Goodrich Corporation

United Technologies Corporation

Hamilton Sundstrand Corporation

Goodrich Corporatioln

Kevin Rehfus

Eric Daniel Cahill

David Bernard Drennen

Harald Klode

Robert French

Joseph E Beason

Thomas Freshour

Albert Keith Pant

Satinder Mann

Marc Georgin

Scott Streng

Jantzen Hinton

David Drennan

Douglas Lee Simpson

Robert L French

Harold Klode

The present disclosure provides an electromechanical brake actuator system comprising an electromechanical brake actuator coupled to a derived position sensor, the derived position sensor comprising a controller, a rotation sensor, and an output drive circuit. In various embodiments, the derived position sensor may be configured to receive a first motor shaft angular velocity at a first time, receive a second motor shaft angular velocity at a second time, calculate a linear translation distance, and sum the linear translation distance and a previous ram position to obtain an actual ram position.

Brake position and wear detection systems and methods

The present disclosure provides an actuator assembly having a ball nut comprising a helical track and a ball screw. The ball screw of the actuator assembly includes a first translation bearing track having a first diameter, wherein the helical track and the first translation bearing track form a first translation bearing raceway in which a first translation bearing ball is disposed. The ball screw further includes a second translation bearing track having a second diameter, wherein the helical track and the second translation bearing track form a second translation bearing raceway in which a second translation bearing ball is disposed. The first diameter and the second diameter are not equal.

Actuator ball screw for improved load sharing

The present disclosure includes the use of a smart load cell in a system for controlling an electromechanical actuator. A load cell may be positioned along the outer surface of the electromechanical actuator. Further, the load cell may utilize strain gages and a microcontroller. The load cell may be configured to transmit data to an electric brake actuator controller which includes calibration for operating temperature of the electromechanical actuator.

Actuator system with smart load cell

A mechanical linear actuator in an aircraft brake may include a ball nut, a ball screw, and an actuator drive unit housing. The ball screw may rotate to drive the ball nut axially. The ball screw and the actuator drive unit housing may form a series of annular raceways. The ball screw may have a first window corresponding to a first raceway and a second window corresponding to a second raceway. Balls may be inserted into the first raceway through the first window and into the second raceway through the second window.

Ball screw assembly for aircraft brake

An electromechanical actuator is provided comprising a housing, a rotor disposed in the housing, an selective gearbox mechanically coupled to the rotor and disposed in the housing, a first output of the selective gearbox configured to rotate at a different speed than the rotor, and a second output of the selective gearbox configured to rotate at a same speed as the rotor.

Electomechanical brake actuator with variable speed epicyclic gearbox

The present disclosure provides an electromechanical actuator comprising an actuator drive unit housing, a relief formed in the actuator drive unit housing, a column defined by the relief positioned adjacent to a second relief, and a load cell comprising the column and a strain gauge coupled to the column.

Actuator drive unit with load cell

An integrated actuator drive unit (ADU) assembly for an electric motor actuator is disclosed. The integrated ADU assembly may comprise at least one of an integrally formed ring gear, an integrally formed thrust bearing and integrally formed load cell. The integrated ADU assembly may comprise a portion of an electromechanical actuator. The electromechanical actuator may be utilized for aircraft braking systems.

Integral actuator design

A park brake system for an electric motor actuator is provided. The system may comprise a wrap spring that may rotatably engage the shaft. In this regard, the system may be configured to exert a radial force on a shaft of the electric motor actuator to lock the actuator. Moreover, in various embodiments, the system may be bi-stable.

Wrap spring park brake system, apparatus and method

An electro-mechanical actuator in an aircraft brake may include a ball nut piston, and endcap coupled to the ball nut piston, a retaining ring coupled to the endcap, and a puck secured within the endcap. The puck may be permanently retained within the retaining ring. The retaining ring may be a split ring which is installed around a base of the puck. The puck may be inserted within a single-piece retaining ring, and the retaining ring may be bent over a base of the puck.

Aircraft brake puck assembly

A brushless DC motor is provided. The brushless DC motor comprises a motor housing around an axis, a stator assembly inside the motor housing, a carrier plate fixed relative to the stator assembly, and a Hall effect sensor assembly removably coupled to the carrier plate. A method of making a brushless DC motor is also provided comprising fixing a carrier plate relative to a stator assembly of a brushless DC motor assembly, and fixing a first Hall effect sensor array to the carrier plate.

Brushless motor with modular position sensor

Systems and methods are disclosed for aircraft braking and taxiing systems for use in, for example, an aircraft. In this regard, a system may comprise an electric motor and a clutch. The electric motor may include a first output shaft and a second output shaft. The clutch may selectively engaging the motor to at least one of a driver transmission and a brake transmission, wherein, in response to engagement with the driver transmission, the electric motor drives, exclusively, an aircraft wheel via the first output shaft, wherein, in response to engagement with the brake transmission, the electric motor drives, exclusively, a brake clamping system via the second output shaft to apply force to an aircraft brake disk stack.

Systems and methods for aircraft braking and taxiing

An electromechanical actuator housing assembly comprising a reinforcement ring is disclosed herein. The design of the electromechanical actuator housing assembly may be directed to improving load measurement accuracy. The design of the electromechanical actuator housing assembly may be directed to reducing housing deflections. A method of manufacture of an EMA housing assembly is also disclosed herein. This method may include an electromechanical actuator housing assembly having a reinforcement ring.

Growing community of inventors

Troy, OH, United States of America

Kevin Rehfus