An apparatus for supporting a wing flap of an aircraft includes a support fitting configured to be coupled to a wing of the aircraft. The apparatus also includes a first link, pivotably coupled to the support fitting and configured to be pivotably coupled to the wing flap, and a second link, separably coupled to the support fitting and configured to be pivotably coupled to the wing flap.

An apparatus for supporting a wing flap of an aircraft includes a support fitting configured to be coupled to a wing of the aircraft. The apparatus also includes a first link, pivotably coupled to the support fitting and configured to be pivotably coupled to the wing flap, and a second link, separably coupled to the support fitting and configured to be pivotably coupled to the wing flap.

A system for the prioritization of flight controls in an electric aircraft is illustrated. The system includes a plurality of flight components, a sensor, and a computing device. The plurality of flight components are coupled to the electric aircraft. The sensor is coupled to each flight component of the plurality of flight components. Each sensor of the plurality of sensors is configured to detect a failure event of a flight component of the plurality of flight components and generate a failure datum associated to the flight component of the plurality of flight components. The computing device is communicatively connected to the sensor and is configured to receive the failure datum associated to the flight component of the plurality of flight component from the sensor, determine a prioritization element as a function of the failure datum, and restrict at least a flight element as a function of the prioritization element.

A system for the prioritization of flight controls in an electric aircraft is illustrated. The system includes a plurality of flight components, a sensor, and a computing device. The plurality of flight components are coupled to the electric aircraft. The sensor is coupled to each flight component of the plurality of flight components. Each sensor of the plurality of sensors is configured to detect a failure event of a flight component of the plurality of flight components and generate a failure datum associated to the flight component of the plurality of flight components. The computing device is communicatively connected to the sensor and is configured to receive the failure datum associated to the flight component of the plurality of flight component from the sensor, determine a prioritization element as a function of the failure datum, and restrict at least a flight element as a function of the prioritization element.

A coaxial rotor system for a rotorcraft includes a mast, a top rotor assembly and a bottom rotor assembly. The top rotor assembly is coupled to the distal end of the mast. The bottom rotor assembly includes a motor configured to provide rotational energy to the mast, thereby rotating the top rotor assembly. The bottom rotor assembly experiences a torque reaction force responsive to the motor rotating the mast such that the top and bottom rotor assemblies counter rotate.

A coaxial rotor system for a rotorcraft includes a mast, a top rotor assembly and a bottom rotor assembly. The top rotor assembly is coupled to the distal end of the mast. The bottom rotor assembly includes a motor configured to provide rotational energy to the mast, thereby rotating the top rotor assembly. The bottom rotor assembly experiences a torque reaction force responsive to the motor rotating the mast such that the top and bottom rotor assemblies counter rotate.

Example flap actuation systems and related methods are disclosed herein. An example control surface actuation system includes processor circuitry to cause a first actuator to generate an output to operatively couple the first actuator to a first drive arm; cause a second actuator to generate an output to operatively couple the second actuator to a second drive arm; cause the first actuator and the second actuator to move a control surface when the first actuator and the second actuator are in an operative state; detect the first actuator as in a failed state; and in response to the first actuator being in the failed state, cause first actuator to refrain from generating the output to disrupt the operative coupling between the first actuator and the first drive arm; and cause the second actuator to move the control surface via the first drive arm and the second drive arm.

Example flap actuation systems and related methods are disclosed herein. An example control surface actuation system includes processor circuitry to cause a first actuator to generate an output to operatively couple the first actuator to a first drive arm; cause a second actuator to generate an output to operatively couple the second actuator to a second drive arm; cause the first actuator and the second actuator to move a control surface when the first actuator and the second actuator are in an operative state; detect the first actuator as in a failed state; and in response to the first actuator being in the failed state, cause first actuator to refrain from generating the output to disrupt the operative coupling between the first actuator and the first drive arm; and cause the second actuator to move the control surface via the first drive arm and the second drive arm.

An automatic actuator system is provided. The automatic actuator system includes an input linkage that receives an input and an output linkage adapted to control a flight surface actuator. The automatic actuator system includes a first strain wave gear having a first circular spline coupled to the input linkage and a first flex spline rotatably coupled to the first circular spline. The automatic actuator system includes a second strain wave gear having a second circular spline coupled to the first flex spline. The second strain wave gear includes a second flex spline, and the second flex spline is coupled to the output linkage such that at least a portion of the input from the input linkage is transferred to the output linkage via the first strain wave gear and the second strain wave gear.

A brake for preventing rotation of a segment of a transmission line used for actuation of control surfaces of an aircraft, including a retaining arm configured for connection to a fixed element of the aircraft, a clamp and a connection member. The clamp includes a first clamp portion having a first engagement surface and a second clamp portion having a second engagement surface facing the first engagement surface. The clamp portions are movable with respect to each other so as to vary a distance between the engagement surfaces. The clamp portions are configured to apply a pressure toward each other with the transmission line segment being received between the engagement surfaces. The connection member interconnects the clamp and the retaining arm, and is selectively configurable between an unlocked configuration allowing relative movement between the clamp and the retaining arm and a locked configuration preventing the relative movement.