子分类：
- B64C2025/325： ..直升机专用
- B64C25/34： ..轮式,例如多轮起落架
- B64C25/38： ..履带式
- B64C25/40： ..部件是在接地前旋转的
- B64C25/42： ..制动器的布置或配置(通过速度情况,例如起落架接合地面滑行的加速度或减速度至少可部分地对地面制动力加以调节的入B60T8/32)〔4〕
- B64C25/50： ..可转向的起落架;减摆架(应用于地面车辆的转向装置入B62D)
- B64C25/52： ..雪橇或滑橇
- B64C25/54： ..浮筒
- B64C25/58： ..减震器或弹簧的布置或配置(减摆器入B64C25/50;一般车辆悬架装置入B60G;减震器本身入F16F)
- B64C25/66： ..可转换的起落架;不同种类地面滑行或类似接合部件的组合
| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 161 | DEBRIS DEFLECTING DEVICE, SYSTEM, AND METHOD | US12031466 | 2008-02-14 | US20090206199A1 | 2009-08-20 | Rick A. JACKSON |
| A debris deflector includes a bracket and a horizontal blade assembly. The bracket is to secure the debris deflector to an aft side of a landing gear assembly. The horizontal blade assembly is secured to the bracket. The horizontal blade assembly includes a blade and flap. The blade has a forward blade edge, blade body, and trailing blade edge. The forward blade edge is configured for placement aft of a tire for the landing gear assembly. The blade body extends outward from the forward blade edge substantially parallel to a road surface. The flap is secured to the trailing blade edge and extends from the trailing blade edge generally rearward and downward from the trailing edge. | ||||||
| 162 | Rotating blade aircraft control system | US11705622 | 2007-02-14 | US07472862B2 | 2009-01-06 | Henry L. Blevio, Sr. |
| In a preferred embodiment, an apparatus, including: an aircraft having rotatable blades; and the rotatable blades are movable between horizontal and vertical positions. | ||||||
| 163 | Ball wheel for an aircraft | US11705650 | 2007-02-14 | US20080197694A1 | 2008-08-21 | Henry L. Blevio |
| In a preferred embodiment, an apparatus, including: a ball wheel; and apparatus to cause the ball wheel to rotate in a selected direction. | ||||||
| 164 | Airplane Protected Against Projections of Tire Debris | US11774135 | 2007-07-06 | US20080006742A1 | 2008-01-10 | Bernard Guering; Jonathan Guering |
| The tires that equip airplane wheels have elastomer treads from which a piece may detach and damage a zone of the airplane. Shredding means, situated between wheel and another part of the airplane, shred the piece of tread, which detaches from the tire and is projected onto the other part of the airplane, into several small pieces. These shredding means, such as a grid with blades that can cut the tread material, are arranged so as to disperse the pieces. A process reinforces the tolerance of an airplane to impacts of a detached piece of the tread, by shredding the piece into several small pieces between the instant when the piece is detached and the instant when the piece would have struck airplane. | ||||||
| 165 | Rotating blade aircraft control system | US11705622 | 2007-02-14 | US20070187548A1 | 2007-08-16 | Henry Blevio |
| In a preferred embodiment, an apparatus, including: an aircraft having rotatable blades; and the rotatable blades are movable between horizontal and vertical positions. | ||||||
| 166 | Aerodynamically stable, high-lift, vertical takeoff aircraft | US10958038 | 2004-10-04 | US20060038061A1 | 2006-02-23 | Henry Blevio |
| In a preferred embodiment, a vertical takeoff aircraft body having an inverted hemispherical upper portion, a generally cylindrical lower portion with a diameter of its upper end slightly greater than a diameter of its lower end but less than a diameter of the lower end of the upper portion, and a truncated inverted generally cone-shaped transition portion joining the upper portion and the lower portion; and a plurality of vertical columns attached to the aircraft body and spaced apart from the aircraft body, equidistantly disposed about the aircraft body. The present invention also provides novel landing gears for such an aircraft as well as a novel method of adjusting the pitches of rotating blades thereof. | ||||||
| 167 | Landing assist probe retention strap | US10860043 | 2004-06-03 | US20050279882A1 | 2005-12-22 | Neal Muylaert; Darrin Tebon |
| An aircraft landing assist apparatus is designed to be retrofit to existing aircraft having internal constructions that have been modified to support the apparatus. The apparatus is designed so that on rough landings of the aircraft on a ship deck, the apparatus will collapse in a controlled manner to avoid any damage to ammunition and/or fuel storage areas of the aircraft. | ||||||
| 168 | Landing assist apparatus interface bulkhead and method of installation | US10860162 | 2004-06-03 | US20050269450A1 | 2005-12-08 | Neal Muylaert; Darrin Tebon; Rolland Lahaie |
| An aircraft landing assist apparatus is designed to be retrofit to existing aircraft having internal constructions that have been modified to support the apparatus. The apparatus is designed so that on rough landings of the aircraft on a ship deck, the apparatus will collapse in a controlled manner to avoid any damage to ammunition and/or fuel storage areas of the aircraft. | ||||||
