Abstract: Apparatus and articles of manufacture are disclosed of an aircraft comprising: a brace to support a wing of the aircraft, the brace including a first end coupled to the wing and a second end coupled to a fuselage of the aircraft, the brace including: a strut extending between the first end and the second end; and an airfoil having a cavity containing the strut.

Abstract: A securing lock for a cargo support apparatus includes one or more first locking interfaces. The one or more first locking interfaces include a tooth assembly including one or more teeth, and a jaws assembly including one or more jaws. The one or more teeth are configured to be engaged by one or more other jaws of a second locking interface of at least one other container to secure the container to the at least one other container. The one or more jaws are configured to engage one or more other teeth of the second locking interface of the at least one other container to secure the container to the at least one other container.

Abstract: A tank system includes a vacuum tank and a pressure tank. The vacuum tank has a vacuum tank main portion extending between vacuum tank end portions. The pressure tank is mounted within the vacuum tank, and has a pressure tank main portion extending between pressure tank end portions. The tank system includes a deflection control system comprising at least one elongate support member extending from a vacuum tank first side of the vacuum tank main portion, and passing through an opening in a pressure tank first side of the pressure tank main portion, and coupled to a pressure tank second side opposite the pressure tank first side. The elongate support member is configured to support the pressure tank main portion and reduce deflections of the pressure tank main portion relative to the vacuum tank main portion when the tank system is subjected to a load.

Abstract: There is provided a segmented vacuum jacketed tank system. The system includes a segmented structurally integrated vacuum tank having a vacuum tank main portion between vacuum tank end portions. The vacuum tank main portion includes a vacuum tank skin having an outer surface and an inner surface, vacuum tank skin segments, and a longitudinal cross section with a profile geometry configured for buckling prevention for the vacuum tank skin under external pressure loads. The vacuum tank main portion includes multipurpose stiffener member(s) configured to carry one or more of system transport line(s), a liquid fuel, or a nitrogen gas in an interior. The system includes a pressure tank within the segmented structurally integrated vacuum tank. The pressure tank is configured to store a cryogenic fluid and includes a pressure tank main portion between pressure tank end portions. The system further includes a vacuum cavity.

Abstract: There is provided an expandable strut assembly for a wing of an aircraft, having a strut with a strut cross section with an airfoil shape, and the strut having an outboard end coupled to the wing, an inboard end coupled to a fuselage, and an elongate body, and having at least one shape transition assembly connected to the strut. Each shape transition assembly is configured to transition the strut between a contracted position and an expanded position, and is configured to transition the strut cross section between a contracted airfoil shape and an expanded airfoil shape. Each shape transition assembly has a shape transition mechanism attached to an interior of the strut. The shape transition mechanism includes fixed length structural members, and a drive mechanism of variable length structural member(s), includes an actuation mechanism connected to the shape transition mechanism, and an activation mechanism coupled to the actuation mechanism.

Abstract: A tank system includes a vacuum tank having a vacuum tank skin, and a pressure tank mounted within the vacuum tank having one or more pressure tank skin segments having a total circumference that is less than that of a complete circle, resulting in one or more longitudinal gaps respectively between the one or more pressure tank skin segments. The tank system includes one or more gap control mechanisms configured to control a width of the one or more longitudinal gaps in a manner facilitating movement of the one or more pressure tank skin segments between at least the following positions: a retracted position in which there is a radial gap between each pressure tank skin segment and the vacuum tank skin, and a fully extended position in which at least a portion of each pressure tank skin segments is in contact with the vacuum tank skin.

Abstract: There is provided a structurally integrated vacuum tank that includes a vacuum tank main portion extending between vacuum tank end portions. The vacuum tank main portion includes a vacuum tank skin forming a cylinder. The vacuum tank skin has a longitudinal cross section with a profile geometry configured for buckling prevention for the vacuum tank skin under external pressure loads. The vacuum tank skin is configured to provide a pressure barrier between an outside ambient pressure and a vacuum in an interior of the vacuum tank main portion. The vacuum tank main portion further includes a plurality of stiffener members coupled to surface portions of the vacuum tank skin. The vacuum tank skin and the plurality of stiffener members are configured to carry structural loads.

