Abstract: A configurable aerial vehicle aerosurface is disclosed, The configurable aerial vehicle aerosurface includes first and second airfoil surfaces in sliding engagement. A plurality of apertures pass transversely through the airfoil surfaces and are disposed in such a relationship so as to define a first position wherein the apertures are in substantial alignment and a second position wherein the apertures are in substantial non-alignment. In this way, the configurable aerial vehicle aerosurface of the present invention can be configured from a first, low drag transport position, to a second, aerodynamic position to provide missile lift and control.

Abstract: Improved methods and techniques for fabricating a panel of control cells, or a “control panel”, useful in various electromagnetic turbulence control (EMTC) applications includes a layered structure which includes three main components or layers: a metal substrate or backing plate having a high magnetic permeability; a ribbed magnetic structure attached to the metal substrate; and an electrode board bonded to the ribs of the magnetic structure. The ribbed magnetic structure is realized, in one embodiment, by a series of rare earth permanent magnets placed side-by-side using a bowed tool to create permanent magnet columns. The magnet columns thus formed are precisely positioned and glued to the substrate or backing plate so as to form parallel magnetic ribs. An electrode board, similar to a printed circuit board, is then bonded to the ribs of the magnet columns, e.g., so that a back side of such electrode board rests on top of the magnetic columns or ribs.

Abstract: An adaptive pneumatic wing for a fixed wing aircraft having an airtight envelope (8) defined by a top skin (1) and a bottom skin (2) subdivided internally by a plurality of cells extending longitudinally of the wing, portions of the cells being airtight forming wing structure adapted to provide an aileron function, a landing flap function, and to change the shape of the wing profile.

Abstract: An airplane has a plurality of airfoils with leading edges. A partition and a nose cap are located at a forward surface of the airfoil, creating upper and lower cavities. The nose cap may be positioned in an extended position or a retracted position. The nose cap is retracted when the airplane reaches supersonic speed. At supersonic speed, a shock wave forms on the leading edge of the airfoil. A compression zone forms between the shock wave and the leading edge, diverting the heat and pressure of the shock wave away from the airfoil. Downstream from the compressed zone, pressure wakes form along the airfoil and cool the airfoil. At subsonic speed, the nose cap is extended to achieve optimal airfoil efficiency. Forward or rearward gaps may be opened between the nose cap and the main body portion of the airfoil to allow airflow from the lower cavity below the partition to the upper cavity above the partition to selectively increase or decrease lift on the airfoil.

Abstract: In accordance with the present invention, there is provided a variable camber delta-shaped aircraft. The aircraft is provided with an integrated fuselage/wing generally defining the aircraft and having longitudinal and lateral axes. The fuselage/wing has a forward section which is rotably attached to an aft section about the lateral axis. The aircraft is further provided with an aerodynamic lifting surface which is disposed about the fuselage/wing and defined by a camber. The forward section has a downwardly deflected position when rotated relative to the aft section. The forward and aft sections are cooperatively formed to increase the camber of the lifting surface when the forward section is in the deflected position.

Abstract: An active control method and apparatus for encouraging the early destruction of trailing vortices formed by a lifting body having at least two control surfaces on each side and creating multiple vortex pairs is provided. The method includes actuating the control surfaces in a manner leading to the direct excitation of one or more of the Transient Growth Mechanism, the Short Wavelength Instability, the Long Wavelength Instability, and the Crow Instability to result in the accelerated breakup of the trailing vortices.

Abstract: A lifting airfoil (10) includes a landing flap (20) movably connected to a main airfoil body (10') so as to form at least a portion of the trailing edge of the airfoil. The landing flap (20) includes a leading edge nose (21) and a trailing edge body (22), which are each bounded by an upper cover skin (23) and a lower cover skin (24). The trailing edge body (22) is connected to the leading edge (21) by the continuous upper cover skin (23), while a gap (25) interrupts the lower cover skin (24) between the leading edge nose (21) and the trailing edge body (22). The flap (20) is mounted on a carriage (31) that moves along a guide rail (30) so as to be slidably and pivotably extendable during take-off and landing phases of a flight.

