| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 21 | Low speed, high performance hang glider | US13986285 | 2013-04-19 | US20130299627A1 | 2013-11-14 | Richard Boone |
| Sail deflection, from large resultant moments, creates excess aerodynamic twist and limits hang glider performance. Incorporating a rear spar and sail attachment system, as a design feature, allows control and definition of this critical performance component. Hang gliders with this design feature will produce more total lift which in turn will produce lower stall speeds and less drag. | ||||||
| 22 | Truss beam having convex-curved rods, shear web panels, and self-aligning adapters | US12574493 | 2009-10-06 | US08375675B1 | 2013-02-19 | Ian M. Fernandez |
| A truss beam comprised of a plurality of joined convex-curved rods with self-aligning adapters (SAA) adhesively attached at each end of the truss beam is disclosed. Shear web panels are attached to adjacent pairs of rods, providing buckling resistance for the truss beam. The rods are disposed adjacent to each other, centered around a common longitudinal axis, and oriented so that adjacent rod ends converge to at least one virtual convergence point on the common longitudinal axis, with the rods' curvature designed to increase prevent buckling for the truss beam. Each SAA has longitudinal bores that provide self-aligning of the rods in the SAA, the self-aligning feature enabling creation of strong adhesive bonds between each SAA and the rods. In certain embodiments of the present invention, pultruded unidirectional carbon fiber rods are coupled with carbon fiber shear web panels and metal SAA(s), resulting in a lightweight, low-cost but strong truss beam that is highly resistant to buckling. | ||||||
| 23 | Light plane in the ultralight category and sport plane category | US10554309 | 2004-04-13 | US08210466B2 | 2012-07-03 | Hans Gygax |
| This light aeroplane at the same time fulfilled the weight limits for the European ultra light class or acolyte class as do at the same time for the US-American sport plan Category. It comprises an engine arranged at the nose and is provided with tractor airscrew and the cabin cell that is arranged behind the engine and is wide enough for two adjacent passenger seats. A central tube (1) with a 200 mm diameter extends forwards towards the engine and to the rear at least behind the front edge of the lateral rudder and elevator control. Everything else is constructed around said tube. A square profiled element (12) is transversally guided edgeways beneath the central tube (1) and is rigidly connected to the same in a positively engaged manner. An upwardly projecting tube bend (11), which arches over the length of the square profiled element is fixed to the rear side of the square profiled element (12) with the ends thereof. The level of a virtual plane cabin floor is defined above the square profile (12). The free space above said floor is orthorhombic: at least 190 cm long, at least 45 cm wide and at least 40 cm high. | ||||||
| 24 | Light Plane in the Ultralight Category and Sport Plane Category | US10554309 | 2004-04-13 | US20090014585A1 | 2009-01-15 | Hans Gygax |
| This light aeroplane at the same time fulfilled the weight limits for the European ultra light class or acolyte class as do at the same time for the US-American sport plan Category. It comprises an engine arranged at the nose and is provided with tractor airscrew and the cabin cell that is arranged behind the engine and is wide enough for two adjacent passenger seats. A central tube (1) with a 200 mm diameter extends forwards towards the engine and to the rear at least behind the front edge of the lateral rudder and elevator control. Everything else is constructed around said tube. A square profiled element (12) is transversally guided edgeways beneath the central tube (1) and is rigidly connected to the same in a positively engaged manner. An upwardly projecting tube bend (11), which arches over the length of the square profiled element is fixed to the rear side of the square profiled element (12) with the ends thereof. The level of a virtual plane cabin floor is defined above the square profile (12). The free space above said floor is orthorhombic: at least 190 cm long, at least 45 cm wide and at least 40 cm high. | ||||||
| 25 | SET OF CONJUGATED COMPONENTS TO BUILD A ULTRALIGHT TYPE AIRPLANE | US11531086 | 2006-09-12 | US20070272793A1 | 2007-11-29 | Fernando de Arruda Botelho |
