Abstract: Certain aspects of the present disclosure provide for modular containers with specialized corner fittings. In one example, a container, includes: six sides; and eight corner fittings, wherein each respective corner fitting of the eight corner fittings comprises: a first outward face on a first side of the six sides; a second outward face on a second side of the six sides; a third outward face on a third side of the six sides; and a corner fitting aperture in at least one of the first outward face, second outward face, or third outward face and centered approximately 3.379 inches from a first edge of the respective corner fitting and approximately 3.379 inches from a second edge of the respective corner fitting.

Abstract: Certain aspects of the present disclosure provide techniques for a modular container, including: six sides, wherein: each side of the six sides of the modular container comprises at least four surface connector arrangements, each surface connector arrangement of the at least four surface connector arrangements comprises at least two connector elements, wherein: at least one connector element of the at least two connector elements is of a first type, and at least one connector element of the at least two connector elements is of a second type; and an access door in at least one side of the six sides.

Abstract: Certain aspects of the present disclosure provide a container, including: a floor; a plurality of vertical walls coupled to the floor; a ceiling coupled to the plurality of vertical walls; a first horizontal gate coupled to a first vertical wall of the plurality of vertical walls and comprising a first plurality of foldable portions; a second horizontal gate coupled to a second vertical wall of the plurality of vertical walls and comprising a second plurality of foldable portions; a third horizontal gate coupled to a third vertical wall of the plurality of vertical walls and comprising a third plurality of foldable portions; and a first vertical gate coupled to the ceiling and comprising a fourth plurality of foldable portions, wherein, when extended, the first horizontal gate, the second horizontal gate, the third horizontal gate, and the first vertical gate form a plurality of separate cargo volumes.

Abstract: Disclosed are structures and features of a space frame aircraft. In particular, this disclosure relates to a space frame aircraft with a pressure membrane.

Abstract: A strut system for a wing of an aircraft, includes a strut member extending from the wing and a first jury strut assembly associated with the wing. The first jury strut assembly includes a first jury strut, which has a first end connected to the strut member and a second jury strut, which has a first end connected to the strut member, wherein a second end of the first jury strut and a second end of the second jury strut are each connected to the wing spaced apart from one another in a direction of a chord.

Abstract: A transportation system includes a first support tower, a second support tower, a suspension cable extending between the first and second support towers, and a tube defining an interior channel extending between the first and second support towers. A vehicle is configured to travel through the interior channel. A tension support member has a first end coupled to the suspension cable and a second end coupled to the first tube through an actuator. The tension support member exerts tension force to upwardly pull the first tube towards the suspension cable. The actuator adjusts the tension force when the vehicle travels through the interior channel under the tension support member to reduce deflection of the tube.

Abstract: An aircraft wing has a plurality of wing segments mounted on a wing spar by joints that allow relative movement between the spar and the wing segments. Tuning of coefficients of thermal expansion is employed to reduce induced stresses from changes in temperature.

Abstract: Modular fuselage assemblies for aircraft, aircraft including modular fuselage assemblies, and methods of assembling modular fuselage assemblies. A modular fuselage assembly includes a plurality of fuselage lobes that may extend along a longitudinal axis of the modular fuselage assembly. Each fuselage lobe includes a plurality of frame members and a lobe skin that is operatively attached to the plurality of frame members and defines an external surface of the fuselage lobe. The modular fuselage assembly also includes a plurality of longerons extending along a longitudinal axis of the modular fuselage assembly. At least two fuselage lobes are operatively attached to each longeron and the plurality of fuselage lobes and the plurality of longerons at least partially bound a cargo hold defined within the modular fuselage assembly. The methods include methods of assembling the modular fuselage assemblies.

Abstract: A pressure vessel includes at least one pair of side bulkheads spaced apart from each other. In addition, the pressure vessel includes at least one substantially flat panel having at least one panel span extending between the pair of side bulkheads and being in non-contacting proximity to the side bulkheads. The panel and the side bulkheads collectively form at least a portion of a structural assembly enclosing the pressure vessel. The pressure vessel also includes a plurality of panel braces coupling the side bulkheads to the panel at a plurality of panel attachment nodes distributed along the panel span. At least two of the panel braces have a different axial stiffness configured to result in the outward deflection of the panel attachment nodes by substantially equal deflection amounts when the panel is subjected to an out-of-plane pressure load during internal pressurization of the pressure vessel.

Abstract: There is provided a vacuum volume reduction system having a volume reduction assembly of a fluid fill assembly coupled to a station wall of a vacuum tube vehicle station, to reduce a volume, under vacuum, in the vacuum tube vehicle station, when a vacuum transport tube vehicle is positioned in the volume at the vacuum tube vehicle station. The fluid fill assembly includes one or more containers, each containing a fluid, and fluid transport member(s), to transport the fluid from the container(s) to one or more enclosed volume portions formed between an exterior of the vacuum transport tube vehicle and an interior of the station wall. The fluid fill assembly further includes one or more fluid pump assemblies attached to the fluid transport member(s), and a control and power system. The vacuum volume reduction system further includes recessed area(s), a vent-to-vacuum assembly coupled to the recessed area(s), and seal elements.

Abstract: Certain aspects of the present disclosure provide an ice management system, including: a plurality of pulsejets located within an interior volume of an aircraft and configured to heat an aircraft surface, wherein each pulsejet of the plurality of pulsejets comprises: an inlet; a combustor; a fuel source; and an exhaust nozzle; and a plurality of intake apertures in the aircraft, wherein each intake aperture of the plurality of intake apertures corresponds to an inlet of one pulsejet of the plurality of pulsejets.