Abstract: Magnetic and electric fields are used in a controlled manner to create equal and oppositely-directed Lorentz forces tangential to the surface of a control tile that affect the flow of a conductive fluid near the boundary layer of the control tile, or a matrix of control tiles, immersed in a conductive fluid. The control tiles are combined to form control cells, with each control cell including a pair of electrodes and at least one permanent magnet. The pair of electrodes are coupled to a current source which biases the electrodes to cause an electrical current to flow from a positive electrode (anode), through the conductive fluid in which the cell electrodes are immersed, to a negative electrode (cathode). The current source may be time multiplexed to better control the direction of the current flow between adjacent electrodes.

Abstract: A vane-airfoil combination for shifting forces associated with an airfoil. The vane-airfoil combination includes an airfoil moving through a fluid, such as air. A plurality of vanes is positioned in front of the airfoil to divert the path of the fluid to the airfoil. The change in the path of the fluid rotates the forces associated with the airfoil in relation to the original path of the fluid. Specifically, a lift force is rotated to provide a thrust component force, as well as a lift component force. In addition, a drag force is rotated to provide a lift component force, as well as a reduced drag component force. The airfoil may be any type of airfoil, such as a rotating cylinder. The vane-airfoil combination may also include a fore-body and an after-body for reducing the pressure along an upper portion of the airfoil.

Abstract: This invention relates to a system and method for reducing the primary vortex wake structure generated by a lifting body mounted on an object moving through a fluid. This is achieved by first, altering the generated initial vortex wake to make it vulnerable to rapid breakup; and, second, producing disturbances to this wake with secondary vortices from auxiliary lifting surfaces, called vortex leveraging tabs, to instigate this breakup. This invention relates to various fields of uses to include vortices generated by any type of lifting body moving through a fluid to include aircraft and watercraft, such as surface vessels and submarines.

Abstract: A method and apparatus for measuring the lift generated by airfoils of an aircraft. This real-time analysis is accomplished by measuring a differential pressure between the upper and lower lift surfaces of the airfoils. The system comprises the steps of: a) measuring an actual differential pressure between the upper and lower lift surfaces for a given aircraft speed, b) transmitting this actual differential pressure measurement to a computer, c) comparing the actual differential pressure measurement with an optimal pressure differential for the same aircraft speed. The apparatus comprises a fixed array of differential pressure sensor mechanisms for measuring actual pressure differentials and a computer for comparing optimal differential pressure measurements to the actual differential pressure measurements. Each sensor mechanism preferably contains a piezoelectric sensor that communicates with the upper and lower lift surfaces.

Abstract: A lift enhancing device for a solid wing is disclosed wherein a where a mr driven, flap dynamically oscillating flap mechanism produces an increase in the lifting capabilities of the wing.

Abstract: A passive porosity airfoil lift management device employed on a leading edge region of said airfoil whereby the lift on said airfoil may be varied and controlled by passively transferring air pressure between the upper surface and lower surfaces of said leading edge region of the airfoil through upper and lower porous skin regions, upper and lower plenum cavities disposed in said airfoil, and controllably monitoring and regulating said passive air pressure transference with at least one valve and a microprocessor.

Abstract: An apparatus, and its accompanying method, for reducing the drag of flows over a surface includes arrays of small disks and sensors. The arrays are embedded in the surface and may extend above, or be depressed below, the surface, provided they remain hydraulically smooth either when operating or when inactive. The disks are arranged in arrays of various shapes, and spaced according to the cruising speed of the vehicle on which the arrays are installed. For drag reduction at speeds of the order of 30 meters/second, preferred embodiments include disks that are 0.2 millimeter in diameter and spaced 0.4 millimeter apart. For drag reduction at speeds of the order of 300 meters/second, preferred embodiments include disks that are 0.045 millimeter in diameter and spaced 0.09 millimeter apart. Smaller and larger dimensions for diameter and spacing are also possible. The disks rotate in the plane of the surface, with their rotation axis substantially perpendicular to the surface.

Abstract: An apparatus for measuring the lift generated by airfoils of an aircraft. This real-time analysis is accomplished by measuring a differential pressure between the upper and lower lift surfaces of the airfoils. The apparatus a) measures an actual differential pressure between the upper and lower lift surfaces for a given aircraft speed, b) transmits this actual differential pressure measurement to a computer, c) compares the actual differential pressure measurement with an optimal pressure differential for the same aircraft speed, and d) evaluates performance of the aircraft based on the result of the comparison. The apparatus comprises a fixed array of differential pressure sensor mechanisms for measuring actual pressure differentials and a computer for comparing optimal differential pressure measurements to the actual differential pressure measurements. Each sensor mechanism preferably contains a piezoelectric sensor that communicates with the upper and lower lift surfaces.

