A partition for dividing a portion of an aircraft including at least a first inflatable cavity defined by a plurality of material sheets, and a nozzle configured to provide fluidic access to the first inflatable cavity, wherein the nozzle is configured to attach to an aircraft air vent.

A partition for dividing a portion of an aircraft including at least a first inflatable cavity defined by a plurality of material sheets, and a nozzle configured to provide fluidic access to the first inflatable cavity, wherein the nozzle is configured to attach to an aircraft air vent.

In one embodiment, a drone is provided with several inflatable tubes that each connect a propeller component to a body of the drone. In order to increase the handling of the drone, a patch is placed on the top surface of each inflatable tube that includes some number of shape memory alloy wires. The shape memory alloy wires shrink and become rigid when an electric current is applied to them. The optimal locations on each tube to place the patches, and the shape of the patches, is determined using a topology optimization. Later, the wires in the patches can be selectively activated or deactivated by an operating entity to provide an additional means to control the drone. Additionally, the drone is equipped with several landing arms which may include a shape memory alloy torsion coil spring to help the arm deployment during landing.

An aircraft has a supporting structure and a shell that can be filled with a gas and which is tensioned by the supporting structure. The supporting structure includes a plurality of rod or tube-shaped sections which define a circular, oval or polygonal main clamping plane for the shell.

An emergency exit system comprising a first primary structure frame, a second primary structure frame extending substantially parallel to the first primary structure frame, a door opening arranged between the first primary structure frame and the second primary structure frame, and a door shiftable substantially parallel to the first primary structure frame and the second primary structure frame between a closed position and an open position. In the closed position, the door closes the door opening. In the open position, the door opens up the door opening. At least one of the primary structure frames comprises a primary structure guide element for guiding the door when the door is shifted between the closed position and the open position.

An emergency exit system comprising a first primary structure frame, a second primary structure frame extending substantially parallel to the first primary structure frame, a door opening arranged between the first primary structure frame and the second primary structure frame, and a door shiftable substantially parallel to the first primary structure frame and the second primary structure frame between a closed position and an open position. In the closed position, the door closes the door opening. In the open position, the door opens up the door opening. At least one of the primary structure frames comprises a primary structure guide element for guiding the door when the door is shifted between the closed position and the open position.

A vehicle is provided including a structure including a skin defining an outside surface exposed to ambient cooling flow and an inside surface. The structure includes a first structural member extending from the inside surface of the skin and a second structural member extending from the inside surface of the skin; and a thermal management system including a heat exchanger assembly positioned adjacent to, and in thermal communication with, the inside surface of the skin, the heat exchanger assembly positioned at least partially between the first and second structural members of the structure.

A vehicle is provided including a structure including a skin defining an outside surface exposed to ambient cooling flow and an inside surface. The structure includes a first structural member extending from the inside surface of the skin and a second structural member extending from the inside surface of the skin; and a thermal management system including a heat exchanger assembly positioned adjacent to, and in thermal communication with, the inside surface of the skin, the heat exchanger assembly positioned at least partially between the first and second structural members of the structure.

In one embodiment, an unmanned aircraft comprises a housing, an inflatable fuselage, three motors, and three propellers. The housing may comprise an enclosure configured to house one or more electrical components. The inflatable fuselage may comprise a first, a second and a third spindle each extending from the housing. The first motor may be coupled to a first propeller and mounted to the first spindle. The second motor may be coupled to a second propeller and mounted to the second spindle. The third motor may be coupled to a third propeller and mounted to the third spindle.

In one embodiment, an unmanned aircraft comprises a housing, an inflatable fuselage, three motors, and three propellers. The housing may comprise an enclosure configured to house one or more electrical components. The inflatable fuselage may comprise a first, a second and a third spindle each extending from the housing. The first motor may be coupled to a first propeller and mounted to the first spindle. The second motor may be coupled to a second propeller and mounted to the second spindle. The third motor may be coupled to a third propeller and mounted to the third spindle.