| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 61 | Sail closure mechanism for cross bar access deployable wing | US09420260 | 1999-10-18 | US06283409B1 | 2001-09-04 | Dennis Van Dam |
| The openings in the fabric ribs of a deployable wing made from fabric sail material is automatically closed by use of a zipper mounted adjacent each of the openings that is actuated by movement of the cross spars of the deployable wing which serves to prevent the airfoil surface to the wing to bulge and cause a drag to the deployable wing when in flight. | ||||||
| 62 | Aircraft having inflatable tubular support structure | US642984 | 1996-05-06 | US5697579A | 1997-12-16 | Masahiko Hayashi |
| An airship has a flexible gas storage tube which forms a frame that maintains an inflated condition of an envelope of the airship permitting the envelope to be charged with hot air. A pump and valve are provided for supplying gas such as air, helium, and hydrogen to the gas storage tube. | ||||||
| 63 | Deployable wing | US156322 | 1993-11-23 | US5474257A | 1995-12-12 | Jeffrey A. Fisher; Edward V. Miller; Dennis Van Dam |
| The deployable wing of the present invention comprises an internal structure having diverging leading edge spars attached to a keel spar and cross spars to form a delta wing configuration. This internal structure is enclosed within a volume defined by a fabric sail having an upper section, a lower section, and fabric ribs disposed therebetween. This fabric sail volume is internally pressurized through a ram air intake at the nose stagnation point. This deployable wing can be folded and deployed in the air. | ||||||
| 64 | Ultralight helicopter and control system | US223175 | 1994-04-05 | US5370341A | 1994-12-06 | Ross Leon |
| An ultralight helicopter has a pair of counter-rotating rotor assemblies which in combination yield zero net angular momentum when rotating at equal speeds. A single motor drives both rotors through a counter-rotating bevel gear set coupled to a pair of concentrically nested output shafts. In an alternative embodiment, the motor is coupled to the rotors through a hydraulic drive system which includes a hydraulic pump and at least one hydraulic motor driving each of the rotor assemblies. The pilot is advantageously suspended in a "hang-glider" type harness from a single hang point positioned proximate the center of lift of the helicopter. A control bar is fixedly mounted to the frame and is grasped by the pilot suspended in the harness. The pilot maneuvers the helicopter in both the pitch and roll directions by manipulating the control bar. The pilot shifts his own center of gravity relative to the center of gravity of the helicopter while grasping the control bar to thereby maneuver the helicopter. | ||||||
| 65 | Weight-shift flight control transducer and computer controlled flight simulator, hang gliders and ultralight aircraft utilizing the same | US816650 | 1991-12-31 | US5252068A | 1993-10-12 | Bradley H. Gryder |
| The weight-shift movements of a suspended pilot are transformed into electrical signals representative of the movements. The signals may be used as the pitch and roll input information in an interactive computerized flight simulation system. The signals may also be generated by an actual pilot of a hang glider or ultralight aircraft and used on board to control ailerons, elevators, rudders, or the like, so as to enhance the performance potentials of these types of aircraft. | ||||||
| 66 | Laminar air-flow sail | US692272 | 1991-04-26 | US5123368A | 1992-06-23 | Duc H. Tran; David A. Reed, Jr. |
| Rows of closely spaced apertures are installed in a sail to control boundary layer air flow over a sail to laminar flow type by "bleeding" high energy air from the windward or concave side of the sail through the apertures to the convex or leeward side of the sail. The "bleed air" vents the windward boundary layer air through the apertures, gently lifts the leeward or convex side boundary layer off the sail surface; then new laminar boundary layers are formed, on each side of the sail, downwind of the aperture. The increase in air energy adjacent to the sail surface maintains desirable air flow velocity and pressure gradients on the sail that prevents flow separation. The apertures permit large camber of sail contour and high angles of attack without stalling. The air "bleeding" action continuously removes old boundary layer air and creates new laminar boundary air layers on the sail. The energy in the boundary layer air on both sides of the sail is increased which prevents thick, turbulent boundary layers of air from forming laminar air flow and provides high dynamic lift forces because less of the wind energy is wasted. | ||||||
| 67 | Off weight lift wing for skiers and the like | US557660 | 1990-07-25 | US5071089A | 1991-12-10 | Robert D. Fagan |
| An off weight lift wing for a skier and the like is provided and consists of a pair of airfoils each supported on an opposite end of a crossbar which extends across the top of a frame with a harness that secures the frame to the back of the skier. The lift wing will create a balanced lift to the upper body of the skier and allow more agile body movement when skiing, as well as extending the length of a ski jump. | ||||||
| 68 | Aerodynamic structural pipe for hang gliders | US287572 | 1988-12-16 | US4871132A | 1989-10-03 | Thomas Finsterwalder |