Abstract: Certain aspects of the present disclosure provide a container, including: a floor; a plurality of vertical walls coupled to the floor; a ceiling coupled to the plurality of vertical walls; a first horizontal gate coupled to a first vertical wall of the plurality of vertical walls and comprising a first plurality of foldable portions; a second horizontal gate coupled to a second vertical wall of the plurality of vertical walls and comprising a second plurality of foldable portions; a third horizontal gate coupled to a third vertical wall of the plurality of vertical walls and comprising a third plurality of foldable portions; and a first vertical gate coupled to the ceiling and comprising a fourth plurality of foldable portions, wherein, when extended, the first horizontal gate, the second horizontal gate, the third horizontal gate, and the first vertical gate form a plurality of separate cargo volumes.

Abstract: A modular tube volume reduction assembly for use at a vacuum tube vehicle station is provided. The assembly includes a modular station vacuum tube having a tube volume and a plurality of cavities longitudinally formed around a circumference of the modular station vacuum tube, and a volume reduction assembly integrated with the modular station vacuum tube, where the volume reduction assembly includes a plurality of blocks longitudinally coupled to a cavity interior of each of the plurality of cavities. The assembly includes a control system coupled between the modular station vacuum tube and the blocks. The control system radially moves the blocks to and from a vehicle outer surface of a vacuum transport tube vehicle at the vacuum tube vehicle station. The assembly displaces the tube volume between a station wall and the vehicle outer surface, and reduces the volume to be evacuated at the vacuum tube vehicle station.

Abstract: Neutralizing deflection in a transportation system comprising connecting a number of support structures to ground. A tube is coupled to the support structures via a number of actuators, wherein the tube defines an interior enclosure through which a vehicle can travel. Utilizing a number of sensors, directional displacement of the support structures can be sensed, and the actuators are controller to counter the sensed displacement of the support structures by producing a directionally-opposite displacement of the tube relative to the support structures.

Abstract: Examples relate to modular cargo handling. An example system for positioning and securing cargo includes a pair of rails extending longitudinally in a parallel configuration. The system includes floor beams coupled between coupling links (e.g., sets of wheels) that removably couple to the pair of rails such that each floor beam can move along the length of the rails with less friction. Each floor beam can include one or more coupling points that can be used to secure units of cargos to the floor beams.

Abstract: A light-weight stiffened wing airfoil includes at least one wing segment (52). The wing segment comprises an upper (53b) and a lower skin assembly (53a), wherein each of the upper and lower skin assemblies incorporates a plurality of inwardly facing stringers (74); a first rib (64-1) at a distal end of the wing segment and a second rib (64-2) at a proximal end of the wing segment; a plurality of rib trusses (70) extending from the first and second ribs to the opposing skin assembly (53); and a plurality of support members extending from the inwardly facing stringers to the opposing skin assembly.

Abstract: A vacuum transport tube vehicle for evacuating a vacuum transport tube has a first end, a second end, and a body comprising a piston head. The vehicle has a blade-actuator assembly, comprising a circumferential blade member sealed to the piston head and having a blade perimeter portion defining a first end outer surface forming an annular gap with an inner surface of the vacuum transport tube. The vehicle further includes a plurality of blade segment actuators arranged circumferentially around the piston perimeter portion and configured to actively adjust a radial position of the blade member at the corresponding blade circumferential locations in a manner accommodating non-uniformities in an inner surface profile of the vacuum transport tube, and maintaining the annular gap at a substantially constant and relatively short gap distance during movement of the vehicle through the vacuum transport tube.

Abstract: Method and computer program product for generating a finite element model of a fastener passing through holes in load-bearing plates. Disks of finite elements are arranged in the holes to model the portions of the fastener aligned with each hole. Fence elements extend about the perimeters of the disks and the perimeters of the holes in directions away from sides of the disks and load-bearing plates. Contact bodies can be arranged on the fence elements. When a finite element model is executed, the fence elements and contact bodies can bear against each other to model contact between the holes and the fastener.

Abstract: A vacuum transport tube vehicle, system, and method for evacuating a vacuum transport tube are provided. The vehicle has a first end having a first end outer surface. An annular gap is formed between the first end outer surface and an inner surface of the vacuum transport tube. The vehicle has a second end having a second end outer diameter, and a body in the form of a piston with a structural framework. The vehicle has an orifice extending from a first inlet portion in the first end to a second outlet portion of the vehicle. The vehicle has a drive assembly coupled to the body, and a power system. The vehicle evacuates the vacuum transport tube by reducing pressure within the tube with each successive vehicle pass through the tube, until a desired pressure is obtained and a vacuum is created in the interior of the tube.

Abstract: A modular tube volume reduction assembly for use at a vacuum tube vehicle station is provided. The assembly includes a modular station vacuum tube having a tube volume and a plurality of cavities longitudinally formed around a circumference of the modular station vacuum tube, and a volume reduction assembly integrated with the modular station vacuum tube, where the volume reduction assembly includes a plurality of blocks longitudinally coupled to a cavity interior of each of the plurality of cavities. The assembly includes a control system coupled between the modular station vacuum tube and the blocks. The control system radially moves the blocks to and from a vehicle outer surface of a vacuum transport tube vehicle at the vacuum tube vehicle station. The assembly displaces the tube volume between a station wall and the vehicle outer surface, and reduces the volume to be evacuated at the vacuum tube vehicle station.