Hamilton Sundstrand Corporation

Adam M Finney

Louis J Bruno

Thomas M Zywiak

Michael James Krenz

Andreas C Koenig

Kris H Campbell

Michael C Harke

Robert Scott Downing

Jeffrey T Wavering

Charles Patrick Shepard

Young Kyu Park

Darrell E Ankney

Victor Barger

Carl A Wagner

Scott F Kaslusky

Erik Harrington

Daniel R Sabatino

Christian Miller

Timothy Michael Mayer

Yuniya S Bishop

Massoud Vaziri

Eugene W Dolfi

Artemio Pérez

Adam Crandall

David L Jacques

Brandon M Grell

Charles Beecroft

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

An integrated torque limiter/no-back device for use in an actuator with an input shaft, an output, and a gear reduction. The device includes an input ramp, an output ramp coupled to the gear reduction, a combined ramp disposed between the input ramp and the output ramp, a first plurality of balls arranged between the input ramp and the combined ramp, a second plurality of balls arranged between the combined ramp and the output ramp, a pin, and a brake. The pin extends from the input ramp to the combined ramp and coupled to the input shaft. The combined ramp, the output ramp, and the second plurality of balls therebetween are configured to operate as a torque limiter by causing the combined ramp and the output ramp to separate and the output ramp to engage the brake when the torque from the input shaft exceeds a torque threshold.

Integrated torque limiter/no-back device

An integrated torque limiter/no-back device for use in an actuator with an input shaft, an output and gear reduction. The device includes an input ramp to receive torque from the input shaft; a combined ramp to transfer torque; an output ramp to transfer torque to the gear reduction; one or more balls between the input ramp and the combined ramp and between the combined ramp and the output ramp to transfer torque; and a brake for causing torque to be grounded and for preventing backdriving of the input shaft by preventing movement of one or more of the input ramp, the combined ramp and the output ramp when a torque threshold has been met. The input ramp and the output ramp are a no-back ramp and a torque limiter ramp, respectively, and the device also includes a pin between the combined ramp and one or more of the no-back ramp and the gear reduction for transferring torque.

An inductor comprises a ferromagnetic core, a litz wire conductor encircling the ferromagnetic core, a housing, a bobbin, a conductive pin, and a seal assembly. The housing encloses the ferromagnetic core and the litz wire conductor. The conductive pin is conductively attached to the litz wire conductor, and extends therefrom to form an external electrical contact. The bobbin supports the litz wire conductor and positions the conductive pin in alignment with an aperture in the housing which is sealed against fluid egress by the seal assembly.

Sealed inductor connection using litz wire

A method for controlling an aircraft power system having a plurality of generators includes determining a load set for controlling aircraft power as a function of a number of generators providing power and as a function of a health status of a load to be included in said load set.

Methods for aircraft emergency power management

A disclosed emergency power system includes multiple emergency power devices that are each sized to provide partial power during emergency operation and/or full power for a portion of emergency operation.

Multi-source emergency power optimization

A cooling system includes a compressor for compressing a refrigerant from a subcritical state to a supercritical state, a cooler for transferring heat from the refrigerant, an expander for expanding the refrigerant in the supercritical state, an expansion valve for expanding the refrigerant from the supercritical state to the subcritical state and an evaporator for transferring heat from a cooling fluid to the refrigerant in the subcritical state. Work extracted by the expander provides power to the compressor. A method for cooling a vehicle includes compressing a refrigerant from a subcritical state to a supercritical state, cooling the refrigerant, expanding the refrigerant in the supercritical state where work produced by expanding the refrigerant is used to compress the refrigerant, expanding the refrigerant from the supercritical state to the subcritical state, cooling a cooling fluid with the refrigerant in the subcritical state and cooling vehicle components with the cooling fluid.

Transcritical fluid cooling for aerospace applications

A gas turbine engine includes a main compressor section for compressing air, a main combustor section positioned downstream of the main compressor section, a main turbine section positioned downstream of the main combustor section, and a spool extending from the main compressor section to the main turbine section. A second turbine is fluidically connected to the main compressor section by a bleed passage. An electrical generator is mechanically driven by both the spool and the second turbine.

Gas turbine bleed energy recovery via counter rotating generator

Growing community of inventors

Rockford, IL, United States of America

Adam M Finney