Lifting Fuselages Patents (Class 244/36)
  • Patent number: 11008088
    Abstract: A method for operating a wing (5) including a fixed wing (9), a foldable wing tip portion (11) mounted to the fixed wing (9) pivotally between an extended position and a folded position, an actuation unit (13) for actuating movement of the foldable wing tip portion (11), and an arresting unit (15) for locking the foldable wing tip portion (11) in the extended position and/or in the folded position. The method includes controlling the actuation unit (13) to move the foldable wing tip portion (11) either to the extended position or to the folded position until the foldable wing tip portion (11) or the actuation unit (13) contacts a stop element (28), continuing actuation until the actuation unit (13) reaches a stall condition, detecting the stall condition of the actuation unit (13), and locking the arresting unit (15) upon detection of the stall condition.
    Type: Grant
    Filed: November 16, 2018
    Date of Patent: May 18, 2021
    Assignee: Airbus Operations GmbH
    Inventors: Saskia Dege, Svenja Jegminat
  • Patent number: 10815010
    Abstract: An air launched rocket for placing payloads in earth orbit comprising a lifting body having a cross sectional shape of an airfoil extending in a spanwise direction between a first and a second wing tip. The lifting body further comprises at least one rocket engine positioned at the first wing tip oriented for propelling the lifting body in the spanwise direction. The air launched rocket is combined with a carrier aircraft which is removably attached to a suction surface of the airfoil.
    Type: Grant
    Filed: December 27, 2017
    Date of Patent: October 27, 2020
    Assignee: Intercept Nexus, LLC
    Inventor: Kyle Snowberger
  • Patent number: 10787255
    Abstract: An aircraft capable of vertical take-off and landing comprises a fuselage, at least one processor carried by the fuselage and a pair of aerodynamic, lift-generating wings extending from the fuselage. A plurality of vectoring rotors are rotatably carried by the fuselage so as to be rotatable between a substantially vertical configuration relative to the fuselage for vertical take-off and landing and a substantially horizontal configuration relative to the fuselage for horizontal flight. The vectoring rotors are unsupported by the first pair of wings. The wings may be modular and removably connected to the fuselage and configured to be interchangeable with an alternate pair of wings. A cargo container may be secured to the underside of the fuselage, and the cargo container may be modular and interchangeable with an alternate cargo container.
    Type: Grant
    Filed: November 18, 2019
    Date of Patent: September 29, 2020
    Assignee: SKY CANOE INC.
    Inventor: Dale Arthur George
  • Patent number: 10696378
    Abstract: Described herein is vehicle comprising a body. The vehicle also comprises a cargo door assembly, coupled to the body. The cargo door assembly comprises a first door, movable, relative to the body, between a first closed position and a first open position. The cargo door assembly also comprises a first aerodynamics control surface, coupled to the first door and selectively movable relative to the first door. The preceding subject matter of this paragraph characterizes example 1 of the present disclosure.
    Type: Grant
    Filed: October 20, 2017
    Date of Patent: June 30, 2020
    Assignee: The Boeing Company
    Inventors: Norman H. Princen, Jaime E. Baraja, Benjamin A. Harber
  • Patent number: 10407887
    Abstract: A self-cleaning floor assembly is configured to form or be positioned on a floor of an enclosed space. The self-cleaning floor assembly includes a moveable floor including a moveable floor panel, an actuation system that is operatively coupled to the floor panel, and a cleaning system proximate to at least a portion of the moveable floor. The actuation system is configured to move at least a portion of the floor panel into and through the cleaning system during a cleaning cycle. The cleaning system is configured to clean the portion(s) of the floor panel during the cleaning cycle.
