Variable Patents (Class 244/46)
  • Patent number: 6547181
    Abstract: A variable sweep winglet with a negative dihedral angle is provided for a ground effect vehicle. The winglet is positionable at a sweep angle to control the winglet tip clearance from ground. Variable winglet tip clearance reduces the risk of damage or instability due to collision with the ground or water, thereby permitting more efficient flight at lower altitude with an equivalent safety. The winglet is generally positioned by an actuator. The actuator is controlled by a flight control system, or by other manual or automatic systems. A sensor may also be included for determining whether an object lies in the path of the winglet. The sensor communicates with the flight control system in order to vary the sweep of the winglet to increase clearance from the ground or water, thus avoiding impact with the object.
    Type: Grant
    Filed: May 29, 2002
    Date of Patent: April 15, 2003
    Assignee: The Boeing Company
    Inventors: Zachary C. Hoisington, Blaine K. Rawdon
  • Patent number: 6398157
    Abstract: An aircraft capable of vertical take off and normal cruise flight has a fuselage and a pair of wings, the wings being movable relative to the fuselage from a rearwardly swept position to which the wings are moved for vertical take off, to a spread position to which the wings are moved for normal cruise flight.
    Type: Grant
    Filed: December 18, 2000
    Date of Patent: June 4, 2002
    Assignee: GKN Westland Helicopter Limited
    Inventor: David Barry Ingram
  • Patent number: 6345790
    Abstract: A subsonic aircraft having backswept lifting wings is equipped with individually rotatable winglets at the wing tips thereof, in order to reduce drag during cruise flight, to minimize the dangers posed by wing tip vortices to following aircraft during take-off and landing, and to minimize the total wingspan during ground operations, with respective different positions of the winglets. A streamline-shaped rotation body made up of at least two individually rotatably supported rotation segments is mounted on the wing tip of each lifting wing. A respective winglet is mounted on each respective rotation segment. Each rotation segment with its associated winglet is individually rotatable about a rotation axis of the rotation body extending substantially parallel to the aircraft lengthwise axis. Thereby, each winglet is individually pivotable to any selected pivot angle relative to a horizontal plane extending through the rotation axis.
    Type: Grant
    Filed: June 12, 2000
    Date of Patent: February 12, 2002
    Assignee: DaimlerChrysler Aerospace Airbus GmbH
    Inventor: Wolfgang Brix
  • Patent number: 6202958
    Abstract: To maintain control accuracy for the pivotable rudder blades (14), which lie in a combustion chamber, of a guided projectile (12) which can be fired by means of propellent charge, there is provide a mounting arrangement in which the trunnions (20) of the rudder blade holders (16) of the diametrally mutually opposite rudder blades (14) are torsionally stiffly rigidly connected through an associated coupling element (32) which is limitedly resilient in the radial direction of the guided projectile (12).
    Type: Grant
    Filed: June 15, 1999
    Date of Patent: March 20, 2001
    Assignee: Diehl Stiftung & Co.
    Inventors: Josef Dommer, Werner Schroppel, Martin Staudenmeir
  • Patent number: 6116539
    Abstract: The instant invention generally relates to a forwardly swept wing 10 for an aircraft comprised of a pair of opposed single piece machined aluminum alloy wing boxes 20 and 40. Specifically, the invention provides for a forward swept wing construction utilizing known in the art computer numerical control machining techniques to produce an aluminum alloy wing 10 having an integral leading edge 24 thereby greatly reducing assembly time. A plurality of integral stiffeners 80 oriented at a forwardly swept angle of approximately 12 to 13 degrees between forward 62 and rear 64 spars provides for a wing 10 that minimizes the effects of aeroelastic divergence.
    Type: Grant
    Filed: March 19, 1999
    Date of Patent: September 12, 2000
    Assignee: Williams International Co. L.L.C.
    Inventors: Samuel B. Williams, John F. Jones
  • Patent number: 6089503
    Abstract: In accordance with the present invention, there is provided an aerodynamic control system which is attachable to an aircraft body and is operable between enhanced control and radar evasive modes. The aerodynamic control system is provided with an aerodynamic support structure which extends from the aircraft body. The support structure is rotatably attached to the aircraft body about a support structure rotational axis. The support structure has an outboard support and an inboard support which is disposed adjacent the aircraft body. The aerodynamic control system is further provided with an elongate torque member which extends from the aircraft body. The torque member has a torque rotational axis which is co-linear with the support structure rotational axis. The torque member further has an outboard end which is fixedly attached to the outboard support of the support structure. In the normal fight mode the inboard and outboard supports cooperatively rotate in response to rotation of the torque member.
