| 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 | Longitudinal flying wing aircraft | US13031421 | 2011-02-21 | US08056852B1 | 2011-11-15 | Faruk Dizdarevic; Mithad Dizdarevic |
| The Longitudinal Flying Wing aircraft idea provides for design of large cargo and passenger aircraft in range from low to high subsonic and transonic speed. Such aircraft would have up to twice lower fuel consumption per unit of payload, higher lift capacity, and a significantly longer range, while having a significantly lower level of noise inside passenger cabin and cockpit relative to classical concept aircraft. This idea is further providing for efficient, reliable, and simple flight controls, hence it may be successfully applied for design of all-size, long range, high-lift-capacity unmanned aircraft throughout the entire range of subsonic speeds. | ||||||
| 82 | Airplane with aerodynamic stall-prevention layout and pertinent longitudinal stability arrangement | US13011680 | 2011-01-21 | US20110180672A1 | 2011-07-28 | Nandor Vestroci; Fatemeh Hajibagher |
| General purpose airplane with a swept back wing provided with a sharp leading edge as to cause flow separation and stall of the wing in cases where the limits of the regular flight envelope are exceeded in terms of angle of attack, and as a result to cause the front part of the airplane to move downward, said airplane also having positive lift-producing horizontal stabilizer provided with rounded leading edge, which does not stall at this point, therefore holds the tail in level during the process, all together acting to restore the original flight attitude. The horizontal stabilizer is essentially a straight (or similar) wing with a steeper lift-coefficient curve as that of the swept-back wing, therefore, in case of an un-commanded pitch-up of the airplane the greater increase of lift on the horizontal stabilizer together with its greater moment arm provides the stabilizing force to counter such pitching. | ||||||
| 83 | Three Wing, Six Tilt-Propulsion Units, VTOL Aircraft | US12900790 | 2010-10-08 | US20110168835A1 | 2011-07-14 | Richard David Oliver |
| A vertical takeoff and landing aircraft having a fuselage with three wings and six synchronously tilt-able propulsion units, each one mounted above, below, or on each half of the aforementioned three wings. The propulsion units are vertical for vertical flight, and horizontal for forward flight. The aircraft wings are placed such that the rear wing is above the middle wing which is placed above the front wing. The placement of each of the propulsion units relative to the center of gravity of the aircraft about the vertical axis inherently assures continued stability in vertical flight mode, following the loss of thrust from any one propulsion unit. The placement of the propulsion units, viewing the aircraft from the front, is such that each propulsion units' thrust wake does not materially disturb the propulsion unit to its rear. When engine driven propellers or rotors are utilized, flapped wing panels are attached outboard of the forward and/or rearward propulsion units to provide yaw control during vertical flight. | ||||||
| 84 | Multi wing aircraft | US12653489 | 2009-12-15 | US20110168832A1 | 2011-07-14 | Stephen H. Funck |
| A multi-wing, airfoil fuselage aircraft that is capable of flying in a ground-effect mode includes a main airfoil fuselage wing, a fin that extends vertically from this wing, a pivot mount that is affixed to the fin, an auxiliary wing that connects to the pivot mount so as to allow its angle of attack to be adjusted and changed during different flight conditions, a main landing gear, an adjustable-length, stabilizing landing gear, assorted control surfaces that are movably affixed to the auxiliary wing and fin, and a ground-effect control system that is adapted to control the operation and movement of these control surfaces when the aircraft is flying in a ground-effect mode of flight. | ||||||
| 85 | Aircraft with dual flight regimes | US12802104 | 2010-05-29 | US20110031355A1 | 2011-02-10 | Alberto Alvarez Calderon F. |
| The aircraft is capable of two distinct fuel-efficient flight regimes: one is a vertical flight regime supported by two large two-bladed rotors with low disc loading located on right and left longitudinal booms. The booms extend between outboard regions of a front wing and inboard regions of a rear wing that has a larger span an area. The other flight regime is high speed up to high subsonic Mach number with the aircraft supported by wing lift with high wing loading, and with the rotors stopped and faired with minimal local drag contiguous to the booms. The longitudinal location of the aircrafts center of gravity, aerodynamic center and the center of the rotors are in close proximity. The front wing is preferably swept back, and the rear wing is preferably of W planform. | ||||||
| 86 | DOUBLE FUSELAGE AIRCRAFT | US12252088 | 2008-10-15 | US20100044521A1 | 2010-02-25 | Richard WILBY |
| According to the present invention, at least the symmetric external parts (9G, 9D) of the front lower wing (9) have a sweep forward (Φa), the lift generated by the rear upper wing (10) is greater than the lift generated by the front lower wing (9), the rear upper wing (10) is in direct contact with the rear upper parts of the fuselages (2G, 2D), and the propulsion system (11, 12, 13) comprises at least one turboprop engine having at least one propeller and is carried by the internal part (10I) of the rear upper wing (10), the axis.(l-l) of the propulsion system lying in the longitudinal mid-plane (L-L). | ||||||