    Type: Grant
    Filed: June 8, 2016
    Date of Patent: September 10, 2019
    Assignee: The Boeing Company
    Inventor: Charles C. Jensen
  • Patent number: 9376207
    Abstract: A system is disclosed including at least one indexing stub secured to a fuselage in the place of one or more wing stubs and including indexing members protruding from opposite sides of the fuselage. A pair of receivers are mounted to a container and define channels to receive the indexing members. The channels may include an upper flared portion and a lower straight portion. The indexing members are lowered into the channels and the flared portions guide the indexing members into the straight portions. In some embodiments, a pair of clamping members are configured to selectively lock the indexing members within the channels. The indexing members may have a cylindrical shape and may be rotatably mounted to the at least one indexing stub.
    Type: Grant
    Filed: August 23, 2013
    Date of Patent: June 28, 2016
    Assignee: Becklin Holdings, Inc.
    Inventors: Dennis S. Becklin, Dean A. Weathers, Adrian P. Tayne
  • Patent number: 9120552
    Abstract: Aircraft engineering applicable for improving aerodynamic quality of helicopters, airplanes, including big airbuses and amphibian airplanes, aerodynamic ground-effect and air-cushion vehicles, by reducing contact area between the external fuselage tail section surface and a high-speed air flow, area of contact is reduced by increasing surface area of holes in the fuselage tail section. To increase lifting force without increasing pressure resistance, the aerodynamic channel bottom is convex upwards, for example, curved upwards according to the shape of the airfoil convex side. The upper hole for the aerodynamic channel in the fuselage skin may be located along the fin middle portion divided lengthwise by the fin to right and left, in two. The aerodynamic channel is made through and may be open. The upper front edge aligned hole of the aerodynamic channel has a greater surface area than the rear hole aligned with the fuselage end.
    Type: Grant
    Filed: September 6, 2012
    Date of Patent: September 1, 2015
    Inventors: Gennady Trofimovich Kreshchishin, Larisa Trofimovna Kreshchishina
  • Patent number: 9090328
    Abstract: Provided is a fuselage segment that extends in a longitudinal fuselage segment axis and is closed in a circumferential direction around this longitudinal fuselage segment axis. The fuselage segment features a plurality of shell components for forming a skin of the fuselage segment that respectively feature two first shell component edges extending along a longitudinal shell component direction and two second shell component edges extending along a lateral shell component direction. The shell components are respectively connected to at least one adjacent shell component along at least one first shell component edge and along at least one second shell component edge. Methods for manufacturing such a fuselage segment are also provided.
    Type: Grant
    Filed: September 20, 2012
    Date of Patent: July 28, 2015
    Assignee: Airbus Operations GmbH
    Inventor: Robert Alexander Goehlich
  • Publication number: 20150122942
    Abstract: The object of the invention is a method for generating lift for an airborne flying device, which has a wing part and/or a fuselage part generating lift by means of interactive movement between the air and the device. In the method, in the frontal view area of the lift-generating part of the device is arranged at least one counterflow impulse surface (1), which is formed by a planar or curved surface extending forward in the direction of travel from the lower surface (2) of the wing and/or fuselage and obliquely upwards, and which generates at least the main part of the lift when the airflow hits this inclined impulse surface and bends when the device is airborne.
    Type: Application
    Filed: February 6, 2012
    Publication date: May 7, 2015
    Inventors: Raimo Hirvinen, Jani Hirvinen, Toni Hirvinen
  • Patent number: 8967526
    Abstract: A flight-operable, truly modular aircraft has an aircraft core to which one or more of outer wings members, fuselage, cockpit, leading and trailing edge couplings, and empennage and tail sections can be removably coupled and/or replaced during the operating life span of the aircraft. In preferred embodiments the aircraft core houses the propulsive engines, avionics, at least 80% of the fuel, and all of the landing gear. The aircraft core is preferably constructed with curved forward and aft composite spars, that couple to outer wing sections and possibly other sections using hardpoints. The aircraft core preferably has a large central cavity dimensioned to interchangeably carry an ordnance launcher, a surveillance payload, electronic countermeasures, and other types of cargo. Contemplated aircraft can be quite large, for example having a wing span of at least 80 ft.