    Type: Grant
    Filed: January 15, 1999
    Date of Patent: July 18, 2000
    Inventor: John Alan Volk
  • Patent number: 6073880
    Abstract: Pairs of aerofins used for stabilization and control of missile flight are deployed through shared longitudinal slots provided in the missile body. Before launch, the pairs of aerofins, each pair comprised of a canard and a deflector, are retained in a folded position by a releasable latch mechanism within the missile body. The deflectors are mounted in a laterally displaced position from the longitudinal slots and are constrained from sliding into alignment with the slots by the presence of the folded canards. When the canards are released by the latch mechanism and permitted to extend outward to their deployed positions, the deflectors are able to laterally shift, effectively displacing the canards in the alignment position and subsequently deploying. The latch mechanism is designed to simultaneously release all the canards following missile launch, with biasing torsional springs operating to urge the canards outward through the associated slots to the extended position upon release.
    Type: Grant
    Filed: May 18, 1998
    Date of Patent: June 13, 2000
    Assignee: Versatron, Inc.
    Inventors: Allan A. Voigt, John M. Speicher
  • Patent number: 5992796
    Abstract: A secondary wing system for use on an aircraft augments the lift, stability, and control of the aircraft at subsonic speeds. The secondary wing system includes a mechanism that allows the canard to be retracted within the contour of the aircraft fuselage from an operational position to a stowed position. The top surface of the canard is exposed to air flow in the stowed position, and is contoured to integrate aerodynamically and smoothly within the contour of the fuselage when the canard is retracted for high speed flight. The bottom portion of the canard is substantially flat for rotation into a storage recess within the fuselage. The single canard rotates about a vertical axis at its spanwise midpoint. The canard can be positioned between a range of sweep angles during flight and a stowed position in which its span is substantially parallel to the aircraft fuselage. The canard can be deployed and retracted during flight.
    Type: Grant
    Filed: March 13, 1997
    Date of Patent: November 30, 1999
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventor: Brian E. Smith
  • Patent number: 5984228
    Abstract: A fixed wing aircraft that can be automatically and rapidly converted to a roadway vehicle within seconds while driving in the highway, comprising a one-piece wing rotatably mounted on top of the fuselage. The aircraft features a 3-horizontal-surface design allowing good pitch stability and damping in a very short fuselage, stall-resistant feature and reduction in induced drag at cruise speed. The aircraft's wing is enlargeable with additional wing tip segments allowing boost in aspect ratio hence improving efficiency at high loads. The vehicle has low center of gravity, four wheels with independent suspension, nose-height leveling for take-off and landing, and anti-sway mechanism in order to prevent roll-over in a tight turn. Ground propulsion is by both a ducted fan and hydraulic rear wheel drive allowing rapid accleration in the roadable mode.
    Type: Grant
    Filed: March 5, 1997
    Date of Patent: November 16, 1999
    Inventor: Roger N. C. Pham
  • Patent number: 5984231
    Abstract: An aircraft with a variable forward-sweep wing and the method of configuring the wing in an optimal position for a desired flight regime. The variable forward-sweep wing is positionable from an essentially unswept position to a full-forward sweep position. In the unswept position the wing is approximately orthogonal to a fuselage centerline, while in the full-forward sweep position the wing has approximately a delta wing planform. Moreover, as the wing position changes from the unswept position to the full-forward sweep position the trailing edge becomes the leading edge. In addition, the aforementioned apparatus may be used in a method to configure the aircraft for flight in a desired flight regime. This method includes moving the wing to an optimal position for the desired flight regime.
    Type: Grant
    Filed: June 19, 1998
    Date of Patent: November 16, 1999
    Assignee: Northrop Grumman Corporation
    Inventors: Heinz A. Gerhardt, Kenneth Seho, Joan Nolan, Matthew N. Mrdeza
  • Patent number: 5934967
    Abstract: An apparatus which transforms itself from one form to another. The apparatus comprises a body having a first rotatable leg and a second rotatable leg mounted thereon. When placed in motion, the apparatus is in its first form. First and second links are rotatably mounted in the first and second rotatable legs, respectively. The first and second links are pivotably joined at a pivot point. The apparatus has a weight disposed at the pivot point. Forces acting on the apparatus at different stages of travel cause forces to shift. This causes rotation of the first rotatable leg and said second rotatable leg. When this occurs, the apparatus is transformed into the second form. Also, a center of gravity shifting apparatus shifts the center of gravity of the apparatus from the front of the apparatus to the rear of the apparatus.
    Type: Grant
    Filed: July 31, 1997
    Date of Patent: August 10, 1999
    Assignee: Blue Leaf Design, Inc.
    Inventors: Douglas M. Brown, Larry G. Lynch, James M. Hair, III
  • Patent number: 5915650
    Abstract: A wing structure for hang gliders, ultralites, gliders, heavy aircraft, ornithopters and sailsoaring flying boats which has a first wing set that pivots on two axis, and a second wing set that remains substantially immobile relative to the fuselage or keel. The wing pivots on the lateral axis of the fuselage or keel by moving along a slider assembly that allows it to move from a swept position to a more perpendicular position relative to the keel to control the amount of lift. The wing also pivots on the longitudinal axis of the fuselage or keel to control banking. On hang glider versions of the device, optional ducted fan, propeller, or jet propulsion units provide power to maintain flight. An optional bungee launch assembly assists takeoff from relatively flat surfaces. An optional "telepresence" wing controller allows the pilot to control wing motion with minimal physical exertion.
