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.

The invention relates to a device of a safety system and/or resource and energy-efficiency improvement system for influencing the flow around an aero- or hydrodynamic body, preferably an aerofoil, according to the principle of a back-flow flap, characterized in that: said device, together with the aero- or hydrodynamic body, in particular aerofoil, form at least a partial shift of the delimitation of the flap region by means of the back-flow flap and the delimiting component thereof when the back-flow flap is partially and/or completely raised, thus influencing the trailing edge separation vortex/vortices and/or the flap separation vortex/vortices; and in that the delimitation of the flap region shifts completely up to or beyond the profile trailing edge, or shifts only to a section in front of the profile trailing edge. The delimitation component is movably connected to the aerofoil by means of a basic element and is preferably permanently secured and/or releasably secured for maintenance purposes, thus ensuring a long service life for the rotor blade and/or wind turbine and/or flap system, preferably >5 years, particularly preferably >10 years, and most particularly preferably >=20 years, and/or thus optionally allowing simple removal/replacement.

The invention relates to a device of a safety system and/or resource and energy-efficiency improvement system for influencing the flow around an aero- or hydrodynamic body, preferably an aerofoil, according to the principle of a back-flow flap, characterized in that: said device, together with the aero- or hydrodynamic body, in particular aerofoil, form at least a partial shift of the delimitation of the flap region by means of the back-flow flap and the delimiting component thereof when the back-flow flap is partially and/or completely raised, thus influencing the trailing edge separation vortex/vortices and/or the flap separation vortex/vortices; and in that the delimitation of the flap region shifts completely up to or beyond the profile trailing edge, or shifts only to a section in front of the profile trailing edge. The delimitation component is movably connected to the aerofoil by means of a basic element and is preferably permanently secured and/or releasably secured for maintenance purposes, thus ensuring a long service life for the rotor blade and/or wind turbine and/or flap system, preferably >5 years, particularly preferably >10 years, and most particularly preferably >=20 years, and/or thus optionally allowing simple removal/replacement.

A method and apparatus for controlling movement of an aircraft. An aerodynamic function desired for controlling the movement of the aircraft at a particular altitude is identified. The aerodynamic function identified is part of a group of aerodynamic functions used to control the movement of the aircraft at a number of different altitudes. A group of inflatable blades is filled with a fluid to a pressure that corresponds to the aerodynamic function. The group of inflatable blades at the pressure has a shape and a group of dimensions that provide the aerodynamic function.

A structure adapted to traverse a fluid environment exerting an ambient fluid pressure is provided. The structure includes an elongate body extending from a root to a wingtip and encapsulating at least one interior volume containing an interior fluid exerting an interior fluid pressure that is different from the ambient fluid pressure. A method of retrofitting a structure adapted to traverse a fluid environment exerting an ambient fluid pressure, the structure comprising an elongate body extending from a root to a wingtip and having at least one interior volume is also provided. The method includes sealing the elongate body to encapsulate the at least one interior volume containing an interior fluid; associating at least one valve with the at least one interior volume; and modifying interior fluid content via the at least one valve to produce an interior fluid pressure that is different from the ambient fluid pressure.

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.

The present invention includes pilotable capsules, detachable from an aircraft and aircrafts including such capsules. According to some embodiments, there may be provided one or more capsules capable of flight and designed to detachably connect to an aircraft. According to some embodiments, detachable capsules may be designed to carry cargo and/or passengers. According to some embodiments, detachable capsules may, after detachment, be piloted by pilots or by automated systems (unmanned) or a combination of the two.

The present invention includes pilotable capsules, detachable from an aircraft and aircrafts including such capsules. According to some embodiments, there may be provided one or more capsules capable of flight and designed to detachably connect to an aircraft. According to some embodiments, detachable capsules may be designed to carry cargo and/or passengers. According to some embodiments, detachable capsules may, after detachment, be piloted by pilots or by automated systems (unmanned) or a combination of the two.

The present invention is a variable geometry lighter-than-air (LTA) aircraft that is adapted to morph its shape from a symmetric cross-section buoyant craft to an asymmetric lifting body and even to a symmetric zero lift configuration. The basic structure is a semi rigid airship with movable longerons. Movement of the longerons adjusts the camber of the upper and/or lower surfaces to achieve varying shapes of the lifting-body. This transformation changes both the lift and drag characteristics of the craft to alter the flight characteristics. The transformation may be accomplished while the craft is airborne and does not require any ground support equipment.