| 169 | Wheel mounted water spray deflector | US10434747 | 2003-05-09 | US20040222330A1 | 2004-11-11 | Justin D. Cottet; Mark N. Simpson |
| A water spray deflector to deflect water spray produced from aircraft landing gear from components of the aircraft. The water spray deflector has an inner diameter and an outer diameter. Coupled to the spray deflector are attachment arms that are adapted to couple with an outer portion of a rim of the landing gear. The attachment arms are also configured to support the water spray deflector position the water spray deflector a distance from a side wall of the tire to prevent the side wall of the tire from coming in contact with the water spray deflector under various loading conditions placed on the tire. In some versions, the water spray deflector is weakened in areas to encourage a failure mode of the water spray deflector. | ||||||
| 170 | External airbag protection system for helicopters | US9409 | 1998-01-20 | US5992794A | 1999-11-30 | Israel Rotman; Gideon Rosenberg |
| An airbag protection system for helicopters. Airbags are inflated either automatically or manually, or a combination of both, prior to the helicopter striking the ground, thus avoiding or ameliorating a crash. Proximity sensors detect a fast descent to trigger inflation of the airbags located beneath the helicopter fuselage so that they can cushion the impact with the ground. Venting of the gas from the airbags is also provided to release the gas from the airbags so as to prevent rebound of the helicopter from the ground. | ||||||
| 171 | Multi-deck passenger aircraft having impact energy absorbing structures | US232387 | 1994-04-25 | US5542626A | 1996-08-06 | Guenter Beuck; Hans-Juergen Mueller; Ralf Schliwa |
| An energy absorbing structural unit is attached outside the fuselage belly of an aircraft having at least two decks arranged one over another. At least the lower deck, of which the floor is adjacent to the fuselage belly, includes passenger cabin compartments and/or service facilities. The energy absorbing structure is an energy absorbing structural unit (5) that is attached outside of the existing aircraft fuselage (2) approximately vertically below the passenger cabin compartment (9) and/or service facilities provided on the lower deck of the aircraft. The energy absorbing structural unit absorbs impact energy arising in a crash or emergency landing of the aircraft. Because impact energy is absorbed by the external structural unit rather than or in addition to the structure of the aircraft fuselage and air frame, it is possible to provide lower deck passenger cabin space that may be continuously occupied by passengers and crew even during the take-off and landing phases of a flight. In this manner it is possible to increase the passenger capacity of an aircraft. | ||||||
| 172 | Runway sander | US729486 | 1978-10-04 | US4099688A | 1978-07-11 | Murray Lawrence Jayne |
| This invention relates to aircraft and particularly to the landing gear, and specifically to a device for promptly sanding an unexpectedly slippery runway as the aircraft is in the process of landing thereon so that the aircraft can be controlled and safely stopped after it is on the ground. | ||||||
| 173 | Torque linkage damper | US27450D | 1970-10-30 | USRE27450E | 1972-08-01 | |
| AN AIRCRAFT LANDING GEAR DAMPING MECHANISM WHICH OPERATES DIRECTLYIN CONJUNCTION WITH THE LANDING GEAR TORQUE LINKAGE AND COMBINES THEW FUNCTIONS OF A HYDRAULIC DAMPER AND A SPRING TYPE OF DAMPER.
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| 174 | Anti-hydroplaning device | US3680885D | 1971-05-06 | US3680885A | 1972-08-01 | DECARDI PEDRO; TAYLOR CARL S; ROBERTS GEOFFREY L |
| A water displacer such as a plow or scraper in front of the tires of a vehicle to remove water from a flooded surface and expose the tires to a mere wet track condition. An air jet optionally may be used between the positive displacer and the tires.
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| 175 | Aircraft landing gear | US58302766 | 1966-09-29 | US3395879A | 1968-08-06 | ROBERT BAYLIFF; LE BLANC WALTER J; JAMES SIDLES |
| 176 | Anti-hydroplaning for aircraft | US48461065 | 1965-09-02 | US3339865A | 1967-09-05 | NETTLES FORREST T |
| 177 | Braking device on a vehicle | US5215860 | 1960-08-26 | US3116897A | 1964-01-07 | LEAROYD THEED WILLIAM DENIS |
| 178 | Aircraft undercarriages | US79041759 | 1959-02-02 | US3010682A | 1961-11-28 | SIDNEY MOSS NORMAN; GEORGE ORLOFF; ARTHUR SCOTT |
| 179 | Aircraft duct screen arrangement | US50345755 | 1955-04-25 | US2814454A | 1957-11-26 | ATKINS FLOYD W; ELKIN HUGH W |
| 180 | Aeroplane construction | US40337729 | 1929-10-30 | US1882416A | 1932-10-11 | LOUIS GASTWIRTH |
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