| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 81 | Streamlined tailfin for bicycle wheel spoke | US14727828 | 2015-06-01 | US09290041B2 | 2016-03-22 | Garth L Magee |
| A streamlined tailfin rotatably attached to a bicycle wheel spoke reduces drag by swiveling as a wind vane in both headwinds and crosswinds. | ||||||
| 82 | Partially-inflated rigid-structure glider | US13925797 | 2013-06-24 | US09162761B2 | 2015-10-20 | Christopher Paul Farbolin |
| A partially-inflated rigid-structure glider is a portable or collapsible gliding apparatus that a user can transport in a carrying case. The gliding apparatus includes a rigid yet collapsible frame, tension membranes over both on the wings and tail, and inflatable bladder, a pair of drogue brakes, and a left and right steering mechanism. The pair of drogue brakes is located on opposing sides of the gliding apparatus and create drag on its respective side in order to turn the gliding apparatus either left or right. The user can activate either drogue brake with the left and right steering mechanism, which are control lines attached to each drogue brake. The tension membranes are fitted over the frame so that the gliding apparatus has an airfoil shape in order to create lift with the wings and tail while the gliding apparatus is in flight. | ||||||
| 83 | System for Airboarding Behind an Aircraft | US14656648 | 2015-03-12 | US20150266573A1 | 2015-09-24 | 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. | ||||||
| 84 | AERODYNAMIC TIRE TREAD | US14727832 | 2015-06-01 | US20150258859A1 | 2015-09-17 | Garth L. Magee |
| A tire having streamlined tread blocks arranged in an aerodynamic pattern for reduced drag on forward-facing critical vehicle-drag-inducing upper wheel surfaces. | ||||||
| 85 | APPARATUS AND METHOD FOR PARAGLIDERS | US13719108 | 2012-12-18 | US20130161451A1 | 2013-06-27 | Adam Edward Alexander Contoret |
| Apparatus and method for propelling a user wearing paragliding equipment are disclosed The apparatus includes at least one thruster for providing thrust in a predetermined direction; and an attachment element for attaching the at least one thruster to a user's body such that the thruster is secured against the front portion of the user's body. | ||||||
| 86 | Sail wing with high span efficiency and controlled pitching moment | US12138900 | 2008-06-13 | US08348198B2 | 2013-01-08 | Robert Parks |
| An aircraft comprising a fuselage, a sail wing appended to the fuselage, the sail wing having a sail wing root chord length, and wherein the sail wing includes a sail wing leading edge spar, a sail wing membrane attached to the sail wing leading edge spar, and a sail wing trailing edge wire located at a trailing edge of the sail wing membrane, the aircraft further comprising a wing surface extension, located aft and at an inboard area of the sail wing trailing edge wire, the wing surface extension having a wing surface extension root chord length, and wherein the wing surface extension includes a wing surface extension membrane attached to the sail wing trailing edge wire, and a wing surface extension trailing edge, and wherein the wing surface extension trailing edge is reflexed such that the wing surface extension trailing edge is positioned upwards at a first angle with respect to a plane formed along a centerline of the aircraft and along the lower surfaces of the sail wing. The wing surface extension is further configured to affect a reduced nose-up pitching moment, and to produce a more even coefficient of lift along the wing of the aircraft. | ||||||
| 87 | Ultralight coaxial rotor aircraft | US11712838 | 2007-02-28 | US20070262197A1 | 2007-11-15 | Arthur Phelps; Dwaine Barnes; Elwood Norris; Eugene Rock; Emitt Wallace |
| An ultralight coaxial dual rotor helicopter having a substantially L shaped frame. Attached to the back of the frame is a vertical shaft engine, and a pair of yaw paddles for controlling yaw of the craft. The drive shaft connects to a belt drive at the top of the frame, which transmits the engine power to a transmission and coaxial drive gear for driving the rotors. Crank actuators are provided for tilting the rotor axis to control the pitch and roll of the craft. A pilot seat and ballast tank are attached to the front of the frame. The ballast tank may be filled with a volume of water to balance the craft for the weight of the pilot. The fuel tank is located behind the pilot seat on the centerline of the helicopter, such that as fuel is used and the weight of fuel in the tank changes, the balance of the craft will not be affected. | ||||||
| 88 | Seat for aircraft and land vehicles, particularly for light aircraft | US09771368 | 2001-01-26 | US20040169405A1 | 2004-09-02 | Derek Stinnes |
| A seat for aircraft and land vehicles that is light, adjustable and dimensionally stable and has good damping properties. The seat comprises a seat shell having at least one guide integrated into the seat surface for holding an aid frame. A base frame comprising compression and tension members is attached to the base of the vehicle and has an additional lateral member which is located forward and at the front. The aid frame is formed from two longitudinal members and at least one lateral member, where the front ends of the longitudinal members are rotatably attached to the additional lateral member of the base frame. | ||||||
