Hamilton Sundstrand Corporation

Christian Miller

Erik Harrington

John A Dickey

Robert C Cooney

Victor Barger

Michael C Harke

Michael J Hanson

Donald G Kilroy

Yuniya S Bishop

Kevin Case Fritz

Timothy Michael Mayer

Darrell E Ankney

Josh C Swenson

Artemio Pérez

Cory M Crandall-Seibert

David G Hill

Adam M Finney

Eugene W Dolfi

Gregory T Wallen

Rachel Gallagher

Adam Crandall

Jason B Kreienheder

Milorad Manojlovic

Michael Skirtich

Artemio Perez

A method of prognostic health monitoring is provided for use with an aircraft. The method includes performing real-time monitoring of torque generated for controlling positions of controllable surfaces at right- and left-hand-sides (RHS and LHS) of the aircraft, generating RHS and LHS torque information from results of the monitoring and comparing the RHS and LHS torque information at least with each other or with corresponding historic torque information.

Prognostic health monitoring for use with an aircraft

An aircraft is provided. The aircraft includes fuselage, an aerodynamic element extending from the fuselage and including a main section and an adjustable section which is adjustable relative to the main section, a power distribution unit (PDU) configured to generate torque to drive an adjustment of the adjustable section, an actuator, torque tubes and elastomeric couplings. The PDU is disposed proximate to a fuselage-aerodynamic interface. The actuator is disposed along the aerodynamic element and is receptive of the torque for driving the adjustment of the adjustable section. The torque tubes transmit the torque from the PDU to the actuator and are arranged between the PDU and the actuator such that adjacent torque tubes define an obtuse angle. The elastomeric couplings are disposed at respective ends of each of the torque tubes to enable torque transmission between at least the adjacent torque tubes defining the obtuse angle.

Flight control system transmission

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

Control surface operating systems for controlling aerodynamic control surfaces of aircraft are provided. The systems includes a drive system operably connected to a drive shaft, the drive system including a continuously variable transmission, at least one actuator operably connected to the drive shaft and arranged to convert rotational movement of the drive shaft to move at least a portion of the aerodynamic control surface, and at least one control surface operably connected to the at least one actuator, wherein the at least one control surface is adjusted by the at least one actuator.

Aerodynamic control surface operating system for aircraft using variable transmission

A method for fabricating a circuit board apparatus includes providing a circuit board that has a socket with at least one plated through-hole and providing a connector that has a housing with first and second connector interfaces that have, respectively, at least first and second connector contacts. The first connector interface opens into an interior of the housing such that there is a vapor path through the first connector interface and interior of the housing to the second connector contact at the second connector interface. The first connector contact is inserted through the resilient seal and into the plated through-hole such that the resilient seal intimately seals around the first connector contact to provide a barrier at the first connector interface into the vapor path.

Method for fabricating circuit board with resilient seal as vapor barrier

A method of prognostic health monitoring is provided for use with an aircraft. The method includes generating torque for controlling positions of controllable surfaces at right- and left-hand-sides (RHS and LHS) of the aircraft in a power drive unit (PDU) based on torque-limiter (TL) thresholds, performing real-time monitoring of the torque at the RHS and LHS of the aircraft, generating RHS and LHS torque information from results of the performing of the real-time monitoring, analyzing the RHS and LHS torque information and controlling operations of the PDU based on results of the analysis by at least one of modifying, tuning and defining the TL thresholds.

Prognostic health monitoring and jam detection for use with an aircraft

Actuator systems and methods for controlling aerodynamic control surfaces of aircraft including a first actuator receiving a first input and a first linear translation element that moves based thereon, the first linear translation element operably connected to a first portion of the control surface. A first sensor assembly is disposed relative to the first actuator that generates an output based on a displacement of the first translation element. A second actuator receives a second input and a second linear translation element moves based on the second input, the second linear translation element operably connected to a second portion of the control surface. A second sensor assembly is disposed relative to the second actuator that generates a second sensor output based on a displacement of the second translation element. A controller generates the inputs and receives the sensor outputs to determine if an error condition exists for the system.

Aerodynamic control surface movement monitoring system for aircraft

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 single-unit aerospace remote sensing and solid state power controller may include a processing module, a remote data concentrator (RDC) module in communication with the processing module, and configured to receive analog or discrete or discrete input comprising load sensor information and translate the analog or discrete input into a protocol operable by the processing module. The single-unit aerospace remote sensing and solid state power controller may further include a solid state power controller in communication with the RDC and the processing module, configured to receive load sensor information from the RDC module and control at least one load mechanism based on the load sensor information.

Combined remote sensing, processing, and solid state power control system

A system for mitigating a solid state power controller (SSPC) open fault caused by single event latchup (SEL) on a power module includes a microprocessor in a control communication and power supply module (CCP) configured to determine whether communication with a microcontroller in at least one of a solid state power controller (SSPC) and a second SSPC in the power module is lost. The microprocessor in the CCP is operatively connected to the power module and configured to notify, via a backplane communication bus, the microcontroller on the power module that the communication with the SSPC in the power module is lost. The microcontroller in the SSPC is configured to set a low power operation of a second SSPC in the power module not affected by SEL in response to loss of reception of command messages from the microprocessor in the CCP.

Single event latch up mitigation in solid state power controllers

A circuit board has a socket with at least one plated through-hole. A connector includes a housing that has first and second connector interfaces with, respectively, at least first and second connector contacts. The first connector interface opens into an interior of the housing such that there is a vapor path through the first connector interface and the interior of the housing to the second connector contact at the second connector interface. A resilient seal is located at the first connector interface. The first connector contact extends through the resilient seal and into the plated through-hole. The resilient seal intimately seals around the first connector contact and provides a barrier at the first connector interface into the vapor path.

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Beloit, WI, United States of America

Christian Miller