| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 181 | AIRCRAFT INCLUDING A PASSENGER CABIN EXTENDING AROUND A SPACE DEFINED OUTSIDE THE CABIN AND INSIDE THE AIRCRAFT | US14263376 | 2014-04-28 | US20140319274A1 | 2014-10-30 | Patrick LIEVEN; Romain DELAHAYE; Catalin PERJU |
| The sealed bottoms of aircraft passenger cabin have to be fastened with heavily sized fasteners so as to withstand loads induced by the cabin pressurization. Besides, the increase in aircrafts seating capacity makes an increase in passenger cabin widths of interest. Such a width increase however makes the structure delimiting passenger cabin less resistant to efforts induced by the cabin pressurization. The present invention proposes an aircraft wherein the structure delimiting passenger cabin extends over 360 degrees around a space defined outside structure. The invention allows structure to be more resistant to loads induced by the cabin pressurization, while allowing to reduce or even to avoid the need for a sealed bottom, and while allowing to increase the space available for passengers. | ||||||
| 182 | Swept-wing powered-lift aircraft | US13759659 | 2013-02-05 | US08567711B1 | 2013-10-29 | Robert D. Gregg, III; Aaron J. Kutzmann; David J. Manley; John C. Vassberg; Neal Harrison; Max Kismarton |
| Apparatus and methods provide for a swept-wing powered-lift aircraft. Aspects of the disclosure provide a powered-lift aircraft that utilizes the engine exhaust flow over upper surface blown flaps to increase lift during various flight operations. The powered-lift aircraft has wings with inboard portions and outboard portions. The adjacent inboard and outboard portions share a swept leading edge. The leading edge is swept to a degree that shifts the outboard portion rearward to a position in which the aircraft center of lift has little to no variance upon the activation or deactivation of a powered-lift system. | ||||||
| 183 | OBLIQUE BLENDED WING BODY AIRCRAFT | US13784438 | 2013-03-04 | US20130221165A1 | 2013-08-29 | William Randall McDonnell |
| An oblique wing aircraft designed for reduced surface area to volume ratio. The aircraft has an oblique wing comprising a forward swept wing segment and an aft swept wing segment. A center oblique airfoil section 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. Preferably, the aircraft is an all-wing aircraft. | ||||||
| 184 | PAYLOAD USE OF WING TO BODY VOLUME IN AN ELLIPTICAL FUSELAGE | US13293958 | 2011-11-10 | US20130119198A1 | 2013-05-16 | Lowell B. Campbell |
| An aircraft passenger cabin in an aircraft fuselage wherein an upper portion of the cabin volume is a substantially elliptical cross section and a lower portion of the cabin volume is a cross section extending laterally into a blended area of the wing and fuselage typically referred to as a wing to body fairing. | ||||||
| 185 | Swept-wing powered-lift aircraft | US12410894 | 2009-03-25 | US08403256B1 | 2013-03-26 | Robert D Gregg, III; Aaron J. Kutzmann; David J. Manley; John C. Vassberg; Neal Harrison; Max Kismarton |
| Apparatus and methods provide for a swept-wing powered-lift aircraft. Aspects of the disclosure provide a powered-lift aircraft that utilizes the engine exhaust flow over upper surface blown flaps to increase lift during various flight operations. The powered-lift aircraft has wings with inboard portions and outboard portions. The adjacent inboard and outboard portions share a swept leading edge. The leading edge is swept to a degree that shifts the outboard portion rearward to a position in which the aircraft center of lift has little to no variance upon the activation or deactivation of a powered-lift system. | ||||||
| 186 | Blended wing aircraft | US12410880 | 2009-03-25 | US08353478B1 | 2013-01-15 | 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. | ||||||
| 187 | System and method for varying the porosity of an aerodynamic surface | US12105450 | 2008-04-18 | US08251317B2 | 2012-08-28 | Dale M. Pitt |
| A variable porosity system for an aircraft includes a first layer, a second layer and an actuator mechanism. Each of the first and second layers has at least one pore and are slidable relative to one another. The actuator mechanism is operative to move the first and second layers relative to one another such that the pores are movable into and out of at least partial alignment with one another to allow for fluid communication therebetween. At least one of the first and second layers is substantially continuous with an outer mold line surface of an aerodynamic member such as an aircraft wing. The actuator mechanism is configured to modulate the frequency of the opening and closing of the pores with respect to flight conditions of an aircraft. | ||||||
| 188 | SUPERSONIC FLYING WING | US13263477 | 2010-04-26 | US20120037751A1 | 2012-02-16 | GeCheng Zha |
| A bidirectional flying wing maximizes efficiency and reduces sonic boom during supersonic flight. The flying wing has bilateral symmetry across two perpendicular planes and a substantially isentropic compression bottom surface that minimizes the shock wave projected downward during flight. The flying wing may be rotated to provide a high aspect ratio and a low sweep angle during subsonic flight. The flying wing may be rotated to provide a low aspect ratio and a high sweep angle during supersonic flight. | ||||||
