Aerodynamic Retarders Patents (Class 244/113)
  • Patent number: 10532818
    Abstract: Systems and methods for aerially delivering cargo into a body of water while avoiding parachute entrapment and entanglement are described. The system includes a parachute having a canopy and suspension lines. The system further includes a weight coupled to a first end of the suspension lines and a ring that is configured to float in the body of water. The weight is coupled to the cargo, and the ring is disposed between the weight and the canopy with the suspension lines passing through the center of the ring.
    Type: Grant
    Filed: July 26, 2016
    Date of Patent: January 14, 2020
    Assignee: THE BOEING COMPANY
    Inventor: Jamie Childress
  • Patent number: 10502086
    Abstract: A system for actuating components of a gas turbine engine may generally include a turbine component incorporating a jamming device. The jamming device may include a bladder and a jammable media contained within the bladder. The jammable media may be jammable within the bladder from an unjammed state, wherein a fluid is contained within the bladder, to a jammed state, wherein the fluid is at least partially evacuated from the bladder. The system may also include a fluid coupling in fluid communication with the bladder. A portion of the turbine component may be located at a first position when the jammable media is in the unjammed state. Additionally, such portion of the turbine component may be located at a second position when the jammable media is in the jammed state.
    Type: Grant
    Filed: March 16, 2016
    Date of Patent: December 10, 2019
    Assignee: General Electric Company
    Inventors: Aaron Todd Sellinger, Nicholas Joseph Kray, Wendy Wenling Lin
  • Patent number: 10479481
    Abstract: A process and a machine for improving a performance of a particular model of an aircraft, via reducing a size of a horizontal stabilizer for the particular model of the aircraft, the process comprising augmenting a nose-up moment, for the particular aircraft model, provided by a reduced horizontal stabilizer for the particular aircraft model, via addition of an ailevatoron mixer.
    Type: Grant
    Filed: September 28, 2016
    Date of Patent: November 19, 2019
    Assignee: The Boeing Company
    Inventor: Henry Llewellyn Beaufrere
  • Patent number: 10370085
    Abstract: In one embodiment, an apparatus includes a first deflector configured to couple to a shaft of an aircraft. The first deflector may form part of a top surface of the aircraft when in a first closed position. The apparatus may further include a second deflector configured to couple to the shaft and form part of a bottom surface of the aircraft when in a second closed position. The first deflector and the second deflector may be configured to be positioned at a junction of a body of the aircraft and a wing of the aircraft. The first deflector and the second deflector may be configured to simultaneously pivot from the closed positions to respective first and second open positions upon actuation of the shaft.
    Type: Grant
    Filed: April 5, 2017
    Date of Patent: August 6, 2019
    Assignee: Lockheed Martin Corporation
    Inventor: Kenneth Merle Dorsett
  • Patent number: 10343764
    Abstract: An aircraft wheel fairing drag device, which increases the functionality and operating capabilities of an aircraft wheel fairing for a fixed landing gear aircraft, has a linear actuator, a drag door, and a mounting plate. The mounting plate is positioned within the aircraft wheel fairing and supports the linear actuator. Meanwhile, the linear actuator is operably coupled to the drag door, wherein a driver linearly positions a push rod that is pivotally engaged with a rod mount of the drag door. The rod mount and a fairing hinge are connected to a drag pane, wherein the rod mount is operably disposed from the fairing hinge to allow the drag pane to be angularly positioned relative to the aircraft wheel fairing as the push rod is linearly extended. The fairing hinge provides a rotational axis between the aircraft wheel fairing and the drag pane about which the drag pane is rotated.
    Type: Grant
    Filed: July 29, 2016
    Date of Patent: July 9, 2019
    Inventor: Robert A. Hensley
  • Patent number: 10239606
    Abstract: A flow interrupting device may cause a flow to separate from a wingtip device at a desired angle of attack. The flow interrupting device may be coupled to a leading edge of a wingtip device where a flow disruptor may be configured to alleviate a load on the wingtip device. The flow disrupter may comprise an edge that extends into a boundary layer at a threshold angle of attack that may disrupt the boundary layer and cause a flow to separate from the wingtip device. This separated flow may reduce stresses experienced by the wingtip device and wing during various flight conditions where a transverse flow is encountered.
    Type: Grant
    Filed: December 4, 2013
    Date of Patent: March 26, 2019
    Assignee: Tamarack Aerospace Group, Inc.