    Type: Grant
    Filed: August 9, 2011
    Date of Patent: March 3, 2015
    Inventor: Abe Karem
  • Publication number: 20140231593
    Abstract: A flight-operable, truly modular aircraft has an aircraft core to which one or more of outer wings members, fuselage, cockpit, leading and trailing edge couplings, and empennage and tail sections can be removably coupled and/or replaced during the operating life span of the aircraft. In preferred embodiments the aircraft core houses the propulsive engines, avionics, at least 80% of the fuel, and all of the landing gear. The aircraft core is preferably constructed with curved forward and aft composite spars, that transfer loads across the center section, while accommodating a mid-wing configuration. The aircraft core preferably has a large central cavity dimensioned to interchangeably carry an ordnance launcher, a surveillance payload, electronic countermeasures, and other types of cargo. Contemplated aircraft can be quite large, for example having a wing span of at least 80 ft.
    Type: Application
    Filed: March 11, 2014
    Publication date: August 21, 2014
    Inventor: Abe Karem
  • Publication number: 20140175215
    Abstract: 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.
    Type: Application
    Filed: December 23, 2013
    Publication date: June 26, 2014
    Inventors: Guillaume Gallant, Romain Delahaye
  • Publication number: 20140103159
    Abstract: Aircraft comprising a single wing suspended under a closed sided chassis. The wing spar is mounted to the sides that enclose and channel the airflow over and under the wing to provide lift. Airflow is provided by a source located in front of the wing by means of either propeller, ducted fan or similar devise. Engines mounted on a rotational engine mount can provide downward thrust to lift front of craft to obtain an angle great enough for lift-off Once aircraft has sustained-angle for lift off engine(s) rotate to produce airflow parallel to wing for flight. Rudders mounted behind the air source and prior to the wing provide steering.
    Type: Application
    Filed: October 17, 2012
    Publication date: April 17, 2014
    Inventor: Wayne Curtis Bert
  • Patent number: 8672259
    Abstract: A supersonic aircraft design using compression lift for enhanced cruise performance. Each engine nacelle at mid-span has a vertical wedge at the nose which creates shock waves under the wings. The increased pressure behind the shock waves pushes up on the wings, creating compression lift. The second part of the process is trapping the shocks by some vertical surfaces. The inboard shocks are intercepted by a keel under the fuselage. This causes the reflected shock effect, which increases compression lift. The keel is just wide enough to store the main landing gear's wheel bogies one behind the other. One strut carrying a wheel bogie retracts upward and forward. The other strut retracts upward and backward. This allows tandem bogie storage in the narrow keel, which reduces drag. Outboard shocks are trapped by wingtip fins with pointed noses to reduce shock interference at the point of shock trapping.
    Type: Grant
    Filed: June 22, 2012
    Date of Patent: March 18, 2014
    Inventor: Patrick Andrew Kosheleff
  • Publication number: 20130341459
    Abstract: A supersonic aircraft design using compression lift for enhanced cruise performance. Each engine nacelle at mid-span has a vertical wedge at the nose which creates shock waves under the wings. The increased pressure behind the shock waves pushes up on the wings, creating compression lift. The second part of the process is trapping the shocks by some vertical surfaces. The inboard shocks are intercepted by a keel under the fuselage. This causes the reflected shock effect, which increases compression lift. The keel is just wide enough to store the main landing gear's wheel bogies one behind the other. One strut carrying a wheel bogie retracts upward and forward. The other strut retracts upward and backward. This allows tandem bogie storage in the narrow keel, which reduces drag. Outboard shocks are trapped by wingtip fins with pointed noses to reduce shock interference at the point of shock trapping.
    Type: Application
    Filed: June 22, 2012
    Publication date: December 26, 2013
    Inventor: Patrick Andrew Kosheleff
  • Publication number: 20130306788
    Abstract: An unmanned air system and method with blown flaps are presented. Air is guided to a fuel cell carried by the unmanned air system. The fuel cell is ventilated by the guided air such that the air is heated by the fuel cell to provide heated air. The heated air is routed from the fuel cell to one or more high lift devices on a lift device of the unmanned air system to provide routed air. The routed air is blown across the high lift devices.