| 189 | DISCRETE CO-FLOW JET (dCFJ) AIRFOIL | US13102844 | 2011-05-06 | US20110210211A1 | 2011-09-01 | 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. | ||||||
| 190 | Emergency Evacuation System, in Particular for a Tailless Aeroplane | US11992274 | 2006-09-14 | US20100243814A1 | 2010-09-30 | André Anger; Wolfram Schöne |
| A device for selective emergency evacuation of persons from a first level to a second level situated above the first level, or to a third level situated below the first level. For evacuation to the second level a stair arrangement is provided. One end of the device is connected to the first level while the other end is displaceable between the second level and the third level or vice versa. For evacuation to the third level, the device is changeable to a slide. The device may provide for emergency evacuation of persons from a first level deck, or passenger deck of a blended wing-body aircraft, selectively to the top, second level of the aircraft, or to the bottom third level of the aircraft. | ||||||
| 191 | CANARDED DELTOID MAIN WING AIRCRAFT | US12764925 | 2010-04-21 | US20100224735A1 | 2010-09-09 | Faruk Dizdarevic; Mithad Dizdarevic |
| Canarded deltoid main wing aircraft idea allows for design of large supersonic civil and military aircraft with cruising speeds of up to Mach 3 at the altitude of over 25,000 meters. The fuel consumption per unit of payload of such aircraft would be at least twice lower with a longer range of over 50% when compared to existing supersonic aircraft of the same size. Simultaneously, the flight safety and ride quality during takeoff and landing at low speeds would be similar to the existing subsonic passenger aircraft. A low fuel consumption, long range, high ride quality, and high flight safety of these aircraft are widely opening a door for design of supersonic long range continental and intercontinental passenger aircraft that would be highly competitive with existing long range high subsonic passenger aircraft. | ||||||
| 192 | Aircraft having a pivotable powerplant | US11451216 | 2006-06-12 | US07766275B2 | 2010-08-03 | Arthur V. Hawley |
| Aircraft including an airframe having a fuselage extending between a forward end and an aft end opposite the forward end. The aircraft further includes a powerplant pivotally connected to the fuselage adjacent the aft end. The powerplant produces exhaust during operation of the aircraft. The powerplant is selectively pivotable to direct exhaust at multiple angles with respect to the fuselage. | ||||||
| 193 | Systems and methods for controlling flows with electrical pulses | US11649706 | 2007-01-03 | US07744039B2 | 2010-06-29 | Richard B. Miles; Sergey O. Macheret; Mikhail Shneider; Alexandre Likhanskii; Joseph Steven Silkey |
| Systems and methods for controlling flow with electrical pulses are disclosed. An aircraft system in accordance with one embodiment includes an aerodynamic body having a flow surface exposed to an adjacent air stream, and a flow control assembly that includes a first electrode positioned at least proximate to the flow surface and a second electrode positioned proximate to and spaced apart from the first electrode. A dielectric material can be positioned between the first and second electrodes, and a controller can be coupled to at least one of the electrodes, with the controller programmed with instructions to direct air-ionizing pulses to the electrode, and provide a generally steady-state signal to the electrode during intervals between the pulses. | ||||||
| 194 | SAIL WING AIRCRAFT WHICH INCLUDES AN ENGINE MOUNTED ON A PYLON | US12509906 | 2009-07-27 | US20100108802A1 | 2010-05-06 | Hervé MARCHE; Fabien RAISON |
| Sail wing aircraft which includes a wing (6) and at least one propulsion engine (8). It includes an upper beam (22) which is firmly fixed at its front end to a first frame (12) located on an air inlet (14) of the propulsion engine and which is in addition firmly fixed at its median part to a second frame (16) located to the rear of the first frame. The sail wing aircraft includes in addition a pylon (26) for attachment of the engine onto the fuselage, where the engine is fixed to the pylon (26). | ||||||
| 195 | Cross-flow fan propulsion system | US11379731 | 2006-04-21 | US07641144B2 | 2010-01-05 | Joseph D. Kummer; Thong Q. Dang |
| A cross-flow propulsion mechanism for use in providing propulsion to an aircraft, includes a housing defining an inlet, a rotor compartment, and an outlet. The inlet is adapted to receive an inflow of air along a first longitudinal axis. The rotor is mounted within the rotor compartment and adapted to receive the airflow introduced into the housing through the inlet and rotate about a second longitudinal axis that is substantially perpendicular to the first longitudinal axis. The outlet is adapted to receive the airflow processed through the rotor and exhaust air along a third longitudinal axis that is substantially parallel to the first longitudinal axis. The propulsion mechanism can be applied in a personal aircraft, an STOL aircraft, and a hybrid automobile and aircraft. | ||||||
