Gardner