A vehicle, such as a micro-aerial vehicle or underwater vehicle, includes at least one lift structure, such as a low-aspect-ratio wing or a fin, respectively. The at least one lift structure comprises one or more alulas. A leading surface of each alula is (a) flush with a leading surface of the lift structure or (b) offset from the leading edge of the lift surface by up to approximately 10% of the chord length of the lift structure. The length of each alula is no more than approximately 20% of a lift structure length corresponding to the lift structure. In various embodiments, the alula is deflected or canted with respect to a plane defined by the lift structure. In an example embodiment, the alulas may be slid or translated along at least a portion of the span of the lift structure.

A vehicle, such as a micro-aerial vehicle or underwater vehicle, includes at least one lift structure, such as a low-aspect-ratio wing or a fin, respectively. The at least one lift structure comprises one or more alulas. A leading surface of each alula is (a) flush with a leading surface of the lift structure or (b) offset from the leading edge of the lift surface by up to approximately 10% of the chord length of the lift structure. The length of each alula is no more than approximately 20% of a lift structure length corresponding to the lift structure. In various embodiments, the alula is deflected or canted with respect to a plane defined by the lift structure. In an example embodiment, the alulas may be slid or translated along at least a portion of the span of the lift structure.

A turbomachine includes a rotor and a stator, the stator having a plurality of profiled structures, each profiled structure being elongated in a direction of elongation in which the profiled structure has a length exposed to an airflow, and having a leading edge and/or a trailing edge, at least one of which is profiled and has, in said direction of elongation, serrations defined by a succession of peaks and troughs and having a geometric pattern transformed, over at least a part of said length exposed to the airflow, by successive scaling, via multiplicative factors, in the direction of elongation and/or transverse to the direction of elongation. The geometric pattern, as defined with reference to a radial distribution of the integral scale of the turbulence, evolves in a non-periodic manner.

Aspects relate to aircraft and methods of use for aerodynamic control with winglet surfaces. In an aspect an exemplary aircraft includes a first wing having a first winglet at a distal end of the wing, wherein the first winglet comprises at least a first control surface at a first trailing edge of the first winglet and a second wing having a second winglet at a distal end of the wing, wherein the second winglet comprises at least a second control surface at a second trailing edge of the second winglet.

An aircraft assembly is disclosed having a wing tip device connected to a wing tip of a wing by a first connector, a second connector, and a third connector. The wing tip device includes a front device spar and a rear device spar. The first connector is associated with the rear device spar. The second connector is spaced apart in a chordwise direction forward of the first connector, and the third connector is spaced apart in a chordwise direction rearward of the first connector. The third connector includes a spigot mounting formation.

An aircraft with a variety of control surfaces including but not limited to multiple winglet rudders. Each winglet can have multiple independently controlled rudders to improve the flight stability and maneuverability of the aircraft. Additionally, improved power supply systems can be implemented to allow for sustained flight.

An aircraft wing assembly including 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).

A system for creating thrust for flying machines with Vertical Take Off and Landing (VTOL) including a first propulsion unit, a second propulsion unit, a top winget, a bottom winget, two or more tracks running over said first and second propulsion units, and wherein the two or more tracks are configured to mount said top and bottom wingets.

A wing for an airplane has an outer wing end and an inner side of the wing for mounting to the airplane. The outer wing has at least two winglets connected to the wing, including an upstream winglet preceding a downstream winglet in a flight direction of the wing. The first winglet and the second winglet are mutually inclined, as seen against the flight direction, by a relative dihedral angle.

An aircraft is disclosed having a device and an aircraft wing. The aircraft wing includes a main wing element and a movable wing tip device attached to a tip end of the main wing element. The movable wing tip device includes an accumulator configured to store energy and the movable wing tip device can move relative to the main wing element to vary a span of the aircraft wing. The accumulator is configured to transmit power to the device. The accumulator enables energy to trickle between the main wing element and the movable wing tip device whilst still providing a suitable power source to the device. Additional embodiments include a method of maintenance, and a method of operating the aircraft wing to store energy in the movable wing tip device.