    Type: Application
    Filed: March 21, 2013
    Publication date: November 21, 2013
    Applicant: The Boeing Company
    Inventor: The Boeing Company
  • Patent number: 8485476
    Abstract: 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.
    Type: Grant
    Filed: May 6, 2011
    Date of Patent: July 16, 2013
    Assignee: University of Miami
    Inventors: Gecheng Zha, Bertrand P. E. Dano
  • Patent number: 8453963
    Abstract: An amphibious large aircraft without traditional airstairs is disclosed. With its flat and oblong fuselage, said amphibious large aircraft has wing-in-ground effect in addition to generating elevating force in flight. Thus, said amphibious large aircraft has smooth takeoff and touchdown on the runway as well as on broad water area. The flight efficiency is increased by 30-40%. The fuselage has only one floor, wherein the passenger cabin is set in the front of the fuselage, and the cargo hold is mounted above the rear. The wings are extended towards two sides from upper side of the fuselage. A jet engine is mounted above the rear of the fuselage and adjacent to the tail wing. Passengers can go on and off the amphibious large aircraft directly without the need of airstairs and can escape from the aircraft directly without the need of an inflator slide during an emergency.
    Type: Grant
    Filed: March 1, 2010
    Date of Patent: June 4, 2013
    Inventor: Shiying Liu
  • Patent number: 8448893
    Abstract: Aircraft configured to operate at Mach numbers from above 0.80 and up to 1.2 with wing sweep angles defined by the wing outboard leading edge of less than 35 degrees, and incorporating calculated values of the ratio of outboard wing panel aspect ratio raised to an exponent of 0.78, divided by the ratio of maximum thickness divided by chord (t/c), greater than about 45, characterized by one of the following: a) where maximum thickness divided by chord (t/c) is at a location approximately 70% of the distance outboard from the attaching aircraft body to the wing tip, or b) where maximum thickness divided by chord (t/c) is the average value of (t/c)'s located between approximately 50% of the distance outboard from the attaching aircraft body to the wing tip.
    Type: Grant
    Filed: January 25, 2011
    Date of Patent: May 28, 2013
    Assignee: Aerion Corporation
    Inventors: Richard R. Tracy, James D. Chase
  • Patent number: 8408490
    Abstract: 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.
    Type: Grant
    Filed: August 29, 2008
    Date of Patent: April 2, 2013
    Assignee: Advanced Product Development, LLC
    Inventor: William R McDonnell
  • Publication number: 20120292435
    Abstract: A flight-operable, truly modular aircraft has an aircraft core to which one or more of outer wings members, fuselage, cockpit, leading and trailing edge couplings, and empennage and tail sections can be removably coupled and/or replaced during the operating life span of the aircraft. In preferred embodiments the aircraft core houses the propulsive engines, avionics, at least 80% of the fuel, and all of the landing gear. The aircraft core is preferably constructed with curved forward and aft composite spars, that couple to outer wing sections and possibly other sections using hardpoints. The aircraft core preferably has a large central cavity dimensioned to interchangeably carry an ordnance launcher, a surveillance payload, electronic countermeasures, and other types of cargo. Contemplated aircraft can be quite large, for example having a wing span of at least 80 ft.
    Type: Application
    Filed: August 9, 2011
    Publication date: November 22, 2012
    Inventor: Abe Karem
  • Publication number: 20120256043
    Abstract: An airborne vehicle having a wing-body which defines a wing-body axis and appears substantially annular when viewed along the wing-body axis, the interior of the annulus defining a duct which is open at both ends. A propulsion system is provided comprising one or more pairs of propulsion devices, each pair comprising a first propulsion device mounted to the wing-body and positioned on a first side of a plane including the wing-body axis, and a second propulsion device mounted to the wing-body and positioned on a second side of the plane including the wing-body axis.