Abstract: There is provided an extendable compression chain system for extending a structure. The system includes a track assembly, a curved guide assembly, an extendable compression chain assembly, an actuation mechanism, and a mechanical power apparatus. The extendable compression chain assembly is configured to travel along the track assembly and to follow the curved portion of the track assembly, to move from a retracted position to an extended position, to extend the structure coupled to the extendable compression chain assembly. The extendable compression chain assembly includes a compression chain structure having a first end, a second end, and modules. The modules are movable between a rigid position and a collapsed position, as the compression chain structure follows the curved portion of the track assembly, and wraps around the curved guide assembly. The extendable compression chain assembly includes an actuation end fitting and a structure interface end fitting.

Abstract: There is provided a strut assembly for a wing of an aircraft. The strut assembly has a strut having an outboard end, an inboard end, and an elongate body. The outboard end is coupled to the wing of the aircraft, and the inboard end is coupled to a fuselage of the aircraft. The strut assembly further has at least one tensioner member having a first end coupled to the strut. The strut assembly further has a first fitting element having a through opening receiving a first portion of the strut and a bearing surface facing inboard. The strut assembly further has a second fitting element having a through opening receiving a second portion of the strut and a bearing surface facing outboard. The at least one tensioner member maintains tension in the strut, to keep the strut taut and in tension, to prevent or to minimize drooping of the strut.

Abstract: There is provided a tank system having a removable plug assembly. The tank system has a vacuum tank with a vacuum tank main portion, a pressure tank mounted within the vacuum tank, and a vacuum cavity formed between the pressure tank and the vacuum tank. The pressure tank has the removable plug assembly with removable plug element(s), each configured to plug and to unplug opening(s) in the pressure tank, and a retraction mechanism within the pressure tank coupled to the removable plug element(s). When an emergency condition occurs, the retraction mechanism is activated to pull the removable plug element(s) away from the opening(s) and into the interior of the pressure tank, to allow a cryogenic fluid to exit from the pressure tank, through the opening(s), and into the vacuum cavity, and when the vacuum tank has a breach, to allow the cryogenic fluid to further exit out into air.

Abstract: Apparatus and articles of manufacture are disclosed of an aircraft comprising: a brace to support a wing of the aircraft, the brace including a first end coupled to the wing and a second end coupled to a fuselage of the aircraft, the brace including: a strut extending between the first end and the second end; and an airfoil having a cavity containing the strut.

Abstract: A tank system includes a vacuum tank having a vacuum tank skin, and a pressure tank mounted within the vacuum tank having one or more pressure tank skin segments having a total circumference that is less than that of a complete circle, resulting in one or more longitudinal gaps respectively between the one or more pressure tank skin segments. The tank system includes one or more gap control mechanisms configured to control a width of the one or more longitudinal gaps in a manner facilitating movement of the one or more pressure tank skin segments between at least the following positions: a retracted position in which there is a radial gap between each pressure tank skin segment and the vacuum tank skin, and a fully extended position in which at least a portion of each pressure tank skin segments is in contact with the vacuum tank skin.

Abstract: There is provided a structurally integrated vacuum tank that includes a vacuum tank main portion extending between vacuum tank end portions. The vacuum tank main portion includes a vacuum tank skin forming a cylinder. The vacuum tank skin has a longitudinal cross section with a profile geometry configured for buckling prevention for the vacuum tank skin under external pressure loads. The vacuum tank skin is configured to provide a pressure barrier between an outside ambient pressure and a vacuum in an interior of the vacuum tank main portion. The vacuum tank main portion further includes a plurality of stiffener members coupled to surface portions of the vacuum tank skin. The vacuum tank skin and the plurality of stiffener members are configured to carry structural loads.

Abstract: There is provided a tank system having a removable plug assembly. The tank system has a vacuum tank with a vacuum tank main portion, a pressure tank mounted within the vacuum tank, and a vacuum cavity formed between the pressure tank and the vacuum tank. The pressure tank has the removable plug assembly with removable plug element(s), each configured to plug and to unplug opening(s) in the pressure tank, and a retraction mechanism within the pressure tank coupled to the removable plug element(s). When an emergency condition occurs, the retraction mechanism is activated to pull the removable plug element(s) away from the opening(s) and into the interior of the pressure tank, to allow a cryogenic fluid to exit from the pressure tank, through the opening(s), and into the vacuum cavity, and when the vacuum tank has a breach, to allow the cryogenic fluid to further exit out into air.

