An aircraft can include a first wing and a second wing. The first wing can extend laterally from an aircraft body to a first tip, and the second wing can extend laterally from the aircraft body to a second tip. The aircraft can include a first end effector and a second end effector, each including a fore winglet and an aft winglet. The fore and aft winglets of the first end effector can be pivotably connected to the first tip. The fore and aft winglets of the second end effector can be pivotably connected to the second tip. The fore and aft winglets of the first and second end effectors can be independently operable. The first and second end effectors can be independently operable. A processor can be operatively connected to control movement of the fore and aft winglets of the first and second end effectors.

An aircraft flight surface deicing system includes an electromagnetic field generator and a deicing boot configured for attachment to an aircraft flight surface. The boot includes: one or more inflation regions including a first inflation region; one or more magnetic fluid reservoirs in fluid communication with the first inflation region, the one or more fluid reservoirs including a first fluid reservoir; a magnetic fluid contained in a combination of the first inflation regions and the one or more magnetic fluid reservoirs. In a first state, the magnetic fluid is contained in the first fluid reservoir and, in a deicing state, the electromagnetic field generator generates one or more fields that cause the magnetic fluid to exit the first fluid reservoir and travels along a length of the inflation region.

An aircraft can include a first wing and a second wing. The first wing can extend laterally from an aircraft body to a first tip, and the second wing can extend laterally from the aircraft body to a second tip. The aircraft can include a first end effector and a second end effector, each including a fore winglet and an aft winglet. The fore and aft winglets of the first end effector can be pivotably connected to the first tip. The fore and aft winglets of the second end effector can be pivotably connected to the second tip. The fore and aft winglets of the first and second end effectors can be independently operable. The first and second end effectors can be independently operable. A processor can be operatively connected to control movement of the fore and aft winglets of the first and second end effectors.

An airfoil surface skin, comprising a network of a solid material, embedded in a base of deformable solid material. Fluid pressure applied to the interface between the network and the surrounding embedding material, opens an internal network of channels by viscous peeling of the surrounding solid from the network. The network is offset from the centerline the surround material, such that pressure driven viscous flow through the narrow channels generates two types of deformation of the skin—an in-plane elongation and a curvature of the skin plane itself. The shape of the internal solid core element and its material, and the material of the encompassing solid are chosen to achieve a desired integral structural rigidity. The injected fluid pressure determines the extent of extension and bending. Use of this skin enables shape amending airfoils having reduced drag compared with similar airfoils having conventional flap mechanisms

A fluid control system includes a deformable surface that covers a body in at least a first and second direction. The first direction is orthogonal to the second direction. The deformable surface includes a bottom side that faces the body and a top side that is opposite the bottom side. The fluid control system also includes at least one deformer between the deformable surface and the body. The at least one deformer is configured to modify a boundary layer of a fluid that is flowing over the deformable surface by selectively deforming the top side of the surface.

A structure for a turbine, the structure comprising a body having a multi-layer construction including an interior layer with substantially uniform concentrations throughout of facultative anaerobic organisms (FAO) that have gene sets capable of producing the enzyme urease and/or the proteins purloin, lustre A and perlustrin, along with glucose, and non-uniform concentrations throughout of a structural composition, the structural composition including a chitin-based component with silk fibronectin and water; an exterior layer of urea, water, calcium ions and facultative anaerobic organisms (FAOs) including urease, aragonite; and a binding layer of conchiolin protein intermediate the interior layer and the exterior layer. The facultative anaeorobic organisms (FAOs) are organisms classified in one of the Saccharomyces, Escherichia and Bacillus genuses.

A morphing airfoil system includes an airfoil including a bulkhead and an airfoil body extending from the bulkhead, at least one inflatable/deflatable bladder positioned within the airfoil body, and a bladder pressurization mechanism configured for controlling pressurization of the at least one bladder. The system also includes one or more processors and a memory communicably coupled to the one or more processors and storing an airfoil control module including instructions that when executed by the processor(s) cause the processor(s) to control operation of the bladder pressurization mechanism to increase or decrease internal pressure in the at least one bladder to change a configuration of the airfoil.

A shock wave suppression device is configured to suppress a shock wave generated on a blade surface of a blade, the shock wave suppression device including a bump cover provided to follow the blade surface and deformable to protrude outward from the blade surface, and a displacing unit configured to displace the bump cover between a steady state to follow the blade surface and a deformed state to protrude outward from the blade surface. The bump cover has a curved shape in the deformed state configured to be a continuous surface from an upstream side to a downstream side in a flow direction of a fluid flowing through the blade surface.

A morphing airfoil system includes an airfoil having a bulkhead structured to form a leading edge of the airfoil. A first spool is rotatably coupled to the bulkhead, and a second spool is rotatably coupled to the bulkhead opposite the first spool. An airfoil skin has a first end secured to the first spool, a second end secured to the second spool, and a portion extending between the first and second spools to form an exterior surface of the airfoil. The airfoil skin is structured to be windable around the first and second spools such that a configuration of the airfoil is controllable by rotating at least one of the first spool and the second spool so as to wind a portion of the airfoil skin around, or unwind a portion of the airfoil skin from, the at least one of the first spool and the second spool.

A wing member (14b) for an air vehicle (10), said wing member comprising a core section (20) defining its longitudinal axis and having upper and lower surfaces, at least one of said surfaces comprising apparatus (22) selectively configurable between at least two positions, wherein in a fully extended position, at least portions of said apparatus extend outwardly from said respective surface so as to increase the effective cross-sectional area of said wing member and define an effective aerofoil in respect thereof.