| 196 | Stealth bomber, transporter, air-to-air fueling tanker, and space plane | US11789718 | 2007-04-25 | US07618005B1 | 2009-11-17 | Samuel Barran Tafoya |
| A stealth transporter aircraft having a rhomboid airframe with a dihedral bottom surface and a top surface designed as an airfoil. The rhomboid cross-sectional configuration of the airframe gives it increased lift, stealth characteristics, and enhanced load bearing capacity. The aircraft does not have conventional wing structure and its dihedral bottom surface allows it to make wheels-up emergency landings on water and hard runway surfaces with greater pilot survivability. A rigid central tubular area extending nearly the full length of the airframe is configured for passengers, luggage, munitions, and/or equipment and provides a backbone for the aircraft. The aircraft further has rear engines, a large fuel carrying capability, and may also undergo primarily interior modifications for function as a space plane or air-to-air fueling tanker. A vortex spoiler on the side edges of the airframe is also preferred, which eliminates trails while in high altitude flight. | ||||||
| 197 | PARAMETRIC GEOMETRY MODEL FOR A BLENDED WING BODY | US11958143 | 2007-12-17 | US20090152392A1 | 2009-06-18 | Thomas A. Hogan; Christopher K. Droney; Dino Roman |
| Lofting of a Blended Wing Body air vehicle is accomplished by first determining the required payload volume of the air vehicle. The payload volume is then analyzed to determine a list of corner points of the payload volume. The list of points is passed to a Loft Module as keep-out points and a body portion of the blended wing body is established using a faceted minimum volume which encloses all of the provided keep-out points. A trapezoidal wing shape and size is then determined to accommodate aerodynamic performance requirements. 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 all other point coordinates and all tangents and remaining curvatures to smoothly enclose the payload volume in a first set of aerodynamic sections are defined. The aerodynamic requirements of the trapezoidal wing including Wing Thickness, Camber, Twist and Shear establish a second set of aerodynamic sections and sections in a transition region between the body portion and the trapezoidal wing are then defined. The blended wing body is then lofted based on the first plurality of sections, second plurality of sections and transition sections. | ||||||
| 198 | Aircraft with forward opening inlay spoilers for yaw control | US11023949 | 2004-12-28 | US07448578B2 | 2008-11-11 | Walter Dennis Clark |
| An aircraft comprises first and second wings positioned on opposite sides of a longitudinal axis with each of the first and second wings including an upper surface and a lower surface, wherein no control surfaces are attached to the lower surface of the wings. A first forward opening control surface is attached by a first hinge to an upper surface of the first wing and a second forward opening control surface being attached by a second hinge to an upper surface of the second wing. Each of the first and second hinges is canted with respect to a direction perpendicular to the longitudinal axis. A method of yaw control performed by the aircraft is also included. | ||||||
| 199 | HYDROGEN FUELED BLENDED WING BODY RING TANK | US11559615 | 2006-11-14 | US20080230654A1 | 2008-09-25 | Alexander Velicki; Daniel A. Hansen |
| A toroidal shaped or ring fuel tank located within the loft line of a blended wing body aircraft is disclosed. The ring tank may be used in an aircraft to store liquid hydrogen fuel with a reduced tank weight. The ring tank may be continuous with no tank end domes typically found on cylindrical pressure tanks, reducing tank weight for a given fuel volume. The ring tank configuration avoids increasing the aerodynamic shape of the aircraft and does not encroach on usable passenger or payload areas of the aircraft. In one example the ring tank may be configured in a nose down position such that the forward portion of the ring tank is outside the pressurized cabin area. | ||||||
| 200 | Systems and methods for controlling flows with electrical pulses | US11649706 | 2007-01-03 | US20080023589A1 | 2008-01-31 | Richard Miles; Sergey Macheret; Mikhail Shneider; Alexandre Likhanskii; Joseph Silkey |
| Systems and methods for controlling flow with electrical pulses are disclosed. An aircraft system in accordance with one embodiment includes an aerodynamic body having a flow surface exposed to an adjacent air stream, and a flow control assembly that includes a first electrode positioned at least proximate to the flow surface and a second electrode positioned proximate to and spaced apart from the first electrode. A dielectric material can be positioned between the first and second electrodes, and a controller can be coupled to at least one of the electrodes, with the controller programmed with instructions to direct air-ionizing pulses to the electrode, and provide a generally steady-state signal to the electrode during intervals between the pulses. | ||||||
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