    Type: Grant
    Filed: July 10, 1997
    Date of Patent: June 29, 1999
    Inventor: Enrique G. Petrovich
  • Patent number: 5901924
    Abstract: A powered parachute or pendulum flying machine which includes a mechanism for shortening the chord length of the parachute wing, a mechanism for shortening the distance between the upper and lower airflow surfaces of the parachute wing, and a mechanism for adjusting position of the pilot module relative to the wing so as to adjust the center of gravity of the powered parachute. The mechanism for shortening chord length includes a tube running along the trailing edge of the parachute wing and control lines running from the tube to the pilot module. Pulling in the lines draws the tube forwardly and shortens the chord length. Preferably at the same time as the chord length is decreased, wing height is decreased by the mechanism for shortening the distance between the upper and lower airflow surfaces. Such is accomplished by collapsing a wall disposed between the upper and lower airflow surfaces to the pilot module.
    Type: Grant
    Filed: February 25, 1998
    Date of Patent: May 11, 1999
    Inventor: Louis Charles Strieber
  • Patent number: 5899410
    Abstract: The aerodynamic body, such as an aircraft, includes a lengthwise extending fuselage and a pair of coplanar joined wings extending outwardly from opposed sides of the fuselage. The pair of coplanar joined wings are formed by at least two forward wings extending laterally outward and rearward from opposite sides of a forward portion of the fuselage, and at least two aft wings extending laterally outward and forward from opposite sides of a rearward portion of the fuselage. Each aft wing is joined to a respective forward wing at a common wingtip to thereby form one of the joined wings. In particular, the aft wing can either be joined to the outermost portion of the respective forward wing or to a medial portion of the respective forward wing such that a portion of the forward wing extends outboard of the common wingtip.
    Type: Grant
    Filed: December 13, 1996
    Date of Patent: May 4, 1999
    Assignee: McDonnell Douglas Corporation
    Inventor: Timothy M. Garrett
  • Patent number: 5897076
    Abstract: A supersonic flight aircraft having a longitudinally forwardly extending fuselage having an axis in the direction of flight, and a wing, and which comprises the wing extending generally laterally relative to the axis, and having a leading edge angled forward or rearwardly relative to a normal to the axis at an angle , and the wing having leading edge sharpness defined by upper and lower wing surfaces, which taper toward the leading edge to define an angle .delta., closely proximate the leading edge at all spanwise locations; the angle and sharpness .delta.
    Type: Grant
    Filed: May 20, 1996
    Date of Patent: April 27, 1999
    Inventor: Richard R. Tracy
  • Patent number: 5836541
    Abstract: A fixed-wing four-seat light aircraft that can be easily converted to a roadway vehicle within minutes by a single person in the field, comprising a one-piece wing center panel with foldable wing tips on each sides. The whole wing unit is then rotatably mounted on top of the fuselage. The aircraft features a conventional front-engine-and-propeller lay-out, with a short fuselage for convenient roadability and garageability, with horizontal stabilizer of significant span with foldable tips for adequate flight stability. The vehicle has a low ride-height with a low center of gravity, four wheels with independent suspension, nose-height leveling for take-off and landing, and anti-sway mechanism for adequate ground handling. Ground propulsion is by automotive-style transmission driving the front wheels.
    Type: Grant
    Filed: May 21, 1997
    Date of Patent: November 17, 1998
    Inventor: Roger N. C. Pham
  • Patent number: 5766055
    Abstract: The present invention relates to a model glider having position-variable wings wherein the installation angle of the main wings of the model glider can be freely adjusted within a certain limit by a user, thus providing optimum flight. The model glider according to the present invention includes a central frame constituting a central body of the model glider, auxiliary frames connected with the central frame on both sides of the central frame, a vertical tail mounted upward on the rear part of the central frame, horizontal tails mounted horizontally on both sides of the rear part of the auxiliary frames, main wings movably mounted on the auxiliary frames and connected to the central frame via the auxiliary frames, and an angle adjusting means to adjust the angle between the main wings and the central frame.
    Type: Grant
    Filed: October 31, 1996
    Date of Patent: June 16, 1998
    Inventors: Cho-kwon Kim, Kang-hee Hahn
  • Patent number: 5671899
    Abstract: The invention is an airborne vehicle. In detail, the invention includes a main body having a longitudinal, lateral and vertical axis. A pair of wings are pivotally mounted to the main body that are movable about an axis of rotation from a retracted position to an extended position external of the main body along the lateral axis. A linkage assembly for controlling the position of the wings is mounted within the vehicle that includes a guide assembly having an open ended slot aligned with the longitudinal axis thereof. First and second links have their first ends pivotally connected to the wings at a position offset from the axis of rotation of the wings, and the second ends thereof pivotally coupled to each other.
