| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 81 | Shovel nose pneumatic vortex control | US7717 | 1998-01-15 | US5927645A | 1999-07-27 | John Paul Latz |
| A system for facilitating the enhanced aerodynamic control of an aircraft having a fuselage including a forebody defining a frontal portion adapted to create a primary vortex under certain flight conditions and a rear portion. The control system comprises a contour discontinuity which is formed between the frontal and rear portions of the forebody. The contour discontinuity is sized and configured to create a secondary vortex under certain flight conditions. In addition to the contour discontinuity, the control system comprises a pressurized fluid injecting device which is disposed within the forebody of the fuselage adjacent the contour discontinuity. The pressurized fluid injecting device is used to selectively manipulate the secondary vortex to control the flight performance characteristics of the aircraft. | ||||||
| 82 | Synthetic jet actuator and applications thereof | US947815 | 1997-10-09 | US5894990A | 1999-04-20 | Ari Glezer; Mark G. Allen; David J. Coe; Barton L. Smith; Mark A. Trautman; John W. Wiltse |
| A synthetic jet actuator, which can be micromachined if desired, generates a synthetic jet stream characterized by a series of successive vortices that can be used for effectively entraining adjacent fluid. The synthetic jet actuator can be used to bend, or vector, a jet stream from another jet actuator. Further, because the synthetic jet actuator exhibits zero net mass flux, the synthetic jet actuator can be used within a bounded volume. In structure, the synthetic jet actuator comprises a housing defining an internal chamber and having an orifice. A flexible metallized diaphragm forms a wall of the housing and can change the volume of the chamber when moved. An electrode is disposed adjacent to and spaced from the diaphragm, and an electrical bias is imposed between the metallized diaphragm and the electrode by a control system to force movement of the diaphragm. As the diaphragm moves, the volume in the internal chamber changes and vortices are ejected from the chamber through the orifice. | ||||||
| 83 | Aerodynamic surface tip vortex attenuation system | US614411 | 1990-11-16 | US5158251A | 1992-10-27 | Robert M. Taylor |
| Apparatus and method for attenuating fluid foil tip vortices, featuring a "Coanda tip" and a "Coanda curtain." The fluid foil tip has a Coanda surface and means for discharging compressed fluid adjacent thereto; a resultant fluid barrier is formed generally chordwise and perpendicular to the fluid foil plane and tangential to the fluid foil tip upon Coanda entrainment and deflection of the discharged compressed fluid. The fluid barrier prevents crossflow from the higher pressure fluid region to the lower pressure fluid region, the fluid regions being separated by the fluid foil when moving relatively through a fluid, the fluid barrier thereby stemming tip vortex generation at its source. | ||||||
| 84 | Stabilized aero-optical free shear layer interface | US781864 | 1985-09-30 | US5069397A | 1991-12-03 | Ralph L. Haslund |
| In an aero-optical interface for an aircraft optical aperture, the separation of the upstream boundary layer from the edge of the aperture creates a region of turbulance which persists downstream over the full area of the aperture. This invention promotes an early develpment of a steady velocity profile at the upstream aperture edge which is approximately the same as a stable, self-similar shear flow velocity profile over the entire aperture. This is accomplished by thickening the boundary layer upstream of the aperture, and blowing a curtain of air across the aperture from its upstream edge at the point of separation of the boundary flow. This produces a shear flow region foot that causes the overall velocity profile to be equal to a stable self-similar free shear layer. | ||||||
| 85 | Jet-propelled aircraft | US501401 | 1990-03-19 | US4969614A | 1990-11-13 | Alfredo Capuani |
| In a jet-propelled aircraft of the type in which the propulsion jets are directed onto a wing so as to achieve an ejector effect, two vertical tail-fin surfaces are provided and extend downwardly beneath the center of gravity of the aircraft to return the aircraft to a correct attitude when it tends to move sideways relative to the direction of flight. | ||||||
| 86 | Arrangement for controlling the air flow over aerodynamic profiles | US768166 | 1985-08-21 | US4641799A | 1987-02-10 | Armin W. Quast; Karl H. Horstmann |
| An arrangement for controlling the air flow past an aerodynamic profile, (such as an aerofoil surface of a wing, tail plane, or fuselage of an aircraft or missile, a propeller, helicopter rotor, or blading of a turbo-engine fan or wind impeller) by providing a number of orifices of small diameter spaced apart in the profile surface in the longitudinal direction of the profile transversely to the direction of air flow over the profile and to the chordwise direction of the profile. Fluid is either discharged or drawn in through the orifices perpendicularly to the air flow in the region of separation of laminar flow. The orifices have a coefficient of flow (i.e., either a discharge or an intake coefficient) C.sub.Q =(V/FV) of up to 10.sup.-4 for a Reynolds Number less than 3.times.10.sup.6, where v=volume flow of the fluid through the discharge orifices, F=profile area and V=velocity of the air stream flowing over the wing or blade. The invention is particularly concerned with controlling the air flow over an aerofoil profile of a wing of a slowly flying aircraft, such as a glider or light aircraft. | ||||||
