Patents Examined by T D Collins
-
Patent number: 7118071Abstract: Methods and systems for controlling shocks on airfoil lower surfaces are disclosed. An airfoil in accordance with one embodiment of the invention includes an upper surface portion having an upper surface positioned to face generally upwardly during the level flight, and a lower surface portion having a leading edge region, a trailing edge region and a lower surface positioned to face generally downwardly during level flight. A shock control protrusion extends away from the lower surface and is positioned to generate a shock extending away from the lower surface at a least one flight condition.Type: GrantFiled: March 31, 2004Date of Patent: October 10, 2006Assignee: The Boeing CompanyInventor: David R. Bogue
-
Patent number: 7118076Abstract: A satellite, in particular a telecommunication satellite, comprises a structure having a north face and a south face that are oriented perpendicularly to the rotation axis of the Earth and an east face and a west face that are periodically exposed to solar radiation as the satellite orbits the Earth. The structure supports equipment dissipating heat, the north, south, east and west faces constituting radiator panels that radiate into space heat dissipated by the equipment.Type: GrantFiled: February 27, 2004Date of Patent: October 10, 2006Assignee: AlcatelInventors: Tisna Tjiptahardja, Marcel Amidieu, GĂ©rard Cluzet
-
Patent number: 7097133Abstract: An articulated wing (20) is readily deployable from a stowed configuration that occupies minimal volume to an extended configuration for flight. The wing (20) includes a frame (24) having a pair of beams (30) spaced by one or more ribs (36), and a flexible covering material (26) over the frame (24) that defines the surface of the wing (20). Each beam (30) typically has multiple segments (40), and each segment (40) is pivotally connected to an adjacent segment (40) at a joint (42). A flexible actuation line (52) extends past each joint (42) and is attached to a portion of the beam beyond the joint. The beam (30) also includes portions that act as stops (46). The stops (46) limit the range of angular motion through which the respective segments (40) can rotate relative to one another. Consequently, when tension is applied to the line (52), the segments (40) rotate until respective stops (46) prevent further rotation. Tension in each line (52) keeps the wing (20) in its extended configuration.Type: GrantFiled: August 19, 2004Date of Patent: August 29, 2006Assignee: Raytheon CompanyInventor: Daryl B. Elam
-
Patent number: 7093801Abstract: A positioning system, device, and method are provided to facilitate the in-flight positioning of two aircraft relative to one another such that a second aircraft is guided to an in-flight refueling position relative to a first aircraft. The system, device, and method of the present invention provide a signal emitted from a positioning device carried by the first aircraft, wherein the signal defines a signal envelope containing the in-flight refueling position. The signal is adapted to be receivable by the second aircraft such that the signal may guide the second aircraft to the in-flight refueling position relative to the first aircraft.Type: GrantFiled: May 28, 2004Date of Patent: August 22, 2006Assignee: The Boeing CompanyInventor: Steven B. Schroeder
-
Patent number: 7070146Abstract: An aircraft thickness/camber control device mounts to the lower surface of a airfoil configuration, for example on a fuselage, and extends along a longitudinal axis. The device, when deployed, generates expansions ahead of compressions generated by off-design conditions, inlet spillage for example, and enables maintenance of a low boom signature. The device, when positioned at appropriate locations, may also be used as a drag reduction device. The thickness/camber control device comprises a structural member capable of coupling to the airfoil at a position forward of the concentrated source of added compression and a control element. The control element is coupled to the structural member and controls the structural member to adjust thickness/camber of the configuration to cancel the far-field effect of the extra compression or concentrated pressure source.Type: GrantFiled: August 29, 2003Date of Patent: July 4, 2006Assignee: Supersonic Aerospace International, LLCInventors: John M. Morgenstern, Alan E. Arslan
-
Patent number: 7066429Abstract: A system and method is provided for directing a separation sequence of structural components, such as, for example, aircraft landing gear components, during an overload condition. This system and method may be used to stop a component in rotation and thereby allow the component to fail in a predictable and controllable manner. This system and method may be used on any type of device that utilizes components that rotate relative to one another and/or that has components that rotate during an overload condition.Type: GrantFiled: June 25, 2004Date of Patent: June 27, 2006Assignee: The Boeing CompanyInventors: Mitchell L. Mellor, Christopher A. Reitz
-