    Type: Grant
    Filed: February 26, 1996
    Date of Patent: September 30, 1997
    Assignee: Lockheed Martin Corporation
    Inventors: Paul H. Nicholas, Larry Lipera, Stephen G. Justice, Joseph M. Wurts
  • Patent number: 5671898
    Abstract: An aircraft having variable airframe geometry includes an elongate fuselage having top and bottom sides, a swept back, high-speed wing mounted to the top of the fuselage, and a high aspect ratio, low-speed wing pivotally mounted adjacent to the bottom of the fuselage. The low-speed wing is adapted to pivot between a slow speed flight position in which a longitudinal axis of the low-speed wing is generally perpendicular to a longitudinal axis of the fuselage, and a high-speed flight position in which the longitudinal axis of the low-speed wing is generally parallel to the longitudinal axis of the fuselage. A fairing extends from the fuselage for receiving at least a portion of the low-speed wing when pivoted into the high-speed flight position. The low-speed wing further includes landing gear.
    Type: Grant
    Filed: February 16, 1996
    Date of Patent: September 30, 1997
    Inventor: Bruce B. Brown
  • Patent number: 5645250
    Abstract: Several innovative systems for an aircraft, and aircraft incorporating them, are disclosed. Features include inboard-mounted engine(s) with a belt drive system for turning wing-situated propellers; compound landing gear integrating ski, pontoon and wheel subcomponents; pivotal mounting armatures for landing gear and/or propellers which provide a plurality of possible landing gear and/or propeller configurations; and a compound wing structure featuring extendable wing panels that permit the wing span of the aircraft to be nearly doubled while in flight. Aircraft incorporating such features will enjoy several safety advantages over conventional multi-engine aircraft and will be capable of modifications during flight which permit landings on any of snow, hard surfaces (runways) and water.
    Type: Grant
    Filed: August 26, 1993
    Date of Patent: July 8, 1997
    Inventor: David E. Gevers
  • Patent number: 5642867
    Abstract: An aerodynamic lifting and control surface comprising an external box structure that encloses an internal grid whose members are parallel to the box structure. The external box structure comprises four panels connected at their comers by spring hinges. When the hinges are unconstrained, the external box structure is compressed into a flat, thin parallelogram shape. The internal grid comprises a plurality of plates connected to each other and to the external box structure by flexible hinges. Control apparatus for use with an aerodynamic vehicle is also disclosed. The control apparatus comprises at least one aerodynamic lifting and control surface that is coupled to an actuator disposed within the vehicle and connected to the aerodynamic lifting and control surface for rotating it.
    Type: Grant
    Filed: June 6, 1995
    Date of Patent: July 1, 1997
    Assignee: Hughes Missile Systems Company
    Inventor: Ralph H. Klestadt
  • Patent number: 5634613
    Abstract: Methods for using tip generated vortices to improve performance of foils. These methods include generating a substantially streamwise beneficial vortex (74) near the outboard end (60) of a foil (82). This beneficial vortex (74) spins in the opposite direction of an induced drag vortex (62), and is used to create an upwash field (76) which neutralizes induced drag by deflecting the flow behind the trailing edge (56) at an upward angle. Upwash field (76) causes the lift vector (118) on the foil (82) to tilt forward, thereby creating a forward directed force of induced thrust upon the foil (82). Beneficial vortex (74) is also used to contain and compress the high pressure field existing along the attacking surface of the foil (82), and displace the induced drag vortex (62) inboard from the tip of the foil (82). Numerous performance parameters are improved dramatically by using beneficial vortex (74), as well as by using a double vortex pattern (124).
    Type: Grant
    Filed: July 18, 1994
    Date of Patent: June 3, 1997
    Inventor: Peter T. McCarthy
  • Patent number: 5564652
    Abstract: A body spoiler rotatably mounted within a recess formed within opposite sides of the forebody of a supersonic air vehicle and configured to conform with the fuselage of the vehicle. A sensor positioned close to the inlet of each engine powering the flight of the vehicle measures the pressure of the fluid entering the engine. If an engine on one side of the vehicle malfunctions, the pressure sensor sends a deploy signal to the body spoiler mounted on the same side of the vehicle. An actuator receives the deploy signal and rotates the spoiler through an angle which is dependent upon the speed of the vehicle. When deployed, the spoiler generates a shock wave which in turn produces pressure along the forebody thereby creating a yaw moment to substantially counterbalance the yaw moment generated by the malfunctioning engine.
    Type: Grant
    Filed: January 3, 1995
    Date of Patent: October 15, 1996
    Assignee: The Boeing Compay
    Inventor: Thomas E. Trimbath
  • Patent number: 5564656
    Abstract: Segmented spoilers are parallel arrays of individually-extended barrier surfaces, such as rotatable eccentrically-mounted disks. The overlapping surface areas extend through a slot on a aircraft surface. When actuated, a segmented array generates a stiff, extendable, profiled spoiler-barrier. The individual surface areas are power-activated from below the airfoil surface according to motor commands from autopilots, operators, sensors and computers. Disk spoiler systems provide very rapid generation and retreat of controllable height barriers. The management of Bernoulli lift phenomenon with disk spoilers has unique use on an aircraft's nose, along the top of its wings, on the forward surfaces of horizontal and vertical stabilizers and within the intake sections of gas turbine aircraft engines. Disks are rotated by electric rotor-positioning motors and aircraft-powered axial force systems.
