| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 121 | Blended Wing Body Boundary Layer Ingesting Inlet Design Integration | US14295578 | 2014-06-04 | US20160144972A1 | 2016-05-26 | Razvan Virgil Florea; Mark B. Stucky |
| An inlet for a propulsion system has an upper wall and a lower wall and a throat extending between the upper wall and the lower wall. The lower wall has a bump edge located immediately after the throat. | ||||||
| 122 | RECESSED LIFT SPOILER ASSEMBLY FOR AIRFOILS | US14262647 | 2014-04-25 | US20160137290A1 | 2016-05-19 | Mark F. Emerick |
| A spoiler assembly is provided that is engageable to a UAV that defines a body, an outer surface and an inner surface. The spoiler assembly comprises a spoiler, translatably connected to the UAV inner surface adjacent a first portion of the spoiler aperture. The spoiler defines an upper surface and an outer surface, the upper surface being substantially the same size and shape as the spoiler aperture. A spoiler shroud is connected to the UAV inner surface and extends within the UAV body about at least a portion of the spoiler aperture. A spoiler activating mechanism is secured to the UAV inner surface and connected the spoiler lower surface. The mechanism is operative to translate the spoiler between a first position wherein the spoiler upper surface is substantially flush with the UAV outer surface, and second a position, wherein the spoiler upper surface is disposed substantially within the UAV body. | ||||||
| 123 | SOLAR RELAY AIRCRAFT POWERED BY GROUND BASED SOLAR CONCENTRATOR MIRRORS IN DUAL USE WITH POWER TOWERS | US14155360 | 2014-01-15 | US20160009402A1 | 2016-01-14 | John William Hunter |
| A solar relay aircraft system includes a solar relay aircraft having an upper surface, and a lower surface, and equipped with a solar radiation receiver on said lower surface and capable of converting solar energy to electrical energy. An electric motor in electrical connection with said solar radiation receiver to receive the electrical energy and drives a propeller to propel the solar relay aircraft. A number of ground-based reflector arrays include a plurality of reflecting mirrors for receiving solar radiation from the sun and direct the solar radiation from the sun towards the solar relay aircraft. | ||||||
| 124 | Driven aircraft, in particular an aircraft designed as a flying wing and/or having a low radar signature | US13704545 | 2011-06-14 | US08888038B2 | 2014-11-18 | Bartholomaeus Bichler; Jochen Dornwald; Gerhard Wedekind |
| An aircraft is provided includes at least one drive flow passage, which runs from an air inlet directed forward on the body surface via a jet engine through the body to a jet nozzle that opens towards the rear on the body surface. At least a part of the jet engine is arranged upstream of the air inlet seen in the flight direction of the aircraft and the drive flow passage has curvature sections embodied and arranged for this in a suitable manner. | ||||||
| 125 | FLYING WING WITH SIDE CARGO COMPARTMENT | US14139295 | 2013-12-23 | US20140175215A1 | 2014-06-26 | Guillaume Gallant; Romain Delahaye |
| Optimization of the use of the available volume in a flying wing for commercial passenger transport, in particular for short- or medium-haul routes. A flying wing is provided including a passenger cabin together with at least one hold for the transport of luggage and/or goods, in which the hold is positioned laterally relative to said passenger cabin. | ||||||
| 126 | Aircraft with rear annular tail | US12516594 | 2007-11-29 | US08573530B2 | 2013-11-05 | Olivier Cazals; Thierry Druot |
| A rear tail assembly for an aircraft, including a fuselage, a wing and at least one propulsion engine attached in the rear portion of the fuselage located behind the wing along the X longitudinal axis of the aircraft, wherein the aforementioned assembly includes aerodynamic surfaces connected in the rear portion of the fuselage. The tail assembly essentially includes horizontal aerodynamic surfaces and essentially vertical aerodynamic surface arranged so as to form an annular structure including at least one ring attached to the fuselage. At least one engine is held in the ring formed by the tail assembly. In one embodiment, a central fin is used for defining two rings in the annular structure. In particular embodiments of an aircraft including such a tail assembly, one or two engines can be fitted in the ring area. | ||||||
| 127 | Aircraft with vertical stabilizers arranged on a central fuselage body and method, as well as control unit, for compensating a negative pitching moment | US12913463 | 2010-10-27 | US08496203B2 | 2013-07-30 | Malte Schwarze; Andreas Westenberger |
| An aircraft includes, but is not limited to a central fuselage body without horizontal stabilizer, at least one high-lift control surface, at least one vertical stabilizer that is arranged on the central fuselage body and at least one extendable compensation control surface. The compensation control surface may be moved independently of the high-lift control surface of the aircraft and generates a positive tail-heavy pitching moment when it is moved into the flow against the aircraft. Due to this measure, a negative pitching moment during the actuation of high-lift control surfaces may be at least partially eliminated without influencing the high lift. Rudder segments that may be moved opposite to one another on two vertical stabilizers that are arranged mirror-symmetrical referred to the longitudinal axis of the aircraft preferably are used for this purpose. | ||||||
