A coaxial rotor system for a rotorcraft includes a mast, a top rotor assembly and a bottom rotor assembly. The top rotor assembly is coupled to the distal end of the mast. The bottom rotor assembly includes a motor configured to provide rotational energy to the mast, thereby rotating the top rotor assembly. The bottom rotor assembly experiences a torque reaction force responsive to the motor rotating the mast such that the top and bottom rotor assemblies counter rotate.

A coaxial rotor system for a rotorcraft includes a mast, a top rotor assembly and a bottom rotor assembly. The top rotor assembly is coupled to the distal end of the mast. The bottom rotor assembly includes a motor configured to provide rotational energy to the mast, thereby rotating the top rotor assembly. The bottom rotor assembly experiences a torque reaction force responsive to the motor rotating the mast such that the top and bottom rotor assemblies counter rotate.

A variable-sweep wing VTOL (vertical take-off and landing) aerial vehicle with distributed propulsion adapted for VTOL flight and horizontal flight includes a fuselage, a pair of symmetrical swiveling canards extending outward from forward portion of the fuselage, a pair of first symmetrical wings extending outward from the upper-rear portion of the fuselage and a pair of second symmetrical wings extending outward from the lower-rear portion of the fuselage. The first and second wings are spaced apart longitudinally and vertically. The pylon joins the first wing and second wing at the tip to from the box-wing. The wings can transition between VTOL mode or airplane mode. The wings are mounted with rotors for propulsion. Moreover, at the trailing edge of the wings, the blown flap work as blown lift system for both VTOL flight or STOL flight. Finally, the fuselage mounted pusher rotor provides propulsive thrust for horizontal flight.

An airfoil system is provided that includes an airfoil and an electric device. The airfoil includes a first exterior surface, a second exterior surface, a first airfoil segment and a second airfoil segment attached to the first airfoil segment. The airfoil extends widthwise between the first exterior surface and the second exterior surface. The first airfoil segment forms the first exterior surface. The second airfoil segment forms the second exterior surface. The electric device is embedded within the airfoil between the first airfoil segment and the second airfoil segment.

An airfoil system is provided that includes an airfoil. This airfoil includes a first exterior surface, a second exterior surface, a first airfoil segment and a second airfoil segment. The airfoil extends widthwise between the first exterior surface and the second exterior surface. The first airfoil segment includes first composite material and a receptacle. A base of the receptacle is embedded within the first composite material. The second airfoil segment includes second composite material and a key. A base of the key is embedded within the second composite material. The key is mated with the receptacle thereby attaching the second airfoil segment to the first airfoil segment.

Integration driving mechanism for fin control assembly applied for UAV, aerial observation equipment, comprises: the control assembly, the fin root assembly, the fin shaft. The control assembly is small size, high temperature operation, waterproof ability, vibration resistance, easily replacement and reparation that is still warrant the operation condition.

Integration driving mechanism for fin control assembly applied for UAV, aerial observation equipment, comprises: the control assembly, the fin root assembly, the fin shaft. The control assembly is small size, high temperature operation, waterproof ability, vibration resistance, easily replacement and reparation that is still warrant the operation condition.

There is provided a method of mounting equipment to an aircraft having an empennage. The method comprises mounting equipment to a mounting structure for mounting to the aircraft; removing an access panel from the outer skin of the empennage of the aircraft to reveal an access panel opening into the empennage; and attaching the mounting structure to or within the access panel opening such that at least a portion of the equipment extends beyond the outer skin of the empennage. The shape of the mounting structure at least partly conforms to the shape of the access panel opening. The method also comprises covering the mounting structure and the equipment mounted thereon with a cover, and attaching the cover to the mounting structure or the empennage. An assembly, structure, tailplane and aircraft are also provided.

There is provided a method of mounting equipment to an aircraft having an empennage. The method comprises mounting equipment to a mounting structure for mounting to the aircraft; removing an access panel from the outer skin of the empennage of the aircraft to reveal an access panel opening into the empennage; and attaching the mounting structure to or within the access panel opening such that at least a portion of the equipment extends beyond the outer skin of the empennage. The shape of the mounting structure at least partly conforms to the shape of the access panel opening. The method also comprises covering the mounting structure and the equipment mounted thereon with a cover, and attaching the cover to the mounting structure or the empennage. An assembly, structure, tailplane and aircraft are also provided.

A leading edge structure for an aerodynamic surface of an aircraft with an outer wall part curved in a streamlined manner around an interior compartment and having an inner surface pointing toward the interior compartment and an outer surface provided for contact with the external surrounding flow. The outer wall part has a first outer wall section extending from a leading edge point in an incident flow direction in a convexly curved manner in the direction of a first side. The outer wall part has a second outer wall section which extends from the leading edge point in the incident flow direction in a convexly curved in the direction of a second side. An inner wall part is arranged in the interior compartment opposite the inner surface of the outer wall part and extends from the first outer wall section to the second outer wall section.