    Type: Grant
    Filed: August 29, 1994
    Date of Patent: October 15, 1996
    Inventor: Raymond D. Gilbert
  • Patent number: 5526999
    Abstract: The spacecraft comprises a fuselage (1), a wing (2), a power unit incorporating two liquid-propellant launching rocket engines (3), two liquid-propellant boost rocket engines (4), six transverse-thrust rocket engines (5) located in the spacecraft fuselage (1) on a rotatable ring (6), solid-propellant emergency deceleration rocket engines (7), and solid-propellant additional boosting rocket engines (8), a payload compartment (9), a crew compartment (10), a tail unit with two vertical fin struts (11) a bottom tailplane (12), and a top tailplane (13). The fuselage (1) is provided with a movable center conical body (14). The spacecraft landing gear has a swivelling tail wheel (21). The crew compartment (10) is interposed between the fin struts (11) under the top tailplane (13). The spacecraft is provided with an orbital maneuvering system whose final control elements are in fact low-thrust rocket engines (22) and (23), and gyrodynes.
    Type: Grant
    Filed: June 29, 1994
    Date of Patent: June 18, 1996
    Inventor: Vyacheslav A. Meston
  • Patent number: 5505409
    Abstract: A method is described for reducing drag in airframes or airfoils. The method includes inducing cavitation in the boundary layer separating the airframe or foil skin and the air currents passing thereover to produce a reduced pressure area instead of turbulent flow. In one embodiment of this invention, a nose cone is provided for the airframe which at the juncture of its base portion provides a step between the terminal portion of the nose cone and the adjacent portion of the fuselage skin. This provides a circumferential step surrounding the fuselage which in its leeward direction induces the cavitation necessary to reduce drag. In another embodiment of this invention, steps can be provided longitudinally at mutually spaced circumferential locations extending from the front along the fuselage toward to the rear to ensure that a continuous boundary layer is provided of reduced pressure.
    Type: Grant
    Filed: May 20, 1994
    Date of Patent: April 9, 1996
    Inventors: Anthony R. Wells, Stanley Blumberg
  • Patent number: 5495999
    Abstract: A canard wing surface for aircraft, especially supersonic aircraft, which can be lowered and retracted flush into the fuselage of the aircraft when no longer needed. The canard is hinged to an extendible platform at or near its upper edge, so that a raising mechanism on the platform can raise the canard from a position integral with the skin of the fuselage to a fully extended position as a curved wing. The platform is extended to allow the canard to clear the fuselage, and may be rotated to adjust the angle of attack of the canard from nearly flat, for the transition to high-speed flight, to a range of low-to-medium angles of attack when used as a lift surface during takeoff and landing, to nearly vertical for use as a speed brake during the landing roll. If desired, multiple canard surfaces can be used on an aircraft, arranged along the fuselage.
    Type: Grant
    Filed: February 17, 1995
    Date of Patent: March 5, 1996
    Inventor: Hermann K. Cymara
  • Patent number: 5417393
    Abstract: A vehicle such as a missile (20) includes an aerodynamically shaped missile body (22) having a longitudinal centerline, a set of control surfaces (26) joined to the missile body (22), and, preferably, a propulsion system (28) operable to drive the missile body (22) forwardly. A cylindrical rotational bearing (32) is mounted on the missile body (22) with its cylindrical axis parallel to the longitudinal centerline (24) of the missile body. A flexible band wing (38) is supported from the rotational bearing (32). The flexible band wing (38) may rotate about the centerline (24) of the missile body (22) responsive to aerodynamic forces exerted on the missile body (22) and the flexible band wing (38) to aid in making maneuvers without requiring the missile (20) to bank to align the flexible band wing (38) with the direction of the maneuver.
    Type: Grant
    Filed: April 27, 1993
    Date of Patent: May 23, 1995
    Assignee: Hughes Aircraft Company
    Inventor: Ralph H. Klestadt
  • Patent number: 5366180
    Abstract: High lift producing apparatus for an aircraft includes a pair of foreplanes, one for each side of the aircraft, each foreplane extending between a root end at the fuselage and a distant tip end. Wings are mounted on the fuselage aft of the foreplanes and, intermediate the wings and the foreplanes, are a pair of strakes which are generally coplanar with their associated foreplanes and strakes, a leading edge of each strake being substantially coincident with a trailing edge of its associated foreplane, and a trailing edge of each strake being substantially coincident with a leading edge of its associated wing. The span of the strakes is smaller than the span of the foreplanes at the location of intersection of said strake and said foreplane. Each foreplane may be pivotally mounted on the fuselage at its root end on a stationary hinge axis which is substantially parallel with the longitudinal axis of the aircraft.