    Inventor: Nicholas R. Guida
  • Patent number: 10189593
    Abstract: A machine for packaging articles includes a frame; a feeder feeding film to a packaging station to wrap articles. A sealing unit includes at least two sealing elements movable relative to each other between a spaced-apart position and a close-together position where the two sealing elements cooperate to seal the film interposed between them. First and second mechanisms having first and second motors move the sealing unit. The second motor is operatively coupled to at least one of the two sealing elements. The first and/or the second mechanisms include at least one articulated arm, respectively. A control unit is operatively connected to the first motor and to the second motor to drive them in proper relationship to move the two sealing elements relative to each other and relative to the frame according to a predetermined law of motion.
    Type: Grant
    Filed: September 26, 2014
    Date of Patent: January 29, 2019
    Assignee: CT PACK S.R.L.
    Inventors: Daniele Davi, Marco Pocaterra
  • Patent number: 10081446
    Abstract: A system for emergency crew return and down-mass orbit comprising a stowable, self-contained, deployable maneuvering reentry vehicle for automated, on-demand reentry to ground for cargo of 1-10 kilograms or up to single or multiple human use for evacuation of orbital facilities. The system includes a deployable “aeroshell” that is contiguous (a single geometric object—surface or hollow shape—that can morph in 3D shape), modular (a collection of modular components externally acting as a contiguous shape, but morphed in 3D via actuators contained in each modular member to create a general asymmetric geometry), or discontiguous (a collection of independently controlled surfaces or bodies that morph to form desirable asymmetric drag configurations).
    Type: Grant
    Filed: March 11, 2016
    Date of Patent: September 25, 2018
    Inventor: William C. Stone
  • Patent number: 10023299
    Abstract: The disclosure refers to a propeller blade for an aircraft engine that includes an airbag system contained inside the blade and comprising at least one bag and at least one gas generator, the at least one gas generator in fluid communication with at least one bag for inflating the bag, a detecting system for detecting a rupture of a part of the blade, a trigger for activating the at least one gas generator when the rupture is detected by the detecting system, and the blade skin being configured for allowing the at least one bag to pass through the blade skin for being expanded outside the blade upon the bag inflation by the gas generator.
    Type: Grant
    Filed: December 23, 2015
    Date of Patent: July 17, 2018
    Assignee: AIRBUS OPERATIONS, S.L.
    Inventors: Javier Toral Vazquez, Diego Folch Cortes, Esteban Martino Gonzalez, Pablo Goya Abaurrea, Vasilis Votsios, Michel Fouinnetau, Sylvain Roumegas
  • Patent number: 10017240
    Abstract: The present invention provides an aircraft including: a main wing; and a flight control surface that is deployed from the main wing in a first direction and in a second direction different from the first direction. In the aircraft, an end surface of the flight control surface facing the main wing when the flight control surface is not deployed is inclined with respect to the first direction or the second direction on at least one side of a longitudinal direction of the flight control surface, and a portion of the main wing facing the end surface is also inclined with respect to the first direction or the second direction in accordance with the end surface.
    Type: Grant
    Filed: September 10, 2015
    Date of Patent: July 10, 2018
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventors: Yoshinori Okabe, Kenya Ishihara, Zenta Sugawara
  • Patent number: 9988138
    Abstract: A method and apparatus for operating an airfoil system. A gas may be generated. The gas may be sent into an inflatable airfoil system comprising an inflatable air foil and a section. The inflatable airfoil may have an inner end and an outer end in which the inflatable airfoil may be comprised of a number of materials that substantially pass electromagnetic waves through the inflatable airfoil. The section may have a number of openings in which the inner end of the inflatable airfoil may be associated with the section. The section may be configured to be associated with a fuselage. The number of openings may be configured to provide communications with an interior of the inflatable airfoil. The section with the number of openings may be configured to reduce reflection of the electromagnetic waves encountering the section.
    Type: Grant
    Filed: April 11, 2014
    Date of Patent: June 5, 2018
    Assignee: The Boeing Company
    Inventors: Kevin Reed Lutke, Aaron Jonathan Kutzmann
  • Patent number: 9969493
    Abstract: An aerodynamic lifting device comprises a chassis (200); a rotor (120) having a rotational axis (R) and a plurality of rotor blades (123) disposed in an annular ring about the rotational axis (R) supported by the chassis (200); and a torque transmission means (126,130,139) to provide tractive force for rotating the rotor (120). The torque transmission means (126,130,139) co-operates with at least one complementary and circumferentially extending drive surface (126a, 126b) of the rotor (120) to transmit tractive force as tangential forces and resultant torque sufficient to drive the rotor (120) and thereby generate lift. The aerodynamic lifting device may be used in airborne craft which may be deployed for waterborne use with a buoyant chassis (200), especially of toroidal shape, for elevating the rotor (120) above a water surface (300) during take off and landing.
