Example flap actuation systems and related methods are disclosed herein. An example flap actuation system includes a first actuator, a second actuator, a first drive arm coupled to the first actuator and to a flap, a second drive arm coupled to the second actuator and to the flap, a first cam, and a first output shaft. The first cam is to couple to the first drive to enable the first actuator to actuate the flap via the first drive arm. The example flap actuation system includes a second cam and a second output shaft. The first cam is to be uncoupled from the first drive arm in response to a failure of the first actuator. The second actuator is to actuate the flap via the first drive arm and the second drive arm in response to the failure of the first actuator.

A system for flight control for managing actuators for an electric aircraft is provided. The system includes a controller, wherein the controller is designed and configured to receive a sensor datum from at least a sensor, generate an actuator performance model as a function of the sensor datum, identify a defunct actuator of the electric aircraft as a function of the sensor datum and the actuator performance model, generate an actuator allocation command datum as a function of at least the actuator performance model and at least the identification of the defunct actuator, and perform a torque allocation as a function of the actuator allocation command datum.

A system for flight control for managing actuators for an electric aircraft is provided. The system includes a controller, wherein the controller is designed and configured to receive a sensor datum from at least a sensor, generate an actuator performance model as a function of the sensor datum, identify a defunct actuator of the electric aircraft as a function of the sensor datum and the actuator performance model, generate an actuator allocation command datum as a function of at least the actuator performance model and at least the identification of the defunct actuator, and perform a torque allocation as a function of the actuator allocation command datum.

An aircraft includes an airframe with first and second wings having a fuselage extending therebetween. A propulsion assembly is coupled to the fuselage and includes a counter-rotating coaxial rotor system that is tiltable relative to the fuselage to generate a thrust vector. Tail assemblies are coupled to wingtips of the first and second wings each having an elevon that collectively form a distributed array of elevons. A flight control system is configured to direct the thrust vector of the coaxial rotor system and to control movements of the elevons such that the elevons collectively provide pitch authority and differentially provide roll authority for the aircraft in the biplane orientation. In addition, when the flight control system detects an elevon fault, the flight control system is configured to perform corrective action responsive thereto at a distributed elevon level or at a coordinated distributed elevon and propulsion assembly level.

An aircraft includes an airframe with first and second wings having a fuselage extending therebetween. A propulsion assembly is coupled to the fuselage and includes a counter-rotating coaxial rotor system that is tiltable relative to the fuselage to generate a thrust vector. Tail assemblies are coupled to wingtips of the first and second wings each having an elevon that collectively form a distributed array of elevons. A flight control system is configured to direct the thrust vector of the coaxial rotor system and to control movements of the elevons such that the elevons collectively provide pitch authority and differentially provide roll authority for the aircraft in the biplane orientation. In addition, when the flight control system detects an elevon fault, the flight control system is configured to perform corrective action responsive thereto at a distributed elevon level or at a coordinated distributed elevon and propulsion assembly level.

A mechanical synchronization device for a distributed system. A plurality of actuators actuate movement of control surface components of an aircraft. Each actuator has a first end coupled to a structure of the aircraft and a second end coupled to a control surface component, and a drive path from a motion provider to the control surface component, the control surface component being configured to move along the respective drive path. A power module controller is operable to simultaneously output motor drive power from a power module through an electrical bus to at least two of the motion providers in a synchronous or nearly synchronous manner to actuate movement of control surface components. The mechanical synchronization device is between at least two of the actuators and transfers torque between the actuators to maintain symmetry between the actuators. A load limiting device may limit the power transferred through the mechanical synchronization device.

A mechanical synchronization device for a distributed system. A plurality of actuators actuate movement of control surface components of an aircraft. Each actuator has a first end coupled to a structure of the aircraft and a second end coupled to a control surface component, and a drive path from a motion provider to the control surface component, the control surface component being configured to move along the respective drive path. A power module controller is operable to simultaneously output motor drive power from a power module through an electrical bus to at least two of the motion providers in a synchronous or nearly synchronous manner to actuate movement of control surface components. The mechanical synchronization device is between at least two of the actuators and transfers torque between the actuators to maintain symmetry between the actuators. A load limiting device may limit the power transferred through the mechanical synchronization device.

Systems and methods for deploying adjacent trailing edge flaps that are part of different flap assemblies of different stiffnesses are disclosed. An exemplary method comprises: deploying a first flap of a first flap assembly having a first stiffness by a first deployment amount and deploying a second flap adjacent the first flap by a second deployment amount where the deployment amount of the first flap part of the flap assembly of lower stiffness is greater than the second deployment amount of the second flap part of the flap assembly of higher stiffness. The difference in deployment amounts may be adapted to improve continuity between the first flap and the second flap when the first and second flaps are deployed and subjected to an aerodynamic load.

Systems and methods for deploying adjacent trailing edge flaps that are part of different flap assemblies of different stiffnesses are disclosed. An exemplary method comprises: deploying a first flap of a first flap assembly having a first stiffness by a first deployment amount and deploying a second flap adjacent the first flap by a second deployment amount where the deployment amount of the first flap part of the flap assembly of lower stiffness is greater than the second deployment amount of the second flap part of the flap assembly of higher stiffness. The difference in deployment amounts may be adapted to improve continuity between the first flap and the second flap when the first and second flaps are deployed and subjected to an aerodynamic load.

A flight control system that is adapted for controlling movements of a rotary wing aircraft while considering passenger discomfort, to a rotary wing aircraft with such a flight control system, and to a method of operating a flight control system. The flight control system includes sensors configured to generate sensor data based on captured motions of the rotary wing aircraft, motion actuators that are adapted for inducing a translational and/or a rotational movement of the rotary wing aircraft about at least one of a yaw axis, a roll axis, or a pitch axis, and a passenger discomfort-aware control unit that is configured to generate, based on the sensor data, passenger discomfort-aware actuator control signals for controlling the motion actuators of the rotary wing aircraft.