| 89 | Rotor craft | US10423831 | 2003-04-25 | US20040007644A1 | 2004-01-15 | Arthur E. Phelps III; Elwood G. Norris; Eugene F. Rock; Emitt Wallace |
| An ultralight coaxial dual rotor helicopter having a substantially L shaped frame. Attached to the back of the frame is a vertical shaft engine, and a pair of yaw paddles for controlling yaw of the craft. The drive shaft connects to a belt drive at the top of the frame, which transmits the engine power to a transmission and coaxial drive gear for driving the rotors. Crank actuators are provided for tilting the rotor axis to control the pitch and roll of the craft. A pilot seat and ballast tank are attached to the front of the frame. The ballast tank may be filled with a volume of water to balance the craft for the weight of the pilot. The fuel tank is located behind the pilot seat on the centerline of the helicopter, such that as fuel is used and the w eight of fuel in the tank changes, the balance of the craft will not be affected. A simplified electronic control system controls all functions of the helicopter in response to pilot input. | ||||||
| 90 | Inflatable airfoils, and elevated and propulsion driven vehicles | US10200456 | 2002-07-23 | US20030127567A1 | 2003-07-10 | 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. | ||||||
| 91 | Ultralight coaxial rotor aircraft | US10077169 | 2002-02-14 | US20020125368A1 | 2002-09-12 | Arthur E. Phelps III; Dwaine R. Barnes; Elwood G. Norris; Eugene F. Rock; Emitt Wallace |
| An ultralight coaxial dual rotor helicopter having a substantially L shaped frame. Attached to the back of the frame is a vertical shaft engine, and a pair of yaw paddles for controlling yaw of the craft. The drive shaft connects to a belt drive at the top of the frame, which transmits the engine power to a transmission and coaxial drive gear for driving the rotors. Crank actuators are provided for tilting the rotor axis to control the pitch and roll of the craft. A pilot seat and ballast tank are attached to the front of the frame. The ballast tank may be filled with a volume of water to balance the craft for the weight of the pilot. The fuel tank is located behind the pilot seat on the centerline of the helicopter, such that as fuel is used and the weight of fuel in the tank changes, the balance of the craft will not be affected. A simplified electronic control system controls all functions of the helicopter in response to pilot input. | ||||||
| 92 | Camber inducer for wing-sail | US667860 | 1996-06-21 | US5799601A | 1998-09-01 | Michael B. Peay |
| A camber inducer for use with a double surfaced wing sail on various sail-driven craft such as sailboats, sailboards, ice boats, land sailors, hang gliders and the like. The camber inducer, in cooperation with battens and the first and second surfaces of a double surfaced sail, provides an efficient and easy to use airfoil sail. | ||||||
| 93 | Airfoil configuration | US264154 | 1988-11-11 | US4927100A | 1990-05-22 | Eugene F. Provenzo, Jr.; Peter A. Zorn |
| An airfoil having two (2) basic components, a sail and spoiler, associated with the leading edge of the sail, is herein disclosed. This unique airfoil design has application in flexible wing aircraft (i.e., ultralites), sport parachutes and sport kites. In the typical sport kite embodiment of this invention, there will generally be at least three (3) aerodynamic flight control surfaces: a sail, a keel, and a flexible resilient spoiler attached to the leading edge of the sail. The sail material is itself resilient, however, sufficiently rigid to maintain a preset configuration without the need for struts, spars or extrinsic physical support. A spoiler, which is located along the entire leading edge of the sail, provides additional structural reinforcement to the sail while undergoing controlled deformation in gusty or high winds. The effect of such deformation of the spoiler causes the sail to stall before any physical damage can occur. The resiliency of the spoiler immediately, thereafter, returns the sail to pre-stall configuration, and flight is thereupon resumed without physical damage to the kite. Under certain conditions, it may be desirable to further enhance the inherent physical strength of the sail along the centerline of the sail coincident with the area of the stress imparted upon the sail by the keel. This is readily accomplished by affixing an additional section of sail construction material, or its equivalent, along the topside surface of the sail, opposite to and coincident with the placement of the keel. | ||||||
| 94 | Tandem seat for ultra light aircraft | US542403 | 1983-10-17 | US4600170A | 1986-07-15 | Terry L. Smith |
| A tandem seat assembly for ultra light aircraft is disclosed which is interchangeable with a single seat configuration. The assembly, which is primarily used for pilot training, is fitted with dual aircraft controls. The single seat must be removable from an ultra light aircraft in order for the tandem seat assembly as described by this invention to be utilized. The tandem seat assembly is thereby placed in the aircraft such that the center of gravity of the seat assembly is near the nominal center of gravity of the aircraft. Universal attachments of the seat assembly to the aircraft frame allow the seat assembly to be used with a number of different manufacturers of ultra light aircraft models. | ||||||
| 95 | Pilot module | US587158 | 1984-03-07 | US4579301A | 1986-04-01 | Rolf Brand |