| A The set of conjugated components to build a ultralight type airplane, in particular a constructive concept that has as end product a ultralight type airplane with a general configuration visually similar to the DEMOISELLE. In summary, the inventive concept has as purpose to enable that a handcrafted and ancient concept airplane is mass-produced, using modern resources, which characterizes by a better aerodynamical sustentation, in particular as a result of parts which are specially designed to carry out the known functions with extraordinarily improved results. In a general concept, without detailing the components in their specific constructions, we define the airplane obtained based on the conjugated components such as the fuselage (1); wings (2); empennages (3); landing gear (4); systems (5) which include the control (6) with rotular ends and fuel systems consisting of a metallic tank (7) fixed on the same level of the engine, with a vent, cover and a system cutting valve and propelling unit (8). | ||||||
| 26 | Inflatable airfoils, and elevated and propulsion driven vehicles | US10200456 | 2002-07-23 | US06659403B2 | 2003-12-09 | Chih-Yu Hsia |
| An aeronautical apparatus, the combination comprising a primary airfoil having at least one panel which is an upper panel, a lower panel, and multiple gas containing tubes associated with the airfoil and extending lengthwise thereof, the tubes including relatively larger cross-section tubes positioned chordwise of the airfoil, and relatively smaller cross-section positioners located to stabilize the relatively larger cross-section tubes. | ||||||
| 27 | Inflatable airfoils, and elevated and propulsion driven vehicles | US10035856 | 2002-01-04 | US20020084386A1 | 2002-07-04 | Chih-Yu Hsia |
| An aeronautical apparatus, the combination comprising a primary airfoil having at least one panel which is an upper panel, a lower panel, and multiple gas containing tubes associated with the airfoil and extending lengthwise thereof, the tubes including relatively larger cross-section tubes positioned chordwise of the airfoil, and relatively smaller cross-section positioners located to stabilize the relatively larger cross-section tubes. | ||||||
| 28 | Inflatable airfoils, and elevated and propulsion driven vehicles | US09617765 | 2000-07-17 | US06398160B1 | 2002-06-04 | Chih-Yu Hsia |
| An aeronautical apparatus, the combination comprising a primary airfoil having at least one panel which is an upper panel, a lower panel, and multiple gas containing tubes associated with the airfoil and extending lengthwise thereof, the tubes including relatively larger cross-section tubes positioned chordwise of the airfoil, and relatively smaller cross-section positioners located to stabilize the relatively larger cross-section tubes. | ||||||
| 29 | Oya computerized glider | US09089602 | 1998-06-02 | US06260795B1 | 2001-07-17 | Kenneth Earl Gay; Marc Margulies |
| The Oya glider is a modified hang-glider that incorporates many advanced aerospace technologies, such as, glues, for binding Shape Memory Alloy materials to Piezoelectric Ceramic Strips, and synthetic feathers. Lightweight composite plastic materials treated with the MuCell Process, both for framing and chassis construction. Piezoelectric Sensors and Actuators. Nano wires, and nano cables, for electrical connections and manual control levers. Computer firmware and software, designed to mimic, in real time, the aerodynamic flight reactions to external wind conditions, of a gliding bird. The Oya computerized glider will come as close as technologically possible to imitating a bird's mastery of the wind. | ||||||
| 30 | Fluid drag reducing apparatus | US333114 | 1994-11-01 | US5456199A | 1995-10-10 | Willem J. A. Kernkamp |
| A unique fluid drag reducing structure arranged such that the center of mass of the apparatus, when assembled, is positioned forward of the center of rotation of the apparatus when installed. Such an arrangement assures that the apparatus will be flutter free, while still allowing the apparatus to feather into the wind. The structure of and method for assembly provides for easy installation and removal of the apparatus on existing cylindrical structures without the need to disassemble the existing structure. | ||||||
| 31 | Flexible wing shape controlling device | US900193 | 1992-06-17 | US5275117A | 1994-01-04 | Jeffrey J. Magnan |
| A tensioner for drawing a point on a flexible wing's surface toward its leading edge. The wing's camber is thereby increased and maintained even at high airflow velocities and low angles of attack. The provision of a tensioner length adjustment system allows the wing's camber to be optimized for a particular set of conditions. The fitment of a plurality of such tensioners along the wing's chordlines and along its span allows the wing's shape to be fine-tuned both in terms of camber as well as twist. | ||||||
