According to one embodiment, a pilot assistance system includes a trim assembly and a trim assembly control system. The trim assembly is operable to communicate with a pilot control device and operable to apply a force against the pilot control device in resistance of a command received from a pilot via the pilot control device. The trim assembly control system is in communication with the trim assembly, configured to identify a first pilot control device position relative to a reference pilot control device position, and configured to instruct the trim assembly to apply a cueing force against the pilot control device if the pilot control device is positioned proximate to the first pilot control device position.

According to one embodiment, a pilot assistance system includes a trim assembly and a trim assembly control system. The trim assembly is operable to communicate with a pilot control device and operable to apply a force against the pilot control device in resistance of a command received from a pilot via the pilot control device. The trim assembly control system is in communication with the trim assembly, configured to identify a first pilot control device position relative to a reference pilot control device position, and configured to instruct the trim assembly to apply a cueing force against the pilot control device if the pilot control device is positioned proximate to the first pilot control device position.

The subject matter of this specification can be embodied in, among other things, a motion control apparatus that includes a brushless DC motor to actuate a mechanical output based on a collection of phase power signals, a collection of first Hall effect sensors configured to provide a collection of first feedback signals in response to a sensed motor position and a sensed motor speed, a controller configured to determine a speed and position of the motor based on the feedback signals, and determine an electrical current level based on a collection of operational parameters and feedback signals including a position of the mechanical output, the motor speed, and the motor position, a current controller configured to provide electrical phase sequence output signals based on the electrical current level, and a motor driver configured to provide the collection of phase power signals based on the electrical phase sequence output signals.

A control device for controlling an aircraft, the control device including at least one motor-driven trim actuator with active type anchoring, the trim actuator including at least one electric motor, at least one electronic power circuit for electrically powering the electric motor(s), and speed reduction means for driving rotation of an outlet shaft of the trim actuator. The control device implements three distinct servo-control loops that are nested in one another, these three servo-control loops being formed by an electric current servo-control loop, a speed servo-control loop, and a force servo-control loop.

A control device for controlling an aircraft, the control device including at least one motor-driven trim actuator with active type anchoring, the trim actuator including at least one electric motor, at least one electronic power circuit for electrically powering the electric motor(s), and speed reduction means for driving rotation of an outlet shaft of the trim actuator. The control device implements three distinct servo-control loops that are nested in one another, these three servo-control loops being formed by an electric current servo-control loop, a speed servo-control loop, and a force servo-control loop.

A method of using a tactile signal warning device forming part of a human-operated flight control member of a rotorcraft. The warning device makes use of an anchorable motorized trim actuator for generating a resisting force against movement of the flight control member. The warning device comprises a warning unit that, as a function of a power margin (MP1) calculated by a predictor unit in compliance with a current regulation rating of the power plant and on condition that state data indicates that an autopilot is activated in a higher operating mode, acts to generate an order to activate the trim actuator depending on the conditions under which the flight control member is being moved as identified by a force management unit.

An apparatus for testing an aircraft Elevator Feel Computer (EFC) including a test box including a housing having a base and a first cover attached to the base. The apparatus includes a pressurized air delivery subsystem with an air pump disposed entirely within the base enclosure. A pressure regulator is to adjustably regulate an air pressure delivered through a regulated air port simultaneously to first and second pitot probes. The apparatus includes a two-channel pneumatic pressure measurement subsystem including first and second pressure gages connected respectively to first and second visco drains, which are connected, respectively to the first and second pitot probes. The apparatus includes a two-channel hydraulic pressure measurement subsystem including first and second hydraulic pressure displays connected respectively to first and second hydraulic transmitters, which are to connect to first and second metered pressure hydraulic inputs of a dual feel actuator from the EFC.

An apparatus for testing an aircraft Elevator Feel Computer (EFC) including a test box including a housing having a base and a first cover attached to the base. The apparatus includes a pressurized air delivery subsystem with an air pump disposed entirely within the base enclosure. A pressure regulator is to adjustably regulate an air pressure delivered through a regulated air port simultaneously to first and second pitot probes. The apparatus includes a two-channel pneumatic pressure measurement subsystem including first and second pressure gages connected respectively to first and second visco drains, which are connected, respectively to the first and second pitot probes. The apparatus includes a two-channel hydraulic pressure measurement subsystem including first and second hydraulic pressure displays connected respectively to first and second hydraulic transmitters, which are to connect to first and second metered pressure hydraulic inputs of a dual feel actuator from the EFC.

The invention relates to a flight control device for an aircraft, the device comprising a mount, a lever pivotally mounted on the mount, and mechanical means for generating a return force for the lever, said means including a spring and a first motor member that are arranged so that a first end of the spring is constrained to move in rotation with the lever and a second end of the spring is constrained to move in rotation with an outlet shaft of the first motor member. According to the invention, the flight control device includes an electrical assistance system for assisting said mechanical means for generating a return force.

An active inceptor apparatus and method for operating a machine. The apparatus comprises a stick member having a grip portion, the stick member being pivotably mounted relative to a housing. It further comprises a position sensor responsive to, and for generating signals indicative of, stick member position. A force sensor is provided on the stick member responsive to, and for generating signals indicative of, force applied to the stick by a user. The apparatus also includes a control unit operable to receive the position and force signals from the position and force sensors respectively. The control unit is operable to process the signals according to a predetermined relationship to determine a value FD indicative of force applied to the stick member relative to displacement of the stick member. The control unit is also operable to generate machine control signals as a function of position signals and force signals in dependence upon the value FD, for communication to the machine.