    Type: Grant
    Filed: June 30, 2014
    Date of Patent: May 15, 2018
    Assignee: ENTECHO PTY LTD.
    Inventors: Kim Christopher Schlunke, Ken Seeber, Rodney Lamb
  • Patent number: 9821907
    Abstract: Provided is an inflatable wing for a rotary-wing aircraft capable of obtaining auxiliary lift by inflating the inflatable wing equipped on the fuselage when a main rotor is in non-powered rotation state by not providing power for rotating the main rotor due to causes such as an engine failure in a conventional type of rotary-wing aircraft having a single engine, thereby providing a safer emergency landing.
    Type: Grant
    Filed: August 5, 2014
    Date of Patent: November 21, 2017
    Assignee: KOREA AEROSPACE RESEARCH INSTITUTE
    Inventor: Joune Ho Kim
  • Patent number: 9809315
    Abstract: An aircraft ejection system is provided. The aircraft ejection system may comprise a seat, a bridle coupled to the seat, suspension lines coupled to the bridle, and a drogue canopy coupled to the suspension lines. A first side of the drogue canopy may have a lower drag than a second side of the drogue canopy. The first side may comprise a mesh portion and/or an opening to reduce drag. The first side may further include a low-resistance structure with a circular or rectangular geometry. The bridle and the suspension lines may be configured to direct the first side in a predetermined direction, such as downward.
    Type: Grant
    Filed: March 31, 2015
    Date of Patent: November 7, 2017
    Assignee: AMI INDUSTRIES, INC.
    Inventor: John Hampton
  • Patent number: 9671200
    Abstract: A missile defense system on an aircraft for destroying threats to the aircraft. The defense system includes at least one miniature guided missile mounted in a launch tube on the aircraft, where the guided missile includes a target acquisition and seeker system. The system also includes at least one sensor on the aircraft for acquiring a target threat, and a controller on the aircraft receiving signals from the at least one sensor. The controller generates a fire control solution that is provided to the at least one guided missile that directs the guided missile once it is fired from the launch tube towards the target threat, and the seeker system on the guided missile acquires the target once it is launched from the aircraft so as to destroy the target.
    Type: Grant
    Filed: April 6, 2016
    Date of Patent: June 6, 2017
    Assignee: Northrop Grumman Systems Corporation
    Inventors: Mark A. Anderson, John P. Latz, Michael Ichino
  • Patent number: 9630705
    Abstract: The present invention provides a drive system which can automatically deploy a ground spoiler even when a wheel is locked. A drive system for a ground spoiler deploys closed ground spoilers 4A to 4D when a wheel speed VW exceeds a wheel reference speed VW1 or when an air speed VB exceeds an air reference speed VB1 after a main gear 6 touches down. The system may also close the deployed ground spoilers 4A to 4D when the wheel speed VW is smaller than a wheel reference speed VW2 or when the air speed VB is smaller than an air reference speed VB2.
    Type: Grant
    Filed: February 26, 2014
    Date of Patent: April 25, 2017
    Assignee: MITSUBISHI AIRCRAFT CORPORATION
    Inventor: Akihiro Hara
  • Patent number: 9573697
    Abstract: An apparatus for energy recovery of an aircraft, an aircraft comprising the apparatus and a method of energy recovery are disclosed. The apparatus comprises a turbine having a body and rotor blades. The turbine is adapted to be mounted to the exterior of an aircraft, such that the body receives an air stream flowing at the exterior of the aircraft. The rotor blades are selectively movable between a stowed position and a deployed position, wherein at the deployed position the rotor blades are rotated by the air stream so as to generate electricity. The blades may be deployed during descent of the aircraft to recover energy normally irretrievably dissipated as the aircraft descends and slows. The blades are stowed when not in use, such as during take-off and cruise.
    Type: Grant
    Filed: December 5, 2014
    Date of Patent: February 21, 2017
    Assignee: THE BOEING COMPANY
    Inventors: Alfredo Criado, Grzegorz M. Kawiecki
  • Patent number: 9505485
    Abstract: A vortex generation apparatus including a vortex generator that deploys in response to deployment of a wing leading edge lift augmentation device. The vortex generator deploys into a position to generate vortices over a main wing body upper surface region trailing the vortex generator.
