Honeywell International Inc.

Terry Ahrendt

Andrew T Johnson

Kevin K Chakkera

Douglas M Smith

Todd Langston

Paul W Schwerman

Dean E Sunderland

Richard J Foley

Tim Moore

Michael R Madsen

Sensing systems and methods are provided for compensating for offset and gain changes. A sensing system includes a magnetic element, a current sensing arrangement to provide a current measurement signal influenced by a flux induced in the magnetic element, an oscillator arrangement to provide a reference oscillating current signal configured to induce an oscillating flux in the magnetic element, and a compensation arrangement coupled the current sensing arrangement to adjust the current measurement signal to compensate for gain changes in the measurement signal output and provide a compensated current measurement based at least in part on the adjusted measurement signal and the reference oscillating current signal. The oscillating flux influences the current measurement signal output by the current sensing arrangement.

Magnetic field sensor compensation methods and systems

Methods and systems are provided for authorizing a command of an integrated modular environment in which a plurality of partitions control actions of a plurality of effectors is provided. A first identifier, a second identifier, and a third identifier are determined. The first identifier identifies a first partition of the plurality of partitions from which the command originated. The second identifier identifies a first effector of the plurality of effectors for which the command is intended. The third identifier identifies a second partition of the plurality of partitions that is responsible for controlling the first effector. The first identifier and the third identifier are compared to determine whether the first partition is the same as the second partition for authorization of the command.

Methods and systems for authorizing an effector command in an integrated modular environment

A system for moving an aircraft thrust reverser component includes a power drive unit, a thrust reverser actuator assembly, and a tertiary lock system. The power drive unit is operable to rotate and supply a rotational drive force. The thrust reverser actuator assembly receives the rotational drive force from the power drive unit and moves the thrust reverser component between a stowed position and a deployed position. The tertiary lock system selectively engages and disengages the thrust reverser component and includes a tertiary lock power unit, an electromechanical tertiary lock assembly, and a voltage limiting circuit. The voltage limiting circuit limits the voltage magnitude of a control signal supplied to the tertiary lock assembly to a predetermined value.

Tertiary lock system power unit

Electrical thrust reverser tertiary lock system including a voltage limiting circuit

A solenoid control circuit that includes two switching networks that are selectively opened and closed in a current limit cycle to control the magnitude of the current flowing through the solenoid. The configuration of the switching networks is such that current flows through an energy dissipating resistor only when the solenoid is commanded off by the solenoid control circuit, and not during the current limit cycle. Thus, the energy dissipated by this resistor is reduced relative to other solenoid control circuits, making it more efficient, and reducing EMI emissions from the circuit while providing for a fast solenoid response.

Circuit and method for controlling current flow through a solenoid

A gearless electric thrust reverser actuator includes an electric motor that is coupled to a jack screw without any intervening gears. The actuator may additionally include all of the actuation and sensing components in a single actuation package. Thus, the actuator is relatively lightweight and compact.

Gearless electric thrust reverser actuators and actuation system incorporating same

An electromechanical thrust reverser actuation system that is designed with non-symmetric redundant channels is interfaced with an aircraft engine control system that is also redundantly designed. In one embodiment, the engine control system is also designed with non-symmetric redundant channels, and in another embodiment it is designed with symmetric redundant channels.

System architecture for electromechanical thrust reverser actuation systems

An electric control system and method for operating the cowl doors of an aircraft engine that includes one embodiment with one or more electric motors that are energized to move the cowl doors to the open position. The motor is de-energized and the cowl doors are allowed to close under their own weight, driving the motor and causing it to operate as a generator. An electrical load absorbs the energy generated by the motor while the cowl doors close, thereby limiting the speed at which the doors close.

System and method for controlling the movement of an aircraft engine cowl door

A system for controlling one or more jet engine thrust reversers includes a motor, a speed sensor, and a controller circuit. The motor is coupled to one or more jet engine moveable thrust reverser components for moving the one or more moveable thrust reverser components to at least a deployed position. The speed sensor is operable to sense the a rotational speed of the motor. The controller circuit has an output coupled to the motor for selectively energizing and deenergizing the motor in response to the speed sensor sensing that the rotational speed of the motor is, respectively, at or above a first predetermined rotational speed and at or below a second predetermined rotational speed. The system controls the deployment operation of the jet engine thrust reversers such that unwanted mechanical and electrical loads are avoided.

Method for controlling the deployment of jet engine thrust reversers

A system for controlling one or more jet engine thrust reversers includes a motor, a position sensing device, and a controller circuit. The motor is coupled to one or more jet engine thrust reverser moveable components for moving the one or more thrust reverser moveable components to at least a stowed position. The position sensing device is operable to sense at least when the one or more thrust reverser moveable components attain a predetermined position relative to the stowed position. The controller circuit has an output coupled to the motor so the motor rotates at a variable speed in response to a position sensing device that senses when the predetermined position is attained. The system controls the stowage operation of the jet engine thrust reversers such that structural damage is avoided, and/or a limit cycle condition is prevented, and/or engagement of stow locks is assured.

System and method for controlling the stowage of jet engine thrust reversers

System and method for controlling the deployment of jet engine thrust reversers

An electric thrust reverser actuation system includes an electric motors that is controlled to operate in both a motoring mode and a generating mode. During normal actuation system operations, the electric motor is controlled to operate in the motoring mode to move one or more moveable thrust reverser components. During a power interrupt event, in which the motor's primary power source is lost, the motor is controlled to operate in the generating mode. The electrical power generated by the motor during its operation in the generating mode maintains the thrust reverser system locking mechanisms in an energized, unlocked condition, thereby preventing damage to system components.

Growing community of inventors

Mesa, AZ, United States of America

Terry Ahrendt