| The invention provides an aerodynamically profiled structural pipe (1) comprising a supporting pipe (2) and a rear tapered part (3) of soft material. The tapered part (3) has on both sides beads (15) forced into and captively held by rearwardly open chambers (12) of the supporting pipe (2). | ||||||
| 69 | Flying wing aircraft | US307861 | 1981-10-02 | US4781341A | 1988-11-01 | Witold A. Kasper |
| An ultralight aircraft having a generally rectangular, swept-back, single-surface wing. The wing, which is formed by fabric mounted on exposed spars and ribs, has a reflex profile to provide pitch stability which is further augmented by horizontal stabilizers projecting rearwardly from the wing adjacent the tips. Roll and yaw control are provided by a pair of rudders pivotally mounted at each wing tip. The forward ends of the rudders pivot inwardly to alter the magnitude of the wing's lift. The rudders pivoted simultaneously act as spoilers and speed brakes controlling the rate of descent. Pivoting one of the rudders individually moves the center of lift for one wing inwardly and increases the drag of that wing to roll the aircraft into that wing. The rudders tilt upwardly and outwardly in a dihedral configuration to provide roll stability. Stationary end plates mounted at each wing tip adjacent the rudders provide yaw stability. The aircraft utilizes a single surface wing so that it can descend safely at zero forward speed in a parachute-like manner. Pitch control is made by shifting the pilot's body forward and back. A chassis mounted beneath the wing supports a pilot and a gasoline engine driving a pusher propeller. | ||||||
| 70 | Aircraft with single surface membranous airfoils | US761983 | 1985-08-02 | US4667898A | 1987-05-26 | Samuel Greenhalgh |
| A remotely piloted vehicle is provided with single surface membranous airls controllable in flight. The airfoils are selectively deployed from a stowed position on either side within the fuselage by spars attached to the leading edges. Pivotal members attached to the root edges of the airfoils are positioned to regulate twist distribution, angle of attack, root camber ratio and root camber distribution. | ||||||
| 71 | Ultralight aircraft with freely rotating wing | US544261 | 1983-10-21 | US4596368A | 1986-06-24 | Hugh J. Schmittle |
| An ultralight aircraft of lightweight minimal construction includes a collapsible Rogallo type wing from which a hang cage is suspended by a main hinge assembly. The wing includes a longitudinal keel of lightweight tubular construction, leading edge members and a cross brace. A flexible lifting panel is secured along and between the wing members to define a lifting surface. The hinge includes a pitch hinge bracket having an upper longitudinal sleeve in which the keel is clamped. A ball joint connection secured to the bracket is connected to upwardly extending hang cage struts by means of hinge connecting plates to permit free rotation of the wing about a spanwise axis extending longitudinally through the cross brace. Rotation of the wing without pilot intervention induced by positive or negative wind gusts striking the flexible wing panel causes the angle of incidence between the wing and hang cage to vary so that the wing presents a relatively constant angle of attack to relative wind enabling the aircraft to be essentially stall free during flight. A cable and spreader tube arrangement interconnecting forward and trailing ends of the keel to the cross brace undergoes tension and compression loading to distribute bending stress acting on the keel during excessive wind loading to other parts of the aircraft. | ||||||
| 72 | Ultralight aircraft | US387487 | 1982-06-11 | US4548371A | 1985-10-22 | John M. Dempsey |
| Improved ultralight aircraft constructed with a tubular keel extending over the length of the aircraft from forward of its wing to the tail thereof. The aircraft includes a cantilever engine mount which is carried on a pair of mounting plates extending longitudinally from the forward end of the tubular keel. The propeller shaft, driven by the engine through a speed reduction arrangement, is supported in a bearing disposed on the engine mount. The aircraft includes a cage assembly for the operator's seat and has upright tubular rails and a pair of longitudinally extending side rails mounted on a shock absorbing landing gear. The landing gear has a nose wheel and a pair of laterally spaced rear wheels. The rear wheels are carried on the outer ends of a pair of longitudinally spaced, transversely extending tubular members. The forward of the tubular members is journaled for rotation on the underside of said side rails, and the rear member is releasably urged against the upper surface of the side rails by elastic bands or cords, which enable the rear member to move vertically relative to said side rails in response to landing impact. The aircraft is further constructed with full length ailerons, which are pivotably supported on the trailing edges on said wing. Each aileron is formed of a tubular frame disposed within a tapered fabric sheath which is in tension because of its tapered configuration and its dimensional relationship to the frame. The frame includes outer peripheral tubular portions and a plurality of parallel, laterally spaced cross tubes, each affixed at its outer end to the peripheral portion of the frame. | ||||||
| 73 | Lightweight aircraft | US203899 | 1980-11-04 | US4424946A | 1984-01-10 | Dale C. Kramer |
| An ultralight aircraft has a single stick three-axis aerodynamic control, twin engined power control, wing- and tail-mounted ailerons, an inverted V-tail and wide span wings with upturned tips. | ||||||