| 128 | Discrete co-flow jet (DCFJ) airfoil | US13102844 | 2011-05-06 | US08485476B2 | 2013-07-16 | Gecheng Zha; Bertrand P. E. Dano |
| The present invention provides an aircraft having one or more fixed wings in a flying wing configuration, where the aircraft further includes a high performance co-flow jet (CFJ) circulating about at least a portion of an aircraft surface to produce both lift and thrust. | ||||||
| 129 | Oblique blended wing body aircraft | US12675165 | 2008-08-29 | US08408490B2 | 2013-04-02 | William R McDonnell |
| An oblique wing aircraft (1) designed for reduced surface area to volume ratio. The aircraft has an oblique wing comprising a forward swept wing segment (27) on one side of the wing and an aft swept wing segment (29) on the opposite side of the wing. A center oblique airfoil section (25) connects the forward and aft swept wing segments. The center oblique airfoil section has a larger chord near its centerline than the chords of either of the forward or aft swept wing segments. The chord of the center oblique airfoil section tapers down more rapidly than the forward or aft wing segments as the center oblique airfoil section extends outboard toward the forward and aft swept wings. The center oblique airfoil section is not shaped solely to function as a circular fairing to fill the gap between an oblique wing and a fuselage at different oblique wing angles, nor is it a second wing in an X wing configuration. Preferably, the aircraft is an all-wing aircraft. | ||||||
| 130 | Blended wing body cargo airplane | US12623404 | 2009-11-21 | US08366050B2 | 2013-02-05 | Richard C. Odle; Dino Roman; Blaine Knight Rawdon |
| A blended wing body cargo aircraft is disclosed. A body section defines a cargo volume, where an outer surface of the body section is shaped to provide an aerodynamic lifting surface. A cargo door and ramp structure is located in an aft end of the body section and is shaped to conform to an outer shape of the aerodynamic lifting surface when in a closed position. A control surface has a slightly cambered downward shape, and is positioned substantially near an aft end of the cargo door and ramp structure. | ||||||
| 131 | Blended wing aircraft | US13428095 | 2012-03-23 | US08302908B1 | 2012-11-06 | Max Kismarton; Aaron J. Kutzmann; Kevin Lutke |
| Apparatus and methods provide for a blended wing passenger or cargo aircraft. Aspects of the disclosure provide an aircraft having wings with spars having a thickness at the wing root corresponding to a height of the payload space within the fuselage to which the wings are attached. The wing spars within the wings on each side of the aircraft may each be spliced into an aircraft frame that is part of the fuselage. The wing thickness provides mounting locations for aircraft engines and other components within the wing and passing through the wing spars. With this mid-wing configuration, the fuselage provides support for the various loads experienced by the wings without the use of a conventional structural wing box. | ||||||
| 132 | Co-flow jet aircraft | US12119193 | 2008-05-12 | US08262031B2 | 2012-09-11 | Gecheng Zha; Sebastian Aspe; Joseph John Dussling; Nicholas Ramsay Heinz; Daniel J. Martinez |
| The present invention provides an aircraft having one or more fixed wings in a flying wing configuration, where the aircraft further includes a high performance co-flow jet (CFJ) circulating about at least a portion of an aircraft surface to produce both lift and thrust. | ||||||
| 133 | Aircraft with jet engines arranged at the rear | US11946579 | 2007-11-28 | US08128023B2 | 2012-03-06 | Olivier Cazals |
| When an aircraft is propelled by at least one jet engine fixed in a rear part of the aircraft, at least one substantially horizontal rear aerodynamic surface, the rear horizontal surface, is arranged at the rear of the aircraft and at least one jet engine is fixed under the rear horizontal surface by an attachment mast fixed by its upper part to the rear horizontal surface and maintains, by its lower part, the jet engine. The rear horizontal surface is also the horizontal tail unit of the aircraft or a horizontal surface maintained above the fuselage. The rear surfaces and the fuselage are arranged such that the engines are installed and removed using a vertical movement of the engines, which are advantageously one, two or three in number, in the rear zone of the aircraft. | ||||||
| 134 | Air transport with scalloped underbody | US11614052 | 2006-12-20 | US08104717B2 | 2012-01-31 | Sean R. Wakayama; Richard C. Odle |
