Fluid Patents (Class 244/52)
  • Patent number: 4569493
    Abstract: Canards are pivotally mounted on the fuselage of a variable sweep wing jet aircraft and project laterally with respect to the fuselage forwardly of the wings. The canards are positioned and configured to produce pitch control moments about the center of gravity. Thrust-vectoring devices extend from the jet engines of the aircraft for varying the thrust direction of such engines. A control system is mounted in the fuselage and extends to the wings, the canards and the thrust-vectoring devices for controlling the wings in angular positions relative to the fuselage, controlling the canards in rotary position relative to the fuselage and controlling the thrust-vectoring devices to control the thrust direction. The positions are controlled in coordination to overcome pitch departure, deep stall and spin, which might otherwise occur due to lack of nose-down pitch power, while also optimizing supersonic cruise and transonic maneuver performance of the aircraft.
    Type: Grant
    Filed: March 14, 1983
    Date of Patent: February 11, 1986
    Assignee: Grumman Aerospace Corporation
    Inventor: Walter R. Burhans, Jr.
  • Patent number: 4560121
    Abstract: An automotive vehicle includes an aerodynamic fin effective for vehicle control at relatively high vehicle velocity, and a nozzle directing a reaction jet toward said fin render the latter also effective for vehicle control at relatively low vehicle velocity.
    Type: Grant
    Filed: May 17, 1983
    Date of Patent: December 24, 1985
    Assignee: The Garrett Corporation
    Inventor: Leslie S. Terp
  • Patent number: 4531693
    Abstract: A steering system for a missile provided with aerodynamic surfaces such as fins comprises a gas generator and lateral nozzles through which the gas generated by the gas generator emerges. The nozzles are arranged to lie between adjacent pairs of the aerodynamic surfaces, to project beyond the fuselage of the missile and to have an oblong cross-section, the largest dimension of which lies substantially parallel to the longitudinal axis of the missile. The gas flow through the nozzles is controlled by complete or partial closing of the nozzles. The shape and placement of the nozzles minimizes changes in the aerodynamic characteristics of the missile caused by interaction between the gas jets emerging from the nozzles and the flow of air over the aerodynamic surface of the missile.
    Type: Grant
    Filed: November 10, 1983
    Date of Patent: July 30, 1985
    Assignee: Societe Nationale Industrielle et Aerospatiale
    Inventors: Jacques Raynaud, Jean Darmois, Pierre Jolivet, Jean Guillot
  • Patent number: 4522357
    Abstract: An opening in the nose of a missile allows entry of ram air during missile flight to a central chamber. Oppositely oriented steering jets are interconnected with the aft end of the central chamber and escaping ram air provides lateral steering thrust forces. A movable diverting means controls the direction that the escaping ram air is diverted and thereby controls the steering forces.
    Type: Grant
    Filed: January 19, 1983
    Date of Patent: June 11, 1985
    Assignee: Ford Aerospace & Communications Corp.
    Inventors: William R. Bains, Calhoun W. Sumrall
  • Patent number: 4512258
    Abstract: One of several inventions claimed is a method of providing increased traction to the driving wheels of a high speed transportation vehicle. The vehicle is placed within a tubular passageway, equipped with wheels arranged to contact the tube at three or more equidistant contact points, and these wheels are pressed against the inside surface of the tube by means of controlled application of powerful hydraulic pressure. Vertical stability of the vehicle is achieved by a new apparatus comprised of a spoke attached to the vehicle which projects outward to a point adjacent to but not touching the tube, a set of wheels transversely mounted on each side of the spoke, and a pair of L-shaped guide rails between which the wheels roll. An improved wind resisting braking system is claimed which uses extendable baffle plates and air ports from which compressed air is ejected in a direction opposed to the direction of travel.
    Type: Grant
    Filed: January 7, 1983
    Date of Patent: April 23, 1985
    Inventor: Kosuke Matsukata
  • Patent number: 4482109
    Abstract: A jet aircraft is provided of the vertical or short take off and land (VSTOL) type which is a stable and controllable in all flight attitudes. The aircraft exhibits a high engine thrust/weight ratio which enables it to achieve shorter take-off, shorter landing distances and faster climbs as compared with prior art aircraft of the same general type. The aircraft includes two jet engines mounted side-by-side in its nose which assist in achieving smooth variation in cross-sectional area so that the area rule is not violated, and this enables efficient flight speeds in the sonic vicinity to be achieved. The exhaust of each engine of the aircraft is controlled by a thrust deflector and associated air foil array, the thrust deflector being deflected downwardly at an angle of substantially 75.degree.
