Abstract: A component for an aircraft and an aircraft with such component. The component includes a heat source enclosed by a housing, heat exchanger, heat sink, at least one structural suspension element, and an air duct. Each structural suspension element is attached to an inner surface of the housing and supports one or more of the heat source within the housing. The heat sink is part of the housing and configured to guide air from an inside of the housing an outside of the housing. Each heat exchanger is thermally coupled to the heat source. Each heat exchanger is fluidly connected to the heat sink via an inlet line and a return line for a coolant. The air duct is configured to guide ambient air from the outside through the housing, past each of the at least one structural suspension element, and through the heat sink out of the housing.

Abstract: An unmanned aerial vehicle (UAV) 1 of the vertical take-off and landing (VTOL)-type that can be launched from a launcher tube 2 is provided. A launcher 2 for launching the UAV 1 is also provided. The UAV 1 comprises a housing 10 and a transition mechanism 100 for transitioning the UAV 1 between a collapsed configuration for stowing the UAV 1 in a launcher tube 21 and a flight configuration. The housing 10 and the transition mechanism 100 are configured so that one or more rotors 12a-d that, in use, are connected to the transition mechanism 100 are located substantially within the housing 10 in the collapsed configuration and outside the housing 10 in the flight configuration. The launcher 2 comprises a hollow tube 21 for receiving a UAV 1 in a collapsed configuration and a trigger mechanism 26 for triggering a propulsion mechanism for propelling the UAV 1 out of an end of the hollow tube 21.

Abstract: In a method of controlling a flying object 1, from the flying object 1 that includes a flying object propulsion apparatus 16 and an energy storage apparatus 7, 8 having a plurality of energy storage devices 6 and configured to supply electricity to the flying object propulsion apparatus 16, one or a plurality of the energy storage devices 6 are separated.

Abstract: A portable dimensional reference (PDR) that is transportable to a tower site and deployable on site at ground level near a tower. The PDR includes a pair of target pads and multiple connecting segments, which may be attached end-to-end between the target pads. The target pads are marked with respective targets that enable photogrammetry software to identify the targets, their locations, and the distance between them with high precision, enabling the software to apply the known distance as a scale constraint for accurately scaling dimensions of imaged components of the tower.

Abstract: A power system with a reliability enhancing battery architecture for electric motors adapted for use in an aerial vehicle. Individual batteries may be used to power a subset two or more motors in systems with six or more motors, for example. Each motor may be powered by two or more subsets of batteries, allowing accommodation for motor failure. With a failed motor in a vertical take-off or landing mode, power may be diverted to other motors to continue proper attitude control, and to provide sufficient thrust. With a failed motor a second motor offset from the failed motor may be powered down to facilitate attitude control.

Abstract: An inner middle rotor is rotated while an inner front rotor, an inner back rotor, and an outer rotor are not rotated. The inner middle rotor is surrounded by the inner front rotor, the inner back rotor, the outer rotor, and a fuselage. After rotating the inner middle rotor while not rotating the inner front rotor, the inner back rotor, and the outer rotor, the inner middle rotor, the inner front rotor, the inner back rotor, and the outer rotor are simultaneously rotated.

Abstract: A landing system suitable for receiving an unmanned aerial vehicle (UAV) comprises an autonomous ground vehicle (AGV). A landing surface is disposed on the AGV, and the landing system comprises a loading channel suitable for passing an object delivered by the UAV through a first loading channel opening in the landing surface. The object passes within the loading channel through to a second loading channel opening at a bottom aspect of the AGV. In this way, a UAV can land on the landing surface, and the AGV positions the object in line with a target delivery location, where the object is delivered. Aspects of the landing system comprise an electromagnet or vacuum chamber for securing the UAV to the landing surface, thereby enhancing stability of the UAV during movement of the landing system.

Abstract: The application provides an autonomous refueling vehicle for a hydrogen-electric aircraft, which includes two or more wings. The wings are provided with one or more removable electric propulsion pods. The autonomous refueling vehicle includes a hydrogen refueling module adapted to connect to the propulsion pods and to a hydrogen source. The autonomous refueling vehicle includes also includes a propulsion pod handling device, which is adapted to remove the propulsion pod from the wings and to position the propulsion pods on the hydrogen refueling module such that the propulsion pods are connected to the hydrogen refueling module. The autonomous refueling vehicle is also adapted to autonomously move itself to the hydrogen source to allow the hydrogen refueling module to removably connect to the hydrogen source for refueling of the propulsion pods.

Abstract: 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.

Abstract: A chair for use in take-off or landing of a user wearing personal flying equipment may include a seat for the user to straddle such that the user faces in a forward direction. The chair may include a torso support for supporting a torso of the user sitting on the seat. The torso support may be concave and define an opening facing the seat. The seat and torso support may be mounted to a structure. A base member may be rigidly connected to the structure and may extend outwardly from either side of the structure, leaving a space below the structure for receiving a leg of the user when the user sits on the seat.