Abstract: There is provided a segmented vacuum jacketed tank system. The system includes a segmented structurally integrated vacuum tank having a vacuum tank main portion between vacuum tank end portions. The vacuum tank main portion includes a vacuum tank skin having an outer surface and an inner surface, vacuum tank skin segments, and a longitudinal cross section with a profile geometry configured for buckling prevention for the vacuum tank skin under external pressure loads. The vacuum tank main portion includes multipurpose stiffener member(s) configured to carry one or more of system transport line(s), a liquid fuel, or a nitrogen gas in an interior. The system includes a pressure tank within the segmented structurally integrated vacuum tank. The pressure tank is configured to store a cryogenic fluid and includes a pressure tank main portion between pressure tank end portions. The system further includes a vacuum cavity.

Abstract: A tank system includes a vacuum tank and a pressure tank. The vacuum tank has a vacuum tank main portion extending between vacuum tank end portions. The pressure tank is mounted within the vacuum tank, and has a pressure tank main portion extending between pressure tank end portions. The tank system includes a deflection control system comprising at least one elongate support member extending from a vacuum tank first side of the vacuum tank main portion, and passing through an opening in a pressure tank first side of the pressure tank main portion, and coupled to a pressure tank second side opposite the pressure tank first side. The elongate support member is configured to support the pressure tank main portion and reduce deflections of the pressure tank main portion relative to the vacuum tank main portion when the tank system is subjected to a load.

Abstract: There is provided a variable radius assembly having a spindle, at least one variable radius guide member coupled to, and driven by, the spindle, and a tension member attached to the variable radius guide member. The tension member is configured to attach to at least one variable length structural member. The variable radius assembly further has at least one gear coupled to, and driven by, the spindle, and has at least one rotational power source coupled to the spindle, and configured to rotate the spindle. The variable radius guide member enables a tension member length change at a non-linear rate for a constant rate of rotation of the spindle, allowing the at least one variable length structural member to be braced by the tension member at an inclination angle to the at least one variable length structural member throughout a range of motion.

Abstract: Transformable cargo containers for use with ground and air transportation vehicles are presented herein. A cargo container includes a main container body defining a storage chamber. The cargo container also includes a transformable assembly coupled to the main container body and positioned at an exterior of the main container body. The transformable assembly includes one or more supplemental containers and is movable between an aircraft configuration and a ground configuration. Based on the transformable assembly being in the aircraft configuration, the transformable cargo container has a non-rectangular cross-sectional area and is configured to occupy a partially-radial cross-sectional storage area of a fuselage of an aircraft. And based on the transformable assembly being in the ground configuration, the transformable cargo container is configured to occupy a rectangular cross-sectional storage area on a ground transportation vehicle.

Abstract: Transformable cargo containers for use with ground and air transportation vehicles are presented herein. A cargo container includes a main container body defining a storage chamber. The cargo container also includes a transformable assembly coupled to the main container body and positioned at an exterior of the main container body. The transformable assembly includes one or more supplemental containers and is movable between an aircraft configuration and a ground configuration. Based on the transformable assembly being in the aircraft configuration, the transformable cargo container has a non-rectangular cross-sectional area and is configured to occupy a partially-circular cross-sectional storage area of a fuselage of an aircraft. And based on the transformable assembly being in the ground configuration, the transformable cargo container is configured to occupy a rectangular cross-sectional storage area on a ground transportation vehicle.

Abstract: There is provided an extendable compression chain system for extending a structure. The system includes a track assembly, a curved guide assembly, an extendable compression chain assembly, an actuation mechanism, and a mechanical power apparatus. The extendable compression chain assembly is configured to travel along the track assembly and to follow the curved portion of the track assembly, to move from a retracted position to an extended position, to extend the structure coupled to the extendable compression chain assembly. The extendable compression chain assembly includes a compression chain structure having a first end, a second end, and modules. The modules are movable between a rigid position and a collapsed position, as the compression chain structure follows the curved portion of the track assembly, and wraps around the curved guide assembly. The extendable compression chain assembly includes an actuation end fitting and a structure interface end fitting.