    Type: Grant
    Filed: June 4, 1981
    Date of Patent: November 13, 1984
    Inventor: Anthony A. duPont
  • Patent number: 4457476
    Abstract: A wingless aircraft that has a generally truncated cone fuselage that has a cockpit in the upper thereof in which the pilot sits, and a transparent rigid dome mounted on the upper portion of the fuselage that extends over the pilot. A number of equally spaced, elongate, jet engine assemblies are pivotally and adjustably supported within the fuselage, with each engine in communication with an air inlet defined in the fuselage. Each jet engine assembly includes a combustion chamber that has an elongate tubular nozzle extending downwardly therefrom, in which exhaust openings are defined through which the hot gaseous products of combustion discharge. The exhaust openings are elongate and substantially angularly disposed relative to the vertical, and as a result the exhaust gases not only rotate the nozzle but exert a reactive force sufficient to lift the fuselage to an airborne position.
    Type: Grant
    Filed: November 20, 1981
    Date of Patent: July 3, 1984
    Inventor: Frank Andresevitz
  • Patent number: 4456203
    Abstract: An aircraft propulsion system is disclosed having an exhaust nozzle structure having an exhaust deflection structure extending within an exhaust duct to direction exhaust flow along selected flow paths. In its preferred embodiment, the exhaust deflection structure is a variable geometry deflection structure having a distal end portion which is movable, relative to adjacent aircraft structure, within an exhaust duct whereby the exhaust deflection structure is positionable as an extension of an upper, aft wall portion of the exhaust duct. In the preferred embodiment, the exhaust nozzle structure includes a guide structure or nozzle segment, connected to the exhaust deflection structure, which is translatably mounted to adjacent aircraft structure for permitting fore and aft movement of the nozzle segment along the aircraft structure.
    Type: Grant
    Filed: August 2, 1982
    Date of Patent: June 26, 1984
    Assignee: LTV Aerospace and Defense Company
    Inventor: John D. Louthan
  • Patent number: 4447024
    Abstract: The disclosure relates to a vehicle that is sustained in flight solely by thrust from a jet engine and directionally controlled by shifting the center of gravity of the vehicle relative to the thrust axis of the engine.
    Type: Grant
    Filed: February 8, 1982
    Date of Patent: May 8, 1984
    Assignee: Williams International
    Inventor: Sam B. Williams
  • Patent number: 4436261
    Abstract: Various forms of V/STOL aircraft are disclosed, each having a tiltable exterior structure that is in the shape of a pair of connected partial circular conoids. In one general form the conoids house the thrust producing engines, whereas in another form they are immediately downstream thereof. Also provided is a sonic boom concentrator in the form of a fin having curved sidewalls and truncated ends.
    Type: Grant
    Filed: December 7, 1981
    Date of Patent: March 13, 1984
    Inventor: Kolio Koleff
  • Patent number: 4433819
    Abstract: An aerodynamic device which can take off and land vertically is disclosed. The device comprises a non-rotating central body surrounded by an outer rotating disc concentric with the central body. A plurality of jets affixed to the disc are selectively vectorable between a vertical, tangential, or radial direction. One or more reaction jets are affixed to the central body and vectored to counteract a torque generated by the rotating disc. The jets affixed to the central body so that as the disc rotates relative to the body the jets are rotated in a counter direction to have a common longitudinal axis with the central body. Pairs of radial vanes disposed along the upper and lower walls of the disc are hinged to their respective walls, and when open impart a lifting action to the disc. The pairs of upper and lower vanes are interconnected by a slot which makes the lifting action of the vanes aerodynamically more effective.
    Type: Grant
    Filed: February 4, 1982
    Date of Patent: February 28, 1984
    Inventor: Alfred C. Carrington
  • Patent number: 4432512
    Abstract: A jet propulsion efflux outlet assembly for effecting control of a flight vehicle in the pitch, yaw and roll senses having a nozzle through which efflux issues, a spoiler plate with an aperture through which the issueing efflux passes, the spoiler plate being movable laterally to effect control in pitch and yaw and being rotatable for control in roll.