Abstract: A package delivery system for delivering a plurality of packages with one or more unmanned aerial vehicles (UAVs) includes a package receptacle to receive and store the plurality of packages. A charging station charges a plurality of UAV batteries which power the one or more UAVs. A UAV landing pad permits the one or more UAVs to land thereon. A loader loads a package of the plurality of packages and/or a UAV battery of the plurality of UAV batteries onto the UAVs when the UAVs are on the UAV landing pad. A transporter moves the packages and/or the UAV batteries s toward the loader.

Abstract: An aircraft includes a fuselage, a wing structure and a tail assembly, and also at least one propeller having the general shape of a ring. The propeller includes a rotor formed by an annular element having blades projecting outwardly therefrom, and a likewise annular base coaxial to the annular element and on which the annular element can turn under the action of a driver. The base is coaxial to the fuselage and integrated into the shell constituting the fuselage. The blades of the rotor are arranged outside the shell.

Abstract: An electric aircraft having fixed pitch lift includes a plurality of flight components, wherein the plurality of flight components further comprises at least a lift propulsor component, wherein the lift propulsor component comprises a plurality of blades configured at an angle of attack, and a flight controller, wherein the flight controller is configured to calculate a flight element using an intermediate representation, and transmit the flight element to the plurality of flight components.

Abstract: A composite assembly for an aircraft, the composite assembly including a first carbon fiber material structured for a portion of an outer skin surface of an aircraft, a second carbon fiber material stitched to the first carbon fiber material, wherein the second carbon fiber material is structured for a structural component of the aircraft, and wherein the stitching is configured to bind the first carbon fiber material and the second carbon fiber material, and wherein the aircraft further includes a single deck, wherein a cargo compartment and a passenger compartment are located on or above the single deck.

Abstract: The invention relates to a method for influencing arthropods by means of electromagnetic radiation, wherein the electromagnetic radiation (10) is emitted from at least one emitter (14). Due to the fact that the characteristic (18) of the electromagnetic radiation (10) is created by means of at least one equivalent electronic equivalent circuit, wherein the equivalent circuit is a model of an arthropod (12), corresponding signals and/or signal patterns to which the corresponding arthropods react can be quickly, simply and systematically determined.

Abstract: An aircraft emergency power unit (EPU) includes a battery powered subsystem that replaces toxic hydrazine fuel use. The battery of the battery powered subsystem is utilized to supply power to an aircraft electrical system in the event of a failure of the EPU turbine-powered generator. The battery of the battery powered subsystem is also utilized to supply power to an electric hydraulic motor pump in the event of a failure of the EPU turbine-powered hydraulic pump (or to augment the output of the EPU-turbine-powered hydraulic pump). The battery of the battery powered subsystem is capable of simultaneously powering the electrical system and the electric hydraulic motor pump or of powering either one of the electrical system and electric hydraulic motor pump independently based upon aircraft fault conditions. Intermittent operation of the electrical system and/or the electric hydraulic motor pump in an intermittent fashion on an as-needed basis is also possible.

Abstract: A fishing lure system with an example having a two-part fishing lure having a replaceable hook-retainer carriage assembly which is removably insertable in an elastomeric body component. When configured as a two-part lure, the fishing lure may be configured with a flexible elastomeric body component with a precisely positioned preformed cavity in the head region for receiving a weighted hook-retainer carriage. The carriage may be inserted into the lure through a slit or passageway. The elastomeric bodies, hooks and weighted carriage assemblies of one example are independently removable and replaceable. The carriage assembly of one example includes an integral hook eye retaining loop and hook shank retainers which exit through passageways from the preformed cavity to the dorsal surface of the elastomeric body. The eyelet and retainers may be configured to position an upward pointing hook that is removably secured adjacent the outside dorsal surface of the lure.

Abstract: Methods, systems, and apparatus, including computer programs encoded on computer storage media, for controlling spraying of chemicals by an unmanned aerial vehicle (UAV). An unmanned aerial vehicle system includes one or more processors configured to perform operations of autonomously performing a flight path by the UAV and dispersing a chemical by the UAV along portions of the flight path. The UAV may include a chemical spray system having one or more spray booms with multiple nozzles for dispersing a chemical. The chemical spray system may include one or more tanks attached to the body of the UAV and a pump fluidly connected to the tanks to disperse chemical via the spray booms.

Abstract: An aircraft includes a wing having an integrated ducted fan. The ducted fan is optionally equipped with inlet louvers and outlet louvers. The inlet louvers and the outlet louvers are adjustable between an open position and a closed position.

Abstract: A propeller guard (200) according to the present disclosure is a propeller guard (200) for an unmanned aerial vehicle including a main body part (1) and a propeller part (2) and includes: an encircling part (210) that extends around the propeller part (2) and protects the propeller part (2); and a connection part (220) that connects the main body part (1) and the encircling part (210), wherein the encircling part (210) has a buoyant force for maintaining at least a part of the main body part (1) and the propeller part (2) above water.