    Type: Grant
    Filed: May 8, 2012
    Date of Patent: November 29, 2016
    Assignee: Lockheed Martin Corporation
    Inventor: Kenneth M. Dorsett
  • Patent number: 9296475
    Abstract: A system for reducing a stopping distance of an aircraft may include an edge control system configured to control a leading edge device mounted to a wing of an aircraft. The edge control system may be configured to automatically command extension of the leading edge device from a first position to a second position in response to deployment of a spoiler if a ground speed of the aircraft is greater than a threshold ground speed.
    Type: Grant
    Filed: September 24, 2013
    Date of Patent: March 29, 2016
    Assignee: The Boeing Company
    Inventors: Matthew A. Moser, David D. Leopold, Michael R. Finn
  • Patent number: 9016638
    Abstract: An aircraft flap system and an associated method are provided to facilitate ground roll breaking without compromising in-flight performance. The aircraft flap system includes a first flap and a panel pivotally attached to the first flap, such as to a rearward portion of the first flap. The aircraft flap system also includes an actuator configured to controllably position the panel in a stowed position and in a deployed position. In the stowed position, the panel serves as a continuation of the first flap, thereby contributing to the lift provided by the first flap during flight. Conversely, in the deployed position, a panel is articulated relative to the first flap, thereby reducing or eliminating the lift otherwise provided by the flap, following landing of the aircraft.
    Type: Grant
    Filed: September 20, 2012
    Date of Patent: April 28, 2015
    Assignee: The Boeing Company
    Inventors: Bruce A. Dahl, Gene A. Quandt
  • Patent number: 8925869
    Abstract: An aerodynamic body, with at least one ancillary flap arranged such that it can be moved on the aerodynamic body with the aid of a guide mechanism, and with a drive device for purposes of actuating the ancillary flap, the guide mechanism having a pivotal articulation, by which the ancillary flap is articulated on the aerodynamic body such that it can be extended, and which is arranged in a rear region of the ancillary flap as viewed in the flow direction.
    Type: Grant
    Filed: January 25, 2013
    Date of Patent: January 6, 2015
    Assignee: Airbus Operations GmbH
    Inventors: Hendrik Friedel, Bodo Zapf
  • Patent number: 8708275
    Abstract: In order to generate an efficient aerodynamic braking force, whatever the speed of a vehicle such as an airplane flying in the air, the method includes a step for the production of energy by the vehicle, a step of storage of the energy produced and a step of utilization of such energy to drive a propeller which generates a force opposing the forward motion of the vehicle. Energy is produced by using the displacement of the vehicle with respect to air using a propeller driving a generator, or using the displacement with respect to the ground, using wheels driving a generator, or using generators driven by motors of the vehicle. The energy can be stored in the pneumatic, electric or kinetic form and the generation and driving means are selected according to the technology used for the storage means.
    Type: Grant
    Filed: March 19, 2008
    Date of Patent: April 29, 2014
    Assignee: Airbus Operations S.A.S.
    Inventor: Mathieu Belleville
  • Patent number: 8640989
    Abstract: A speed brake for aircraft in the form of a flap is provided. The flap can be extended into the air stream for increasing the flow resistance of the air. An extension is attached on the upper side of the flap on one side with respect to the center line of the flap, and the extension is attached in such a manner that in the retracted state of the flap, the extension extends along the flow direction of the air.
    Type: Grant
    Filed: August 26, 2009
    Date of Patent: February 4, 2014
    Assignee: EADS Deutschland GmbH
    Inventor: Otfrid Herrmann
  • Patent number: 8616496
    Abstract: Embodiments of the invention relate to systems and methods for a self-deploying vehicle drag device. In one embodiment, a drag device for a vehicle can be provided. The drag device can include a chute body, wherein the chute body is connected to the vehicle. The drag device can also include at least one collapsible member mounted to the chute body, wherein the at least one collapsible member and chute body are maintained in respective compressed configurations until deployed. Furthermore, the drag device can include at least one device adapted to release the chute body from the vehicle, wherein the chute body and the at least one collapsible member are deployed in expanded configurations with respect to the vehicle.
    Type: Grant
    Filed: August 3, 2011
    Date of Patent: December 31, 2013
    Assignee: The Aerospace Corporation
    Inventors: Brian S. Hardy, Jerome K. Fuller
  • Publication number: 20130032667
    Abstract: Embodiments of the invention relate to systems and methods for a self-deploying vehicle drag device. In one embodiment, a drag device for a vehicle can be provided. The drag device can include a chute body, wherein the chute body is connected to the vehicle. The drag device can also include at least one collapsible member mounted to the chute body, wherein the at least one collapsible member and chute body are maintained in respective compressed configurations until deployed. Furthermore, the drag device can include at least one device adapted to release the chute body from the vehicle, wherein the chute body and the at least one collapsible member are deployed in expanded configurations with respect to the vehicle.
