Patents Examined by Barry L. Kelmachter
  • Patent number: 4283029
    Abstract: A trailing edge flap moveable from a stowed position behind a wing to a downwardly and rearwardly extending position to deflect jet exhaust from an upper surface blowing jet engine downwardly and rearwardly to augment lift. The actuating mechanism rotates the flap about a variable radius which maintains the upper surface of the flap in contact with and generally in tangential alignment with the trailing edge of the upper surface of the wing. This mechanism comprises forward and rear radius links pivotally mounted at their lower ends to a stationary mounting arm, and extending upwardly and divergently therefrom to attach to the flap. In two embodiments, the rear radius link has its pivot end mounted to a moveable member which in turn enables the flap to be rotated so that its forward end moves downwardly. Thus, in its fully deployed position, the flap can be rotated to form a slot between the aft end of the wing and the leading edge of the flap.
    Type: Grant
    Filed: January 2, 1979
    Date of Patent: August 11, 1981
    Inventor: Peter K. C. Rudolph
  • Patent number: 4275861
    Abstract: A preselected axis other than the axis of maximum moment of inertia of a momentum stabilized spacecraft is oriented for alignment with the total angular momentum vector of the spacecraft by rotating one or more rotors to a critical rate of rotation. The rotation of the rotor or rotors is maintained at the critical rate to effect the desired rotation. The axis of the rotor or the effective angular momentum vector of the resultant momentum of a plurality of rotors is aligned with the axis of the desired spacecraft orientation. Energy dissipation assures stability by dissipating energy on the spacecraft body at a faster rate of dissipation than the rate of energy dissipation on the rotor.
    Type: Grant
    Filed: August 4, 1978
    Date of Patent: June 30, 1981
    Assignee: RCA Corporation
    Inventor: Carl H. Hubert
  • Patent number: 4261533
    Abstract: Tilting the stabilizer at an extreme angle to the fuselage, with leading edge down, and controlling and varying engine thrust comprise a method for all-axis control of a generally conventional aircraft in ultra deep stall. The method is effective in recovery from unstable and unusual flight attributes and in landing emergencies; the aircraft may land in the ultra deep stall configuration or conventional flight may be resumed. So-called flying wing aircraft, where pitch control surfaces are incorporated with the trailing edge of the primary lift surface, are also controllable in ultra deep stall by the method of this invention.
    Type: Grant
    Filed: June 26, 1978
    Date of Patent: April 14, 1981
    Assignee: Dynamic Engineering, Inc.
    Inventors: Lawrence T. Roberts, Thomas H. Strom
  • Patent number: 4258890
    Abstract: The system is used in power-assisted control systems to provide a restoring force to the control stick indicative to the pilot of the deflection of a control surface. The feel system is trimmable in that the neutral position can be altered. In prior systems trimming was accomplished by releasing a brake which permitted movement of a part of the control stick linkage toward an equilibrium position in response to the restoring force. In prior systems the released part acquired sufficient momentum to cause it to overshoot and oscillate about the equilibrium position. If the brake were engaged prematurely, the momentum was imparted to the control stick resulting in a disagreeable "kick" felt by the pilot. To overcome these problems, the brake is repetitively disengaged and engaged at a repetition rate in the range 5-40 Hz. The small amount of momentum built up in each of the successive cycles results in an almost imperceptible vibratory reaction on the control stick rather than a single large "kick".
    Type: Grant
    Filed: July 3, 1978
    Date of Patent: March 31, 1981
    Assignee: Summa Corporation
    Inventor: Gregory J. Korkosz
  • Patent number: 4254924
    Abstract: An aircraft seat having a pivotal seat back which has an upright position for occupancy and an advanced position for affording additional living space to the passenger occupying the next rearward seat including a detent mechanism to maintain the seat back in either of its positions and to allow passenger adjustment of the seat back between these two positions.
    Type: Grant
    Filed: May 25, 1979
    Date of Patent: March 10, 1981
    Assignee: Koehler-Dayton, Inc.
    Inventor: Edward J. Brennan
  • Patent number: 4253625
    Abstract: A single winged aircraft adapted to be attached to the back of a pilot, including a jet fuel engine whereby it may be propelled into space and sustained in flight, and provided with manually operable controls for controlling operation of ailerons and the directional issuance of the jet stream exhausting from the engine, whereby the aircraft may be directionally controlled in flight by the pilot.