    Type: Application
    Filed: May 8, 2012
    Publication date: October 11, 2012
    Applicant: GO SCIENCE LIMITED
    Inventor: Harry George Dennis Gosling
  • Patent number: 8282036
    Abstract: 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.
    Type: Grant
    Filed: December 15, 2009
    Date of Patent: October 9, 2012
    Inventor: Stephen H. Funck
  • Patent number: 8272594
    Abstract: A method of providing an aircraft having a fuselage and a wing configured for extensive laminar flow at design cruise conditions, the method characterized by a) providing wing biconvex-type airfoils having values of thickness, chord and shape along the wing span which provide substantially optimal aircraft range at design cruise conditions, considering the influences of wing drag and wing weight; b) providing wing leading edges, which are configured to effect laminar flow; c) providing fuselage and wing contours which, in combination, produce reduced total wave drag and produce extensive areas of laminar boundary layer flow on the wing; and d) providing wing sweep angularity that facilitates provision of a), b) and c).
    Type: Grant
    Filed: October 26, 2009
    Date of Patent: September 25, 2012
    Assignee: Aerion Corporation
    Inventors: Richard R. Tracy, Peter Sturdza, James D. Chase
  • Patent number: 8262031
    Abstract: 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.
    Type: Grant
    Filed: May 12, 2008
    Date of Patent: September 11, 2012
    Assignee: University of Miami
    Inventors: Gecheng Zha, Sebastian Aspe, Joseph John Dussling, Nicholas Ramsay Heinz, Daniel J. Martinez
  • Patent number: 8256706
    Abstract: Methods, aircraft, and engine nacelles are disclosed. A wing leading edge of a planform is superimposed on a wing shockwave that extends in a first direction from a shockwave apex toward the wing leading edge. A waverider shape is streamline traced between the wing leading edge and a trailing edge of the planform to form a waverider wing. A position of an engine inlet vertex relative to the waverider wing is identified. An inlet shockwave is projected from the inlet vertex in a second direction generally opposed to the first direction. The inlet shockwave intersects the wing shockwave. An inlet leading edge of an engine inlet includes a lower leading edge including a plurality of points where the inlet shockwave intersects the wing shockwave.
    Type: Grant
    Filed: October 8, 2009
    Date of Patent: September 4, 2012
    Assignee: The Boeing Company
    Inventors: Thomas R. Smith, Kevin G. Bowcutt
  • Patent number: 8251310
    Abstract: 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).
    Type: Grant
    Filed: July 27, 2009
    Date of Patent: August 28, 2012
    Assignee: Airbus Operations SAS
    Inventors: Herve Marche, Fabien Raison
  • Patent number: 8210472
    Abstract: Disclosed is a method for improving the performance of transport aircraft. In particular, the aircraft is provided with a rounded nose cone in front of a center of gravity of the aircraft. The rounded nose cone has an upper longitudinal surface and a lower longitudinal surface configured, respectively, to generate a lifting force and a negative lifting force and produce a resultant that is lifting and to produce an auxiliary nose-up moment. The method involves shaping the nose cone to increase the lifting resultant. This shaping is carried out-by increasing the upper longitudinal surface of the nose cone, so as to increase the lifting force, and by reducing the lower longitudinal surface of the nose cone, so as to decrease the negative lifting force.
    Type: Grant
    Filed: October 20, 2009
    Date of Patent: July 3, 2012
    Assignee: Airbus Operations SAS
    Inventors: Lionel Espagnan, Arnaud Hormiere, Francois Guillaumel
  • Patent number: 8205824
    Abstract: An aircraft fuselage structure is described for a flying-wing aircraft, having a central area of slight curvature and side areas of greater curvature, which forms a pressure body and has an outer skin and structure reinforcements which support the outer skin. According to the invention, the structure reinforcements contain three-dimensional truss bending supports which extend over the area of light curvature and comprise first straps, which run close to the outer skin 9, and second straps, which run at a distance from the outer skin, and are connected to one another by coupling elements.