| 87 | System, apparatus and method to improve the aerodynamics of a floatplane | US11163185 | 2005-10-07 | US07552895B2 | 2009-06-30 | Dave From |
| The aerodynamics of a floatplane can be improved by providing a wing suitable for mounting on a spreader bar between floats of the floatplane, mounting said wing on the spreader bar between the floats of a floatplane, and preventing the wing from rotating around the spreader bar during flight operations. In one apparatus embodiment, the invention comprises a wing mountable on a spreader bar between floats of the floatplane, a plurality of ribs spaced along the wing's axis, each rib having a recess suitable for accepting the spreader bar, and torque-restraining means to prevent the wing from rotating around the spreader bar. | ||||||
| 88 | Vertical take-off and landing (VTOL) aircraft with distributed thrust and control | US11035263 | 2005-01-13 | US20060151666A1 | 2006-07-13 | Timothy VanderMey; Josiah VanderMey |
| An aircraft having a vertical take-off and landing (VTOL) propulsion system. The aircraft includes a fuselage, the VTOL propulsion system, at least one forward thruster, a power source used for both the VTOL propulsion system and forward thruster, fore and aft wings and a plurality of spars attached to and spanning the space between the two wings. The VTOL propulsion system includes a plurality of VTOL cells (including a motor, motor controller, and propeller) attached in a spaced relation along each spar. The VTOL cells are used exclusively for vertical flight or hovering and are powered down as the aircraft develops forward flight velocity and corresponding wing lift. During forward flight the VTOL propellers are articulated to allow the aircraft to take on a low drag configuration. The present invention is suitable for use in manned or un-manned aircraft of any scale. | ||||||
| 89 | SYSTEM, APPARATUS AND METHOD TO IMPROVE THE AERODYNAMICS OF A FLOATPLANE | US11163185 | 2005-10-07 | US20060144999A1 | 2006-07-06 | Dave From |
| The aerodynamics of a floatplane can be improved by providing a wing suitable for mounting on a spreader bar between floats of the floatplane, mounting said wing on the spreader bar between the floats of a floatplane, and preventing the wing from rotating around the spreader bar during flight operations. In one apparatus embodiment, the invention comprises a wing mountable on a spreader bar between floats of the floatplane, a plurality of ribs spaced along the wing's axis, each rib having a recess suitable for accepting the spreader bar, and torque-restraining means to prevent the wing from rotating around the spreader bar. | ||||||
| 90 | Link between the wing and canard for flutter reduction | US10926455 | 2004-08-26 | US20060060696A1 | 2006-03-23 | Clifford Cordy |
| The efficiency of a canard airplane increases with increasing aspect ratio of the canard. As the aspect ratios of the canard and wing increase, it becomes increasingly difficult to avoid flutter at high speed. The basic modes of vibration in flutter generally include torsion in the member that is fluttering. A link between the wing and canard is added to greatly increase the torsional stiffness of both the wing and canard, with a corresponding reduction in the tendency of either of them to flutter. The link is an aerodynamic shape, much smaller than the wing or canard, that supports little static load in flight. | ||||||
| 91 | Aircraft | US11039847 | 2005-01-24 | US20050230518A1 | 2005-10-20 | John Lamont |
| An aircraft includes a fuselage with a circular airfoil body supported thereabove on a vertical drive shaft mechanism. The airfoil body includes an upper disk forming an upper surface of the body and a lower disk forming a lower surface of the body in which the upper and lower disks are supported at a fixed spacing on the vertical drive shaft mechanism for counter-rotation. Vanes are supported in both the upper and lower disks which are movable between a takeoff position in which the vanes are supported in respective openings in the disk for diverting air downwardly through the openings in the disks as the disks are rotated and a cruising position in which a surface of the vanes are continuous with the respective upper and lower surfaces of the bodies. | ||||||
| 92 | Aircraft lift arrangement | US09612694 | 2000-07-10 | US06446908B1 | 2002-09-10 | Manuel Munoz Saiz |
| An aircraft lift arrangement that consists of fine fins which are parallel among themselves and slightly curved, arranged attached along the sides of the aircraft fuselage, beginning at the front and running downward toward the rear, with a positive angle of attack and with the additional of small thin wings to provide lateral stability and to carry the engines, flaps and ailerons. | ||||||
| 93 | Wing combination for drag reduction, aircraft including such a wing, and a method of reducing the drag of an existing aircraft | US09415209 | 1999-10-12 | US06340134B1 | 2002-01-22 | Ronald G. Meschino |