    Type: Grant
    Filed: June 30, 1993
    Date of Patent: November 22, 1994
    Assignee: Northrop Corporation
    Inventors: Barnaby S. Wainfan, Matthew N. Mrdeza
  • Patent number: 5337974
    Abstract: An aircraft wing pivot structure is described which provides a flexible ring attached to the aircraft wing at flexible wing attachment points by spherical bearings. The ring is attached to the fuselage of the aircraft by pins fixed to the fuselage and fittings partially enclosing sliding shoes formed at the bottom edge of the ring to allow rotation of the wing. The wing is locked in the flight position by retractable pins connected to the primary fuselage attachment fittings. The ring is a unitary stainless structure which accepts wing strains induced by flight loads by flexing at the wing attachment points. The use of a flexible ring eliminates truss-like members mounted on spherical bearings used in conventional designs. The elimination of a substantial number of components by the use of a flexible ring substantially reduces the weight of the aircraft and improves the reliability.
    Type: Grant
    Filed: April 15, 1992
    Date of Patent: August 16, 1994
    Assignee: The Boeing Company
    Inventors: William E. Rumberger, Wayne S. Steffier
  • Patent number: 5332177
    Abstract: An aircraft capable of sustained flight including a fuselage and a spiral-formed flat-section right hand and left hand wing positioned in generally horizontally opposing relation along either side of the fuselage. Each wing is formed of an elongated flat panel or plate having generally parallel leading and trailing edges, the length of the panel being substantially greater than its width, the width being substantially greater than its thickness. The forward and rearward ends of each wing are movably connected within forward and rearward longitudinal channels of the fuselage. By appropriate controlled linear and rotational movement of the wing ends, in combination with a conventional rudder of an upright rear stabilizer fin of the fuselage, all aerodynamic flight path variable control is accomplished. Both single and multiple spiral-turned wings are provided.
    Type: Grant
    Filed: September 9, 1993
    Date of Patent: July 26, 1994
    Inventor: James J. Boyle, Jr.
  • Patent number: 5312070
    Abstract: A segmented variable sweep wing for an aircraft has a plurality of wing segments. A structural device movably affixes the wing segments to the fuselage of the aircraft adjacent each other at their root areas. The structural device moves the segments conjointly to a power position where the segments are perpendicular to the fuselage and spaced from each other. The structural device also moves the segments conjointly to a cruise position wherein the segments are swept back at an angle with the fuselage and in abutment with each other thereby forming a unitary continuous surface airfoil.
    Type: Grant
    Filed: April 2, 1992
    Date of Patent: May 17, 1994
    Assignee: Grumman Aerospace Corporation
    Inventor: Aldo Arena
  • Patent number: 5280863
    Abstract: The aircraft includes a free wing freely pivotally supported about a spanwise axis for flight in a free wing mode and lockable in selected predetermined, fixed angles of incidence with respect to a fuselage for flight in a fixed wing mode. The predetermined angle of incidence in the fixed wing flight mode is selected to provide sufficient lift for flying the aircraft at low speeds as necessary for takeoff and landing. The aircraft can be converted in flight between the free wing or conventional fixed wing aircraft flight modes. A control system is provided for selectively enabling or disabling the elevators on the horizontal stabilizer and the wing flaps.
    Type: Grant
    Filed: November 20, 1991
    Date of Patent: January 25, 1994
    Inventor: Hugh Schmittle
  • Patent number: 5192037
    Abstract: A double-pivoting deployment system for aerosurfaces, such as wings or fins, for use on aerospace vehicles. Each aerosurface has an inner segment and an outer segment. The inner segment is pivotally connected at a first axis of rotation to the support structure of the aerospace vehicle. An outer side portion of the inner segment is pivotally connected at a second axis of rotation to an inner side portion of the outer segment. In operation, the outer segment is stowed adjacent to the body of the aerospace vehicle such that the surface plane of the outer segment is longitudinally aligned with the longitudinal axis of the aerospace vehicle, and the aerosurface span is longitudinally aligned with, the longitudinal axis of the aerospace vehicle. From the stowed position, the outer segment is first rotated substantially 90.degree.
    Type: Grant
    Filed: August 23, 1991
    Date of Patent: March 9, 1993
    Assignee: McDonnell Douglas Corporation
    Inventor: William J. Moorefield
  • Patent number: 5160100
    Abstract: An aircraft comprises a vehicle (1) suspended in flight by a steering control rod (68) pivotally mounted to the body of the vehicle and having outer ends (12, 14) connected to the lower ends of load suspension lines (3, 5, 6) connected at their upper ends to a flexible wing portion (2) of a ram air inflatable type of airfoil canopy. Steering of the aircraft is by pivotal movement of control rod (68) to manipulate the load suspension lines and thereby the canopy surfaces. The aircraft may be radio controlled by a radio receiver (112) in the vehicle body for operating the speed of a drive motor (36) for driving a propeller (38) and a steering drive motor (98) coupled to the control rod (68) by a suitable linkage system. Battery pack (104) is removably mounted in the vehicle body for providing power to the receiver and motors therein. The radio controlled aircraft is controlled by a remote transmitter which controls the steering and speed of the aircraft.