    Type: Grant
    Filed: March 17, 2008
    Date of Patent: June 26, 2012
    Assignee: Airbus Deutschland GmbH
    Inventor: Joern Goos
  • Patent number: 8191820
    Abstract: The invention is an aircraft that includes a flying wing having a plurality of extendable flaps mounted on the trailing edge of the flying wing. A canard is mounted on the nose of said flying wing. A system is mounted in the flying wing for providing high pressure air over the canard and the flaps. A second system is provided for controlling the flow of air over the canard to provide pitch control of the aircraft.
    Type: Grant
    Filed: December 11, 2007
    Date of Patent: June 5, 2012
    Assignee: Northrop Gurmman Corporation
    Inventors: Bryan Wayne Westra, Roxanne Marie Sato, Douglas Ellwood Shultz, James Franklin Kerswell, Perry Bruce Petersen, Scott Walter Collins
  • Publication number: 20120091262
    Abstract: An aircraft may include a pair of wings. A forward swept winglet may be attached proximate to a wing tip of each wing. The forward swept winglet may include a leading edge and a trailing edge. The leading edge of each winglet may extend from the wing at a predetermined forward sweep angle relative to a line perpendicular to a chord of the wing tip in a direction corresponding to a forward portion of the aircraft.
    Type: Application
    Filed: October 15, 2010
    Publication date: April 19, 2012
    Applicant: THE BOEING COMPANY
    Inventors: Blaine K. RAWDON, John C. VASSBERG
  • Patent number: 8157204
    Abstract: Symmetric external parts of a front lower aircraft wing sweep forward such that lift generated by a rear upper wing is greater than lift generated by the front lower wing. The rear upper wing is in direct contact with rear upper parts of fuselages. A propulsion system of the aircraft has a turboprop engine and is carried by an internal part of the rear upper wing, with the propulsion system lying in a longitudinal mid-plane.
    Type: Grant
    Filed: October 15, 2008
    Date of Patent: April 17, 2012
    Assignee: Airbus
    Inventor: Richard Wilby
  • Publication number: 20110309187
    Abstract: An aircraft, with the ability to cruise at supersonic speeds, designed to increase cruise lift/drag ratio, reduce sonic boom and have greater downward visibility by having an ‘inverted’ nose profile that has greater inclination of the lower surfaces to the flight direction than the upper surfaces.
    Type: Application
    Filed: August 26, 2011
    Publication date: December 22, 2011
    Inventor: Sudarshan Paul Dev
  • Patent number: 8056852
    Abstract: 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.
    Type: Grant
    Filed: February 21, 2011
    Date of Patent: November 15, 2011
    Inventors: Faruk Dizdarevic, Mithad Dizdarevic
  • Patent number: 7988088
    Abstract: An air transport vehicle of the present invention comprises a tubular body, said body comprising an upper half and a lower half. The upper half is positioned above the lower half and connected thereto. A central bore is formed between the upper half and the lower half. The bore extends longitudinally from the nose end of the vehicle to the tail end of the vehicle. The vehicle also comprises at least one propulsion device, preferably positioned inside the bore. The vehicle further comprises at least one bulkhead. The bulkhead connects the upper half to the lower half, and extending longitudinally inside the bore, thus dividing the bore into parallel subsections. In preferred embodiments, the upper half and the lower half comprise cavities, used among other things, for cargo and passenger transport.
    Type: Grant
    Filed: June 5, 2008
    Date of Patent: August 2, 2011
    Inventor: Alexandr Konstantinovskiy
  • Publication number: 20110121130
    Abstract: 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.
    Type: Application
    Filed: November 21, 2009
    Publication date: May 26, 2011
    Inventors: Richard C. Odle, Dino Roman, Blaine Knight Rawdon
  • Patent number: 7854409
    Abstract: 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.