| 87 | Aircraft with jet propulsion | US434073 | 1982-10-12 | US4478378A | 1984-10-23 | Alfredo Capuani |
| A jet propelled aircraft of the kind in which propulsion jets are directed over the top surface of the wing so as to cause additional lift as a result of the supercirculation induced on the wing and the deflection of the jets downwards, due to the Coanda effect, immediately downstream of the wing is provided with two longitudinal surfaces projecting from said top surface so as to form a single surface ejector system. The wing of the aircraft has a fixed front part which occupies a minor portion of the wing chord, and a movable rear portion which is articulated to the fixed portion about a substantially transverse axis and can be inclined downwards relative to the fixed part. The portion of the wing between the two longitudinal surfaces may be provided on its trailing edge with a movable attitude control surface of the aircraft. The aircraft may also include a sensor to detect variations in the relative air flow direction in a determined flight attitude, and an actuator to control the movable control surface as a function of the output signal of the sensor in such a manner as to maintain unchanged the attitude of the aircraft. | ||||||
| 88 | Directional control of engine exhaust thrust vector in a STOL-type aircraft | US251695 | 1981-04-07 | US4392621A | 1983-07-12 | Hermann Viets |
| 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. | ||||||
| 89 | Wing mounted thrust reverser | US40538573 | 1973-10-11 | US3884433A | 1975-05-20 | ALEXANDER JOHN D |
| A Coanda surface located to direct an augmenting gas flow along the span of extended flaps is pivotally linked to the wing structure to allow two pivot points for rotation of a member which has the Coanda surface. When pivoted the curved back side of the member is placed directly into the stream of augmenting gas to redirect the flow forward.
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| 90 | Air foil structure | US28940672 | 1972-09-15 | US3807663A | 1974-04-30 | BARTOE O |
| A powered air foil structure particularly adapted for use during low speed operation associated with take off and landing of an air craft and an air foil therefor. The air foil comprises an upper surface including first and second portions, the trailing edge of said first portion being vertically spaced above the leading edge of said second portion by an amount equal to approximately 0.03 to 0.20 times the chord of said air foil, the trailing edge of said first portion being disposed rearwardly from the leading edge of said air foil by an amount equal to approximately 0.20 to 0.33 times the chord of said air foil, said spaced apart trailing edge of said first portion and the leading edge of said second portion forming a nozzle for directing gas rearwardly of said air foil and across substantially the entire upper surface of the air foil disposed rearwardly of said nozzle, said nozzle extending in a generally spanwise direction of said air foil, and means for supplying pressurized gas to said nozzle. One shown air foil structure includes said air foil in combination with an augmentor air foil which is disposed rearwardly of the trailing edge of the first portion of said air foil and vertically spaced thereabove for the purpose of entrapping or incorporating ambient air within the gas exiting from said nozzle. The air foil structure may also include said air foil having a flap extending spanwise adjacent the trailing edge thereof and a deflector air foil for directing at least a portion of the ambient air-gas mixture across the upper surface of said flap and downwardly of the trailing edge thereof. The method of this invention involves the steps of directing gas rearwardly of said air foil from a spanwise extending nozzle disposed along a line located rearwardly from the leading edge of said air foil by an amount equal to approximately 0.20 to 0.33 times the chord of said air foil and having an opening the height of which is equal to approximately 0.03 to 0.20 times the chord of said air foil wherein said gas is directed across substantially the entire upper surface of the air foil disposed rearwardly of said spanwise extending nozzle, entrapping ambient air within the gas directed rearwardly of said nozzle and across the upper surface of said air foil downstream of said spanwise extending nozzle and directing at least a portion of said ambient air-gas mixture across the upper surface of said flap and downwardly of the trailing edge thereof. The method of this invention also comprises pressurizing a gas, supplying said pressurized gas to the interior of said air foil, and directing gas rearwardly of said air foil from a spanwise extending nozzle disposed along a line located rearwardly from the leading edge of said air foil by an amount equal to approximately 0.20 to 0.33 times the chord of said air foil and having an opening the height of which is equal to approximately 0.03 to 0.20 times the chord of said air foil wherein said gas is directed across substantially the entire upper surface of the air foil disposed rearwardly of said nozzle.
