A control system for an aircraft, the system including a pilot input device configured to receive a pilot input, a plurality of sensors, each of the plurality of sensors positioned on a corresponding landing gear of the aircraft and configured to sense a parameter on the corresponding landing gear, and a controller in communication with the plurality of sensors, the controller configured to calculate an output command based on the pilot input and the sensed parameters of the landing gear, the output command including instructions for controlling a rotor of the aircraft.

A control system for an aircraft, the system including a pilot input device configured to receive a pilot input, a plurality of sensors, each of the plurality of sensors positioned on a corresponding landing gear of the aircraft and configured to sense a parameter on the corresponding landing gear, and a controller in communication with the plurality of sensors, the controller configured to calculate an output command based on the pilot input and the sensed parameters of the landing gear, the output command including instructions for controlling a rotor of the aircraft.

A system for adjusting a load on a tethered aircraft is disclosed. The aircraft is tethered to a payload. The system determines a new position for the tethered aircraft in the event that due to environmental effects, e.g., the aircraft is flying upwind or downwind, the load experienced by the tethered aircraft is not optimal.

A system for adjusting a load on a tethered aircraft is disclosed. The aircraft is tethered to a payload. The system determines a new position for the tethered aircraft in the event that due to environmental effects, e.g., the aircraft is flying upwind or downwind, the load experienced by the tethered aircraft is not optimal.

A wing, a method of controlling lift on a wing, and a system to produce lift on a wing are provided. The wing may include a fore-element, an aft-element, a pivotable linkage that operatively connects the aft-element leading edge to the fore-element trailing edge in a span-wise direction, and an actuator. The actuator may deflect the aft-element through a predetermined deflection angle about the pivotable linkage relative to the fore-element within less than or equal to two convective periods. The method may include deflecting a span-wise flap through the deflection angle in less than or equal to two convective periods to produce high lift. The system may include a sensor to detect an input and a controller to deflect the span-wise flap of the wing by the deflection angle in not more than two convective periods based on the received input signal.

A wing, a method of controlling lift on a wing, and a system to produce lift on a wing are provided. The wing may include a fore-element, an aft-element, a pivotable linkage that operatively connects the aft-element leading edge to the fore-element trailing edge in a span-wise direction, and an actuator. The actuator may deflect the aft-element through a predetermined deflection angle about the pivotable linkage relative to the fore-element within less than or equal to two convective periods. The method may include deflecting a span-wise flap through the deflection angle in less than or equal to two convective periods to produce high lift. The system may include a sensor to detect an input and a controller to deflect the span-wise flap of the wing by the deflection angle in not more than two convective periods based on the received input signal.

A system for communicating at least a pre-charging datum for an electric vehicle, the system including an electric aircraft, wherein the electric aircraft comprises, a sensor, wherein the sensor is configured to detect a connection with a charging connector, at least a battery pack, wherein the at least a battery pack including a plurality of battery cells, an aircraft recharging component, the aircraft recharging component including an aircraft side recharging component, wherein the aircraft side recharging component is configured to form a charge connection with the charging connector, a controller, wherein the controller is configured to generate a battery parameter set as a function of the connection with the charging connector, and transmit the battery parameter set to the charging connector.

An system (10) for an aircraft (1) including a controller (100) configured to receive at least one signal during a take-off procedure of the aircraft. The signal includes information representative of at least one parameter of the aircraft. The controller is configured to determine whether a current or future aircraft climb rate associated with the take-off procedure meets a criterion, on the basis of the at least one signal. The controller is configured to determine at least one remedial action to be taken, such as performance of at least a portion of a procedure to retract a landing gear of the aircraft, when the controller determines that the aircraft climb rate does not meet the criterion.

An system (10) for an aircraft (1) including a controller (100) configured to receive at least one signal during a take-off procedure of the aircraft. The signal includes information representative of at least one parameter of the aircraft. The controller is configured to determine whether a current or future aircraft climb rate associated with the take-off procedure meets a criterion, on the basis of the at least one signal. The controller is configured to determine at least one remedial action to be taken, such as performance of at least a portion of a procedure to retract a landing gear of the aircraft, when the controller determines that the aircraft climb rate does not meet the criterion.

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.