Apparatus and methods for limiting trailing edge deflection in aircraft folding wing tips are disclosed herein. An example aircraft wing disclosed herein includes a fixed wing portion. The fixed wing portion includes an outboard rib. The aircraft wing also includes a wing tip moveably coupled to the fixed wing portion. The wing tip is moveable between an extended position and a folded position. The wing tip includes an inboard rib that is disposed in a trailing edge section of the wing tip. The wing tip includes a stop plate coupled to the inboard rib. The stop plate extends inboard from the inboard rib such that when the wing tip is in the extended position, the stop plate is disposed below a portion of the outboard rib of the fixed wing portion to limit upward deflection of the trailing edge section of the wing tip relative to the fixed wing portion.

An aircraft (1) having a wing (3) and a wing tip device (4) at the tip of the wing (3), the wing tip device (4) having front and rear spars (14, 13), wherein the wing tip device (4) has a cross-brace spar (18) that links the front and rear spars and is oriented such that it is oblique to the front and rear spars (14, 13).

Various aerospace vehicle systems and methods are disclosed. In one embodiment, a fuel efficient, low emissions aerospace vehicle includes a fuselage having a fineness ration of equal to or greater than 8. The fuselage is comprised of at least 50% composite materials. The aerospace vehicle also includes a first wing, a second wing, and a third wing coupled to the fuselage, each wing having an aspect ratio of equal to or greater than 35. The wings each have a span within 10% of one another and an aspect ratio within 10% of one another. Each wing is comprised of at least 50% composite materials. The aerospace vehicle also includes at least one stabilizing unit coupled to the fuselage. The stabilizing unit includes first and second stabilizer surfaces configured in a V-tail configuration. The aerospace vehicle further includes at least one propulsion system.

A wingtip device to attach to a wing of an aircraft includes an aerofoil portion and a connection spar arranged to be received in a connection spar receiving portion of the wing of an aircraft. The spar includes a first through hole in a first portion of the connection spar and a second through hole in a second rearward portion of the connection spar, the second portion being rearward of the first portion with respect to a direction of flight. The first and second through holes are arranged to receive a retaining pin that is to be inserted through both the first and second through holes.

A vortex generator apparatus for an aircraft includes a surface section having a receiving recess, a vortex generator having a first edge, an opposite second edge and a vortex generator surface component extending from the first edge to the second edge, wherein the first edge is fixedly arranged in or adjacent to the receiving recess. The vortex generator surface component includes at least one electroactive polymer assembly, wherein the at least one electroactive polymer is switchable into an extended state by applying an electrical voltage and into a neutral state by removing the electrical voltage. The electroactive polymer assembly and the vortex generator surface component are configured to retract the vortex generator surface component completely into the receiving recess in the neutral state of the electroactive polymer assembly and to extend the vortex generator surface component from the receiving recess in the extended state.

A vortex generator apparatus for an aircraft includes a surface section having a receiving recess, a vortex generator having a first edge, an opposite second edge and a vortex generator surface component extending from the first edge to the second edge, wherein the first edge is fixedly arranged in or adjacent to the receiving recess. The vortex generator surface component includes at least one electroactive polymer assembly, wherein the at least one electroactive polymer is switchable into an extended state by applying an electrical voltage and into a neutral state by removing the electrical voltage. The electroactive polymer assembly and the vortex generator surface component are configured to retract the vortex generator surface component completely into the receiving recess in the neutral state of the electroactive polymer assembly and to extend the vortex generator surface component from the receiving recess in the extended state.

The present disclosure presents systems, apparatuses, and methods of active flow controls for dissipating tip vortices. In this regard, a method comprises positioning one or more fan-shaped plasma actuators on an end surface of a tip of one or more airfoils of an aircraft, wherein the fan-shaped plasma actuators are surface compliant with the surface of the tip of the one or more airfoils; and activating the one or more fan-shaped plasma actuators during a flight of the aircraft, wherein at least one tip vortex generated by a flight of the aircraft is reduced by an introduction of one or more vortices generated by the one or more fan-shaped plasma actuators on the end surface of the tip of the one or more airfoils of the aircraft. Other systems, apparatuses, and methods are also presented.

The present disclosure presents systems, apparatuses, and methods of active flow controls for dissipating tip vortices. In this regard, a method comprises positioning one or more fan-shaped plasma actuators on an end surface of a tip of one or more airfoils of an aircraft, wherein the fan-shaped plasma actuators are surface compliant with the surface of the tip of the one or more airfoils; and activating the one or more fan-shaped plasma actuators during a flight of the aircraft, wherein at least one tip vortex generated by a flight of the aircraft is reduced by an introduction of one or more vortices generated by the one or more fan-shaped plasma actuators on the end surface of the tip of the one or more airfoils of the aircraft. Other systems, apparatuses, and methods are also presented.

A wing includes a low pressure side, a high pressure side opposite the low pressure side, and a drag reducing apparatus coupled to the low pressure using an adhesive. The drag reducing apparatus includes a first side coupled to the low pressure side of the wing, and a second side opposite the first side. The second side includes a plurality of vortex generators arranged in an array configuration. The vortex generators generate one or more vane vortices near an end of the low pressure side of the wing, thereby weakening a wingtip vortex generated by the wing.

A wing includes a low pressure side, a high pressure side opposite the low pressure side, and a drag reducing apparatus coupled to the low pressure using an adhesive. The drag reducing apparatus includes a first side coupled to the low pressure side of the wing, and a second side opposite the first side. The second side includes a plurality of vortex generators arranged in an array configuration. The vortex generators generate one or more vane vortices near an end of the low pressure side of the wing, thereby weakening a wingtip vortex generated by the wing.