An overall efficiency of an actuator system can be monitored to determine the health of the actuator system. A ratio between the output power of the actuator system and the input power of the actuator system is monitored over time. Degradation of the efficiency of the actuator system may be observed and corrective action taken before failure of the actuator system.

A simplex Flight Control Computer (FCC), usable in conjunction with a neighboring FCC, includes an input providing module for receiving sensor, system and neighboring FCC data; a processing unit for executing a command partition and a monitor partition, the processing unit receives the sensor, system data and neighboring FCC data; the monitor partition monitors the neighboring FCC data and provides a monitoring indicative signal to the neighboring FCC, and the command partition generates command signals; a hardware monitoring module provides a validity signal indicating FCC health; an output cutoff module receiving the FCC validity signal and enable signals generated by each monitor partition; the output cutoff module providing an enable signal based on a predetermined enabling strategy; and an enable switch connected with the output cutoff module and the processing unit and providing a received signal from the command partition according to the enable signal.

The redundancy control device includes three controllers that output status signals, a majority voting circuit to which a first voltage or a second voltage is supplied as an output signal through an output line of each controller, a switch provided in each output line, a voltage supply unit provided for each output line to supply the second voltage to the output line when the first voltage is lost, a latch circuit provided for each output line to latch the second voltage when the second voltage is supplied thereto and continue to output the second voltage, a comparison circuit provided for each controller to output a comparison signal based on a comparison of the status signals, and a switch control unit provided for each switch to outputs a switch signal to the switch in response to the comparison signal from the comparison circuit.

A braking unit includes a braking means and means, configured to receive power from a power line, for engaging and disengaging the braking means. A first power signal line is provided that is connected to the means for engaging and disengaging said braking means and a second power signal line is also provided that is connected to said means for engaging and disengaging said braking means. The first power signal line is connected to the means for engaging and disengaging the braking means via a first power switching device and the second power signal line is connected to the means for engaging and disengaging the braking means via a second power switching device.

A system for distributed pilot control of an aircraft includes a plurality of flight components, an aircraft control located within the aircraft, and an aircraft component attached to a flight component of the plurality of flight components, wherein the aircraft component is configured to receive, from a command sensor attached to the aircraft control, an aircraft command, obtain, from an attitude sensor, an aircraft orientation, receive, as a function of a notification unit, a pilot signal, and command the flight component to produce a response command as a function of the pilot signal.

A hover and thrust control assembly for dual-mode aircraft including a plurality of flight components mechanically coupled to an aircraft includes a support structure attached to an aircraft frame of an aircraft having a control stick coupled to the support structure. The control stick may include a length and radius and configured to be manipulated along a plurality of axes, wherein the manipulation of the control stick produces an electronic signal, wherein the control stick is further configured to be manipulated rotationally about the length of the control stick. A first interface device disposed on the control stick may be configured to receive an interaction and adjust a lift of the dual-mode aircraft as a function of the interaction. A second interface device may be configured to receive an interaction and adjust the lift of the dual-mode aircraft as a function of the interaction.

The present invention is directed to systems and methods for redundant flight control configured for use in an aircraft. More specifically, a system is provided that includes a plurality of actuators that are configured to move a flight component of an aircraft such that one actuator is configured to move the flight component if the other actuator fails to move the flight component upon receipt of an attitude command from a pilot control.

A Stability and Control Augmentation System (“SCAS”) module comprising one or more SCAS actuators, the or each SCAS actuator comprising a mechanical component that translates rotational motion to linear motion along a first axis of said SCAS; one or more electric motors for driving linear movement of the mechanical component in response to a command signal; and one or more angular transducers to detect the position of the SCAS actuator along the first axis.

An actuator provided with a motor for moving an output arrangement, the actuator including both an output lever and a fusible connection that acts up to a mechanical torque threshold to constrain the output arrangement and the output lever to move together in rotation about an axis of rotation. The actuator also includes a fluid damper device housed between the output lever and the output arrangement to act, following rupture of the fusible connection, to damp movement of the output lever relative to the output arrangement in rotation about the axis of rotation.

In an embodiment, a method of monitoring force equalization (FEQ) sensors on a vehicle utilizing redundant actuation systems for one or more control surfaces includes determining, via a force sensor, a first measured force applied by a first actuation system in relation to a control surface, where the control surface is redundantly serviced by a plurality of actuation systems that include the first actuation system. The method also includes updating a measured-force time series for the first actuation system with the first measured force. The method also includes determining variation in at least a portion of the measured-force time series responsive to the updating. The method also includes identifying a first static condition in the measured-force time series in response to a determination that the variation in the measured-force time series is no greater than a minimum amount of variation.