    Type: Application
    Filed: August 3, 2011
    Publication date: February 7, 2013
    Applicant: THE AEROSPACE CORPORATION
    Inventors: Brian S. Hardy, Jerome K. Fuller
  • Patent number: 8231079
    Abstract: A speed brake apparatus reduces the airspeed of an aircraft by increasing aerodynamic drag. First and second brake panels are located on opposite sides of a portion of the aircraft, such as the fuselage, and are adapted to swing outward about a downstream hinge axis into deployed positions extending into the air stream. The panels are controlled by an operating device that includes a linear actuator. The actuator moves an operating head connected to a pair of toggle assemblies to convert linear movement of the operating head to the deployment and retraction movement of the brake panels.
    Type: Grant
    Filed: March 31, 2009
    Date of Patent: July 31, 2012
    Assignee: Honda Patents & Technologies North America, LLC
    Inventor: Hiroki Oyama
  • Publication number: 20120056038
    Abstract: An apparatus comprises a structure having a first side, a second side substantially opposite to the first side, a flexible skin, and a plurality of deformable assemblies. The flexible skin is attached to the first side and the second side of the structure. The plurality of deformable assemblies is moveably connected to the structure, in which each deformable assembly in the plurality of deformable assemblies has a vertex and a base. The each deformable assembly in the plurality of deformable assemblies has a height that is capable of changing to change a shape of the structure and a shape of the flexible skin.
    Type: Application
    Filed: November 14, 2011
    Publication date: March 8, 2012
    Applicant: THE BOEING COMPANY
    Inventor: Robert Erik Grip
  • Patent number: 8076623
    Abstract: A spin-stabilized projectile is steered by taking air from an air intake at the front of the projectile, and expelling the air along an outer surface of the projectile to alter its trajectory toward the desired impact location. Air taken in through the air intake is directed toward a rotor that is able to rotate relative to the rest of the projectile. The rotor has an outlet that may direct the air taken in at the air inlet out in a direction having both radial and circumferential components. The force produced in the radial direction provides a steering force substantially normal to the projectile axis, used to steer the projectile. The force produced in the circumferential direction is used to provide impetus to spin the rotor. A brake is used to control the rotational speed of the rotor, to control the direction that the air is expelled from the projectile.
    Type: Grant
    Filed: March 17, 2009
    Date of Patent: December 13, 2011
    Assignee: Raytheon Company
    Inventor: Richard L. Dryer
  • Publication number: 20110233330
    Abstract: An aircraft comprises an airbrake which is disposed upstream in front of a vertical tail and which can be swung out into the airflow approaching the vertical tail. In order to reduce structure dynamic loads on the vertical tail, passages are formed in the brake flap.
    Type: Application
    Filed: April 7, 2011
    Publication date: September 29, 2011
    Inventor: Christian Breitsamter
  • Publication number: 20110215197
    Abstract: A speed brake for aircraft in the form of a flap is provided. The flap can be extended into the air stream for increasing the flow resistance of the air. An extension is attached on the upper side of the flap on one side with respect to the center line of the flap, and the extension is attached in such a manner that in the retracted state of the flap, the extension extends along the flow direction of the air.
    Type: Application
    Filed: August 26, 2009
    Publication date: September 8, 2011
    Applicant: EADS Deutschland GmbH
    Inventor: Otfrid Herrmann
  • Publication number: 20110210208
    Abstract: System and method for inducing rapid reentry of orbital debris including determining a spatial extent of the orbital debris, and deploying dust to the orbital debris to enhance the drag on the orbital debris.
    Type: Application
    Filed: January 31, 2011
    Publication date: September 1, 2011
    Applicant: THE GOVERNMENT OF THE UNITED STATES, AS REPRESENTED BY THE SECRETARY OF THE NAVY
    Inventors: Gurudas Ganguli, Scott Steven Chappie, Leonid Ivanovich Roudakov, Christopher Eugene Crabtree
  • Patent number: 7964830
    Abstract: A vehicle may include a vehicle body maneuverable onto a near collision course with a target and a plurality of inflatable ballutes which, when inflated, extend generally radially from the vehicle body. A controller may cause the ballutes to be inflated prior to an anticipated time of collision with the target. A plurality of explosive charges may be attached to at least some of the ballutes. A detonation controller may be coupled to the controller and to the plurality of explosive charges.
