In some examples, an unmanned aerial vehicle (UAV) may control a position of a first camera to cause the first camera to capture a first image of a target. The UAV may receive a plurality of second images from a plurality of second cameras, the plurality of second cameras positioned on the UAV for providing a plurality of different fields of view in a plurality of different directions around the UAV, the first camera having a longer focal length than the second cameras. The UAV may combine at least some of the plurality of second images to generate a composite image corresponding to the first image and having a wider-angle field of view than the first image. The UAV may send the first image and the composite image to a computing device.

A device includes a control input generator and a neural network trainer. A flight simulator is configured to generate first state data responsive to a first control input from the control input generator and to provide the first state data to a first neural network to generate a candidate second control input. The control input generator is also configured to select, based on a random value, a second control input from between the candidate second control input and a randomized offset control input that is based on a random offset applied to the first control input. The flight simulator is configured to generate second state data responsive to the second control input from the control input generator. The neural network trainer is configured to update weights of the first neural network based, at least in part, on the first state data and the second state data.

Systems, devices, and methods that may include: determining one or more take-off variables for a vertical take-off and landing (VTOL) aerial vehicle; increasing an altitude of the VTOL aerial vehicle to a first altitude, where increasing the altitude comprises substantially vertical flight of the VTOL aerial vehicle; performing a first pre-rotation check of the VTOL aerial vehicle; adjusting a pitch of the VTOL aerial vehicle to a first pitch angle via motor control; adjusting the pitch of the VTOL aerial vehicle to a second pitch angle via at least one of: motor control and one or more effectors; and adjusting the pitch of the VTOL aerial vehicle to a third pitch angle via the one or more effectors, where the third pitch angle is substantially perpendicular to a vertical plane.

Disclosed is an aircraft and a method of controlling an aircraft. The aircraft comprises a continuous wing assembly extending from port to starboard sides of the aircraft. The aircraft is controlled partially by flexing portions of the wing, and partially or totally by mechanical systems that alter the position of a fuselage with respect to the wing. The fuselage is attached to the wing by a wing/fuselage joint structure that permits at least two mutually orthogonal axes of rotation of the fuselage relative to the wing. The aircraft includes a sensors, a telemetry system linked to a remote server, and a control system for programming flight information and aircraft control instructions and a plurality of actuators responsive to the control system for rotating the fuselage relative to the wing and flexing the wing for controlling the flight of the aircraft in response to instructions from the control system.

Embodiments of the present invention are a flight control method and device, and an unmanned aerial vehicle. The method comprises firstly acquiring the current flight velocity of the unmanned aerial vehicle, then obtaining the current optimum inclination angle corresponding to the unmanned aerial vehicle according to the current flight velocity, and further adjusting the flight state of the unmanned aerial vehicle according to the current optimum inclination angle. The method can relieve the restrictions on the flight freedom of unmanned aerial vehicles and make the user experience rapid flight pleasure.

A method for positioning a target in a building based on the assistance of two aircraft includes the following steps: allowing two aircraft with respective direction-finding devices to fly around a building, and sending a signal by a positioning tag carried by an indoor target; measuring projections of directions of the signal source on a horizontal plane respectively by the two aircraft, and indicating a position of the indoor target on the horizontal plane by an intersection of the two projections; and according to a difference between barometric pressures of the indoor target and the aircraft, obtaining an altitude of the target to further obtain position coordinates of the target. The method avoids deploying an indoor positioning base station, and improves the positioning accuracy, stability and anti-interference performance.

The embodiment of this present disclosure provides a control method of unmanned aerial vehicle (UAV) hovering in tunnel, which comprises the following steps: acquiring hovering information of hovering position of UAV; acquiring the position information of the current position of the UAV; determining flight parameters based on hovering information and position information. The flight parameters are used to control the UAV to move from the current position to the hovering position.

A system for flight control configured for use in an electric aircraft includes an inertial measurement unit (IMU) and configured to detect an aircraft angle and an aircraft angle rate. The system includes a flight controller including an outer loop controller configured to receive the input datum from the sensor, receive the aircraft angle from the IMU, and generate a rate setpoint as a function of the input datum. The system includes an inner loop controller configured to receive the aircraft angle rate, receive the rate setpoint from the outer loop controller, and generate a moment datum as a function of the rate setpoint. The system includes a mixer configured to receive the moment datum, perform a torque allocation as a function of the moment datum, and generate a motor command datum as a function of the torque allocation.

A lighter than air platform an unfinned envelope having two or more propulsion elements coupled with the unfinned envelope proximate to the center of gravity. At least one navigation sensor is configured to monitor an actual flight path of the unfinned envelope, and at least one perturbation sensor is configured to monitor one or more perturbations of the unfinned envelope. A navigation controller is configured to guide the unfinned envelope with coordinated propulsion of the two or more propulsion elements. The navigation controller includes a navigation comparator that compares the actual flight path with a specified flight path of the unfinned envelope and determine a navigation instruction. A perturbation comparator compares the navigation instruction with the monitored one or more perturbations to determine a perturbation compensation. A propulsion coordinator controls propulsion values of each of the propulsion elements based on the navigation instruction and the perturbation compensation.

The present invention discloses a heading generation method of an unmanned aerial vehicle including the following steps of: making a preliminary flight for selecting a point of view to record flight waypoints, the waypoints including positioning data and flight altitude information of the unmanned aerial vehicle; receiving and recording flight waypoints of the unmanned aerial vehicle; generating a flight trajectory according to waypoints of the preliminary flight; editing the flight trajectory to obtain a new flight trajectory; and transmitting the edited new flight trajectory to the unmanned aerial vehicle to cause the unmanned aerial vehicle to fly according to the new flight trajectory. The present invention further relates to a heading generation system of an unmanned aerial vehicle.