    Type: Grant
    Filed: August 27, 1979
    Date of Patent: February 21, 1984
    Assignee: British Aerospace Public Limited Company
    Inventor: Robert W. Young
  • Patent number: 4407469
    Abstract: An attitude control system for spacecraft having thrusters utilizes the exhaust plume of the thrusters for attitude control. At least one of the thrusters is canted so that its reaction line of thrust, when misaligned with one of the spacecraft's primary axes; causes a control torque to develop about said axis which aids the plume torque about said axis resulting from the plume of the one thruster impinging on a surface such as that of a solar panel on the spacecraft.
    Type: Grant
    Filed: March 31, 1981
    Date of Patent: October 4, 1983
    Assignee: RCA Corporation
    Inventor: Stephen M. Fox
  • Patent number: 4402475
    Abstract: The use of thrusters at the bow and stern of an airship for control of the direction, attitude, and orientation of such an airship is described. The thruster utilizes an electric motor or a gas turbine for power. In the electric motor embodiment, the motor utilizes two contra-rotating rotors which each drive a separate and contra-rotating propeller to generate the controlling jet of air. Thrusters are arranged in pairs at the top, bottom, and each side of the bow and stern of the airship. Lifting thrusters directed downwardly and located above the longitudinal extent of the hull are provided to augment the static lift capability of the airship when under heavy load.
    Type: Grant
    Filed: May 20, 1980
    Date of Patent: September 6, 1983
    Assignee: Airships International, Inc.
    Inventor: Vladimir H. Pavlecka
  • Patent number: 4398682
    Abstract: A displacement mechanism for effecting both rotary movement of a movable member (for example a fin) with respect to a fixed member (for example a flight vehicle body) from a first, inoperative position to a second, operative position about a longitudinal axis and axial movement of the movable member along that axis to effect subsequent locking in the second position, comprises a fluid operated vane motor to effect rotation and a fluid operated piston/cylinder arrangement to effect the axial movement. Preferably the vane motor and the piston/cylinder arrangement are closely integrated one with another.
    Type: Grant
    Filed: September 11, 1980
    Date of Patent: August 16, 1983
    Assignee: British Aerospace Public Limited Company
    Inventor: Alan R. Bithrey
  • Patent number: 4392621
    Abstract: A method and apparatus for controlling the direction of the thrust vector of the engine exhaust stream in an upper surface blowing type aircraft includes ducts in the aircraft wings having rotary control valves for controlling the flow of air through the ducts from a source of high pressure to the low pressure upper surface of the wing. Introduction of the airflow at the upper surface rearwardly of the jet engine produces separation of Coanda effect attachment of the engine exhaust stream from the curved upper wing surface. Coanda effect attachment deflects the exhaust stream over the wing and toward the ground and results in a predominantly vertical thrust vector which augments lift of the aircraft. However, separation of the exhaust stream from the upper surface results in a predominantly horizontal thrust vector which augments forward acceleration of the aircraft. The fluidic action of the valves can rapidly change the thrust vector between basically horizontal and highly inclined orientations.
    Type: Grant
    Filed: April 7, 1981
    Date of Patent: July 12, 1983
    Inventor: Hermann Viets
  • Patent number: 4391424
    Abstract: A method and structure for selectively conducting pressurized gas flow over the upper surface of an airfoil, the airflow being selectively directable either rearward through a spanwise outlet to produce thrust and augment lift or, alternatively, directed forward to spoil the aerodynamic flow over the wing to diminish lift and provide a reverse-thrust braking. The structure includes a plenum defined in the airfoil and ducting to receive pressurized air or gas, the plenum being defined in part by a panel longitudinally pivoted at the central portion thereof to, preferably, change the area of a rearward directed opening while concurrently and proportionally changing in the opposite sense the area of a forward oriented opening to selectively direct the pressurized air or gas rearwardly, forwardly, or in combinations of openings while preferably maintaining a substantially constant opening area.
    Type: Grant
    Filed: August 30, 1976
    Date of Patent: July 5, 1983
    Assignee: Ball Brothers
    Inventor: Otto E. Bartoe, Jr.