    Type: Grant
    Filed: February 23, 2009
    Date of Patent: June 21, 2011
    Assignee: Raytheon Company
    Inventors: Thomas A. Olden, Robert J. Cavalleri
  • Publication number: 20100308180
    Abstract: A system for loading and unloading a cargo assembly onto and from an aircraft. The system comprises an aircraft and a movable platform. The aircraft comprises a forward fairing, an aft fairing, a spine disposed between the forward fairing and the aft fairing and a plurality of mounts coupled to the spine and configured to structurally engage the cargo container onto the spine. The aft fairing is movable between a fixed position for flight and an open position for at least loading and unloading of the cargo assembly. The aircraft is configured such that an unobstructed passageway is provided in an area underneath the spine during loading or unloading of the cargo assembly. An aft access is provided when the aft fairing is moved to the open position. The movable platform is used to maneuver the cargo assembly for loading and unloading onto and from the spine, respectively.
    Type: Application
    Filed: July 29, 2010
    Publication date: December 9, 2010
    Inventor: Elie HELOU, JR.
  • Patent number: 7775147
    Abstract: A latch including a first electrical explosive device disposed between first and second surfaces and a second electrical explosive device disposed between said first and second surfaces in series with said first electrical explosive device. In the illustrative embodiment, the vehicle is a missile or torpedo, the first surface is a drag door and the second surface is a vehicle body. In this embodiment, the first electrical explosive device is coupled to the vehicle body on a first end of the device and to a common series attachment on another end thereof and the second electrical explosive device is connected to the common series attachment on a first end and to the drag door on a second end thereof. An arrangement is included for activating the electrical explosive devices to effect a deployment of the drag door with a high degree of reliability.
    Type: Grant
    Filed: March 17, 2008
    Date of Patent: August 17, 2010
    Assignee: Raytheon Company
    Inventors: Daniel M. Crawford, Bruce E. Morgan
  • Publication number: 20100170981
    Abstract: In order to generate an efficient aerodynamic braking force, whatever the speed of a vehicle such as an airplane flying in the air, the method includes a step for the production of energy by the vehicle, a step of storage of the energy produced and a step of utilisation of such energy to drive a propeller which generates a force opposing the forward motion of the vehicle. Energy is produced by using the displacement of the vehicle with respect to air using a propeller driving a generator, or using the displacement with respect to the ground, using wheels driving a generator, or using generators driven by motors of the vehicle. The energy can be stored in the pneumatic, electric or kinetic form and the generation and driving means are selected according to the technology used for the storage means.
    Type: Application
    Filed: March 19, 2008
    Publication date: July 8, 2010
    Applicant: AIRBUS OPERATIONS
    Inventor: Mathieu Belleville
  • Publication number: 20100127115
    Abstract: It illustrated in FIG. 1 and FIG. 2. A controlled reservoir with at least 2 Adjustable holes. In our example 6 adjustable holes will able an aircraft to maneuver in 3 dimensions vectors. It will give more control to the pilot to make better and quicker maneuvers. And it can help to avoid accidents. Also it will give advantage to pilot in air to air combat.
    Type: Application
    Filed: May 8, 2007
    Publication date: May 27, 2010
    Inventor: Yigal Adir
  • Patent number: 7717370
    Abstract: A (bird tail type) airplane tail section (compound delta wing design) which includes: movable wing assemblies (92), attached to a center boom pitch assembly (76). Each rear wing assembly (92) is connected to a hydraulic control system (74) that selectively moves each rear wing assembly (92) in an arc on opposite sides of the boom pitch assembly (76). Each rear wing assembly (92) includes two pivoting parabrakes (32) mounted on the top and bottom surfaces of the wing assembly (92) that moves between a flush mounted configuration to an extended, air brake configuration. Hydraulic cylinders connected to the aircraft hydraulic system (74) are used to control the wing assemblies (92) and parabrakes (32). Disposed between the proximal end of the boom pitch assembly (76) and the aircraft fuselage is the pivoting joint (100) that enables the boom pitch assembly (76) to rotate and to pivot in all direction to simulate the movement and function of a bird's tail, when a bird is in flight.
    Type: Grant
    Filed: January 23, 2003
    Date of Patent: May 18, 2010
    Inventor: Rodney Cliff Levy
  • Publication number: 20100001131
    Abstract: The invention concerns an apparatus for and a method of producing aerodynamic resistance on an aircraft, comprising at least one braking flap, wherein the at least one braking flap can be extended into the airflow around the aircraft. In accordance with the invention at least one braking flap is arranged on the fuselage of the aircraft in a region over the wings of the aircraft.