    Type: Grant
    Filed: July 1, 1991
    Date of Patent: November 3, 1992
    Inventor: Stephen L. Snyder
  • Patent number: 5141084
    Abstract: A brake stop for limiting the rotation of a rotating member to a predetermined amount comprises a brake which is actuable for stopping rotation of the rotating member and an actuator mechanism responsive to the rotation of the rotating member for actuating the brake after a predetermined amount of rotation of the rotating member. The actuator mechanism includes a differential counter gear set and a ball-ramp mechanism which converts rotary motion of the rotating member by way of the differential counter gear set into linear motion for actuation of the brake. Provision is made for sufficient lost motion or backlash in the differential counter gear set upon reversal of gear rotation to allow release of the brake from a braked condition upon reversal of the direction of rotation of the rotating member.
    Type: Grant
    Filed: September 28, 1990
    Date of Patent: August 25, 1992
    Assignee: Sundstrand Corporation
    Inventors: David J. Lang, David E. Russ
  • Patent number: 5104061
    Abstract: A dual eccentric bearing system for precise adjustment of wing incidence and dihedral. The bearing system is utilized in the attachment of wings that vary the sweep by rotation about a pivot fixedly located on an aircraft fuselage through an interconnecting wing pivot pin. The top portion of the pivot pin is supported by the dual eccentric bearing system and the bottom by a non-eccentric bearing system. The eccentric bearing system has both an eccentric ball retaining ring free to rotate relative to its fuselage attachment and a ball contained within the ring which includes an eccentric pivot pin receiving aperture free to rotate within the ring containment. The bottom end of the pin is supported by a conventional non-eccentric bearing system with the ring fixedly held in position by its fuselage connection. The ball of the non-eccentric bearing has a similar pin receiving aperture with the ball free to rotate angularly relative to the ring.
    Type: Grant
    Filed: May 25, 1990
    Date of Patent: April 14, 1992
    Assignee: General Dynamics Corporation, Convair Division
    Inventor: William J. Doane
  • Patent number: 5096143
    Abstract: The tailplane 6 is mounted to an aircraft by a spigot 7 and is also rotatable about the spigot 7 to provide aerodynamic control. At the same time the tail plane is pivotable about an axis extending generally parallel to the longitudinal axis of the aircraft in order to optimise the tail plane configuration for various speeds.
    Type: Grant
    Filed: July 31, 1990
    Date of Patent: March 17, 1992
    Inventor: William Nash
  • Patent number: 5078338
    Abstract: An assembly for controlling the lateral stability of a swept-wing aircraft by varying the geometric dihedral of the wing as a function of the wing's lift coefficient, such assembly including a mechanism for producing a signal or other type response representative of the lift coefficient of the wing at any particular point in time during flight including changes in such lift coefficient due to changes in the particular flight condition or aerodynamic characteristics of such wing, and a mechanism responsive to such signal or other response for controlling and activating movement of variable dihedral panels associated with the respective opposite portions of the wing.
    Type: Grant
    Filed: January 19, 1990
    Date of Patent: January 7, 1992
    Inventors: Terrence O'Neill, Timothy O'Neill
  • Patent number: 5078339
    Abstract: An aircraft including a fuselage and a double wing unit which is pivotably mounted onto the fuselage and arranged to selectably assume a first orientation, generally parallel to the fuselage, during storage and transport and a second orientation, generally perpendicular to the fuselage, for flight.
    Type: Grant
    Filed: July 6, 1990
    Date of Patent: January 7, 1992
    Assignee: Israel Aircraft Industries Ltd.
    Inventor: Ehud Lapidot
  • Patent number: 5035378
    Abstract: An alignment mechanism for independently adjusting the deployable aerosurfaces of an aerospace vehicle in both the stowed and deployed positions. The alignment mechanism includes a guide means having a slot with both a constant width portion and a variable width portion. A slide, interconnected to the deployable aerosurfaces, is pivotally engaged to the guide means so that it travels along the length of the slot. The slide is capable of pivotal movement when the slide is engaged in the slot's variable width portion and incapable of pivotal movement when it is engaged in the slot's constant width portion. An actuator is employed to selectively position the slide along the slot.
    Type: Grant
    Filed: May 7, 1990
    Date of Patent: July 30, 1991
    Inventor: Joseph P. Spanovich
  • Patent number: 5031857
    Abstract: A two-stage earth-to-orbit transport includes an orbiter vehicle and a pair of boosters, each having a depolyable oblique wing located along a longitudinal axis of the booster. The wing is deployed in an oblique disposition in supersonic and hypersonic speeds, and disposed at 90.degree. for subsonic speeds encountered during entry. The oblique wing is driven axially and rotated by means of a turret mounted on rails.
    Type: Grant
    Filed: November 9, 1989
    Date of Patent: July 16, 1991
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventors: Ian O. MacConochie, Charles A. Briener
  • Patent number: 4998689
    Abstract: A high speed aircraft fitted with a unitary, rotatable wing coupled to the craft's fuselage at a hollow turret or solid pivot pin, enabling it to operate with the wing in either of two ninety degree opposed positions.