| 74 | Connecting apparatus for a powerplant | US252153 | 1981-04-08 | US4398684A | 1983-08-16 | Dennis Von Ruden |
| A connecting apparatus (16) for attaching a propeller or fan (14) to an engine (12) is disclosed. A connecting apparatus (16) includes a centrifugal clutch device (48) and drive and driven gears (40, 78) for reducing the speed of propeller (14) relative to engine (12). These elements are contained within a lubricant-filled housing comprised of housing (38) and spider bracket (34). Spider bracket (34) includes two pairs of vibration-dampening first and second mountings (140). First mountings (140) more stiffly resist engine vibration than second mountings (142), thereby dynamically balancing the powerplant with respect to the structural frame (20). | ||||||
| 75 | Compound wing aircraft | US081198 | 1979-10-02 | US4336913A | 1982-06-29 | Eric B. Hall |
| An aircraft, either rigid-wing or a collapsible hang-glider, is provided which is a bi-plane of apparent annular-wing construction in plan view, but the wing tips of an anhedral foreplane are separated from and above the wing tips of a dihedral aftplane. In a hang-glider construction the wing tips of the foreplane may be supported above the wing tips of the aftplane by struts, the trailing edges of the foreplane wing tips being supported by the struts above the leading edges of the aftplane wings. Also in the hang-glider, the geometry of the fore and aftplanes can be varied by moving their points of connection to the keel therealong. | ||||||
| 76 | Hang glider with collapsible airfoil | US728785 | 1976-10-01 | US4116407A | 1978-09-26 | Stephen C. Murray |
| A device capable of flight comprising a wing which includes a leading edge member. The leading edge member has an aerodynamically shaped exterior surface and upper and lower aft sections. The wing also includes upper and lower flexible membranes, a first connector for attaching the upper flexible membrane adjacent the forward region thereof to the upper aft section of the leading edge member and second connector for attaching the lower flexible membrane adjacent a forward region thereof to the lower aft section of the leading edge member. The flexible membranes are joined together rearwardly of the leading edge member. At least one of the connectors includes a track. A member carried by one of the flexible membranes is received in the track and cooperates therewith to attach such flexible membrane to the leading edge member. A support or other device is coupled to the wing for supporting a load. | ||||||
| 77 | Hang glider | US754572 | 1976-12-27 | US4050654A | 1977-09-27 | Ronald A. Heckman |
| A foot-launched passenger carrying wing capable of flight including a frame, a flexible wing covering the frame, a keel, a bracket slidable on the keel, cross brace members pivotally attached to the bracket at one end and to leading edge members of the frame at the other end, and cables connecting the parts to provide an operative structure when the bracket is moved in one direction to extend the frame into flying condition and to collapse the frame when the bracket is moved in the opposite direction. Movement of the bracket also adjusts the billow of the sail and the dihedral of the frame. The wing sail is attached to the leading edge members along their entire length and to the keel along a portion of the rearward end thereof. An arrangement is provided to adjust the bracket before or during flight to provide different billow and dihedral conditions. | ||||||
| 78 | Flying craft, particularly space craft | US34075564 | 1964-01-28 | US3269673A | 1966-08-30 | KURT REINIGER |
| 79 | MINIMIZING DRAG-INDUCED FORCES ON A WHEELED VEHICLE | US15788377 | 2017-10-19 | US20180037275A1 | 2018-02-08 | GARTH L. MAGEE |
| An aerodynamically optimized drag-reduction apparatus and method for optimal minimization of the drag-induced resistive forces upon a terrestrial vehicle, where the drag-induced resistive moments on wheel surfaces pivoting about the stationary point of ground contact are reduced, and the vehicle propulsive forces needed to countervail the resistive forces on the wheel are reduced. The drag reduction apparatus includes: a streamlined fairing or wind deflector positioned on a vehicle to shield the faster moving upper wheel surfaces from headwinds; an engine exhaust pipe disposed on a vehicle whereby exhaust gases deflect headwinds to shield the faster moving upper wheel surfaces of an automotive wheel; an automotive spoked wheel having streamlined oval-shaped wheel spokes; a wheel assembly with a streamlined tailfin rotatably attached to a wheel spoke; a wheel with a tapered spoke having a thin aerodynamic profile near the rim and tapering to a round profile toward the central hub; and a tire having streamlined tread blocks arranged in an aerodynamic pattern. | ||||||
| 80 | System for airboarding behind an aircraft | US14656648 | 2015-03-12 | US09637238B2 | 2017-05-02 | Aaron Wypyszynski |
| A system for airboarding and performing stunts behind an aircraft includes a lifting board, a handle, and a tow rope connected to the board and handle. The lifting board may include landing gear, a binding for securing an operator to the board, tail sections for stabilizing the board during flight, and ailerons for facilitating turns and rolls. The system may include a control system integrated into the handle and board that improves the operator's ability to control the board. | ||||||
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