    Type: Application
    Filed: May 9, 2007
    Publication date: January 7, 2010
    Applicant: AIRBUS DEUTSCHLAND GMBH
    Inventors: Anil B. Mertol, Volker Cleemann, Carsten Weber, Markus Fischer
  • Publication number: 20090242698
    Abstract: A speed brake apparatus reduces the airspeed of an aircraft by increasing aerodynamic drag. First and second brake panels are located on opposite sides of a portion of the aircraft, such as the fuselage, and are adapted to swing outward about a downstream hinge axis into deployed positions extending into the air stream. The panels are controlled by an operating device that includes a linear actuator. The actuator moves an operating head connected to a pair of toggle assemblies to convert linear movement of the operating head to the deployment and retraction movement of the brake panels.
    Type: Application
    Filed: March 31, 2009
    Publication date: October 1, 2009
    Applicant: HONDA MOTOR CO., LTD.
    Inventor: Hiroki Oyama
  • Patent number: 7070148
    Abstract: An aerodynamic including a main body and a control member. The main body is configured to be connected to a wing of an aircraft. The control member is connected to the main body, the control member including a fixed member secured to the main body and a pivotable member configured to increase a drag of the aircraft without substantially changing a lift of the aircraft.
    Type: Grant
    Filed: November 17, 2003
    Date of Patent: July 4, 2006
    Assignee: Airbus Deutschland GmbH
    Inventors: Susanne Wyrembek, Peter May, Klaus Muthreich
  • Publication number: 20040169110
    Abstract: An aerodynamic including a main body and a control member. The main body is configured to be connected to a wing of an aircraft. The control member is connected to the main body, the control member including a fixed member secured to the main body and a pivotable member configured to increase a drag of the aircraft without substantially changing a lift of the aircraft.
    Type: Application
    Filed: November 17, 2003
    Publication date: September 2, 2004
    Inventors: Susanne Wyrembek, Peter May, Klaus Muthreich
  • Publication number: 20040155146
    Abstract: A method of controlling a landing guide path of an aircraft and a method of steeping a landing guide path of an aircraft include rotating a portion of an aerodynamic component to increase a drag without influencing a lift. A method of controlling a landing guide path of an aircraft including an aerodynamic component having a main portion and a control portion, the main portion connected to a wing of the aircraft, and the control portion including a fixed member connected to a pivotable member. The method includes rotating the pivotable member to increase a drag without influencing a lift.
    Type: Application
    Filed: November 17, 2003
    Publication date: August 12, 2004
    Inventors: Susanne Wyrembek, Peter May, Klaus Muthreich
  • Publication number: 20040089765
    Abstract: A (bird tail type) airplane tail section (coumpound delta wing design) which includes: movable wing assemblies (92), attached to a center boom pitch assembly (76). Each rear wing assembly (92) is connected to a hydraulic control system (74) that selectively moves each rear wing assembly (92) in an arc on opposite sides of the boom pitch assembly (76). Each rear wing assembly (92) includes two pivoting parabrkaes (32) mounted on the top and bottom surfaces of the wing assembly (92) that moves between a flush mounted configuration to an extended, air brake configuration. Hydraulic cylinders connected to the aircraft hydraulic system (74) are used to control the wing assemblies (92) and parabrakes (32). Disposed between the proximal end of the boom pitch assembly (76) and the aircraft fuselage is the pivoting joint (100) that enables the boom pitch assembly (76) to rotate and to pivot in all direction to simulate the movement and function of a bird's tail, when a bird is in flight.
    Type: Application
    Filed: January 23, 2003
    Publication date: May 13, 2004
    Inventor: Rodney Cliff Levy
  • Patent number: 6682014
    Abstract: A braking device for increasing the drag coefficient of an associated shell at a desired point while in flight is described. The device comprises: at least two braking vane means which, when released, extend substantially symmetrically into a surrounding airstream while said shell is in flight; retaining means for maintaining said at least two vane means in a retracted first position out of said airstream during an initial portion of said flight; releasing means to allow said at least two vanes to extend to a second position into said airstream at a desired point during said flight; said at least two vane means being extended by centrifugal force due to rotation of said associated shell about its axis; and, said at least two vane means further including co-operating means to ensure substantially symmetrical extension into said airstream.