| 32 | Suspension flight control method and apparatus | US876048 | 1992-04-30 | US5217189A | 1993-06-08 | Merle T. Sandage |
| A flight control apparatus for use in an aircraft includes support structure for suspending a pilot beneath a pair of wings while permitting movement of the pilot relative to the aircraft in the forward, rearward and both lateral directions. A control system is connected between the support structure and the wings for altering the geometries of the wings during flight to vary the drag and lift characteristics of the wings and alter the direction of flight and the speed/performance range of the aircraft in response to movement of the pilot relative to the aircraft in any of the forward, rearward, and lateral directions. The geometries of the wings are altered during flight by moving the leading edges between extended and retracted positions relative to the central longitudinal axis of the aircraft in response to movement of the pilot in the forward, rearward and both lateral directions relative to the aircraft. | ||||||
| 33 | Vertical takeoff aircraft | US327298 | 1989-03-22 | US5054721A | 1991-10-08 | David L. Brenholt |
| A vertical takeoff ultralight aircraft having an operator controlled high volume vane axial fan in communication with a conduit configured to direct an air stream produced by the fan to a spanwise air duct disposed forwardly of a wing including an air foil. High velocity air is discharged from the air duct and directed over the upper surface of the air foil. An induced air stream flows upwardly and rearwardly through an air flow path defined by the spanwise air duct and the air foil. The wing and air duct are configured such that the induced air stream joins the air stream discharged from the air duct to create reduced static pressure zone on the upper surface of the wing of sufficient magnitude to effect vertical lift. Fan discharge may be partially deflected rearwardly to provide horizontal thrust. | ||||||
| 34 | Inflatable aerodynamic wing structure | US169032 | 1988-03-16 | US4858854A | 1989-08-22 | Barry J. Jacobson |
| An inflatable aerodynamic wing structure comprising an aerodynamic skin, a first inflatable member positioned inside the skin such that it extends longitudinally of the wing structure adjacent a leading edge portion of the wing structure, a second inflatable member positioned inside the skin such that it extends longitudinally of the wing structure adjacent a trailing edge portion of the wing structure, and an inflatable chamber positioned between the first and the second inflatable members, the wing structure being such that the first and the second inflatable members are adapted to be inflated to a higher pressure than the inflatable chamber so that, in use of the wing structure, the first and the second inflatable members provide longitudinal rigidity and the inflatable chamber forms the skin into the aerodynamic shape required by the wing structure, and the inflatable chamber being such that it is inflatable at least primarily by dynamic pressure. | ||||||
| 35 | Hand sail | US762037 | 1985-08-02 | US4651665A | 1987-03-24 | James R. Drake |
| A novel freely grasped hand-sail is described, which consists essentially of two profiled airfoil surfaces inclined towards each other at an angle between about 180.degree. and 120.degree., the leading edges of this hand-sail also forming an angle between about 180.degree. and 120.degree.. In one embodiment, the airfoil consists of sails kept rigid by aerodynamically preformed battens, which sails are stretched symmetrically between two masts and a middle boom. The freely grasped sail turns around its horizontal axis when set against the wind, and stabilizes itself at a certain turn, whereby the section that is more vertically directed yields forward thrust forces, to propel, for example, a sailboard, and the section that is more horizontal in this position mainly yields upward thrust forces to compensate the weight of the hand-sail and the rolling moment exerted on the sail. Wave-jumping while wind-surfing, in particular, can be made easier with the help of this hand-sail. | ||||||
| 36 | Ultra-light aircraft with freely rotating rigid wing | US588079 | 1984-03-09 | US4568043A | 1986-02-04 | Hugh J. Schmittle |
