| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 1 | AIRCRAFT WITH SELECTIVELY ATTACHABLE PASSENGER POD ASSEMBLY | EP16185727.1 | 2016-08-25 | EP3263445A1 | 2018-01-03 | McCULLOUGH, John Richard; OLDROYD, Paul K. |
In some embodiments, an aircraft (10) includes a flying frame (12) having an airframe (26), a propulsion system (34) attached to the airframe (26) and a flight control system (68) operably associated with the propulsion system (34) wherein, the flying frame (12) has a vertical takeoff and landing mode and a forward flight mode. A pod assembly (70) is selectively attachable to the flying frame (12) such that the flying frame (12) is rotatable about the pod assembly (70) wherein, the pod assembly (70) remains in a generally horizontal attitude during vertical takeoff and landing, forward flight and transitions therebetween.
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| 2 | AIRCRAFT WITH SELECTIVELY ATTACHABLE PASSENGER POD ASSEMBLY | EP16185727.1 | 2016-08-25 | EP3263445B1 | 2018-10-17 | McCULLOUGH, John Richard; OLDROYD, Paul K. |
| In some embodiments, an aircraft (10) includes a flying frame (12) having an airframe (26), a propulsion system (34) attached to the airframe (26) and a flight control system (68) operably associated with the propulsion system (34) wherein, the flying frame (12) has a vertical takeoff and landing mode and a forward flight mode. A pod assembly (70) is selectively attachable to the flying frame (12) such that the flying frame (12) is rotatable about the pod assembly (70) wherein, the pod assembly (70) remains in a generally horizontal attitude during vertical takeoff and landing, forward flight and transitions therebetween. | ||||||
| 3 | Pivotable aircraft nose portion | EP03075275.2 | 2003-01-28 | EP1334905B1 | 2006-06-21 | Salmon, James J. |
| 4 | Aircraft with selectively attachable passenger pod assembly | US15200163 | 2016-07-01 | US09963228B2 | 2018-05-08 | John Richard McCullough; Paul K. Oldroyd |
| In some embodiments, an aircraft includes a flying frame having an airframe, a propulsion system attached to the airframe and a flight control system operably associated with the propulsion system wherein, the flying frame has a vertical takeoff and landing mode and a forward flight mode. A pod assembly is selectively attachable to the flying frame such that the flying frame is rotatable about the pod assembly wherein, the pod assembly remains in a generally horizontal attitude during vertical takeoff and landing, forward flight and transitions therebetween. | ||||||
| 5 | Method and apparatus for actuating an aircraft nose portion | US10073496 | 2002-02-11 | US06663045B2 | 2003-12-16 | James J. Salmon |
| A method and apparatus for actuating an aircraft nose portion. The aircraft can have a longitudinal axis and a pitch axis generally transverse to the longitudinal axis. The fuselage can include a pressure bulkhead and a pressurized payload portion aft of the pressure bulkhead. The nose portion can be positioned forward of the pressure bulkhead and can be changeable from a first configuration to a second configuration while the pressurized payload portion is capable of being pressurized relative to a region external to the aircraft. For example, the nose portion can be inclined upwardly relative to the longitudinal axis when pivoted from a first position to a second position. Accordingly, the length of the aircraft can be reduced, for example, to accommodate the aircraft at a loading gate or other ground support area. | ||||||
| 6 | Rotating variable nose | US3690600D | 1970-11-24 | US3690600A | 1972-09-12 | COOPER CLIFFORD B |
| An aircraft having a geometrical means for revolving the nose portion thereof about an axis oblique to the normal centerline of the vehicle, resulting in a pitch-down, nonfaired configuration to increase clear field of vision in the critical area lying below and ahead of the aircraft for landing and takeoff while in one position, and an optimum aerodynamically acceptable supersonic configuration in the other position.
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| 7 | Heavy lift helicopter with vertically adjustable cockpit | US3679154D | 1970-07-21 | US3679154A | 1972-07-25 | NICHOLS JOHN B; GAMAUNT ROGER L |
| A helicopter for use in transporting large loads and having a cockpit movably connected to the main body fuselage by a parallelogram linkage which may be actuated by the pilot and/or load operator for increasing visibility when loading the helicopter and providing easy access to its interior.