    Type: Grant
    Filed: April 21, 2010
    Date of Patent: December 21, 2010
    Inventors: Faruk Dizdarevic, Mithad Dizdarevic
  • Publication number: 20100252674
    Abstract: Runway length requirement for take-off and landing of an aircraft is reduced by taking advantage of dynamic lift overshoot, and in some cases, dynamic stall. In take-off and landing, the angle of attack is rapidly increased so that the lift coefficient exceeds the maximum predicted by the steady flow lift curve. By increasing the angle of attack at an appropriate rate, the increased lift coefficient can be maintained, without loss of control, until the aircraft touches down in the case of a landing, or until the aircraft can begin a normal climb, in the case of take-off. A low aspect ratio lifting body is preferred because of its more gradual stall behavior, and the potential to use dynamic stall for further deceleration before touchdown. Vortex fences can be oscillated to delay the onset of stall, and, in cruise, to energize the boundary-layer and reduce drag and/or control roll and/or yaw.
    Type: Application
    Filed: January 16, 2007
    Publication date: October 7, 2010
    Applicant: Aereon Corporation
    Inventor: James D. Lang
  • Publication number: 20100243795
    Abstract: 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.
    Type: Application
    Filed: August 29, 2008
    Publication date: September 30, 2010
    Applicant: ADVANCED PRODUCT DEVELOPMENT, LLC
    Inventor: William R McDonnell
  • Patent number: 7793884
    Abstract: “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.
    Type: Grant
    Filed: December 31, 2008
    Date of Patent: September 14, 2010
    Inventors: Faruk Dizdarevic, Mithad Dizdarevic
  • Publication number: 20100213308
    Abstract: Provided is a positive-pressure floating type airplane comprising an airfoil portion, left-right fuselages, a central fuselage, an elevator and a rudder disposed at the back of the airfoil portion, a thruster disposed at the back of the central fuselage, and a horizontal stabilizer disposed at the rear ends of the left-right fuselages. The individual front ends of the airfoil portion, the left-right fuselages and the central fuselage are formed into arcuate shapes in longitudinal sections. On the lower side of the airfoil portion, a recessed air capture is formed from the front end to the rear end. As a result, the positive-pressure floating type airplane is floated by the reaction from the air at the time when the air to pass the air capture through the airfoil portion is pushed by the thrust of the thruster, and is propelled forward by the component of that thrust.
    Type: Application
    Filed: August 12, 2008
    Publication date: August 26, 2010
    Inventor: Masahiko Suzuki
  • Patent number: 7766275
    Abstract: 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.
    Type: Grant
    Filed: June 12, 2006
    Date of Patent: August 3, 2010
    Assignee: The Boeing Company
    Inventor: Arthur V. Hawley
  • Publication number: 20100187352
    Abstract: The invention relates to multi deck passenger aircraft, having passenger cabins and/or service facilities arranged on the upper and lower deck and inner load bearing cell structure provided within aircraft body. The present invention is also directed toward methods for manufacturing derivative multi deck aircrafts. Energy absorbing, floatable cargo containers (24) attached to fuselage belly. External fuel tanks (26) displaced on the top of fuselage. Center wing region of the fuselage is using for arranging rows of seats and service facilities. Addition seating configuration for narrow and wide bodied aircraft is provided. Multi deck seating configuration significantly reduces per passenger operating cost over existing technology. Less fuel per passenger is required since there is less airframe weight and wetted area per passenger. Due to the lower overall cost per passenger seat within the multi deck seating structure, the net profit and return on investment in the aircraft are also increased.