Patent number: 7063291Abstract: An amphibian delta wing jet aircraft, which has a plurality of triangular folding wing panels, two of which are hingedly attached to a lifting shape body, which incorporates a W-shaped hull in it's cross section of a fuselage so that the craft operates efficiently as an aircraft when flying through the air with the wings in a fully unfolded extended position. The craft also performs well as a watercraft capable of relatively high speeds on the water surface when the wing are folded-up in a non extended position. The W-shape hull transverse cross section also provides excellent characteristics so that the craft can hydroplane over marshlands or waterlogged soil which may be covered with emersed rushes, or snow, cattails and other tall grasses. The craft is also provided with four retractably mounted mechanically extendable wheels, to be utilized when configured as a land vehicle.Type: GrantFiled: May 25, 2004Date of Patent: June 20, 2006Inventor: Kenneth S. Rado
-
Patent number: 7063292Abstract: An actuation apparatus for a control flap which is disposed on the trailing edge of the wing of an aircraft and which can be displaced between a stowed position and an extended position, in which it is displaced rearwardly relative to the trailing edge of the wing and angled downwardly relative to the wing plane; and corresponding intermediate positions. The actuation apparatus has a pyramid mechanism arrangement connected, on the one hand, to the load-bearing structure of the wing and, on the other hand, to the control flap, with at least one virtual axis which lies, in particular, at a finite distance from the plane of the wing profile and relative to which the control flap can be displaced.Type: GrantFiled: September 23, 2004Date of Patent: June 20, 2006Assignee: EADS Deutschland GmbHInventor: Juan Perez-Sanchez
-
Patent number: 7040573Abstract: An aerodynamically efficient fiberglass hull consisting of a pointed bow, a step amidships, and aft section coming to a point which will be attached to the hull of land aircraft and convert them to water operations. In addition, one wing float will be securely attached to the outboard section of each wing. The main and nose landing gear will be removed enabling the propellers to have adequate clearance from water. Landing gear removal procedures will not be used for amphibious aircraft.Type: GrantFiled: June 4, 2004Date of Patent: May 9, 2006Inventor: Richard Selman
-
Patent number: 7040571Abstract: The present invention concerns a single pull horn with a control arm that may be used to control the movement of a component of a remote or radio-controlled vehicle having a center line. The control arm includes a threaded rod as well as a base member. The base member is positionable on the side of the component.Type: GrantFiled: April 2, 2004Date of Patent: May 9, 2006Assignee: Du-Bro Products, IncInventor: James E. Broberg
-
Patent number: 7036768Abstract: A multi-purpose airship usable for multi-purposes with less maintenance cost is provided. The multi-purpose airship comprises an operator cabin (1) to which a work device of agricultural chemical scattering device (10) or the like is fittable, a rotor (4) fitted to a top of the operator cabin (1) and having rotor blades of plural stages (or coaxial rotors) of which fitting angle (or pitch) is adjustable to generate a lifting force and propulsive force, a balloon (5) detachably fitted to a top of the rotor (4) and filled with gas lighter than air to generate a lifting force, a stabilizing wing (2) elongating horizontally from each side of the operator cabin (1) and a propulsion device (3) comprising a propeller device or jet engine fitted to a distal end of the stabilizing wing (2) to vary a thrust direction between the horizontal direction and the vertical direction.Type: GrantFiled: July 30, 2004Date of Patent: May 2, 2006Inventor: Mutsuro Bundo
-
Patent number: 7032864Abstract: An aerodynamic wing formed by a flexible canopy with integrated inflatable, elastically deformable members integrated into the lifting surface. Preferably, the elastically deformable member extends and contracts the lifting surface depending on forces experienced by the wing. In one embodiment, the wing comprises an inflatable leading edge kite.Type: GrantFiled: December 9, 2003Date of Patent: April 25, 2006Inventor: Tony Logosz
-
Patent number: 7032860Abstract: An anti-torque thruster system implemented onboard an aircraft comprising a propulsion means coupled to the aircraft, wherein the propulsion means is capable of providing a measure of anti-torque thrust to the aircraft, a fuel storage container coupled to the propulsion means via a fuel delivery conduit, wherein the fuel storage container is capable of storing an appropriate fuel for the propulsion means, a valve means disposed between the fuel storage container and the propulsion means, wherein the valve means may be useable to regulate the flow of fuel from the fuel storage container to the propulsion means, and a controller for controlling the valve means to regulate the flow of fuel from the fuel storage container to the propulsion means, wherein the controller is capable of receiving input from at least one input device.Type: GrantFiled: November 5, 2004Date of Patent: April 25, 2006Assignee: EATTS, LLCInventors: Charles T. Kirk, Virginia L. Hodder, legal representative, Grover L. Moore, deceased
-
Patent number: 7021587Abstract: A system for providing automatic trim control associated with a control surface in an aircraft that utilizes at least two sensors that must agree in direction before trim adjustment is made. Each sensor is provided with a separate an independent controller channel to further enhance fail-safe operation. A trim sensor is placed in the coupling link between a servo and aircraft primary control linkage leading to the associated control surface. A trim sensor is provided that utilizes a spring with a portion disposed laterally with respect to the direction of the force to be measured. An arm is attached to the lateral portion of the spring to effect motion that can be sensed by various sensors including optical, mechanical switch and magnetic sensors.Type: GrantFiled: January 7, 2004Date of Patent: April 4, 2006Assignee: Trutrak Flight Systems, IncInventor: James R. Younkin