    Type: Grant
    Filed: September 10, 1979
    Date of Patent: March 3, 1981
    Inventor: Igor Dmitrowsky
  • Patent number: 4248395
    Abstract: Dual flap sections are supported by linkage, first for chordwise movement of the forward flap section rearwardly from the wing and for chordwise movement of the rear flap section rearwardly from the forward flap section, and then for tilting of the two flap sections conjointly to increase their angle of incidence relative to the wing. The forward flap section is supported by motion-amplifying compound linkage for effecting chordwise movement of the forward flap section relative to the wing, and the rear flap section is supported by motion-amplifying compound linkage from the forward flap section for effecting chordwise movement of the rear flap section relative to the forward flap section. Control mechanism for both motion-amplifying compound linkages is connected to the wing and is movable first to actuate the linkages primarily for shifting the two flap sections chordwise rearwardly from the wing and then primarily to tilt the foward and rear flap sections conjointly to increase their angle of incidence.
    Type: Grant
    Filed: July 3, 1978
    Date of Patent: February 3, 1981
    Assignee: The Boeing Company
    Inventor: James B. Cole
  • Patent number: 4248394
    Abstract: A remotely controlled powered aircraft equipped with engine, propeller and landing gear, radio-controlled from the ground and capable of towing a manned hang glider to an appropriate altitude. On reaching altitude, the pilot of the hang glider releases the tow, and the pilotless towing aircraft is returned to the launching site under radio control from the ground. During towing of the hang glider, two-way communication is maintained between the hang glider pilot and the towing aircraft remote pilot.
    Type: Grant
    Filed: March 5, 1979
    Date of Patent: February 3, 1981
    Inventor: Marlin K. Klumpp
  • Patent number: 4247063
    Abstract: Retractable wing-tip mounted vanes are actuated from the normal cockpit controls of an airplane to provide both roll control and direct lift control. When not required, these devices retract into wing fairings. Simple to manufacture and operate, these controls permit reduced manufacturing costs through much simpler wing construction. The vanes consist of suitably constructed plates that slide over one another and which form an end plate to the wing when fully deployed. Asymmetric deployment produces an out-of-balance moment in roll; symmetric deployment induces direct lift by increasing wing lift on both wing panels.
    Type: Grant
    Filed: August 7, 1978
    Date of Patent: January 27, 1981
    Assignee: Lockheed Corporation
    Inventor: Michael W. Jenkins
  • Patent number: 4247062
    Abstract: A high efficiency vertical tail unit is combined with a variable wing geory for large angles of attack, primarily for all-wing aircraft such as delta-type craft. The vertical tail unit is hinged for adjustment about an axis substantially parallel to the longitudinal axis of the fuselage. The outer wing portions are connected, at an angle, with a vertical tail unit which is directed vertically downward in its normal position. The assembly comprising an outer wing portion and a vertical tail unit is rotatable about the parallel axis whereby three different wing types may be realized in the same craft.
    Type: Grant
    Filed: November 27, 1978
    Date of Patent: January 27, 1981
    Assignee: Messerschmitt-Boelkow-Blohm Gesellschaft mit beschraenkter Haftung
    Inventor: Hartmut Brueckner
  • Patent number: 4247066
    Abstract: Airfoil device and method providing smooth, continuous, variation in airfoil camber and surface curvature over substantially the entire length of the device by use of a trusslike bendable beam as an airfoil rib having the airfoil skin surfaces flexibly slidable relative thereto. The beam is divided chordwise into upper and lower beam members each formed of a plurality of articulated sections. The beam members are connected by a bendable jackscrew which upon rotation causes one member to move chordwise, and its curvature to be changed, relative to the other thereby effecting deflection of the airfoil with concomitant variation in its camber and the curvatures of its outer skin surfaces.
    Type: Grant
    Filed: February 21, 1978
    Date of Patent: January 27, 1981
    Assignee: General Dynamics Corporation
    Inventors: Richard C. Frost, Eduardo W. Gomez, Robert W. McAnally
  • Patent number: 4247061
    Abstract: A helicopter stabilator having naturally high response to the main rotor wake excitation frequency in roll and yaw stabilator vibratory modes is selectively mounted so as to be detuned therefrom in antisymmetric stabilator vibratory modes without adversely affecting symmetric stabilator vibratory modes, stabilator vertical stiffness, or stabilator pitch stiffness.
    Type: Grant
    Filed: July 12, 1978
    Date of Patent: January 27, 1981
    Assignee: United Technologies Corporation
    Inventors: William A. Kuczynski, John Marshall, II, deceased
  • Patent number: 4245803
    Abstract: For a winged high speed missile that includes a two-dimensional inlet supplying air to the missile power plant, the compression ramp of the inlet is oriented with respect to the outwash angle produced by the missile body and the underneath surface of the wing such that the compression ramp of the inlet is subjected to an effective angle of attack. By proper inlet orientation the captured flow is turned inwardly toward the missile center line further compressing the incoming air.