Abstract: A pliant, controllable contour control surface comprising a first flexible facesheet formed to a first initial contour of the control surface, and a second flexible facesheet formed to a second initial contour of the control surface. The first and second facesheets each have a set of prestrained shape memory alloy tendons embedded therein, extending from a leading edge to a trailing edge of the control surface. Each set of the shape memory alloy tendons is separately connected to a controlled source of electrical current such that tendons of the first and second flexible facesheets can be selectively heated in an antagonistic, slack-free relationship, to bring about a desired modification of the configuration of the control surface. A computer based control system is utilized for maintaining a constant temperature of the antagonists to establish conditions conducive to the stress induced transformation from austenite to martensite, accomplished by causing constant current to flow through the antagonists.

Abstract: A low turbulence cambered surface foil, hydrofoil or airfoil, which contains indentations located on maximum camber across which a fluid can be flowed. The indentations create turbulence in the boundary layer downstream of the indentations, changing the characteristics of the flowing fluid to a turbulent boundary layer ahead of the normal point of separation of the fluid from the foil, this causing the fluid to cling close to the surface of the foil and postpone or delay trailing edge separation of the fluid stream from the foil. The noise level is reduced, the performance and efficiency of the foil is improved, or both the noise level is reduced and the performance and efficiency of the foil is improved.

Abstract: A method and apparatus for measuring the lift generated by airfoils of an aircraft. This real-time analysis is accomplished by measuring a differential pressure between the upper and lower lift surfaces of the airfoils. The system comprises the steps of: a) measuring an actual differential pressure between the upper and lower lift surfaces for a given aircraft speed, b) transmitting this actual differential pressure measurement to a computer, c) comparing the actual differential pressure measurement with an optimal pressure differential for the same aircraft speed. The apparatus comprises a fixed array of differential pressure sensor mechanisms for measuring actual pressure differentials and a computer for comparing optimal differential pressure measurements to the actual differential pressure measurements. Each sensor mechanism preferably contains a piezoelectric sensor that communicates with the upper and lower lift surfaces.

Abstract: Aerodynamic boundary layer control apparatus comprising a panel assembly having one surface for immersion in an ambient fluid flow and provided with perforations, a first array of fluid transporting channels fluidly coupled with various ones of the perforations, a second array of fluid transporting channels overlapping the first array of channels, and a suction-generating apparatus fluidly coupled with the second array of channels. An opposing surface of the panel assembly has a contour congruent with that of the aircraft wing or body structure to which it is to be removably attached. The suction-generating apparatus applies a suction force to the second array of channels to draw the ambient fluid into the first array of channels to enable conformace of the fluid with the one surface.

Abstract: Controlling turbulence in a medium caused by injection of energy into the medium at relatively large scale with consequent dissipation of energy at relatively small scale, is achieved by introducing into the medium a broad spectrum stochastic external disturbance.

Abstract: An articulated wing has a fore wing portion and after wing portion connected to an articulate axis support structure which extends along the length of the wing and separates the two wing portions. Control actuators separately connect the fore and after wing portions to the articulate wing support structure in order to provide separate angular positioning capabilities for the two wing portions. Further, the articulate wing support structure itself may be rotated with respect to the mechanism it is attached to. These and other flexible controls over the wing attitude and size allow the wing to provide a number of force vector amplitudes as well as directions for any given fluid flow direction and velocity.

Abstract: A high speed aircraft fitted with a unitary, rotatable wing coupled to the craft's fuselage at a hollow turret or solid pivot pin, enabling it to operate with the wing in either of two ninety degree opposed positions.

Abstract: A fixed wing aircraft that can be converted to an automotive vehicle, comprising a generally rectangular planform fuselage having four wheels as in conventional automobile practice, and a telescopic wing which retracts into a housing in the roof of the fuselage. Telescopic horizontal and vertical stabilizers are provided at the rear end of the fuselage, as well as a retractable pusher propeller that is driven by an engine mounted on the front end of the fuselage. Both the propeller and the rear wheels are connected by a transmission box to the engine, so that either can be driven to operate the vehicle as an aircraft or as an automobile. On take-off, the rear wheels are partially retracted so as to place the aircraft at a proper angle of attack at the same time that the elevators are raised by pulling back on the control wheel. The control wheel is also connected to both the front wheels and the ailerons, and when turned 90.degree.

