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: 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 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 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 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 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: 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: 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: 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.