Abstract: A flying mobile body 4 includes: a rotary blade to rotate to generate lift; an airframe in which the rotary blade is provided; a power reception antenna to include a power reception surface that receives a radio wave transmitting electric power, the power reception surface having an area larger than an area projecting the airframe onto a rotation axis perpendicular plane that is a plane perpendicular to a rotation axis direction that is a direction parallel to a rotation axis of the rotary blade, and a drag reducing structure that reduces a drag generated with respect to a descending airflow generated by rotation of the rotary blade: a converter to convert electric power of the radio wave received by the power reception antenna into DC electric power; a storage battery; and an electric motor to generate power rotating the rotary blade.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a fixed structure, a translating structure, a blocker door and a folding linkage. The translating structure is configured to move between a stowed position and a deployed position. The blocker door is pivotally attached to the translating structure at a first pivot joint. The folding linkage links the blocker door to the fixed structure. The folding linkage includes a member pivotally attached to the blocker door at a second pivot joint that is radially outboard of a skin of the blocker door when the translating structure is in the stowed position. The second pivot joint is radially outboard of the first pivot joint when the translating structure is in the stowed position.

Abstract: A fishing system includes an unmanned aerial vehicle and a fishing line fixing portion placed on a main body of the unmanned aerial vehicle, the fishing line fixing portion including a first fixing portion for fixing a fishing line and a second fixing portion detachably connected to the first fixing portion. The unmanned aerial vehicle includes an imaging device, a fish school tracking processing unit configured to identify a fish in imaging data captured by the imaging device and control the unmanned aerial vehicle to track the fish. A connection between the first fixing portion and the second fixing portion is released when the fish is hooked on an artificial bait attached to a first end of the fishing line.

Abstract: In an aspect the present disclosure is directed to an electric aircraft. An electric aircraft may include a plurality of fixed wings, a tail, a first boom, and a second boom and a plurality of lift components. The aircraft also includes a tail affixed to the aft end of the fuselage, a first boom including a first rear end affixed to the tail and a first forward end proximal to the fore end of the fuselage, wherein the first boom is affixed to a first wing, a second boom including a second rear end affixed to the tail and a second forward end proximal to the fore end of the fuselage, wherein the second boom is affixed to the second wing. The aircraft may include a plurality of lift components which may be affixed to the booms.

Abstract: A power supply device that supplies power to a power load of a flying body, comprises: a power generation unit; a hollow housing including a reserving portion configured to reserve a fuel of the power generation unit, and a storage portion configured to store the power generation unit; and a connecting portion configured to connect the housing to an airframe of the flying body. The housing has a shape long in a front-and-rear direction of the flying body, and is arranged outside the airframe, and the reserving portion and the storage portion are arranged in a longitudinal direction of the housing.

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 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: The invention relates to an aircraft propulsion system (100) intended for being built into the rear of an aircraft fuselage, the propulsion system comprising at least two gas generators (102a, 102b) supplying a power turbine (104) having two counter-rotating turbine rotors (104a, 104b) for driving two fans (112a, 12b), and separate air inlets (106a, 106b) for supplying each gas generator, characterised in that it comprises an electrical drive device (140) configured to rotate at least one of the turbine rotors, at least one electrical generator (142a, 142b) configured to transform part of the energy of the flow from the gas generators into electrical power and an electric motor (146) supplied by said electrical generator and capable of rotating at least one of the turbine rotors, said electrical generator being installed on one of said gas generators, and in that said turbine rotor is capable of being rotated simultaneously by a flow from said gas generators and by the electrical drive device.

Abstract: A flight vehicle includes a main body, a thrust generating unit, and one or more joints. The thrust generating unit includes one or more thrust generating subunits. Each joint is respectively associated with a corresponding thrust generating subunit. Each joint couples a corresponding thrust generating subunit to the main body and permits the associated thrust generating subunit to freely pivot relative to the main body. Each thrust generating subunit includes a plurality of thrust generators. Within each thrust generating subunit, one or more of the thrust generators is arranged to generate thrust that induces a first torque in one direction along a circumference of a circle centered on a first pivot axis, and other one or more of the thrust generators is arranged to generate thrust that induces a second torque in an opposite direction along the circumference of the circle centered on the first pivot axis.

Abstract: A method of operating an electromechanical actuator includes coupling an inner portion of a split ball screw with an outer portion of the split ball screw, rotating the split ball screw about an axis to drive a ball nut in a first axial direction, in response to a failure mode of the electromechanical actuator, decoupling the outer portion of the split ball screw from the inner portion of the split ball screw, and translating the outer portion of the split ball screw and the ball nut in a second axial direction.