    Type: Grant
    Filed: March 8, 1999
    Date of Patent: January 27, 2004
    Assignee: BAE Systems plc
    Inventor: Dennis J Hickey
  • Patent number: 6588465
    Abstract: The aerial refueling drogue utilizes a bleeding drogue canopy providing substantially constant loads over a range of refueling speeds, by passive movement of the bleeding drogue between a retracted position and and extended position. The passive variable speed drogue comprises leading edge support arms, center support arms, and trailing edge support arms mounted to a refueling coupling member, with a forward drogue canopy attached between the leading edge support arms and the center support arms. An aft bleeding drogue canopy is connected between the center support arms and the trailing edge support arms. Springs in the trailing edge support arms bias the bleeding drogue canopy to a retracted position. In an alternate embodiment, cords are attached to the trailing edge of the aft bleeding drogue canopy, continue through the trailing edge support arms, up each center support arm, and through rings attached to the inside of the aft bleeding drogue canopy.
    Type: Grant
    Filed: January 15, 2002
    Date of Patent: July 8, 2003
    Assignee: West Coast Netting, Inc.
    Inventors: William L. Kirkland, Matts Lindgren, Jerry Stultz
  • Publication number: 20030106961
    Abstract: To control and particularly steepen the landing glide path of an aircraft, a respective aerodynamic component mounted on each wingtip includes a fixed plane member and a pivotable control element pivotally connected to the fixed plane member. The pivot axis is perpendicular to the major plane of the wing. The pivotable control element can be selectively pivotally deflected about the pivot axis relative to the fixed plane member, so as to thereby increase the overall drag without influencing the overall lift of the aircraft. This achieves a fine adjustment that is superimposed on the basic landing configuration established by the setting of the flaps, spoilers, engine thrust, etc. By increasing the drag without influencing the lift, this steepens the landing glide path slope.
    Type: Application
    Filed: December 6, 2002
    Publication date: June 12, 2003
    Inventors: Susanne Wyrembek, Peter May, Klaus Muthreich
  • Patent number: 6511016
    Abstract: A spin-stabilised artillery projectile (11) can be easily subsequently fitted with an axially symmetrical aerodynamic braking device for reducing the ballistic trajectory if the tip (14) which is equipped with the fuse (13) and which is easily removable from the projectile body (12) is equipped at approximately half its height with flap-shaped sectors (24) which are pivotably mounted in such a way that they can be pivotably extended and which in their launch position fit snugly into the conical peripheral surface of the tip (14) and in the operative position are pivotably extended to form a radial ring which is closed or which has gaps.
    Type: Grant
    Filed: May 10, 2001
    Date of Patent: January 28, 2003
    Assignee: Diehl Munitionssysteme GmbH & Co. KG.
    Inventors: Klaus Bär, Jürgen Bohl, Karl Kautzsch
  • Patent number: 6497600
    Abstract: An automatic pilot system for a model airplane comprising one or more flexible control elements. When installed on a vertical stabilizer of the airplane, a flexible control element acts as an automatic rudder which provides directional control for the airplane so that it takes off in a straight line at high speed and glides in a circular path of a predetermined radius at low speed. When installed on a horizontal stabilizer of the airplane, a flexible control element acts as an automatic elevator which provides a reduced angle of attack during take-off to minimize the aerodynamic drag, an increased angle of attack during gliding flight to make the flight slower and longer-lasting, and an even greater angle of attack during landing to make the landing even slower for safety. When installed on a wing of the airplane, a flexible control element acts as an automatic dihedral wing tip which provides increased lateral stability for the airplane.
    Type: Grant
    Filed: October 5, 1999
    Date of Patent: December 24, 2002
    Inventors: Alejandro Velasco Levy, Ildiko Palyka
  • Patent number: 6491261
    Abstract: A wing mounted yaw control device is disclosed. The wing mounted yaw control device includes a spoiler hingedly mounted on a first wing surface and a deflector hingedly mounted on a second wing surface. A deployment mechanism is provided to effect simultaneous deployment of the spoiler and deflector. During operation, the spoiler and deflector are selectively deployed in order to impart an unbalanced drag force on one wing, thereby imparting the desired yaw moment to an aircraft in flight.
    Type: Grant
    Filed: April 17, 2000
    Date of Patent: December 10, 2002
    Assignee: The United States of America as represented by the Secretary of the Air Force
    Inventor: William Blake
  • Patent number: 6398167
    Abstract: An aircraft braking system including a port formed in a side of an airplane. The port has an openable door disposed therein. The openable door is in operative communication with a computerized hydraulic system of the airplane whereby the openable door will open once the airplane begins a turn and will not close until the turn is complete.
    Type: Grant
    Filed: July 3, 2000
    Date of Patent: June 4, 2002
    Inventor: Eddie Ortiz