    Type: Application
    Filed: January 29, 2008
    Publication date: July 29, 2010
    Applicant: Mr. Michael Yavilevich
    Inventor: Michael Yavilevich
  • Publication number: 20100163669
    Abstract: An aircraft structure is provided. The aircraft structure for an aircraft includes a fuselage, front wings, rear small wings, vertical winglets, and four levels. The fuselage has a cross-section of substantially a half circle fuselage shape. Being is wide enough to provide lifting force, and includes four levels separated by multi partition structure. The front wings are disposed horizontally in front portions of the fuselage. The rear small wings are disposed horizontally in rear portions of the fuselage. The vertical winglets are disposed at the wingtips of the rear small wings. The first level disposed at a bottom of the four levels includes a fuel tank storages and a plurality of landing gear bays. The second level disposed at a middle of the four levels includes cargo bay. The third level may comprise a top cockpit and a plurality of passenger cabins. The fuselage provides major portion of lifting force and the wings provides steering force, and lifting force.
    Type: Application
    Filed: December 29, 2008
    Publication date: July 1, 2010
    Inventor: Sunstar Im
  • Publication number: 20100163670
    Abstract: 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.
    Type: Application
    Filed: December 31, 2008
    Publication date: July 1, 2010
    Inventors: FARUK DIZDAREVIC, MITHAD DIZDAREVIC
  • Publication number: 20100102165
    Abstract: According to the invention, the nose cone (2.I) of the aircraft is modified so as to increase the lifting resultant (R?).
    Type: Application
    Filed: October 20, 2009
    Publication date: April 29, 2010
    Applicant: AIRBUS OPERATIONS
    Inventors: Lionel Espagnan, Arnaud Hormiere, Francois Guillaumel
  • Patent number: 7654489
    Abstract: A lifting body aircraft suitable for atmospheric flight and/or as a reentry vehicle. The craft has a substantially flat upper surface, a lower surface with a doubly convex first section and a flat sloping second section. Chines may be provided between the upper and lower surfaces. The doubly convex first section allows the craft to have its center of gravity forward of its longitudinal center line. The flat sloping second half of the lower surface and the substantially flat upper surface form the aft end of an airfoil. A pair of vertical stabilizers enhance stability and include rudders which, along with a pair of elevons, provide steerage. The craft may glide or it may have an engine or rockets for thrust. The result is an extremely stable lifting body design that is well suited for launch or conventional take off, insertion, orbital operations, reentry, atmospheric flight, and conventional landings.
    Type: Grant
    Filed: June 27, 2005
    Date of Patent: February 2, 2010
    Assignee: Aviation Dynamics, Corp
    Inventor: Jon C. Stephenson
  • Publication number: 20100012773
    Abstract: An aircraft structure is provided. The aircraft structure for an aircraft includes a fuselage, front wings, rear delta wings, vertical winglets, and three levels. The fuselage has a cross-section of substantially rectangular flat shape, being is wide enough to provide lifting force, and includes three levels separated by multi-partition structure. The front wings are disposed horizontally in front portions of the fuselage. The rear delta wings are disposed horizontally in rear portions of the fuselage. The vertical winglets are disposed at wingtips of the rear delta wings. The first level disposed at a bottom of the three levels includes a cargo bay and a plurality of landing gear bays. The second level disposed at a middle of the three levels includes fuel tank storages. The third level may comprise a top cockpit and a plurality of passenger cabins. The fuselage provides major portion of lifting force and the wings provides steering force.
    Type: Application
    Filed: July 16, 2008
    Publication date: January 21, 2010
    Inventor: Sunstar IM
  • Patent number: 7618005
    Abstract: 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.
    Type: Grant
    Filed: April 25, 2007
    Date of Patent: November 17, 2009
    Inventor: Samuel Barran Tafoya
  • Publication number: 20090230238
    Abstract: An aircraft fuselage structure is described for a flying-wing aircraft, having a central area of slight curvature and side areas of greater curvature, which forms a pressure body and has an outer skin and structure reinforcements which support the outer skin. According to the invention, the structure reinforcements contain three-dimensional truss bending supports which extend over the area of light curvature and comprise first straps, which run close to the outer skin 9, and second straps, which run at a distance from the outer skin, and are connected to one another by coupling elements.
    Type: Application
    Filed: March 17, 2008
    Publication date: September 17, 2009
    Inventor: Joern Goos