The invention discloses a propeller-driven helicopter or airplane which comprises a fuselage and a propeller comprising a plurality of blades, wherein a plurality of pressure pipes are uniformly distributed between windward sides and leeward sides of the blades; a plurality of first inlets are formed in the windward sides and are communicated with outside via first channels in the blades and second outlets at tails of the blades; a high-pressure fluid of a low-speed fluid layer formed when a fluid flows through the leeward sides in a widthwise direction flows towards a low-pressure fluid of a high-speed fluid layer formed when the fluid flows through the first inlets, the first channels and the second outlets; and an upward pressure generated by the high-pressure fluid is opposite to a downward pressure generated by an external fluid above the windward sides, so that a fluid pressure above the propeller is decreased.

The invention discloses a propeller-driven helicopter or airplane which comprises a fuselage and a propeller comprising a plurality of blades, wherein a plurality of pressure pipes are uniformly distributed between windward sides and leeward sides of the blades; a plurality of first inlets are formed in the windward sides and are communicated with outside via first channels in the blades and second outlets at tails of the blades; a high-pressure fluid of a low-speed fluid layer formed when a fluid flows through the leeward sides in a widthwise direction flows towards a low-pressure fluid of a high-speed fluid layer formed when the fluid flows through the first inlets, the first channels and the second outlets; and an upward pressure generated by the high-pressure fluid is opposite to a downward pressure generated by an external fluid above the windward sides, so that a fluid pressure above the propeller is decreased.

A split-flap wing assembly having a wing with a flap frame, a flap having a lateral pivot axis, and one, two or more flap sweep members having a forward end attached at a hinge in a forward end of the flap frame of the wing, and a rearward end attached pivotally to a flap hinge of the flap along the lateral pivot axis. The flap sweep members are pivotable at the forward end from a neutral sweep position within the flap frame, to a deployment angle at which the rearward end of the flap sweep members are farther away from the wing's camber line, to form a slot between the flap frame and a forward edge of the flap that allows airflow from along the lower surface of the wing to flow through the slot and to the interior surface of the flap.

A split-flap wing assembly having a wing with a flap frame, a flap having a lateral pivot axis, and one, two or more flap sweep members having a forward end attached at a hinge in a forward end of the flap frame of the wing, and a rearward end attached pivotally to a flap hinge of the flap along the lateral pivot axis. The flap sweep members are pivotable at the forward end from a neutral sweep position within the flap frame, to a deployment angle at which the rearward end of the flap sweep members are farther away from the wing's camber line, to form a slot between the flap frame and a forward edge of the flap that allows airflow from along the lower surface of the wing to flow through the slot and to the interior surface of the flap.

A High Altitude Pseudo Satellite (HAPS) aircraft is disclosed, the aircraft including at least one aeroelastic span loaded fixed wing, an aspect ratio greater than 15 and wing loading less than 6 kg/m.sup.2, where the at least one wing has a plurality of spoilers distributed across the span of the wing and each spoiler being chordwise located adjacent the centre of pressure of the wing. The HAPS aircraft further includes a control system for controlling the spoilers, sensors which allow at least one of the quantity or quantities selected from the group comprising the amount of lift at points or regions along the wing span the pitch and roll at points or regions along the wing span, the bending and torsional strain at points or regions along the wing span, or the net speed and roll and pitch angle of the wing to be determined by the control system, and the spoiler being activatable to reduce the lift experienced by the wing in the location of the spoiler in response to the quantities determined by control system.

A High Altitude Pseudo Satellite (HAPS) aircraft is disclosed, the aircraft including at least one aeroelastic span loaded fixed wing, an aspect ratio greater than 15 and wing loading less than 6 kg/m.sup.2, where the at least one wing has a plurality of spoilers distributed across the span of the wing and each spoiler being chordwise located adjacent the centre of pressure of the wing. The HAPS aircraft further includes a control system for controlling the spoilers, sensors which allow at least one of the quantity or quantities selected from the group comprising the amount of lift at points or regions along the wing span the pitch and roll at points or regions along the wing span, the bending and torsional strain at points or regions along the wing span, or the net speed and roll and pitch angle of the wing to be determined by the control system, and the spoiler being activatable to reduce the lift experienced by the wing in the location of the spoiler in response to the quantities determined by control system.

A system and method for lift augmentation of an aircraft having a wing with a leading edge and a trailing edge extending along a wingspan, a plurality of thrust-producing devices connected to the bottom of said wing, at least one flap connected to an inboard portion of said wing proximate the trailing edge, and an aircraft roll control device connected to said wing, wherein the improvement comprises a plurality of slipstreams associated with a plurality of thrust producing devices and a flap adaptable to deflect from a chord of the inboard portion of the wing.

A system and method for lift augmentation of an aircraft having a wing with a leading edge and a trailing edge extending along a wingspan, a plurality of thrust-producing devices connected to the bottom of said wing, at least one flap connected to an inboard portion of said wing proximate the trailing edge, and an aircraft roll control device connected to said wing, wherein the improvement comprises a plurality of slipstreams associated with a plurality of thrust producing devices and a flap adaptable to deflect from a chord of the inboard portion of the wing.

A wingless vertical take-off and landing (VTOL) vehicle has a main body including airfoil sections on either side of a central module in which a load may be carried. Articulated forward thrust systems are mounted on a leading edge of the main body and lateral members are located on either side of the main body and form winglets. At least one rear vertical-thrust system may also be provided and, in one embodiment, is mounted in an aperture aft of the central module. The forward thrust systems transition between a vertical flight configuration and a horizontal flight configuration. The lateral members are configured as both vortex-damping members and also to channel backwash from the forward thrust systems over the airfoil formed by the main body.

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).