A signal line protection assembly of an aerial vehicle includes a foot stand and a protection sleeve. The foot stand includes a foot stand sleeve and a lower cover including an antenna compartment configured to receive an antenna of the aerial vehicle. The protection sleeve is configured to receive a signal line. At least a portion of the protection sleeve is received in the foot stand sleeve. The signal line includes a data line for the antenna.

A signal line protection assembly of an aerial vehicle includes a foot stand and a protection sleeve. The foot stand includes a foot stand sleeve and a lower cover including an antenna compartment configured to receive an antenna of the aerial vehicle. The protection sleeve is configured to receive a signal line. At least a portion of the protection sleeve is received in the foot stand sleeve. The signal line includes a data line for the antenna.

The present invention provides an unmanned aerial vehicle built-in antenna. The unmanned aerial vehicle built-in antenna includes a substrate and a microstrip antenna disposed on the substrate. The substrate is provided with a first surface and a second surface disposed opposite to each other. The microstrip antenna includes a microstrip feeder, an antenna element arm, a grounding wire and a first grounding terminal that are disposed on the first surface of the substrate, a second grounding terminal disposed on the second surface of the substrate and a feeding coaxial line. A feed terminal of the feeding coaxial line is connected to a first terminal of the microstrip feeder, and a grounding terminal of the feeding coaxial line is connected to the first grounding terminal. A first end of the grounding wire is connected to a first terminal of the antenna element arm, and a second end of the grounding wire is connected to the first grounding terminal. The first grounding terminal is connected to the second grounding terminal.

An unmanned aerial vehicle includes a main body, a propulsion assembly including a rotary blade and a motor to rotate the rotary blade about a rotation axis, the propulsion assembly being attached to the main body, a rechargeable battery to supply electric power to the propulsion assembly, a leg portion connected to the main body on a lower side of the main body in a vertical direction, and a power receiving coil to provide non-contact power feeding, the power receiving coil being electrically connected to the battery and being provided in the leg portion.

An unmanned aerial vehicle includes a main body, a propulsion assembly including a rotary blade and a motor to rotate the rotary blade about a rotation axis, the propulsion assembly being attached to the main body, a rechargeable battery to supply electric power to the propulsion assembly, a leg portion connected to the main body on a lower side of the main body in a vertical direction, and a power receiving coil to provide non-contact power feeding, the power receiving coil being electrically connected to the battery and being provided in the leg portion.

An assembly, by way of example, an aircraft, including an aircraft motor apparatus including at least one motor located within a protective structure, the protective structure having movable sub-structure components, wherein the portion of the aircraft motor apparatus is configured to move the movable sub-structure components to increase or decrease airflow through the protective structure.

An assembly, by way of example, an aircraft, including an aircraft motor apparatus including at least one motor located within a protective structure, the protective structure having movable sub-structure components, wherein the portion of the aircraft motor apparatus is configured to move the movable sub-structure components to increase or decrease airflow through the protective structure.

A fixed-wing VTOL hybrid UAV is disclosed comprising: a central frame 104; a pair of quick lockable fixed-wings 102 comprising right wing 102-2 and left wing 102-1 that lock with each other over the central frame; and four electrically operated rotors 108 in downward facing configuration attached to fixed-wings with help of rotor-blade arms 110. Arms 110 are pivotally fixed to wings 102 so that arms 110 are movable between a working position in which arms 110 are oriented parallel to central frame 104, and a storage position in which arms 110 are aligned with wings 102. Central frame 104 is a thin rod and works as fuselage. Drivers and control modules are fitted in wings 102. UAV includes rudders attached to arms at 45 degrees for maneuvering UAV for yaw and a secondary roll response. UAV includes two landing gears 106 attached to each end of central frame.

The present disclosure relates to a leaf spring type landing gear mounted on a lower portion of a fuselage of an aircraft, and more particularly, to a leaf spring type landing gear having improved performance for mitigation and absorption of shocks, including: a first frame connected to the fuselage and bent to have a circle center below; a second frame connected to the first frame; and a third frame connected to the second frame and at least partially bent to have a circle center below, wherein the second frame includes a 2-1st frame and a 2-2nd frame having circle centers formed in opposite directions and is formed to be bent in an S shape.

The present disclosure relates to a leaf spring type landing gear mounted on a lower portion of a fuselage of an aircraft, and more particularly, to a leaf spring type landing gear having improved performance for mitigation and absorption of shocks, including: a first frame connected to the fuselage and bent to have a circle center below; a second frame connected to the first frame; and a third frame connected to the second frame and at least partially bent to have a circle center below, wherein the second frame includes a 2-1st frame and a 2-2nd frame having circle centers formed in opposite directions and is formed to be bent in an S shape.