| An exemplary embodiment provides an air transport that has a scalloped aerodynamic underside that includes at least one depression. The depression is configured to receive at least an upper portion of a cargo pod to preclude an air passage way between an upper surface of a pod and the scalloped underside of the transport. Certain embodiments provide conformal pods that nest into the depressions so that pod under surfaces blend smoothly with the scalloped underside of the transport to provide a smooth aerodynamic underside. The scalloped underside may be retrofitted to existing aircraft or supplied as original equipment on new transports, and may be of composite, plastic or other light weight materials. | ||||||
| 135 | 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. | ||||||
| 136 | Parametric geometry model for a blended wing body | US11958143 | 2007-12-17 | US08019574B2 | 2011-09-13 | Thomas Allen Hogan; Christopher K. Droney; Dino Roman |
| A required payload volume of a Blended Wing Body air vehicle is determined and analyzed for a list of corner points that is passed to a Loft Module as keep-out points to be enclosed by a body portion established using a faceted minimum volume. Trapezoidal wing shape and size are determined, a leading edge of the body portion and trapezoidal wing leading edge are trimmed and a trailing edge of the body portion and trapezoidal wing trailing edge are blended. A leading edge elevation is established and with leading edge radius as an input smoothly encloses the payload volume in a first set of defined aerodynamic sections. A second set of aerodynamic sections and transition sections between the body portion and the trapezoidal wing are defined. The blended wing body is then lofted based on the defined sections. | ||||||
| 137 | Deltoid main wing aerodynamic configurations | US12347997 | 2008-12-31 | US07793884B2 | 2010-09-14 | Faruk Dizdarevic; Mithad Dizdarevic |
| “T-tailed Deltoid Main Wing” idea allows for design of high-subsonic passenger aircraft with a capacity between 200 and 650 passengers with outer dimensions fitting within 80 m box on class VI airports while having more than twice lower fuel consumption per unit of payload when compared to the present classical-concept aircraft with fuselage that have the same passenger capacity. T-tailed deltoid main wing aircraft is satisfying all safety requirements for a passenger aircraft while having over 50% longer range than the aircraft of equivalent capacity with fuselage. Simple aerodynamic and structural solutions of T-tailed deltoid main wing aircraft are resulting with low development risks and production cost. Simple and reliable flight control systems of aircraft that are based on T-tailed deltoid main wing aerodynamic configuration allow for design of all-purpose, high-lift-capacity, and long range unmanned aircraft. | ||||||
| 138 | DELTOID MAIN WING AERODYNAMIC CONFIGURATIONS | US12347997 | 2008-12-31 | US20100163670A1 | 2010-07-01 | FARUK DIZDAREVIC; MITHAD DIZDAREVIC |
| Deltoid Main Wing idea provides for several innovative aerodynamic configurations for large subsonic and supersonic civil and military aircraft including “T-tailed Deltoid Main Wing” configuration that allows for design of high-subsonic jumbo jet passenger aircraft with a capacity between 200 and 700 passengers whose outer dimensions fit within 80 m box on class VI airports while having more than twice lower fuel consumption per unit of payload when compared to the present classical-concept aircraft with the same passenger capacity, while further allowing for design of all-size and all-purpose, high-lift-capacity, and long-range unmanned aircraft. | ||||||
| 139 | Blended Wing Body Unmanned Aerial Vehicle | US12271556 | 2008-11-14 | US20100123047A1 | 2010-05-20 | Jeffrey L. Williams |
| A Blended Wing Body SUAV and MUAV is disclosed having a novel airfoil profile, wing configuration, rigging and tractor pull propeller placement that provide improved stability and safety characteristics over prior art SUAVs and MUAVs of comparable size and weight. This unique blended wing design includes wing twist on the outboard wing and an inverted “W” shaped planform to provide lateral and longitudinal stability, and smooth, even flight characteristics throughout the range of the expected flight envelope. These flight characteristics are crucial to providing a stable reconnaissance platform with favorable stall speeds, an increased payload and the ability to hand launch without the danger of exposing ones hands or wrist to a propeller. | ||||||
| 140 | Unconventional integrated propulsion systems and methods for blended wing body aircraft | US11563099 | 2006-11-24 | US07665689B2 | 2010-02-23 | James G. McComb |
| Integrated propulsion systems and methods for blended wing aircraft are disclosed. In one embodiment, a propulsion system at least one engine operatively disposed within an engine flow duct having an engine inlet and an engine exhaust aperture, and at least one fan operatively disposed within a fan flow duct having a fan inlet and a fan exhaust aperture. The engine and fan rotational axes extending at least approximately along a lengthwise direction of the aircraft, the fan flow duct being separate from the engine flow duct. A transmission assembly is operatively coupled between the at least one engine and the at least one fan, the transmission assembly being configured to transmit a rotary output from the at least one engine to rotate the at least one fan. | ||||||
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