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| 91 | Turbofan-powered stol aircraft | US3614028D | 1970-01-12 | US3614028A | 1971-10-19 | KLECKNER HAROLD F |
| A short takeoff and landing (STOL) aircraft employing turbofan engines and a wing and flap arrangement to provide propulsive lift, a high lift capability, and a steeper landing approach flight path. Improvements in these characteristics are achieved by a particular positioning of the engine fan and primary exhaust efflux flow relative to the wing and by locating the flaps for operation in consort with the engine-derived gaseous flow and the wing.
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| 92 | Stol aircraft having by-pass turbojet engines | US3478988D | 1967-11-28 | US3478988A | 1969-11-18 | ROED AGE EILEF |
| 1,212,705. Propulsion jet deflection by blown flaps. SAAB A.B. 28 Nov., 1967 [29 Nov., 1966], No. 54071/67. Heading B7G. [Also in Division F2] An aircraft wing 2 comprises a trailing edge flap 9 pivotable about an axis 13 below the wing from a first position A where it forms a smooth continuation of the wing to a second position D where it forms an acute angle with the undersurface of the wing, a slot 21 between the forward edge of the flap and the main body of the wing, a gas turbine engine 5 mounted on the wing forward of the flap and the slot, a lower flap 23 movable (e.g. about axis 23) in dependence on the movement of the flap 9 (e.g. via a link 24 between a first position where it closes the slot to a second position corresponding to position D of the flap 9 where exhaust air flow from the engine 5 is deflected upwardly through the slot, an upper flap 25 movable from a position A where it forms a smooth continuation of the wing contour, and a position D at an acute angle with the upper surface of the wing, and control means 18 to co-ordinate the flap movements. The above arrangement may comprise the inboard halves of the wings, the outboard halves comprising further trailing edge flaps 7, upper flaps 8 and also leading edge flaps 6 which when extended provide further slots 6a and 6b through the wing. These flaps together with the undercarriage 30 may have their movements also controlled by the pilot's control means 18. All flap and undercarriage movement may be provided by hydraulic actuators 16, 26, 31, 32, 33 and 34. The lower end of the forward wall of the passage 21 may be rounded, and the flap 23 may itself be slotted. When the trailing edge flaps 7, 9, lower flaps 23 and leading edge flaps 6 are moved to the positions B, the left of the wing is increased due to increased camber and boundary layer control provided by air passing through the slots 6a, 6b, 12 and 21. | ||||||
| 93 | Jet flap control | US3456904D | 1967-06-20 | US3456904A | 1969-07-22 | DORAND PIERRE RENE LEON BERNAR |
| 1,174,496. Jet flaps on aerofoils. GIRAVIONS DORAND. 15 June, 1967 [20 June, 1966], No. 27652/67. Headings B7G and B7W. [Also in Division F2] A jet flap mounted on the trailing edge of an aerofoil 1 (e.g. an aircraft wing or a helicopter rotor blade) comprises a deflector flap 3 hinged about an axis 2 parallel and adjacent to an edge of a jet outlet, and a secondary flap 5, located in the path of the jet, and pivoting about the axis 2 to vary the cross-sectional area of the outlet, and to divide it into two apertures 6, 7. The secondary flap 5 may have its upper face curved about the axis 2 so that the aperture 6 remains constant, and always smaller than variable aperture 7. The two