| An ultra-light aircraft of light-weight minimal construction includes a rigid wing from which a hang cage is suspended by a main hinge assembly. Rotation of the wing without pilot intervention induced by positive or negative wind gusts striking the wing causes the angle of pitch between the wing and hang cage to vary via the hinge so that the wing presents a relatively constant angle of attack to relative wind enabling the aircraft to be essentially stall free during flight. Twist and/or dihedral of the wing is maintained by first and second sets of tensioned cables or landing wires connecting leading and trailing wing edges to a kingpost projecting upward from the wing, and by first and second sets of flying wires connecting the wing to the hang cage. Each first and second set of flying wires is a stress distributing arrangement including a pair of tubes respectively connected at upper ends thereof to leading and trailing wing edges and at lower ends to a plate suspended between the wing and hang cage. A pair of tensioned cables in each set connect the plate to the hang cage. The point of attachment of the cables to the plate establishes a pivot point located collinear with the hinge axis. The tubes are free to rotate about the pivot point during co-rotation of the wing while maintaining proper dihedral and wing twist as well as tension transmitting bending stress acting on the wing to the hang cage. | ||||||
| 37 | Human powered hang glider | US342833 | 1982-01-26 | US4417707A | 1983-11-29 | Ken Leong |
| A human powered hang glider (10) has a fixed wing portion (12) and a pair of movable wing portions (14, 16). Flexible sheet material (26, 28) is connected to trailing edges (30, 32) of the movable wing portions (14, 16). A support structure (34, 36) for the flexible sheet material (26, 28) overlies each flexible sheet material (26, 28). Elastic bands (52) and wires (74, 76) are connected in opposing relationship to the movable wing portions (14, 16) to allow reciprocation of the movable wing portions (14, 16). When the flexible bands (52) cause upward movement of the movable wing portions (14, 16) the flexible sheet members (26, 28) move away from their associated support structures (34, 36), allowing air to pass through the support structures (34, 36). When pilot (70 pulls on wires (74, 76) to move the movable wing portions (14, 16) downward, the flexible sheet portions (26, 28) move against their associated support structures (34, 36) to provide increased lift from the movable wing portions (14, 16). In a typical flight, these movements are performed occasionally, and the hang glider is otherwise launched, flown and landed in a conventional manner. | ||||||
| 38 | Hang glider having inflatable airfoil | US807412 | 1977-06-17 | US4116406A | 1978-09-26 | Paul D. Hamilton |
| A high performance hang glider includes a frame to which is attached flexible sail fabric to create a delta-shaped Rogallo wing. The sail is of double thickness throughout a substantial portion of the wing area to provide an envelope inflatable in flight by air entering an intake opening at the nose of the wing and exhausting through nozzles in the underside of the wing tips. A more efficient double-surface airfoil is thus provided which automatically changes its camber in response to changes in speed for optimum performance. | ||||||
| 39 | Hang glider | US580440 | 1975-05-23 | US3995799A | 1976-12-07 | Frank J. Bartolini |
| A biwinged high performance collapsible hang glider having a simplified integrated frame, having a reinforcing cable system, having a variable camber upper swept wing including a sail, with non-rigid leading and trailing edges, and a flexible batten, having a bridge spacing the sail from the frame, having a lower undercambered sail wing including a sail with a tubular leading edge and nonrigid trailing edge, having an optional collapsible Y-tail modification including sail with non-rigid leading edge and hinged tubular-trailing edges, having a low wing-loading effect, a high lift-drag ratio, a high glide-ratio, a low sink-rate and minimal spiral instability, yielding the capability of effective body-english pilot control for short duration training flights or for long duration cross-country flights, and being collapsible so as to be readily transported by a common passenger vehicle. | ||||||
| 40 | Hang glider | US33789573 | 1973-03-05 | US3863868A | 1975-02-04 | OBERLE ROGER A |
| A hang glider which relies upon ground effect forces in order to dynamically support a person suspended therefrom.
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