    Type: Grant
    Filed: July 14, 1989
    Date of Patent: March 12, 1991
    Assignee: Rockwell International Corporation
    Inventor: Robert R. Woodcock
  • Patent number: 4986493
    Abstract: A fixed wing aircraft that can be converted to an automotive vehicle, comprising a generally rectangular planform fuselage having four wheels as in conventional automobile practice, and a telescopic wing which retracts into a housing in the roof of the fuselage. Telescopic horizontal and vertical stabilizers are provided at the rear end of the fuselage, as well as a retractable pusher propeller that is driven by an engine mounted on the front end of the fuselage. Both the propeller and the rear wheels are connected by a transmission box to the engine, so that either can be driven to operate the vehicle as an aircraft or as an automobile. On take-off, the rear wheels are partially retracted so as to place the aircraft at a proper angle of attack at the same time that the elevators are raised by pulling back on the control wheel. The control wheel is also connected to both the front wheels and the ailerons, and when turned 90.degree.
    Type: Grant
    Filed: December 5, 1988
    Date of Patent: January 22, 1991
    Inventor: Branko Sarh
  • Patent number: 4917333
    Abstract: Actuated forebody strakes provide yaw control at high angles of attack. In one embodiment, the strakes are axially slidable in the forebody to be deployed out of slots provided for the strakes in the forebody. In another embodiment, the strakes are pivotally connected at the tip of the strakes to pivot radially outwardly out of the slots provided in the forebody. In another embodiment, the forebody is provided with either a single strake or two strakes and the forebody is rotatable to vary the radial location of the strake or strakes. All embodiments achieve significant yaw control capability over a wide angle of attack and sideslip ranges.
    Type: Grant
    Filed: May 11, 1988
    Date of Patent: April 17, 1990
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventor: Daniel G. Murri
  • Patent number: 4913378
    Abstract: An airplane construction is described in which the flight characteristics of the airplane, are radically changed from hypersonic capable to short take off and landing (STOL) capable by the approximate ninety degree (90) rotation of a new component of the airplane, referred to as a body spar, which function is to maintain structural integrity of the airplane and maintain the required alignment of such elements as the fixed wings, thrust providers, control surfaces and landing gear, regardless of the mode of flight of the airplane.The single largest component of the airplane, referred to as the wing/fuselage component, is so shaped as to be a high aspect ratio, highly cambered, (STOL) wing when the airplane is configured for subsonic/STOL flight, that is when this wing/fuselage is positioned at an approximate right angle to the body spar.
    Type: Grant
    Filed: November 13, 1987
    Date of Patent: April 3, 1990
    Inventor: Galen E. Calvert
  • Patent number: 4863117
    Abstract: The invention relates to a contoured wing intended to serve as a airfoil or a blade. This wing comprises a longitudinal stringer (3), a plurality of juxtaposed wing sectors (1, 2), each articulated about the stringer, a series of cranks (7), each crank associated with a sector in such a manner as to fix the angular position thereof about the stringer, and a control device (10) for the cranks, able to cause their pivoting. The wing according to the invention permits control of the angle, continuously and progressively variable along the contour. It may particularly be applied for use in beating wing aircraft.
    Type: Grant
    Filed: January 7, 1988
    Date of Patent: September 5, 1989
    Inventor: Roland Riout
  • Patent number: 4848700
    Abstract: A system with a canard disposed in a cage with canard fore and aft movement within the cage for trimming purposes. Rails support the cage and include both horizontal and inclined segments with the cage and canard inclined by the latter segments to increase the canard angle of attack to preserve the canard-stallfirst characteristic of the aircraft. A combined canard and flap control assures automatic advancement and inclining of the canard to counteract forward pitching of the aircraft caused by flap deployment.
    Type: Grant
    Filed: April 16, 1987
    Date of Patent: July 18, 1989
    Inventor: John A. Lockheed
  • Patent number: 4836470
    Abstract: An aerospace vehicle having multiple propulsion systems on a relatively rotatable flying wing capable of takeoff and subsequent landing with intermediate space flight in the manner of a conventional aircraft and rocket, respectively, comprising an elongated wing member having internal passenger and crew, cargo and fuel storage compartments. A plurality of propulsion systems are distributed about the wing member for providing thrust and aerodynamic control. The vehicle also includes rotating means for controlling the direction of the thrust of the propulsion systems relative to the longitudinal axis of the wing whereby to rotate the wing member relative to the direction of flight. The vehicle takes off and lands with the longitudinal wing axis being transverse to the direction of thrust and therefore to the flight direction in a manner similar to that of conventional aircraft.
    Type: Grant
    Filed: June 13, 1985
    Date of Patent: June 6, 1989
    Inventor: David R. Criswell
  • Patent number: 4773619
    Abstract: The invention relates to an aircraft structure to make possible take-off and landing on a pilot's feet. The aircraft structure according to the invention can be regarded as a category between kite-shaped aircraft structures and light structures. The gist of the aircraft structure of the invention consists in providing freely supported or outerly reinforced wings (12) adapted to be moved by a pilot (15) actuated mechanism, in their own plane during flight.
    Type: Grant
    Filed: January 23, 1987
    Date of Patent: September 27, 1988
    Inventor: Erno Rubik