Abstract: A rotary geared actuator for pivotally connecting a flap to a wing of an aircraft, includes at least two adjacent actuator slices rotatably coupled together, each actuator slice including a sun gear rotatably coupled to a drive shaft and having gear teeth with a curved profile to enable movement of the actuator slices with respect to each other in conformance with bending of the wing, planetary gears in surrounding and meshing engagement with the gear teeth of the sun gear, a movable ring gear in surrounding and meshing engagement with the planetary gears, and a fixed ring gear in surrounding and meshing engagement with the planetary gears on opposite sides of the movable ring gear, each fixed ring gear being in meshing engagement only with planetary gears of one actuator slice; at least one fixed side tie bar connecting each fixed ring gear with the wing; at least one movable flap side tie bar connecting each movable ring gear with the flap; securing pins for securing each fixed side tie bar to one fixed rin

Abstract: An airfoil having improved aerodynamic characteristics has a leading edge and a trailing edge longitudinally spaced therefrom. A continuous lower surface of the air foil forms a lower camber extending from the leading edge to the trailing edge. The upper surface of the air foil has a first fixed upper surface extending rearwardly from the leading edge and terminating in an offset and a second upper surface extends rearwardly therefrom and is movable from a first position defining a first upper camber portion of the airfoil to a second position defining a second upper camber portion thereof.

Abstract: The present variable airfoil assembly has a fixed airfoil member with a shallow recess in the top in which an adjustable airfoil member is seated snugly, when lowered, to present a convex top surface which merges smoothly with the top surface on the fixed airfoil member in front and behind. When the adjustable airfoil member is raised, the fixed airfoil member presents a top surface below it which is continuous for most of its extent to minimize air turbulence. Reinforcing ribs on the adjustable airfoil member extend down through longitudinal gaps in the top of the fixed airfoil member and are coupled to cylinder-and-piston units for raising and lowering the adjustable airfoil member. A transverse gap extending across the top of the nose of the fixed airfoil member passes adjustable filler pieces which can extend up between the nose and the front edge of the adjustable airfoil member when the latter is raised or be retracted down to permit air to flow under the adjustable airfoil member for braking purposes.

Abstract: A device for enhancing the lift capability of an aircraft wing is characterized by at least one forwardly projecting finger member mounted on the leading edge of the wing. The finger generates counter-rotating vortices, each in contact with the other, trailing backwardly across substantially the entire upper surface of the wing behind the fingers as the airflow moves upwardly and around the lateral edges of the finger. As the counter-rotating vortices trail backwardly over the upper surface of the wing, a blockage effect is created and the airflow patterns across the wing are modified to produce an increase in lift.

Abstract: Apparatus for monitoring the operational status of the air delivery and momentum injection subsystems of a Boundary Layer Control (BLC) system of an aircraft, by sensing an air flow parameter in the supply duct supplying air to the BLC manifold is disclosed. The air flow parameter is sensed as a ratio of two discreet pressures [stagnation/static (P.sub.T /P.sub.S) or static/static (P.sub.S1 /P.sub.S2)]. When the ratio falls outside of a predetermined range, an indication that the air delivery and momentum injection subsystem has failed is provided. The failure may be due to either a rupture or a blockage of the air delivery and momentum injection subsystem. A combined BLC status indication is provided by combining the signal related to the sensed air flow parameter with signals related to the correctness of the position of the valves controlling the bleed air flowing to the air delivery momentum and injection subsystem and the position of the high lift surfaces (e.g., flaps) of the aircraft.

Abstract: An expandable fuel storage tank for aircraft has a resilient exterior wall panel in the form of a leaf spring anchored at both ends to a surface region of the aircraft, one anchorage being in the form of a simple hinge and the other incorporating a translatory device so that when the wall panel becomes bowed outwards due to the fuel storage tank being filled with fuel the ends of the panel can move relatively toward one another. The panel is formed as a spring such that when fuel is removed from the fuel storage tank, the panel tends to flatten to resume a position in general continuity with the surface region of the aircraft.