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 solar powered aircraft including a modular main wing and a pair of relatively large modular winglets attached to the transverse end portions of the main wing. To collect solar radiation, including relatively low-angle radiation, solar panels are mounted to both the main wing and the winglets. In some embodiments, the aspect ratio of the main wing is relatively low, such as between 9 and 15, i.e., the main wing is relatively deep compared to its wing span. In some embodiments, the winglets are relatively long, such as in the range of 0.2 to 0.7 times the length of the main wing semi-span. In some embodiments, a truss-like spar passes through and helps support the wing and the winglets.

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: Technologies are described herein for sailing wing for a vehicle such as a sailboat. As described herein, a sailing wing includes a main sail and a control surface. The control surface is rotatable around a hinge. When deflected, the control surface using force imparted on the control surface by the wind causes the main sail to rotate about a pivot axis, creating thrust.

Abstract: Technologies are described herein for sailing wing for a vehicle such as a sailboat. As described herein, a sailing wing includes a main sail and a control surface. The control surface is rotatable around a hinge. When deflected, the control surface using force imparted on the control surface by the wind causes the main sail to rotate about a pivot axis, creating thrust.

Abstract: A method of covering a portion of a fastener, protruding from a surface, that comprises providing a cap comprising a wall, a base, an interior, at least partially delimited by the wall and the base, and pawls, located in the interior of the cap. The method further comprises coupling a tooth to the fastener, covering the portion of the fastener with the cap, and positively engaging the pawls with the tooth, such that the pawls are loaded in tension against the tooth.

Abstract: Ignition-quenching systems comprise an ignition-quenching cover configured to quench an ignition event in a combustible environment triggered by an ignition source associated with a fastener stack. The ignition-quenching cover comprises a porous body that is gas permeable and that has pores sized to quench ignition in the combustible environment. The ignition-quenching cover further comprises a cover attachment feature configured to mate with a fastener attachment feature of the fastener stack. The ignition-quenching cover is configured to cover the fastener stack, which may be associated with a potential ignition source that produces an ignition event in the combustible environment. The porous body may include one or more porous elements that may be formed of various polymeric, mesh, or fabric materials. The ignition-quenching cover may comprise a non-porous frame that is bonded to the porous body and that defines the cover attachment feature.

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: 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 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: Ignition-quenching systems comprise an ignition-quenching cover configured to quench an ignition event in a combustible environment triggered by an ignition source associated with a fastener stack. The ignition-quenching cover comprises a porous body that is gas permeable and that has pores sized to quench ignition in the combustible environment. The ignition-quenching cover further comprises a cover attachment feature configured to mate with a fastener attachment feature of the fastener stack. The ignition-quenching cover is configured to cover the fastener stack, which may be associated with a potential ignition source that produces an ignition event in the combustible environment. The porous body may include one or more porous elements that may be formed of various polymeric, mesh, or fabric materials. The ignition-quenching cover may comprise a non-porous frame that is bonded to the porous body and that defines the cover attachment feature.

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 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 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: 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: 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: 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 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 stringer grooves (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 stringer grooves to the opposing skin assembly.

Abstract: A solar powered aircraft including a modular main wing and a pair of relatively large modular winglets attached to the transverse end portions of the main wing. To collect solar radiation, including relatively low-angle radiation, solar panels are mounted to both the main wing and the winglets. In some embodiments, the aspect ratio of the main wing is relatively low, such as between 9 and 15, i.e., the main wing is relatively deep compared to its wing span. In some embodiments, the winglets are relatively long, such as in the range of 0.2 to 0.7 times the length of the main wing semi-span. In some embodiments, a truss-like spar passes through and helps support the wing and the winglets.