A moisture control system includes an anode coupled to an insulation blanket that is positioned between an inner wall and an outer wall of an aircraft fuselage, a cathode coupled to an interior surface of the outer wall, and a power control unit coupled to the anode and the cathode to apply voltage across the anode and the cathode. When the voltage is applied across the anode and the cathode, moisture is drawn away from the anode and toward the cathode on the interior surface of the outer wall and guided along a drainage path provided via structural members disposed between the inner wall and the outer wall toward a drainage port.

Systems and methods for mating component parts are described. In some embodiments, a system for mating components may include a first component, a second component, a first adhesive, and a second adhesive. The first adhesive may be configured to set in less than 5 minutes after the first component and the second component are placed in a mating position, and the second adhesive may require greater than 5 minutes to set. The first adhesive, after setting, may have sufficient strength to maintain the first component and the second component in the mating position while the second adhesive sets.

Embodiments described herein relate to a vertical take-off and landing aircraft, specifically an electric or hybrid electric aircraft having a plurality of ducted fans. The aircraft includes a plurality of axially oriented fans, laterally oriented fans, forward air intakes, side exit ports and rear exhaust ports. The aircraft achieves flight by capturing air in the intakes and diverting the air through the axially oriented fans or the laterally oriented fans through the channels selectively.

An example system includes a plurality of processor modules. Each of the plurality of processor modules is communicatively couplable to an autonomous system of a plurality of autonomous systems. Each of the processor modules includes an autonomous software defined network (A-SDN) data-plane communications controller. The system further includes a portable network controller including an A-SDN control-plane communications controller.

A system and method for forming a composite part. The apparatus comprises a sleeve that molds a composite material. The sleeve has a first face and a second face. The second face has features to mold the composite material. The first face comprises a first inclined surface having an angle less than about 90 degrees and greater than about 0 degrees.

Disclosed herein is a body of a mobile vehicle. The body includes skin, a stringer, and a frame. The skin comprises a first tab and a second tab, opposite the first tab. The first tab is fixed directly onto the skin and the second tab is fixed directly onto the skin. The frame comprises a cut-out, a first foot, and a second foot. The second foot is spaced apart from the first foot by the cut-out. The first foot is fixed directly onto the first tab of the stringer, such that the first tab of the stringer is immediately interposed between the first foot of the frame and the skin. The second foot is fixed directly onto the skin, such that no portion of the frame is fixed directly onto the second tab of the stringer.

A fuselage structure splice may include a panel having an edge and a strap connected to the first panel along the panel edge. A strap surface not in contact with the panel tapers toward the panel with distance from the panel edge. A stringer is mounted on the panel and extends away from the edge of the panel and has a flange mounted to the panel. A fitting has a stringer base portion and a strap base portion. The stringer base portion is connected to the stringer flange and extends along a first line extending in a plane normal to the panel edge. The strap base portion of the fitting is mounted on the strap surface and extends along a second line in the plane. The second line is transverse to the first line and the strap base portion of the fitting has a constant thickness along the second line.

A fuselage assembly for an aircraft including a stringer extending longitudinally along the fuselage. The stringer defines a fluid channel. The fluid channel is configured to form at least part of a distribution duct of a cabin air distribution system.

An airframe or a part thereof 3, for example a skin assembly or a profile such as a structural profile, comprises: a wall W having an aperture A therethrough, wherein the wall W provides a frame F surrounding, at least in part, the aperture A; a panel P conforming with the aperture A; and wherein the airframe or the part 3 thereof is configurable in: a first configuration, wherein the panel P and the frame F are mutually spaced apart; and a second configuration, wherein the panel P is received in the frame F and wherein the frame F resists movement of the panel P in two or three mutually orthogonal directions.

An unmanned aerial vehicle according to certain embodiments generally includes a chassis, a power supply mounted to the chassis, a control system operable to receive power from the power supply, at least one rotor operable to generate lift under control of the control system, and a winch mounted to the chassis. The winch includes a reel and a motor. The reel has a line wound thereon, the line having a free end. The reel includes a circumferential channel in which a wound portion of the line is wound onto the reel. The circumferential channel includes an inner portion, an outer portion, and a passage connecting the inner portion and the outer portion. The motor is operable to rotate the reel under control of the control system to thereby cause the line to wind onto and off of the reel, thereby causing the free end of the line to raise and lower.