An attachment structure for an equipment unit of an aircraft includes a first attachment device extending in a longitudinal direction of the aircraft, wherein the first attachment device is attached to a stringer and to a frame and wherein the first attachment device has a first engagement element and a second attachment device attachable to the equipment unit, wherein the second attachment device has a second engagement element adapted for engaging into the first engagement element, such that a force from the equipment unit in the longitudinal direction on the second attachment device is transferred via the second engagement element to the first engagement element and via the first attachment device to the stringer and the frame.

An attachment structure for an equipment unit of an aircraft includes a first attachment device extending in a longitudinal direction of the aircraft, wherein the first attachment device is attached to a stringer and to a frame and wherein the first attachment device has a first engagement element and a second attachment device attachable to the equipment unit, wherein the second attachment device has a second engagement element adapted for engaging into the first engagement element, such that a force from the equipment unit in the longitudinal direction on the second attachment device is transferred via the second engagement element to the first engagement element and via the first attachment device to the stringer and the frame.

An aircraft includes a fuselage having a front, a center, and a rear section. A first mounting member is coupled to the front section. A second mounting member is coupled to the rear section. A first and a second wing are coupled to the center section. A plurality of power generator systems are included and coupled to the first or second mounting member. Each power generator system includes a power source, a first and a second propeller. The power source is configured to drive the first and second propeller. The first and second propeller have an axis of rotation, and are pivotable between a first and a second position. An amphibious landing gear system is coupled to an underside of the fuselage and has a flap and a bladder. The bladder is located under the flap, configured to inflate and deflate, and sized to provide buoyancy for the aircraft.

A composite structure includes a first composite material, a second composite material bonded to the first composite material, and a corner fillet part provided at a corner part formed by the first composite material and the second composite material. In the composite structure, the rigidity of the corner fillet part is adjustable, and a pull-off stress to be applied to the corner part is adjusted by adjusting the rigidity of the corner fillet part. The pull-off stress to be applied to the corner part is adjusted to be decreased by adjusting the rigidity of the corner fillet part to be decreased.

According to an embodiment, an aircraft comprises a fuselage including composite skin; an enclosure located inside the fuselage; a rechargeable battery disposed inside the enclosure; and a ventilation conduit extending from the enclosure to an opening in the composite skin, the ventilation conduit including: a first portion having a first end coupled to the enclosure and a second end spaced from the composite skin, and a second portion extending between the composite skin and the second end of the first portion, the second portion comprising an electrically non-conductive material.

According to an embodiment, an aircraft comprises a fuselage including composite skin; an enclosure located inside the fuselage; a rechargeable battery disposed inside the enclosure; and a ventilation conduit extending from the enclosure to an opening in the composite skin, the ventilation conduit including: a first portion having a first end coupled to the enclosure and a second end spaced from the composite skin, and a second portion extending between the composite skin and the second end of the first portion, the second portion comprising an electrically non-conductive material.

There is provided a conductive radius filler system and method. The system has a composite assembly with one or more composite structures having one or more radius filler regions. The system further has one or more conductive radius fillers filling the one or more radius filler regions. Each of the conductive radius fillers has a conductive element of electrically conductive material. The system further has one or more over-arching systems connected to the one or more conductive radius fillers, via one or more conductive radius filler connections, forming one or more current handling systems of the system. The one or more current handling systems include one or more of an edge glow handling system configured to handle edge glow, a static dissipation handling system configured to handle static dissipation, and a current return handling system configured to handle current return.

There is provided a conductive radius filler system and method. The system has a composite assembly with one or more composite structures having one or more radius filler regions. The system further has one or more conductive radius fillers filling the one or more radius filler regions. Each of the conductive radius fillers has a conductive element of electrically conductive material. The system further has one or more over-arching systems connected to the one or more conductive radius fillers, via one or more conductive radius filler connections, forming one or more current handling systems of the system. The one or more current handling systems include one or more of an edge glow handling system configured to handle edge glow, a static dissipation handling system configured to handle static dissipation, and a current return handling system configured to handle current return.

The current disclosure describes a cloaking system for an aircraft. Cameras on the aircraft can detect background colors during flight. Electroluminescent paint on the aircraft can be powered on that resembles the background color. The color and luminescence of the aircraft will allow for dynamic cloaking unachievable by prior art camouflage paint colors.

The current disclosure describes a cloaking system for an aircraft. Cameras on the aircraft can detect background colors during flight. Electroluminescent paint on the aircraft can be powered on that resembles the background color. The color and luminescence of the aircraft will allow for dynamic cloaking unachievable by prior art camouflage paint colors.