| A pilot module for a lightweight aircraft having a fuselage primary structure that includes a longitudinally disposed support structure, or boom and also having a wing structure attached to the fuselage primary structure, a tail structure attached aft of the wing structure to the fuselage primary structure, and a propeller assembly attached to the fuselage primary structure. The pilot module includes a pilot support shell constructed of a composite material formed to support the seat, legs, and back of a pilot positioned on it and forming an integral part of the fuselage primary structure. The pilot support shell is positioned at least partially forward of the forward end of the boom. At least one reinforcing member is connected to the pilot support shell and to the boom and is constructed in a single piece with the support shell. The reinforcing member also forms an integral part of the fuselage primary structure. An external fairing is positioned behind and attached to the pilot support shell. | ||||||
| 96 | Power unit for hang-gliders | US421192 | 1982-09-22 | US4546938A | 1985-10-15 | Jerzy W. Kolecki |
| A power unit for a hang-glider (1) or the like comprises a combustion motor (2) connected to one end of a drive shaft (9) and a propeller (10) connected to the other end of the drive shaft. To enable the power unit to be used both with pulling or traction-force propellers and pushing propellers (10) there is provided between the drive shaft (9) and the shaft (22) of the propeller (10) a flexible coupling (14) which enables the angle between the drive shaft and the propeller shaft to be adjusted at least in a vertical direction. | ||||||
| 97 | Arc wing aircraft | US146636 | 1980-05-05 | US4415131A | 1983-11-15 | William R. Bertelsen; William D. Bertelsen |
| A lightweight, man carrying aircraft including a skeletal fuselage assembly in combination with a primary arc-shaped lifting airfoil having variable camber, incidence angle, and pitching moment and a secondary stabilizing airfoil of a tubular, ring-like configuration. The arc-shaped primary airfoil is superior to traditional low speed airfoil forms due to its high aerodynamic efficiency, inherent design simplicity and strength. The ring-tail assembly, offering marginal aerodynamic lift, contributes significantly to the in-flight stability and safety of the aircraft. Both airfoil members are independently controllable and constructed of a fabric or like skin material which is fitted over a wing assembly and tensioned into an operable airfoil form by the aerodynamic forces of the air during flight. Typically, the wing assemblies are supported and maintained by a lightweight, tubular fuselage structure to which is affixed the propulsion system, control mechanisms and ground support assemblies. | ||||||
| 98 | Landing gear for ultralight aircraft | US156768 | 1980-06-05 | US4372506A | 1983-02-08 | David Cronk; Lyle M. Byrum |
| A landing gear for ultralight aircraft includes a main landing gear assembly disposed in a position relative to the longitudinal axis of the aircraft to permit either tail wheel type landing or tricycle landing operations with the assembly including an arched axle wherein the arch provides a spring for the landing gear as well as provides clearance to enable foot launching of the aircraft. A nose wheel strut assembly is linked to and extends forward of the main wheel landing gear assembly and includes a resilient tension link member. | ||||||
| 99 | Powered hang glider with reduction drive | US869833 | 1978-01-16 | US4262863A | 1981-04-21 | Charles J. Slusarczyk |
| A foot-launched and foot-landed hang glider is powered by an internal combustion two-cycle engine drivingly connected through a reduction-drive unit to a large relatively slow-moving propeller. A reduction mount, so referred to because it couples the reduction-drive unit closely to the engine, allows the engine to rotate a large propeller relatively slowly, thus providing more thrust at near-stalling flight conditions. The hang glider, thus powered, also obviates the necessity of being launched from the edge of a precipice and permits flight which is not predicated on the fortuitous selection of favorable air currents. | ||||||
| 100 | Flying wing | US866617 | 1978-01-03 | US4209148A | 1980-06-24 | Pierre M. Lemoigne |
| The flying wing comprises a rigid frame and a fabric canopy secured to the frame. The canopy has propelling, braking and steering hyperlift nozzles arranged on the surface of the canopy for canalizing the flow of air rearwardly from the under side to the upper side of the canopy. A support device for the pilot comprises at least two rigid members connected to the frame and extending downwardly from the frame and terminating in a seat for the pilot. Members maintain the rigid members stationary relative to the frame. The canopy has a longitudinal intermediate strip held planar by the frame and two relatively flexible substantially triangular lateral portions on laterally opposite sides of the strip and connected to the latter. The canopy has in plan substantially the shape of an isosceles trapezium the small base of which defines the leading edge of the wing. The intermediate strip has one of the aforementioned nozzles and each of the two lateral portions has two of the aforementioned nozzles. | ||||||
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