    Type: Grant
    Filed: August 2, 1978
    Date of Patent: January 20, 1981
    Assignee: United Technologies Corporation
    Inventor: Raymond L. DeBlois
  • Patent number: 4245804
    Abstract: A wing extension or tip fin is disclosed wherein the tip fin is joined to an aircraft wing to form a nonplanar wing configuration which minimizes induced drag during both low speed and high speed operation of an aircraft. The tip fin which is of generally trapezoidal geometry, extends streamwise along the end of the aircraft wing and is canted to project upwardly and outwardly therefrom. Additionally, the tip fin is twisted to toe-out relative to the freestream direction with the angle of twist varying along the lower portion of the tip fin length. Viewed from the side, the tip fin has a sweep angle at least equal to the sweep angle of the aircraft wings with the leading edge of the tip fin intersecting the wing tip chord at a position aft of the wing leading edge. A strake which extends along the upper surface of the wing from the wing leading edge to the tip fin leading edge, forms a smooth transition between the wing and tip fin.
    Type: Grant
    Filed: December 19, 1977
    Date of Patent: January 20, 1981
    Assignee: The Boeing Company
    Inventors: Kichio K. Ishimitsu, Neal R. Van Devender
  • Patent number: 4245805
    Abstract: Command from engine rating control prevents throttle position from exceeding the value at which the engine operates at its rated power. Flare initiation changes the throttle command signal from a closed loop control signal to a fixed number of degrees per second retard rate, thereby overriding an aft limit switch signal allowing throttles to reach the idle position. A servo feedback arrangement utilizes a tachometer signal and an engine PLA (power lever angle) signal to optimize servo performance and overcome undesired control cable characteristics.
    Type: Grant
    Filed: November 25, 1977
    Date of Patent: January 20, 1981
    Assignee: The Boeing Company
    Inventor: Leonard P. Stephan
  • Patent number: 4243188
    Abstract: Precompression fins extending perpendicular from the wings of a high speed missile are judiciously located relative to an axisymmetric inlet of an airbreathing power plant such that the outwash angle induced by the body and wing of the missile enhances the performance of the inlet.
    Type: Grant
    Filed: August 2, 1978
    Date of Patent: January 6, 1981
    Assignee: United Technologies Corporation
    Inventor: Raymond L. DeBlois
  • Patent number: 4243190
    Abstract: A rotary wing device has a circular stabilizer disc and, secured normally thereto, a bilaterally symmetrical wing member having a first symmetry axis intersecting the center of the stabilizer disc. The ends of the wing member at the first symmetry axis are connected through pin connections to a string harness whereby the device functions as a kite when the wing member rotates about the first symmetry axis. At least one guy wire connects the frame of the stabilizer disc to the frame of the wing member in each quadrant of the device. The same device may function in free flight without the string harness. The device preferably is fabricated from rod or tube frames covered with plastic films.
    Type: Grant
    Filed: March 8, 1979
    Date of Patent: January 6, 1981
    Inventor: Kenneth Sams
  • Patent number: 4240601
    Abstract: A method wherein a propeller driven, hydrazine powered aircraft is remotely piloted through rarefied atmosphere of a selected planet, including the planet Earth, and employed as a communication platform for a telemetry system provided for relaying information relating to features characterizing the surface of the planet.
    Type: Grant
    Filed: May 30, 1979
    Date of Patent: December 23, 1980
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventor: Robert D. Reed
  • Patent number: 4238092
    Abstract: An accessory for a jet engine for tuning turbine exhaust gases for maximum thrust capabilities in the absence of a turbine thrust reverser and cowling combination normally for and utilized thereon. The accessory comprises an inner streamlined nozzle shell forming a continuation of the outer skin of the turbine exhaust duct, a center mounted engine plug providing a path for the turbine gases between the inner nozzle surface and the engine plug outer surface and a transition adapter for mating and attaching the plug to the center of the engine. The engine plug is further provided with an opening between its engine attached and outer ends providing communication between the engine and the atmosphere adjacent the rear end of the plug. The accessory further comprises a fairing for attachment to the pylon supporting the engine to further tune the gases leaving the nozzle.
    Type: Grant
    Filed: August 17, 1978
    Date of Patent: December 9, 1980
    Assignee: Rohr Industries, Inc.
    Inventor: John M. Brennan
  • Patent number: 4235397
    Abstract: A flow deflector blade primarily for mounting within the efflux of an aircraft propulsion fan so that a change of flow direction can be effected, includes a leading edge member, a trailing edge member, a leaf spring member of arcuate form connecting the two, and filler portions of rubber bonded to each side of the leaf spring member shaped to provide a desired blade contour.
    Type: Grant
    Filed: April 26, 1979
    Date of Patent: November 25, 1980
    Assignee: British Aerospace
    Inventor: Christopher J. Compton