A computer-implemented method for communication includes obtaining power data associated with a plurality of channels of a frequency band, predicting an error rate for each of the plurality of channels based at least in part on the power data, and selecting a hopset of channels for frequency hopping from the plurality of channels based at least in part on the predicted error rates for the plurality of channels.

A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one fore conduit and at least one tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the fore conduit, coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element is coupled to the tail portion. A surface of the primary airfoil element is located directly downstream of the first and second fore ejectors such that the fluid from the first and second fore ejectors flows over the such surface.

A motor mounted on a drone includes a rotor including a propeller mounting portion with a propeller detachably attached, the rotor being rotatable about a central axis, a stator radially facing the rotor with a gap therebetween, and an auto-balancer capable of automatically correcting dynamic balance of the rotor.

An aircraft has a propulsion unit and a fuselage unit. The propulsion unit has a first rotor for providing a propulsion force on the aircraft. The fuselage unit extends along a rotation axis of the first rotor and has a rotationally symmetrical shape with respect to the rotation axis of the first rotor. The fuselage unit has a suspension at a first end by which the fuselage unit is coupled to the first rotor so that the fuselage unit is spaced apart from the first rotor along the rotation axis. A detection unit for the detection of environmental information is provided in the area of a second end of the fuselage unit. The propulsion unit is designed to keep the aircraft in a hovering flight condition so that a relative position of the aircraft with respect to a reference point on the Earth's surface remains unchanged.

An aerial vehicle is provided including rotor units connected to the aerial vehicle, and a control system configured to operate at least one of the rotor units. The rotor unit includes rotor blades, wherein each rotor blade includes a surface area, and wherein an asymmetric parameter is defined, at least in part, by the relationship between the surface areas of the rotor blades. The value of the asymmetric parameter is selected such that the operation of the rotor unit: (i) moves the rotor blades such that each rotor blade produces a respective vortex and (ii) the respective vortices cause the rotor unit to produce a sound output having an energy distribution defined, at least in part, by a set of frequencies, wherein the set of frequencies includes a fundamental frequency, one or more harmonic frequencies, and one or more non-harmonic frequencies having a respective strength greater than a threshold strength.

The present disclosure pertains to self-piloted, electric vertical takeoff and landing (VTOL) aircraft that are safe, low-noise, and cost-effective to operate for cargo-carrying and passenger-carrying applications over relatively long ranges. A VTOL aircraft has at least one wing that is rotatable relative to a fuselage of the VTOL aircraft for transitioning the VTOL aircraft between a hover configuration and a forward-flight configuration. Rotation of the wing may be passively controlled using aerodynamic forces, thereby obviating the need of using an actuator for actively controlling the rotation.

A noise cancelation system for an unmanned aerial vehicle may have an audio capture module, a metadata module and a filter. The audio capture module may be configured to receive an audio signal captured from a microphone, e.g., on a camera. The metadata module may be configured to retrieve noise information associated with noise generating components operating on the unmanned aerial vehicle (UAV). The filter may be configured to receive the audio signal and noise information from the audio capture module. The filter also may be configured to retrieve a baseline profile from a database based on the noise information. The baseline profile includes noise parameter to filter out audio frequencies from the audio signal corresponding to the noise generating component. The filter may generate a filtered audio signal for output.

The invention relates to a method for controlling aircraft. A specified flight position of the aircraft is compared with a piece of geographical height information corresponding to the provided flight position. The piece of geographical height information is obtained from a set of pieces of height information, said set corresponding to a geographical area, wherein for a first part of the geographical area, the set of pieces of height information indicates a piece of relevant geographical height information and for a second part of the geographical area, the set indicates a piece of height information deviating from the actual geographical height. The second part of the geographical area comprises a first special area, in which the aircraft is only permitted to operate to a limited degree. The height information deviating from the actual geographical height is evaluated in order to actuate an operating component of the aircraft such that the aircraft complies with the limitation when the aircraft is operated in the first special area. The invention additionally relates to a corresponding control system.

The invention relates to a method for controlling aircraft. A specified flight position of the aircraft is compared with a piece of geographical height information corresponding to the provided flight position. The piece of geographical height information is obtained from a set of pieces of height information, said set corresponding to a geographical area, wherein for a first part of the geographical area, the set of pieces of height information indicates a piece of relevant geographical height information and for a second part of the geographical area, the set indicates a piece of height information deviating from the actual geographical height. The second part of the geographical area comprises a first special area, in which the aircraft is only permitted to operate to a limited degree. The height information deviating from the actual geographical height is evaluated in order to actuate an operating component of the aircraft such that the aircraft complies with the limitation when the aircraft is operated in the first special area. The invention additionally relates to a corresponding control system.

This disclosure describes a configuration of an unmanned aerial vehicle (UAV) in which the fuselage of the UAV is center mounted and at least some of the motors are configured to encompass at least a portion of the fuselage. In such a configuration, the stator and rotor of the motor extend around a perimeter of the fuselage, the propellers are coupled to an outer perimeter of the rotor, and the propellers extend radially outward away from the fuselage. Likewise, a closed wing may be coupled to the fuselage and positioned to encompass the radially extending propellers and at least a portion of the fuselage.