  • Patent number: 4379532
    Abstract: A winged aircraft attachable to the body of a pilot including multiple jet engines whereby it may be propelled into and sustained in flight, having angularly adjustable side fins, having pilot operable controls for simultaneously controlling directional issuance of jet streams issuing from the engines and angular adjustment of the fins, including a support for the head of the pilot, and including a support for his feet.
    Type: Grant
    Filed: October 22, 1980
    Date of Patent: April 12, 1983
    Inventor: Igor Dmitrowsky
  • Patent number: 4358074
    Abstract: A propulsion system for an aircraft having a fuselage and a wing with two nacelles disposed on opposite sides of the fuselage, each of the nacelles having a turbo fan therein with drive means connected thereto for air flow through the nacelle from a forward air inlet to air exit openings, the air flow within the nacelle divided into twi air streams, one of the air-streams being directed downwardly through a variable area forward chin nozzle provided with a cascade of vanes for directing the outflow in a desired direction with the other air stream exhausted through an aft nozzle of variable area at the aft outlet opening against a slotted flap system mounted aft of the aft nozzle against which the outflow from the aft nozzle is directed so that the two air streams provide pitch, roll and yaw control as well as balanced lift and propulsion utilizing controlled thrust modulation and vectoring for all regimes of flight from vertical takeoff and landing (VTOL) or short takeoff and landing (STOL) or a combination o
    Type: Grant
    Filed: May 24, 1979
    Date of Patent: November 9, 1982
    Assignee: The Boeing Company
    Inventors: Allen H. Schoen, John J. Schneider, David Bevan, Harold Rosenstein, David R. Woodley
  • Patent number: 4312483
    Abstract: An aircraft is provided with a circular wing member which is rotatably mounted to a fuselage member. The circular wing member provides lift for horizontal flight and also provides gyroscopic stabilization of aircraft attitude. The circular wing member is substantially free of aerodynamically active flight control or propulsion members and, in a preferred embodiment, has a concentration of mass at its outer rim. The fuselage is provided with propulsion means for effecting and controlling vertical and horizontal flight. The propulsion means provides horizontal or vertical thrust along vectors which pass through the aircraft center of mass.
    Type: Grant
    Filed: October 13, 1978
    Date of Patent: January 26, 1982
    Inventor: Nicolae Bostan
  • Patent number: 4298177
    Abstract: Aircraft safety apparatus includes front and rear parachutes mounted at the front and rear portions of the aircraft for adding to the buoyancy thereof during emergency landings. Devices are provided for moving the parachutes into their operating positions. A plurality of auxiliary jet propulsion units containing fluid under pressure propel the aircraft to aid in its manueverability should the aircraft malfunction in flight, as well as during emergency landing procedures. At least some of the jet propulsion units are directed transversely to the body of the aircraft to direct fluid under pressure laterally to cause lateral reaction movement of the aircraft for steering purposes while the aircraft is descending under parachute assist.
    Type: Grant
    Filed: November 9, 1979
    Date of Patent: November 3, 1981
    Inventor: John J. Berlongieri
  • Patent number: 4267990
    Abstract: The present aircraft steering method makes use of additional lift gained by ontrolling the separating of vortical flows from the leading edges of the wings for the purpose of controlling the aircraft about its pitch axis, its roll axis, and its yaw axis. The vortical flows are selectively or differentially separated from the leading edge of the wings by raising or lowering leading edge flaps and/or blowing a flowing medium over the wing surfaces substantially in parallel to the leading edge.
    Type: Grant
    Filed: November 9, 1978
    Date of Patent: May 19, 1981
    Assignee: Messerschmitt-Boelkow-Blohm Gesellschaft mit beschraenkter Haftung
    Inventor: Werner Staudacher
  • Patent number: 4236684
    Abstract: Yaw control surfaces are provided for a jet propelled aircraft wherein a thrust augmented rudder is disposed above the jet exhaust stream and a thrust rudder tab extends downward therefrom into the jet exhaust stream with these components being cooperatively deflected to thereby generate yawing moments for directional control of the aircraft.
