Hamilton Sundstrand Corporation

Timothy Michael Mayer

Cory M Crandall-Seibert

Victor Barger

Erik Harrington

Andrew N Baines

Gary L Voss

Sean Bradshaw

Roger F Glenn

Artemio Pérez

Christian Miller

Yuniya S Bishop

Michael C Harke

Darrell E Ankney

David G Hill

Adam M Finney

Eugene W Dolfi

Dale W Massolle, Jr

Rachel Gallagher

Adam Crandall

Paul F Hastings

Artemio Perez

Dale W Massolle

A secondary flight control system comprising: a first flight control surface system; a second flight control surface system; and a power distribution unit operably connected to the first flight control surface system and the second flight control surface system, wherein the power distribution unit is configured to generate torque to actuate the first flight control surface system and the second flight control surface system.

Control of multiple flight control surface systems using single power drive unit

A method for braking a motor in a high lift system of an aircraft, the high lift system comprising a central power drive unit for moving high lift surfaces arranged at a wing through providing rotational power by means of a transmission shaft to a plurality of drive stations operably coupled with the high lift surfaces; which power drive unit is operatively coupled to a controller and comprises at least one electric motor coupled therewith. The method includes determining a braking requirement for the at least one electric motor, measuring at least one of a current command to the motor and a current speed and direction of the at least one electric motor, based on the braking requirement, applying a braking command to the at least one electric motor, and reducing the braking command as the at least one electric motor comes to rest.

Flight control system regenerative braking

A predictive system is provided and include a torque-limiter, a sensor disposed to sense a condition of the torque-limiter and a processing system. The processing system is coupled to the sensor and configured to process readings of the sensor, to calculate whether the condition of the torque-limiter is indicative of degradation or failure incidents based on the readings being processed and to determine whether an action should be taken based on a calculation result.

Torque-limiter health monitoring

A braking test for a high lift system. The system including a plurality of high lift surfaces movably arranged at a wing, a plurality of drive stations coupled with the high lift surfaces via a transmission shaft, a power drive unit coupled with the transmission shaft including an electric motor operably coupled with a brake, and a control unit operably coupled to the power drive unit. The control unit executing a method for testing the brake, including actuating an electric motor, acquiring a sensor output of a sensor coupled during the actuating of the motor and determining a motion of the motor, activating a selected brake under test, measuring an elapsed time until the brake has arrested the motion, and determining if the elapsed time is less than a threshold. Generating a brake failure signal for the selected brake if the elapsed time exceeds the threshold.

Method to measure aircraft high-lift system brake response time

A selector lever that comprises a shaft rotatably attached to a pivot and arranged between two detent plates, each of the detent plates having a plurality of slots arranged for receiving a detent pin located on the shaft. Each of the plurality of slots on each of the two detent plates is defined by a radial depth. One or more of the plurality of slots is a failure detection slot having an extended radial depth. When one of the detent pins has failed, the opposing detent pin is allowed to travel into the extended radial depth when placed in the failure detection slot. This action reveals a failure indicator, providing a visual indication that one of the detent pins has failed.

Visual failure indication for selector lever

A selector lever with redundant detent pins and detent plates and a method for using the selector lever to test for a failure of one or more detent pins. The selector lever includes at least two slides for independently moving the detent pins within the detent plates. The independent slides allow one detent pin to remain engaged. With only one detent pin engaged, the operator may test the ability to move the shaft and conclude whether or not the detent pin has failed.

Selector lever with independent slides

A selector lever with two detent plates and corresponding detent pins that travel along a shaft includes a float that moves with each of the detent pins. When a detent pin fails, a float pin remains engaged with a catch, thereby preventing rotational movement of the shaft.

Device for preventing rotational movement of failed selector lever

A slat disconnect sensor includes a base. First and second arms are spaced apart from one another and are operatively supported by the base. At least one of the first and second arms have an end mounted to the base and is rotatable relative thereto at a pivot between connect and disconnect conditions. A mechanical link includes first and second link portions respectively secured to the first and second arms. The link interconnects the first and second arms and includes a weakened area providing a frangible connection in the connect condition and is configured to break at the frangible connection in the disconnect condition. A fuse includes first and second fuse portions operatively mounted to the first and second arms. The fuse is interconnected between the first and second arms providing continuity in the connected condition, and continuity is broken between the first and second portions in the disconnect condition.

Growing community of inventors

Belvidere, IL, United States of America

Timothy Michael Mayer