Method and device for determining trajectory to optimal position of a follower aircraft with respect to vortices generated by a leader aircraft. The method includes controlling trajectory of a follower aircraft to an optimal position where the follower aircraft benefits from effects of at least one of the vortices of a leader aircraft. A first section control step controls flight of the follower aircraft using current measurements of flight parameters, from a safety position to a search position, along an approach section passing through an approach zone. A second section control step controls flight of the follower aircraft using current measurements of flight parameters, from the search position to a precision position, along a search section passing through a search zone, and a third section control step controls flight of the follower aircraft, from the precision position to the optimal position, along an optimization section passing through an optimization zone.

This invention is to provide a method to entirely and effectively shade fixed tracts of land, such as school yard or athletics stadium, etc., with no roof, pole to support roof, or the like. To fix a sheet to multiple flying objects so that such sheet forms a fixed size of surface and make such flying objects fly in accordance with flying positions (including heights) decided based on elements, such as positions of the sun, etc.

This invention is to provide a method to entirely and effectively shade fixed tracts of land, such as school yard or athletics stadium, etc., with no roof, pole to support roof, or the like. To fix a sheet to multiple flying objects so that such sheet forms a fixed size of surface and make such flying objects fly in accordance with flying positions (including heights) decided based on elements, such as positions of the sun, etc.

An aircraft control system includes a longitudinal control module, an engine torque control module, and an actuator control system. The longitudinal control module is configured to generate a desired torque value and a desired elevator position value for an aircraft based on a desired airspeed value, a desired altitude value, an actual airspeed value, and an actual altitude value. The engine torque control module is configured to generate a desired power lever position value based on the desired torque value and a measured engine torque value that indicates a measured engine torque in the aircraft. The actuator control system is configured to generate a power lever position command and an elevator position command for the aircraft based on the desired power lever position value and the desired elevator position value.

A vertical lift rotor propulsor assembly comprises a boom having a casing with a casing profile and a first propeller blade having a blade profile that corresponds substantially to at least a portion of the casing profile of the casing of the boom. A drive mechanism is at least partially housed within the boom and at the first propeller blade is rotatably mounted to the drive mechanism to be driven thereby. The drive mechanism is to operationally move the first propeller blade between a stowed position in which the first propeller blade is substantially flush with the casing of the boom, and a deployed position in which the first propeller blade is extended a determined distance from the casing of the boom.

A flight device configured to fly in an air includes an acquisition part configured to acquire a flight plan of the flight device; and a flight control part configured to change the flight plan during a flight along a flight route according to the flight plan for the flight device to circumvent a high-density area having a density of avoided objects equal to or above a threshold density in a first area located forward and downward from a position of the flight device.

A system for automated flight correction in an electric aircraft includes an input control configured to generate a control datum, at least a sensor connected to the electric aircraft, wherein the at least a sensor is configured to detect a status datum, and a flight controller communicatively connected to the input control and the at least a sensor, wherein the flight controller is configured to determine a command datum as a function of the control datum and the status datum, wherein determining the command datum comprises comparing the control datum to a limitation set based on the status datum, and calculating a modified control datum based on a flight plan of the electric aircraft through a remote device.

A system for automated flight correction in an electric aircraft includes an input control configured to generate a control datum, at least a sensor connected to the electric aircraft, wherein the at least a sensor is configured to detect a status datum, and a flight controller communicatively connected to the input control and the at least a sensor, wherein the flight controller is configured to determine a command datum as a function of the control datum and the status datum, wherein determining the command datum comprises comparing the control datum to a limitation set based on the status datum, and calculating a modified control datum based on a flight plan of the electric aircraft through a remote device.

In an aspect of the present disclosure is a system of automated fleet management for aerial vehicles, including a first aerial vehicle, the aerial vehicle comprising: a first sensor configured to measure an external metric and generate external datum based on the external metric; and a second sensor configured to measure an aircraft metric and generate aircraft datum based on the aircraft metric; and a computing device operating on the first aerial vehicle, the computing device communicatively connected to a network including at least a second aerial vehicle, the computing device configured to: receive the external datum from the first sensor of the first aerial vehicle and the aircraft datum from the second sensor of the first aerial vehicle; and transmit at least a flight plan update element to the network based on the external datum and the aircraft datum.

In one or more embodiments, a method for providing continuously variable feel forces for an aircraft comprises sensing, by each of at least one sensor associated with at least one aircraft control, a force sensor value. The method further comprises determining a net force value by using the force sensor value for each of at least one sensor. Also, the method comprises comparing the net force value to a desired breakout force. In addition, the method comprises determining whether the net force value exceeds the desired breakout force. Additionally, the method comprises determining an adjusted force value by using the desired breakout force and the net force value, when the net force value exceeds the desired breakout force. Also, the method comprises determining an actuator torque command based on the adjusted force value. Further, the method comprises commanding an autopilot actuator with the actuator torque command to apply torque.