    Type: Grant
    Filed: April 27, 1979
    Date of Patent: December 2, 1980
    Assignee: The United States of America as represented by the Administrator of the National Aeronautics and Space Administration
    Inventor: Bobby L. Berrier
  • Patent number: 4192461
    Abstract: The invention relates to the propulsion of transport vehicles in air or water, which involves the new use of a nozzle comprising an internal surface, a curved surface merging into the internal surface, a narrowed throat in the internal surface located towards the leading edge of the nozzle, a jacket surrounding the internal surface, an annular internal slot located in the internal surface between the curved surface and the narrowed throat and communicating with the jacket. The fluid under pressure is supplied through the slot the arrangement of the slot being such that the fluid is ejected at an acute angle of under 45.degree. to the direction of the exit flow tangentially to the curved surface.
    Type: Grant
    Filed: October 26, 1977
    Date of Patent: March 11, 1980
    Inventor: Ole J. M. Arborg
  • Patent number: 4171112
    Abstract: An aircraft has three propulsion engines, two of which each include one pivotable exhaust nozzle which are arranged one on each side of the aircraft, and a third engine including two pivotable exhaust nozzles, one of which is arranged on either side of the aircraft. The arrangements being such that upon failure of one of the two engines the efflux from the third engine is only directed through the nozzle situated on the side of the aircraft which the failed nozzle is arranged.
    Type: Grant
    Filed: July 5, 1978
    Date of Patent: October 16, 1979
    Assignee: Rolls-Royce Limited
    Inventor: Harry M. Harvey
  • Patent number: 4163534
    Abstract: A vehicle has two pairs of transversely oriented rudders and duplex nozzles; three motors pivot the rudders and nozzles for yaw, pitch and roll steering whereby each motor drives the requisite rudder(s) and pivots one or two nozzles so that thrust vector and aerodynamic steering is provided always in unison.
    Type: Grant
    Filed: May 12, 1978
    Date of Patent: August 7, 1979
    Assignee: Vereinigte Flugtechnische Werke-Fokker GmbH
    Inventor: Hans-Jochen Seeger
  • Patent number: 4140290
    Abstract: The roll control of V/STOL aircraft is augmented by deriving a controlled, transverse thrust component from the lift producing engine. This is accomplished by redirecting a jet to introduce such a component not compensated by a counteracting jet or jet component of the craft. Jets can be redirected through pivoting of bent pipe sections of gimbal-hung nozzles.
    Type: Grant
    Filed: June 15, 1976
    Date of Patent: February 20, 1979
    Assignee: Vereinigte Flugtechnische Werke-Fokker GmbH
    Inventors: Hans-Justus Meier, Herbert Sadowski
  • Patent number: 4132089
    Abstract: In order to drive a unit mounted on a carrier rotatable about an axis, the drive for the unit is transmitted from a unit actuator to the unit-drive mechanism on the carrier by a shaft-driven member so arranged that its rotation relative to the carrier is unaffected by rotation of the carrier itself. In one alternative this is achieved by transmitting the output of the unit actuator through a flexible shaft which enters the carrier tangentially and is guided in the fixed structure for its adjacent end to project in a direction normal to the axis of rotation of the carrier, and in an alternative arrangement rotation transmitted to the carrier actuator is superimposed, by means of a differential gear drive arrangement, one gear of which is geared to the output shaft of the carrier drive actuator, upon the rotation of the pinion transmitting, to a ring gear coaxially rotatable about the carrier, the movement of the unit drive servomotor output shaft.
    Type: Grant
    Filed: June 8, 1976
    Date of Patent: January 2, 1979
    Assignee: Plessey Handel und Investments AG
    Inventors: Alexander Skinner, Ronald G. T. Cook
  • Patent number: 4116405
    Abstract: An airplane having a fuselage, a high wing projecting from the upper part of the fuselage to either side first at an upward angle and then slightly downwardly whereby said wing presents a gull wing frontal contour, fins to either side and forward of and at the bottom of the fuselage with ducted fans nested to the wing under the high point of the gull wing frontal contour to be unobstructed thereby.