Abstract: To replace a depleted battery in a drone with a fresh battery, the drone first lands on the exchange and charging system, aligned between two battery holders. A freshly charged battery, in a docking bay in one battery holder, is then moved against the drone's depleted battery. The depleted battery, in turn, is moved out of the drone into the other battery holder, and the fresh battery takes its place. While in the battery holders, the batteries are charged. After a battery exchange, the battery holders track round so that another battery and vacant docking bay are brought into place for a subsequent exchange.

Abstract: The invention relates to the rating (S) of a propulsion unit (2) comprising a main engine (3) providing main thrust assisted by an auxiliary engine (4) providing auxiliary thrust, according to the following steps: (i) determining (S1) a distribution between the main thrust and the auxiliary thrust so as to obtain the takeoff thrust of the propulsion unit, the auxiliary thrust making a 5% to 65% contribution to the takeoff thrust, (ii) depending on the distribution determined for the takeoff condition, determining (S2) distribution between the main thrust and the auxiliary thrust so its to obtain the top of climb thrust of the propulsion unit, the auxiliary thrust making at most 70% contribution to the top of climb thrust, and (iii) rating (S3) the propulsion unit (2) in such a way that the main thrust of the main engine (3) determined fir the takeoff condition corresponds to the maximum thrust likely to be achieved by the main engine (3).

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: The bait lock structure is a towed device. The bait lock socket is adapted for use with a bait fish. The bait lock socket is adapted for use with a game fish. The bait lock socket displays the bait fish in order to attract and capture the game fish. The bait lock socket incorporates a lure structure, a locking post, and a capture structure. The locking post secures the capture structure to the lure structure. The bait fish attaches to the lure structure. The capture structure captures the game fish.

Abstract: Methods, systems, and apparatus, including computer programs encoded on computer storage media, for a distributed system architecture for unmanned air vehicles. One of the methods includes obtaining information identifying flight information of a UAV, with the flight information including flight phase information or a contingency condition associated with a flight critical module included in the UAV. The obtained information is analyzed, and one or more first payload modules are determined to enter a modified power state. Requests to enter the modified power state are caused to be transmitted to each determined payload module in the one or more first payload modules.

Abstract: A convertible aircraft system is provided that can convert to a helicopter configuration, an airplane configuration, or a gyroplane configuration before, during, or after flight. The convertible aircraft system includes a fuselage, a proximal flight assembly, a distal flight assembly, a support spar, and a tail assembly. The fuselage is the main structural body of the present invention. The proximal flight assembly and the distal flight assembly are the flight system of the present invention. The support spar provides an axis of rotation and a pole support for the proximal flight assembly and the distal flight assembly. The tail assembly provides stability during flight of the present invention. In more detail, the tail assembly may comprise at least one vertical stabilizer, at least one horizontal stabilizer, and at least one rudder in order to provide stability during flight of the present invention.

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: A cargo transport system comprising a spine assembly and a container assembly. The spine assembly comprises a rigid spine and a plurality of mounts arranged on the rigid spine in a plurality of mount rows. The container assembly comprises a plurality of containers and is secured to the spine assembly using at least a subset of the plurality of mounts. Each container of the plurality of containers comprises a plurality of fittings for securing the container to the spine assembly and/or another container of the container assembly. Each mount row extends along a width of the spine assembly, and the plurality of mount rows are spaced apart at regular distance intervals along a length of the spine.

Abstract: A battery-powered pilotless aerial vehicle has a center unit, a plurality of rotor units coupled to the center unit, a plurality of battery assemblies, and a plurality of electrical circuitry components including a central control circuitry and at least a flight control subsystem, a detecting and avoiding subsystem, and an emergency communication subsystem controlled by the central control circuitry. The center unit receives one or more of the electrical circuitry components and has a compartment for accommodating one or more passengers or cargo goods. Each rotor unit comprises a propelling module functionally coupled to the central control circuitry. The one or more battery assemblies are configured for being controlled by the flight control subsystem for at least powering the propelling modules, and are at a distance away from the center unit for reducing electromagnetic interference to the electrical circuitry components therein.

Abstract: A center C of a connecting portion coincides with a center U of lift generated in a body of a rotary-wing aircraft. The center C of the connecting portion is a point of action of gravitational force of a support rod and a first mounting portion with respect to the connecting portion. The center U of the lift is a point of action of the lift on the rotary-wing aircraft and is the center of rotation of the connecting portion.

Abstract: An item to be secured to an aircraft floor can be secured to a Load Transfer Structure that resides under the floor, via access passages provided in selected floor panels. The Load Transfer Structure transfers the weight of the item to members of the airframe, and is designed to accommodate loads during normal flight without restricting the designed movement of the airframe; however, under abnormal conditions such as a crash, the Load Transfer Structure engages members of the airframe to transfer loads thereto to secure the item.