| An apparatus and method are provided for reducing the drag of an aircraft wing. Many modern high speed aircraft have a low aspect ratio wing generating significant induced drag. The invention provides a drag reduction system, which is made up of a high aspect ratio supplementary wing connected to the fuselage by a streamlined fuselage connection, and at least two struts connecting the supplementary wing to the main wing. The drag reduction system is capable of reducing the total drag of a modern high speed, high altitude aircraft with a low aspect ratio cantilevered wing, by at least 29.1%. At least 65% of the total lift of the aircraft can be provided by the supplementary wing. The main wing then provides structural strength to transfer lifting loads to the fuselage of the aircraft, and for this purpose, the main wing and interconnections for the supplementary wing can be designed with this structural function in mind. | ||||||
| 94 | Ground-effect flying boats also applicable to aircraft, drones, and spacecraft | US121056 | 1998-07-23 | US6164591A | 2000-12-26 | Michel Henri Descatha |
| A Ground-Effect Flying-Boat system with a special hull producing a very low drag, but high lift, both in the water and in the air. A high pivoting-wing of an auto-stable airfoil, and one or more rear spoilers fitted on the hull-stern of the vessel having a special airfoil and determined horizontal and vertical slots producing very low drag, but a strong downward airstream deflection so as to increase the height of the ground-effect. The wing configuration allows for automatic maintenance of horizontal flight and automatic inclination in turns as well as an automatic anti-crash system against strong descendent gusts. These automatic stability features allow the craft to fly in rain or foggy weather without need of I.F.R. instruments, due to slide and spin resistance. In addition, the craft will not stall "nose down", but lose altitude slowly, with the hull remaining always practically horizontal. Water-landing is possible at a very reduced speed and even vertically into very strong winds and waves. The craft is easier and cheaper to build than conventional aircraft or seaplanes. The system can be scaled to craft of any size. | ||||||
| 95 | N-dimensional fighter aircraft | US667615 | 1991-03-08 | US5176338A | 1993-01-05 | Bert A. Silich |
| An improved fighter aircraft has three primary lifting surfaces acting as wings on the airframe. The lifting surfaces are attached 120 degrees apart on the airframe so the fighter may turn in any direction without prior movements. The pilot has means to position himself to feel only positive g's in these maneuvers. A rotatable cockpit section, for example, moves independent of the airframe with the canard wings thereon. The pilot flies the cockpit section and the airframe with wings thereon responds accordingly. | ||||||
| 96 | V/STOL Aircraft | US380480 | 1982-05-20 | US4469294A | 1984-09-04 | Robert T. Clifton |
| A V/STOL aircraft comprising a fuselage, having three sets of wings that are offset lengthwise and vertically. The center set of relatively small relatively thick wings 34 between the canard 14 and the rear relatively thin relatively large aerodynamic lift wings 18 are equipped with identical lift fans 36 enclosed in the wing by upper and lower movable slotted deflectors 40. The attitude of the slatted deflectors may be varied to transition the present invention from hovering to forward flight, and vice versa. The present invention's lift fans are interconnected by a balanced power distribution system, to insure constant, efficient use of total power and provide symmetrical lift about the aircraft's center of gravity resistibility. In the event of an engine failure, the remaining lift is still properly distributed to maintain symmetrical lift, so as to maintain balance and operational control of the aircraft in the lift mode. | ||||||
| 97 | Tandem wing airplane | US6698 | 1979-01-26 | US4390150A | 1983-06-28 | Philip C. Whitener |
| A tandem wing aircraft having two wings of similar area wherein a lower first wing is located at the forward end of the fuselage attached directly to fuselage structure. A second higher wing is located at the aft end of the fuselage but is aerodynamically separated from the fuselage structure by strut structure. Pitch control is achieved by increasing or decreasing the lift on either wing; but downward acting load is not required. The two wings are preferably vertically separated by 25% to 50% of the span of the wings. Control redundancy for flight safety is achieved because of availability and location of control surfaces. Higher aspect ratio wings can be used because of inherently reduced bending moments on the wing; and overall aircraft gross weight is reduced due to structural and aerodynamic efficiency. | ||||||
| 98 | Tandem wing airplane | US745150 | 1976-11-26 | US4165058A | 1979-08-21 | Philip C. Whitener |
| A tandem wing aircraft is provided having two independent spaced apart fuselages and two wings of similar area, a lower forward wing and a higher aft wing. The lower forward wing is attached to the forward region of each of the spaced apart fuselages; the higher aft wing is aerodynamically spaced apart from and located above the aft region of the spaced apart fuselages. An aft strut member is disposed between the aft wing and each of the fuselages; each aft strut member has a length sufficient to cause the wing tips of the lower forward wing and the upper aft wing to be vertically spaced apart by a distance of at least 25% of the span of either of the wings. | ||||||
| 99 | Airplane | US1291150 | 1950-11-08 | USD166843S | 1952-05-27 | BAILEY KENNETH ROBERT |
| 100 | Tandem wing aircraft | US62262445 | 1945-10-16 | US2470602A | 1949-05-17 | COEHRANE CAMPBELL THOMAS; VINCENT HALL ERIC |
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