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| 8 | Windshield for supersonic aircraft | US3477667D | 1967-07-11 | US3477667A | 1969-11-11 | LOCK STANLEY ANTHONY |
| 9 | Method of repelling water from a transparent member | US53766666 | 1966-03-28 | US3310429A | 1967-03-21 | KEITH GUNNAR; HANSEN ROBERT S |
| 10 | Fuselage frame | US77051058 | 1958-10-29 | US3048355A | 1962-08-07 | DORNIER JR CLAUDIUS |
| 11 | Retractable cabin enclosure for aircraft | US8187136 | 1936-05-26 | US2142997A | 1939-01-10 | CASE HAROLD W |
| 12 | Method of improving visibility in aircraft | US22392927 | 1927-10-04 | US1715277A | 1929-05-28 | THOMAS CARROLL; REID ELLIOTT G |
| 13 | Aircraft wing shift device | US15088615 | 2016-04-01 | US10046850B2 | 2018-08-14 | Dustin Eli Gamble; Matthew Curran |
| An aerial vehicle includes a fuselage, a wing, and a wing shift device. The wing shift device is configured to be coupled to the fuselage. The wing shift device comprises a plurality of apertures for coupling the wing to the aerial vehicle. The plurality of apertures are configured to permit the wing to be shifted in a forward or aft direction along the fuselage based on a center of gravity of the aerial vehicle. | ||||||
| 14 | ENHANCED NET PITCHING MOMENT MULTI-WING VTOL COMPACT PERSONAL AIRCRAFT | US15683870 | 2017-08-23 | US20180093765A1 | 2018-04-05 | BRENDAN GRAHAM |
| This disclosure describes a multi-wing manned or unmanned compact personal vertical takeoff and landing aircraft, comprising the integration of: a plurality of parallel wings forming a boxed planform multi-wing assembly with no dynamic airfoil control surfaces, statically affixed to a co-planar adjacent counter-rotating quad-rotor air propulsion system; and a fuselage free to rotate under servo control about an axial shaft, permitting dynamic orientation manipulation. The vehicle described herein achieves: high maneuverability and attitude orientation control incumbent upon the ratio of power delivered to the quad-rotors; area constrained and enhanced wind gust insensitive VTOL capability; high fuel efficient non-hover aerodynamic flight capability; high external field-of-view optical visibility from the fuselage interior; convenient fuselage interior accessibility; and enhanced net pitching moment of inertia about the multi-wing assembly net aerodynamic center, permitting rapid transitioning to and from aerodynamic flight orientation. | ||||||
| 15 | Aircraft with Selectively Attachable Passenger Pod Assembly | US15200163 | 2016-07-01 | US20180002011A1 | 2018-01-04 | John Richard McCullough; Paul K. Oldroyd |
| In some embodiments, an aircraft includes a flying frame having an airframe, a propulsion system attached to the airframe and a flight control system operably associated with the propulsion system wherein, the flying frame has a vertical takeoff and landing mode and a forward flight mode. A pod assembly is selectively attachable to the flying frame such that the flying frame is rotatable about the pod assembly wherein, the pod assembly remains in a generally horizontal attitude during vertical takeoff and landing, forward flight and transitions therebetween. | ||||||
| 16 | Method and apparatus for actuating an aircraft nose portion | US10073496 | 2002-02-11 | US20030150956A1 | 2003-08-14 | James J. Salmon |
| A method and apparatus for actuating an aircraft nose portion. The aircraft can have a longitudinal axis and a pitch axis generally transverse to the longitudinal axis. The fuselage can include a pressure bulkhead and a pressurized payload portion aft of the pressure bulkhead. The nose portion can be positioned forward of the pressure bulkhead and can be changeable from a first configuration to a second configuration while the pressurized payload portion is capable of being pressurized relative to a region external to the aircraft. For example, the nose portion can be inclined upwardly relative to the longitudinal axis when pivoted from a first position to a second position. Accordingly, the length of the aircraft can be reduced, for example, to accommodate the aircraft at a loading gate or other ground support area. | ||||||
| 17 | Apparatus and method for allowing a pilot to see outside an airplane | US988563 | 1992-12-10 | US5351898A | 1994-10-04 | Michael S. Koehn |
| An airplane, such as a supersonic airplane, includes at least one viewing tunnel located behind the cockpit instrument panel for allowing the pilot to see in front of and to the side of the airplane during low speed flight. The viewing tunnel is especially useful during landing approaches and touchdown when the airplane's high angle of attack and long nose prevents the pilot from seeing the landing environment through the conventional forward cockpit windows. The viewing tunnel allows the pilot to see through a large opening in the bottom and sides of the airplane. This opening is covered by canards during high speed flight and uncovered during low speed flight when the canards are moved to the extended position to provide additional control authority for the airplane. | ||||||
| 18 | Airplane with spatial panorama | US3643899D | 1969-11-13 | US3643899A | 1972-02-22 | FIRESTONE FLOYD A |
| A fixed wing airplane having a substantially transparent fuselage, which in straight and level flight permits both the pilot and copilot to see the entire ground and sky in all directions and from nadir to zenith, with the exception of roughly two steradians of solid angle in the quadrant above and behind him. The necessary opaque struts which cross the transparent areas are so oriented and dimensioned that the distant scene as seen through the major areas of the plane appears to be continuous, advantage being taken of the fact that the pilot has two eyes whose lines of regard are not simultaneously occulted by narrow struts properly spaced and oriented. Utilizing the same fact of vision, instrument arrays and stressed skin structures are described, that the pilot can see through.
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| 19 | Ultrasonic cabin enclosure means | US41438464 | 1964-11-27 | US3334846A | 1967-08-08 | SPIVAK WALTER A; MCQUILKIN FREDERICK T; MARTIGNONI ANGELO P |
| 20 | Aircraft fuselages | US29682763 | 1963-07-22 | US3171620A | 1965-03-02 | DAVID WALLEY GERALD; STOKES WARBURTON DENNIS |
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