A flight-capable imaging system includes a set of parallel rails, a power source mounted to the set of parallel rails, an imaging device mounted to the set of parallel rails, an aerial vehicle body mounted to the set of parallel rails, a set of aerial vehicle arms attached to the aerial vehicle body that each include a set of propellers and a motor configured to turn the set of propellers to enable flight of the flight-capable imaging system, and at least one processing module configured to control the flight of the of the flight-capable imaging system based on controlling a motor speed of the motor of each of the set of aerial vehicle arms.

An unmanned aerial vehicle (UAV) having a UAV body, a propeller, an engine, a motor and a battery. The engine includes an engine body and an engine output shaft arranged on the engine body. The motor includes a stator, a rotor and a stator connector. The UAV provides the motor rotor, propeller and engine output shaft to be coaxially connected, and the motor can be used as a generator to charge the battery by doing negative work on the engine output shaft, or as an electric motor, that is, to receive the power of the battery and do positive work on the engine output shaft to realize power output, so that the UAV can realize high energy utilization and power redundancy at the same time.

The present embodiment relates to a composite fibre structure (100) and a method (200) of manufacturing the composite fibre structure (200). The composite fibre structure (100) includes a core (102) and an outer layer (108) enclosing the core (102). The core (102) further includes at least one of a permanent core (104) and a temporary core (106). The permanent core (104) is 3-D printed along with the temporary core (106) to form the core structure (102). The permanent core (104) and the temporary core (106) are placed alternatively along the section, extending throughout the length of the composite fibre structure (100), or the permanent core (104) and temporary core (102) can be alternate along the length of the composite fibre structure (100). The layer (108), made of a reinforcement material, wraps the core (102) to form the composite fibre structure (100).

A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector.

An unmanned helicopter platform includes a fuselage, a tail coupled with the fuselage, a payload rail coupled with and extending along the fuselage and a main rotor assembly coupled with the fuselage. The tail includes a tail rotor and a tail rotor motor. The main rotor assembly includes a main rotor having an axis of rotation and a main rotor motor. The payload rail allows mechanical connection of payloads to the fuselage and positioning of the payloads such that a center of gravity of the payloads is alignable with the axis of rotation.

A plug-in assembly structure for a UAV includes a first component (1), a second component (2) and a limit assembly (3). The first component (1) includes a first plug (11) and a positioning sleeve (12), and the positioning sleeve (12) is provided with a first through hole (121). The second component (2) includes a second plug (21), the radial direction of the second plug (21) is provided with a limit hole (2111), the second plug (21) can be electrically connected to the first plug (11), and the limit hole (2111) is facing the first through hole (121). The limit assembly (3) is installed in the limit hole (2111). The limit assembly (3) includes a first elastic element (31) and a limit element (32).

Systems, devices, and methods including: a latching mechanism comprising: a first latch configured to attach to a door of an unmanned aerial vehicle (UAV); a second latch configured to attach to a portion of the UAV distal from the first latch; a string connected between the first and second latch, where the string secures the door shut; at least two radio modules in communication with a ground control station; and at least two burn wires in contact with a portion of the string between the first latch and the second latch; where current from a backup battery passes to at least one burn wire when the burn signal is received, where the burn wire causes the connection between the first latch and the second latch to be broken and the door of the UAV is separated from the UAV, and where the parachute is deployed when the door of the UAV is separated from a rest of the UAV.

An unmanned helicopter platform includes a fuselage, a tail coupled with the fuselage, a payload rail coupled with and extending along the fuselage and a main rotor assembly coupled with the fuselage. The tail includes a tail rotor and a tail rotor motor. The main rotor assembly includes a main rotor having an axis of rotation and a main rotor motor. The payload rail allows mechanical connection of payloads to the fuselage and positioning of the payloads such that a center of gravity of the payloads is alignable with the axis of rotation.

Systems, methods, and aircraft for managing center of gravity (CG) while transporting large cargo are described. Management of CG is achieved in many ways. In some instances, the aircraft itself is designed to assist in managing CG by providing fuel tanks that minimize the impact of fuel on the net CG of the aircraft. The fuel tanks utilize only a small amount of available volume in the wings for fuel. Disclosures related to properly managing CG while loading wind turbines onto cargo aircraft are also provided. The CG management techniques provided for herein allow for the transportation of wind turbine blades via aircraft, running counter to the typical rail or truck transportation of the same. One such management technique includes accounting for how a rotation of the blades when loading impacts the CG of the blades, and thus taking this into account when placing the blades in the aircraft.

A long-distance drone is disclosed having a canard body style with a main body, a left main wing, a right main wing, a left forewing, and a right forewing. The left forewing is attached to the main body forward of the left main wing, and the right forewing is attached to the main body forward of the right main wing. There is a left linear support connecting the left forewing to the left main wing, and a right linear support connecting the right forewing to the right main wing. A plurality of propellers are disposed on the left and the right linear supports.