-
Patent number: 7017521Abstract: A bird feeder having a rechargeable electrical power source and a solar energy system that collects solar energy, converts it into electrical energy, and uses the electrical energy to recharge the rechargeable electrical power source is disclosed. The rechargeable electrical power source can be used to power a wide variety of electrical devices, such as microphones, radio receivers or transmitters, cameras, audio recording and playback devices, video recording and playback devices, loud speakers, lighting elements, timing devices, remote controls, motors, etc.Type: GrantFiled: February 22, 2005Date of Patent: March 28, 2006Assignee: World Factory, Inc.Inventor: Gregory G. Kuelbs
-
Patent number: 7004431Abstract: An aircraft attached apparatus/method for spraying pesticides having two propeller shafts attached to the aircraft. Each shaft has a full feathering propeller mounted at the forward ends of the propeller shaft and a control cable extending to the cockpit. High pressure pumps, typically piston pumps, are mounted on the aft ends of each of the propeller shafts. The input side of the pumps are connected to a tank, and the output side is connected to respective matrix spray boom assemblies. The forward ends of each of the spray boom assemblies are connected to the output side of each respective pump. Spray nozzles, typically impingement nozzles, are attached to each of the aft ends of each spray boom. The high pressure pumps have an electrically operated magnetic brake attached thereto, and each of the spray boom assemblies have a pressure transmitter connected to a digital display in said aircraft.Type: GrantFiled: May 18, 2004Date of Patent: February 28, 2006Assignee: Aeromister, LLCInventor: Richard Howe
-
Patent number: 7004426Abstract: A flight control system for a rotorcraft to prevent the adverse effects of the vortex ring state is disclosed. In the flight control system of the present invention, selected control inputs are sent the rotorcraft prior to the onset of the vortex ring state. In the preferred embodiment, the control inputs are transient, do not require input from the pilot, and do not affect the flight path of the rotorcraft.Type: GrantFiled: March 1, 2005Date of Patent: February 28, 2006Assignee: Bell Helicopter Textron Inc.Inventor: Ronald L. Kisor
-
Patent number: 6966262Abstract: Current modulation-based talkback in a system in which the background noise in the level of current draw is minimized such that the talkback is effected with a desirably high signal-to-noise ratio, such as by the master device holding the system voltage low such that the slave devices will not be performing tasks that would cause the current draw on the system to have an undesirable level of background noise, or, in an electronic blasting system, by preventing all other detonators from performing tasks that would create an undesirable background current draw when a particular detonator is talking back.Type: GrantFiled: July 15, 2003Date of Patent: November 22, 2005Assignee: Special Devices, Inc.Inventor: David T. Jennings, III
-
Patent number: 6959896Abstract: An aircraft capable of supersonic flight comprises a body portion including a fuselage, a wing, and an engine nacelle mounted below the wing. The aircraft may also include a high-mounted aft, tail. The area/lift distribution of the body portion is tailored to reduce sonic boom disturbance. The body portion further includes a blunt nose and a gull dihedral wing configuration that further reduces sonic boom disturbance and eases constraints on area/lift distribution tailoring. The gull dihedral wing or tail is configured to carry lifting force to its trailing edge to create an expansion at the aft end of the aircraft that reduces aft sonic boom ground shock strength. The volume of the mid-portion of the fuselage can be reduced above the wing to create a sloped surface that generates an expansion fan over the wings.Type: GrantFiled: July 3, 2003Date of Patent: November 1, 2005Assignee: Lockheed Martin CorporationInventors: Tom Hartmann, John M. Morgenstern
-
Patent number: 6945497Abstract: A cockpit door body 10 can be opened toward a cockpit in a direction shown by arrow R1 by a crew inside a cockpit 3 by manipulating a knob on a first hinge device 40. When rapid decompression occurs in the cockpit, a mechanical pressure-sensitive device of the first hinge device 40 operates to release a bolt from a catch. By the difference in pressure between the cabin and the cockpit, the door body 10 opens in the direction of arrow R1 to thereby reduce pressure difference. When rapid decompression occurs in cabin 4, a second latch device 60 detects this pressure difference and operates mechanically to rotate a link lever 62 to release a stopper 64 from a catch 66. Flaps 30 and 32 are opened toward cabin 4 in the direction of arrow R2 by the difference in pressure between the cockpit and cabin to thereby reduce pressure difference.Type: GrantFiled: January 20, 2004Date of Patent: September 20, 2005Assignee: Jamco CorporationInventors: Fumiaki Saku, Tadashi Watanabe, Yasuo Sekikawa