    Type: Grant
    Filed: March 28, 1977
    Date of Patent: September 26, 1978
    Assignee: Grumman Aerospace Corporation
    Inventors: Anthony C. Bacchi, Robert W. Kress
  • Patent number: 4069977
    Abstract: Apparatus for producing a component of thrust at right angles to the main thrust direction of a jet engine. The apparatus comprises a deflecting device which provides a surface, bounded by side walls normal to the surface, that curves outwardly from tangency to the main thrust direction at the tail pipe edge. A series of control ports extending transversely of the curved surface at the point of tangency are connected to ambient air pressure through a normally open remotely controlled air valve. Closure of the air valve causes that portion of the jet stream adjacent to the curved surface to follow the surface because of the Coanda effect, thus producing a thrust component normal to the main jet stream. The device is particularly useful for yaw control of air cushion equipped jet powered aircraft when taxiing and during the low speed portions of takeoff and landing runs.
    Type: Grant
    Filed: May 11, 1976
    Date of Patent: January 24, 1978
    Assignee: The United States of America as represented by the Secretary of the Air Force
    Inventor: John C. Vaughan, III
  • Patent number: 4063685
    Abstract: Aerodynamic surfaces are fixedly mounted in the diverging section of a rot nozzle and a fluid is injected through the fixed jet vane to flow about the vane. Fluid flow is controlled to make it appear that from upstream the jet vane is at an angle of attack. This deflects the main flow and produces side force. A minimum of injection flow enables high side forces to be obtained for missile control.
    Type: Grant
    Filed: July 30, 1976
    Date of Patent: December 20, 1977
    Assignee: The United States of America as represented by the Secretary of the Army
    Inventor: Paul L. Jacobs
  • Patent number: 4050631
    Abstract: A nozzle assembly for use with a jet engine for controlling the direction of the discharged fluid and hence the direction of thrust is disclosed. The nozzle housing and an internally mounted bifurcation structure are arranged to divide the exhaust fluid flowing into a circular entrance orifice into two separate fluid streams that flow out of rectangular discharge orifices on the rear face of the nozzle. Flow deflection doors, stored within a rearwardly opening cavity formed by the bifurcation structure between the two rectangular discharge orifices, are selectively extendable into each fluid stream to modify the direction of the discharged fluid. The two flow ducts formed by the bifurcation structure and nozzle housing are configured to discharge the two fluid streams toward one another such that the fluid streams converge into a single, thrust-producing fluid stream aft of the exit orifices when the flow deflection doors are not deployed.
    Type: Grant
    Filed: March 26, 1976
    Date of Patent: September 27, 1977
    Assignee: The Boeing Company
    Inventor: Bjarne Elroy Syltebo
  • Patent number: 3986687
    Abstract: An aircraft propulsion system is provided which incorporates a flight maneuverable exhaust nozzle. In one embodiment, gas turbine engines are mounted on both sides of an aircraft fuselage, each engine having an exhaust duct partially defining an exhaust stream flow path. The duct transists from a substantially cylindrical diffuser section aft of the engine to a relatively high aspect ratio section proximate the trailing edge of the wing. Exhaust gases are expelled through a thrust vectorable nozzle which is contoured within the wing and which is adapted to increase wing lift through the concept of supercirculation. Maximum aerodynamic advantage is achieved by distributing the exhaust flow over a significant portion of the wing span at the trailing edge. Thrust augmentation is provided through use of a long, flat duct burner disposed within the high aspect ratio section proximate the exhaust nozzle thereby minimizing turning losses and cooling air requirements.
    Type: Grant
    Filed: June 30, 1975
    Date of Patent: October 19, 1976
    Assignee: General Electric Company
    Inventors: Robert G. Beavers, Kermit F. Byrd
  • Patent number: 3957226
    Abstract: A mechanism is provided for controlling the directional heading of a helicopter, particularly during hover and autorotation. In addition the mechanism provides additional thrust which enables the helicopter to increase its maximum velocity. The mechanism includes three nozzles with valves positioned therein, located in the rearward portion of the helicopter fuselage. Two of the nozzles are located on opposite sides of the aircraft fuselage to provide thrust for use in controlling the directional heading of the aircraft. This thrust is also used to counteract the torque generated by the driving of the lifting rotor of the helicopter. The third nozzle is positioned so that the thrust generated by it will increase the forward velocity of the helicopter. A propeller or fan located in the body of the aircraft forces air from intakes through the fuselage to the nozzles. The position of the valves is determined by suitable control linkage.
    Type: Grant
    Filed: January 27, 1975
    Date of Patent: May 18, 1976
    Assignee: The Boeing Company
    Inventors: Myron L. Daggett, Jr., Leon L. Douglas