Abstract: An aerial vehicle including a main body having a leading edge. An inlet is recessed aft from the leading edge. Forward protrusions extend from the main body on opposite sides of the inlet. An outlet nozzle is proximate to an aft end. The inlet is in fluid communication with the outlet nozzle. Wings extend from the main body.

Abstract: A coupling system is configured to secure one or more struts to a wing of an aircraft. The coupling system includes one or more splice straps that secure the one or more struts to the wing. A method for securing one or more struts to a wing of an aircraft includes securing, by one or more splice straps, the one or more struts to the wing.

Abstract: A cleaning system and method for an enclosed space include a floor including a hydrophobic material configured to repel liquid. One or more wipers are configured to sweep one or both of the liquid or debris off the floor, such as into an inlet of a vacuum.

Abstract: A vehicle includes an internal cabin, a lavatory within the internal cabin, and a cleaning system within the lavatory. The cleaning system includes a floor having an exposed upper surface. The floor includes a hydrophobic material configured to repel liquid. An air knife is configured to output an airstream over the exposed upper surface of the floor to remove one or both of liquid or debris off the floor. The air knife is at or proximate to a first portion of the floor. A vacuum has an air inlet. The vacuum draws in the airstream through the air inlet. The vacuum is at or proximate to a second portion of the floor that is opposite from the first portion. The first portion is at a first level that is above a second level of the second portion.

Abstract: Composite fabrication system and associated methods. In one embodiment, a composite fabrication system comprises a molding tool that includes a forming surface at least partially disposed within a constrained space, and a foamable material that expands inside of the constrained space to form an expanded material that presses a layup of one or more composite layers against the molding tool. The composite fabrication system further comprises a curing device configured to cure the layup to form a composite part, and a cutting wire embedded in the constrained space that is heated and configured to cut the expanded material into pieces that are removable from the constrained space.

Abstract: A method for use in forming a composite structure that includes dispensing a first sheet of composite material, cutting the first sheet of composite material to form one of a plurality of plies of composite material, and providing the plurality of plies of composite material to a forming tool one at a time in a ply laydown sequence. A first sequential ply in the ply laydown sequence is provided, and then a second sequential ply in the ply laydown sequence is automatically provided after the first sequential ply has been provided.

Abstract: A method, apparatus, apparatus, and computer program product for managing an autonomous aerial vehicle. A copy of a mission plan is stored in a mission work queue. The mission plan is located in the autonomous aerial vehicle and comprises mission components that define tasks performed by the autonomous aerial vehicle. A change to the mission components in the copy of the mission plan in the mission work queue is received to form a modified mission component in the copy of the mission plan. A determination is made as to whether the copy of the mission plan including the modified mission component can be executed by the autonomous aerial vehicle. The copy of the mission plan including the modified mission component is synchronized with the mission plan in the autonomous aerial vehicle such that the mission plan includes the modified mission component. The autonomous aerial vehicle executes the mission plan.

Abstract: A composite charge used to compression form a stringer comprises multiple plies of unidirectional, prepreg having various fiber orientations. Certain of the plies have a pattern of angled cuts allowing the plies to stretch both longitudinally and transversely during forming, thereby reducing ply wrinkling in contoured areas of the stringer.

Abstract: A system, device and method to facilitate tying a knot are provided. In the context of a device, the device includes a fixture defining an internal passage therethrough. The fixture defines a circumferential groove opening through an interior surface of the fixture and into the internal passage. The groove includes first and second groove portions that cross one another. Opposite ends of the groove are coincident and open through an exterior surface of the fixture. With relation to a system, the system includes a fixture and a lead member supply mechanism configured to alternately feed a lead member through the groove and to withdraw the lead member from the groove once the tie member is connected thereto.

Abstract: The present disclosure provides polyanilines, articles thereof, and methods of forming polyanilines. In at least one aspect, a polyaniline has a thermal stability of about 100° C. or greater, a weight average molecular weight (Mw) of from about 50,000 g/mol to about 150,000 g/mol and a molecular weight distribution (Mw/Mn) of from about 1 to about 5. In at least one aspect, a film includes a polyaniline, the film having a hydrocarbon content of about 1 wt % or less, based on the total weight of the film. In at least one aspect, a method includes introducing an emulsion of an aqueous solution of an aniline and an alkyl-substituted aryl sulfonic acid having 1 wt % or less of hydrocarbon content into a flow reactor, the flow reactor having a length of tubing having an inner diameter. The method includes polymerizing the monomer within the tube to form a polyaniline.

