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: A system and methods for deployment operations from an airborne vehicle are presented. A designated location of a target is received at a flight control system coupled to a location tracking guided container comprising an agent. The location tracking guided container is ejected at an ejection point from the airborne vehicle approximately above the designated location of the target to descend at a descent rate and a descent angle. A calculated path to the designated location is calculated based on the designated location and a current location of the location tracking guided container. The location tracking guided container is aerodynamically guided by a glide control structure to fly along the calculated path from the ejection point to a load release altitude near the designated location of the target. The agent is delivered to the designated location of the target by releasing the agent at the load release altitude near the designated location.

Abstract: A cap for use in covering a portion of a fastener protruding from a surface is provided. The portion includes threads. The cap includes an interior, a base that at least partially delimits the interior, a threaded receptacle on the interior configured to threadably engage the portion of the fastener, and a seal coupled to the base to engage the surface.

Abstract: A system for use in covering a portion of a fastener protruding from a surface is provided. The system includes a cap that includes an interior, a base that at least partially delimits the interior, and pawls on the interior. The system may also include a tooth configured to be associated with the fastener and configured to positively engage the pawls.

Abstract: In an embodiment of the disclosure, there is provided a strain isolation layer assembly. The assembly has a rigid solar layer; a strain isolation layer having a discontinuous configuration, a vertical rigidity, and a horizontal shear flexibility; and an underlying substrate layer. The strain isolation layer is coupled between the rigid solar layer and the underlying substrate layer to form a strain isolation layer assembly, such that the strain isolation layer isolates the rigid solar layer to reduce one or more strains induced on the rigid solar layer.

Abstract: An airship comprises a shell having a bi-convex shape, wherein the shell encompasses a volume, and a gas storage system located within the volume.

Abstract: The present disclosure is generally directed to a cargo transfer system, a method of transferring cargo containers, and a method of handling cargo containers including a cargo transfer pallet capable of supporting a plurality of cargo containers thereon, a cargo loader vehicle capable of receiving the cargo transfer pallet thereon, and a cargo staging structure capable of receiving the cargo transfer pallet thereon and capable of receiving the cargo loader vehicle therein such that the cargo transfer pallet is supported by the cargo staging structure over at least a portion of the cargo loader vehicle.

Abstract: A system and methods for deployment operations from an airborne vehicle are presented. A designated location of a target is received at a flight control system coupled to a location tracking guided container comprising an agent. The location tracking guided container is ejected at an ejection point from the airborne vehicle approximately above the designated location of the target to descend at a descent rate and a descent angle. A calculated path to the designated location is calculated based on the designated location and a current location of the location tracking guided container. The location tracking guided container is aerodynamically guided by a glide control structure to fly along the calculated path from the ejection point to a load release altitude near the designated location of the target. The agent is delivered to the designated location of the target by releasing the agent at the load release altitude near the designated location.

Abstract: A method and apparatus for improved aircraft control through the use of adjustable winglets. The adjustable winglets are located at the terminal ends of an aircraft's wings and may pivot about an axis parallel to the yaw axis of the aircraft. The adjustable winglets may also include outboard ailerons for improved control of the aircraft.

Abstract: In an embodiment of the disclosure, there is provided a strain isolation layer assembly. The assembly has a rigid solar layer; a strain isolation layer having a discontinuous configuration, a vertical rigidity, and a horizontal shear flexibility; and an underlying substrate layer. The strain isolation layer is coupled between the rigid solar layer and the underlying substrate layer to form a strain isolation layer assembly, such that the strain isolation layer isolates the rigid solar layer to reduce one or more strains induced on the rigid solar layer.

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: A method and apparatus for transporting containers in an aircraft. A number of containers is loaded into the aircraft. The aircraft is comprised of first and second outer planar structures, a number of planar structures located between the first outer planar structure and the second outer planar structure, a wing, and a support structure. The first outer planar structure, the second outer planar structure, and the number of planar structures are substantially parallel to each other, are coupled to each other to form a fuselage structure, and are configured to receive the number of containers. The support structure connects the wing to a first bottom end of the first outer planar structure, a second bottom end of the second outer planar structure, and a number of bottom ends of the number of planar structures. The aircraft is operated to transport the number of containers to a destination.

Abstract: A blended wing body cargo aircraft is disclosed. A body section defines a cargo volume, where an outer surface of the body section is shaped to provide an aerodynamic lifting surface. A cargo door and ramp structure is located in an aft end of the body section and is shaped to conform to an outer shape of the aerodynamic lifting surface when in a closed position. A control surface has a slightly cambered downward shape, and is positioned substantially near an aft end of the cargo door and ramp structure.

Abstract: An airship comprises a shell, a gas storage system, an air storage system, a cargo storage system, a heating system, and a propulsion system. The shell encompasses a volume. The gas storage system is located within the volume, wherein the gas storage system is capable of storing a lighter than air gas. The air storage system is located within the volume, wherein the air storage system is capable of storing heated air. The heating system is capable of heating air. The propulsion system is capable of propelling the shell during flight.

Abstract: A blended wing body cargo aircraft is disclosed. A body section defines a cargo volume, where an outer surface of the body section is shaped to provide an aerodynamic lifting surface. A cargo door and ramp structure is located in an aft end of the body section and is shaped to conform to an outer shape of the aerodynamic lifting surface when in a closed position. A control surface has a slightly cambered downward shape, and is positioned substantially near an aft end of the cargo door and ramp structure.

Abstract: An airship comprises a shell having a bi-convex shape, wherein the shell encompasses a volume, and a gas storage system located within the volume.

Abstract: An airship comprises a shell, a gas storage system, an air storage system, a cargo storage system, a heating system, and a propulsion system. The shell encompasses a volume. The gas storage system is located within the volume, wherein the gas storage system is capable of storing a lighter than air gas. The air storage system is located within the volume, wherein the air storage system is capable of storing heated air. The heating system is capable of heating air. The propulsion system is capable of propelling the shell during flight.