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 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.

Abstract: Aircraft wing assemblies are disclosed herein. An example apparatus disclosed herein includes a trailing edge of a wing of an aircraft. The trailing edge has an elastically deformable skin defining a first surface. The trailing edge has a first end to be fixed to the wing and a second end opposite the first end that is to move relative to the first end. A flap is movably coupled to the second end of the trailing edge. The flap is movable between a stowed position and a deployed position. The trailing edge is to elastically elongate when the flap moves from the stowed position to the deployed position and the trailing edge is to elastically collapse when the flap moves from the deployed position to the stowed position.

Abstract: Described herein is an aircraft. The aircraft comprises a body. The aircraft also comprises a wing coupled to and extending from the body. The wing comprises a wing inboard end portion, a wing outboard end portion, opposite the wing inboard end portion, and an intermediate portion between the wing inboard end portion and the wing outboard end portion. The aircraft further comprises a strut. The strut comprises a strut inboard end portion coupled to and extending from the body and a strut outboard end portion coupled to and extending from the intermediate portion of the wing. The aircraft additionally comprises at least one aerodynamic control surface movably coupled to the strut.

Abstract: An aircraft includes a body, a wing coupled to and extending from the body, and a strut. The wing includes a wing thickest region bounded by a wing thickest region leading boundary and a wing thickest region trailing boundary. The strut includes a strut thickest region bounded by a strut thickest region leading boundary and a strut thickest region trailing boundary. In a planform view, the wing thickest region overlaps the strut thickest region at an overlap region, where the overlap region including less than fifteen percent of the strut thickest region.

Abstract: An aircraft that comprises a body, a wing, and a strut. The wing is coupled to and extends from the body. The wing comprises a wing inboard end portion, a wing outboard end portion, opposite the wing inboard end portion, and an intermediate portion between the wing inboard end portion and the wing outboard end portion. The strut comprises a strut inboard end portion and a strut outboard end portion. The strut inboard end portion is coupled to and extends from the body and the strut outboard end portion is coupled to and extends from the intermediate portion of the wing. The strut outboard end portion of the strut is configured to generate a download acting on the strut outboard end portion of the strut when the aircraft is in flight.

Abstract: Disclosed herein is an aircraft that comprises a body, a wing, and a strut. The wing is coupled to and extends from the body. A strut inboard end portion is coupled to and extends from the body and a strut outboard end portion is coupled to and extends from an intermediate portion of the wing. The wing further comprises a first thinned portion adjacent the intermediate portion of the wing. An overall thickness of the first thinned portion of the wing decreases and increases in a spanwise direction along the wing. The strut further comprises a second thinned portion adjacent the outboard end portion of the strut. An overall thickness of the second thinned portion of the strut decreases and increases in a spanwise direction along the strut.

Abstract: An aircraft includes a body, a wing coupled to and extending from the body, and a strut. The wing includes a wing thickest region bounded by a wing thickest region leading boundary and a wing thickest region trailing boundary. The strut includes a strut thickest region bounded by a strut thickest region leading boundary and a strut thickest region trailing boundary. In a planform view, the wing thickest region overlaps the strut thickest region at an overlap region, where the overlap region including less than fifteen percent of the strut thickest region.

Abstract: Described herein is an aircraft. The aircraft comprises a body. The aircraft also comprises a wing coupled to and extending from the body. The wing comprises a wing inboard end portion, a wing outboard end portion, opposite the wing inboard end portion, and an intermediate portion between the wing inboard end portion and the wing outboard end portion. The aircraft further comprises a strut. The strut comprises a strut inboard end portion coupled to and extending from the body and a strut outboard end portion coupled to and extending from the intermediate portion of the wing. The aircraft additionally comprises at least one aerodynamic control surface movably coupled to the strut.

Abstract: An aircraft that comprises a body, a wing, and a strut. The wing is coupled to and extends from the body. The wing comprises a wing inboard end portion, a wing outboard end portion, opposite the wing inboard end portion, and an intermediate portion between the wing inboard end portion and the wing outboard end portion. The strut comprises a strut inboard end portion and a strut outboard end portion. The strut inboard end portion is coupled to and extends from the body and the strut outboard end portion is coupled to and extends from the intermediate portion of the wing. The strut outboard end portion of the strut is configured to generate a download acting on the strut outboard end portion of the strut when the aircraft is in flight.

Abstract: Disclosed herein is an aircraft that comprises a body, a wing, and a strut. The wing is coupled to and extends from the body. A strut inboard end portion is coupled to and extends from the body and a strut outboard end portion is coupled to and extends from an intermediate portion of the wing. The wing further comprises a first thinned portion adjacent the intermediate portion of the wing. An overall thickness of the first thinned portion of the wing decreases and increases in a spanwise direction along the wing. The strut further comprises a second thinned portion adjacent the outboard end portion of the strut. An overall thickness of the second thinned portion of the strut decreases and increases in a spanwise direction along the strut.

Abstract: Aircraft wing assemblies are disclosed herein. An example apparatus disclosed herein includes a trailing edge of a wing of an aircraft. The trailing edge has an elastically deformable skin defining a first surface. The trailing edge has a first end to be fixed to the wing and a second end opposite the first end that is to move relative to the first end. A flap is movably coupled to the second end of the trailing edge. The flap is movable between a stowed position and a deployed position. The trailing edge is to elastically elongate when the flap moves from the stowed position to the deployed position and the trailing edge is to elastically collapse when the flap moves from the deployed position to the stowed position.

Abstract: Aircraft wing assemblies are disclosed herein. An example apparatus disclosed herein includes a trailing edge of a wing of an aircraft. The trailing edge has a flexible skin defining a first surface. The example apparatus also includes a flap movably coupled to the trailing edge. The flap defines a second surface. The first surface and the second surface form a substantially continuous surface when the flap is in a stowed position and when the flap is in a deployed position.

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: A method and apparatus for forming a platform. In one embodiment, the apparatus comprises a set of support members associated with the structure, and a set of adjustment members. An adjustment member in the set of adjustment members is associated with a corresponding support member in the set of support members. The adjustment member is configured to adjust an angle between the corresponding support member and the structure.

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: A method and apparatus for forming a platform. In one embodiment, the apparatus comprises a set of support members associated with the structure, and a set of adjustment members. An adjustment member in the set of adjustment members is associated with a corresponding support member in the set of support members. The adjustment member is configured to adjust an angle between the corresponding support member and the structure.

Abstract: An aircraft comprises an airframe, an electric propulsion system, a number of battery pods, and an engagement system. The number of battery pods has a physical connector system. The engagement system is attached to the airframe and is capable of engaging the physical connector system to connect the number of battery pods to the airframe.

Abstract: An aircraft comprises an airframe, an electric propulsion system, a number of battery pods, and an engagement system. The number of battery pods has a physical connector system. The engagement system is attached to the airframe and is capable of engaging the physical connector system to connect the number of battery pods to the airframe.