Abstract: Disclosed herein is an apparatus for preventing a user from moving beyond a first distance from a support structure. The apparatus comprises an extension member, comprising a first end and a second end that is opposite the first end. The first end is configured to be fixed to the support structure. The second end is movable relative to the first end along a plane and the second end is configured to extend away from the first end to an extended position and retract from the extended position towards the first end to a retracted position. The apparatus also comprises a flexible tether, having a fixed length and comprising an anchor end, attached to the second end of the extension member, and a user end, configured to attach to a user. The extended position is no more than a second distance away from the first end. The sum of the fixed length and the second distance is less than the first distance.

Abstract: A graded multilayered composite comprises a metal matrix material having a first side and a second side opposite the first side. A first layer of microspheres is dispersed on the first side of the metal matrix material. A second layer of microspheres is dispersed on the second side of the metal matrix material.

Abstract: In an example, a cargo system for storage in a seating area of an aircraft is described. The cargo system includes a plurality of storage containers including a first container operably connected to a second container via at least one connector. The connector(s) is/are configured to allow relative movement of the first container to the second container between a first and second position. Based on the first container being in the first position, the plurality of storage containers are in a stacked arrangement in which the second container supports the first container. And based on the first container being in the second position, the plurality of storage containers are in a seated arrangement in which (i) the first container is positioned relative to the second container and configured to sit on a passenger seat in an aircraft and (ii) the second container abuts or sits adjacent to the passenger seat.

Abstract: Assemblies for air vehicle control surfaces and related methods are disclosed. An example apparatus includes a control surface; a bullnose carried by the control surface, the bullnose moveable relative to the control surface; a first actuator operatively coupled to the control surface to cause the control surface to rotate; and a second actuator operatively coupled to the control surface, the second actuator to cause the bullnose to move from a first position to a second position to cause an opening to be formed relative to the control surface, the movement of the bullnose independent of rotation of the control surface.

Abstract: Examples provide a seat assembly, a system including the seat assembly and a method for reducing electromagnetic interference in an aircraft. A seat assembly for an aircraft includes a frame having a base and a support member operatively coupled to the base. A seat is coupled to the base and a first side of the support member. The seat includes a conductive substrate layer configured to absorb electrical charges.

Abstract: A hinge assembly for connecting a door to a fuselage of an aircraft includes a hinge arm having a fuselage fitting pivotably coupled to a fuselage rotatable interface and a door fitting pivotably coupled to a door rotatable interface. The hinge assembly includes a programmable gear assembly coupled to the hinge arm allowing the hinge arm to pivot around the fuselage fitting when the door is moved from a door closed position to a door open position and causing the door to maintain in a generally parallel orientation relative to the fuselage between the door closed position to the door open position. The programmable gear assembly includes a fuselage gear coupled to the fuselage fitting, a door gear coupled to the door fitting, and a rack operably coupled between the fuselage gear and the door gear.

Abstract: A system and a method include a software management control unit configured to receive one or more changes to one or more portions of a first software configuration for hardware components of one or more vehicle, such as aircraft, or other assets. The software management control unit is further configured to revise the first software configuration for the hardware components of the one or more aircraft to provide a second software configuration that includes the one or more changes.

Abstract: A method of forming an object from a material includes directing a first beam of light toward a first target location of the material to define a first portion of the object. The method also includes, after directing the first beam of light toward the first target location, determining an optical correction to be applied by an optical system. The optical correction is based on an atmospheric change in an atmospheric distortion region proximate the first target location due, at least in part, to interaction of the first beam of light and the material. The method further includes directing a second beam of light toward a second target location of the material to define a second portion of the object. The second beam of light is directed through at least a portion of the atmospheric distortion region while the optical correction is applied.

Abstract: A system and method for removing a backing from a ply of composite material is disclosed. The system includes a roller having a roller axis and a roller surface that circumscribes the roller axis. The system also includes an adhesion feature disposed on the roller surface. The system further includes a roller drive to move the roller along a travel path that is perpendicular to the roller axis and to rotate the roller about the roller axis.

Abstract: There is provided an acoustically treated landing gear door for reducing noise from a landing gear of an aircraft. The acoustically treated landing gear door includes a landing gear door for attachment to the aircraft. The landing gear door includes an acoustic treatment assembly integrated on an inner mold line of an interior side, and extending within an interior cavity of the landing gear door. The acoustic treatment assembly includes a core structure having a first side and a second side, a plurality of core cells extending between the first side and the second side, and a drainage system. The acoustic treatment assembly further includes an acoustic facesheet and a nonporous backsheet. The acoustically treated landing gear door reduces the noise from the landing gear, when the landing gear is in a deployed position, by attenuating acoustic waves emanating from the landing gear and reflected off the acoustic treatment assembly.