flaps 3, 5 may be moved together to vary the direction of the jet, and the flap 5 may be moved independently to vary the jet cross-sectional area. The flap 3 may comprise a second rigid part 9 pivoted at 10, and a flexible surface element 8 forming a flexible continuation of the upper surface of flap 3 and pivoted to the rear end of part 9. In a rotor blade the effective area of the nozzle may be increased along the trailing edge of an advancing blade and reduced on retreating blade, thereby providing additional propulsive thrust. The flaps may be moved in unison in the same direction in the manner of a vectored jet nozzle. | ||||||
| 94 | Flap systems for aircraft | US66934067 | 1967-08-17 | US3447763A | 1969-06-03 | ALLCOCK ALASTAIR WILLIAM RODNE |
| 1,083,267. Aircraft trailing edge flaps. POWER JETS (RESEARCH & DEVELOPMENT) Ltd. Dec. 13, 1965 [Dec. 11, 1964], No. 50618/64. Heading B7G. [Also in Division F2] An aircraft wing trailing edge blown flap has a discontinuity in its surface to promote separation, and means are provided for shielding the discontinuity from the flow over the flap. The flap 2 described may have in its nose a notch 5 which is covered by the wing shroud until the flap is lowered to more than, say, 60 degrees; or a passage (6, Fig. 3, not shown), leading from the nose to the lower surface, which is normally closed by the wing shroud; or a step (9, Fig. 4, not shown) below which the nose is cut away to form a passage through which air can flow from the lower to the upper surface when the flap is lowered sufficiently; or a spoiler plate may be pivotally mounted on the flap nose and spring biased to extend away from the flap surface when it is not constrained by the shroud. The discontinuity is intended to produce an increase in drag and reduction in lift after landing or aborted take-off. The aircraft may be a jet flap aircraft. | ||||||
| 95 | Vertical take-off aircraft | US46353365 | 1965-06-14 | US3360218A | 1967-12-26 | MILLER WENDELL S |
| 96 | Airfoil | US42585365 | 1965-01-15 | US3298636A | 1967-01-17 | ERIC ARNHOLDT |
| 97 | Ventilated aircraft elements | US17666862 | 1962-03-01 | US3240445A | 1966-03-15 | ELLZEY FLOYD P |
| 98 | Stall pattern lift regulator for airplanes | US20997262 | 1962-07-16 | US3142457A | 1964-07-28 | QUENZLER HENRY H W |
| 99 | Aircraft | US86169959 | 1959-12-23 | US3090584A | 1963-05-21 | DIETRICH KUCHEMANN; MICHAEL LILLEY GEOFFREY; CYRIL MASKELL ERIC |
| 100 | Airfoil boundary layer control means | US83562759 | 1959-08-24 | US3005496A | 1961-10-24 | NICHOLS JOHN B |
| 898,203. Boundary layer control on helicopter blades. HILLER AIRCRAFT CORPORATION. Aug. 22, 1960 [Aug. 24, 1959], No. 28934/60. Class 4. A helicopter rotor blade, adjustably mounted for pitch change, has boundary layer control means including operating means therefor comprising a first member fixed on the blade, and a second member movable on the blade under the control of restraining means operative in response to conditions of flight independent of the angle of attack of the blade, relative movement between the first and second members operating the boundary layer control means. Fig. 2 shows a rotor blade tip, a hollow spar 3 receiving compressed air through the hollow rotor shaft from a compressor or gas turbine engine, and communicating through valves (not shown) with ducts 9 leading to a trailing edge slot 10. The valves are controlled by a rod 12 secured to an arm 13 on which are a small aerofoil 14 and a mass balance 15. The aerofoil 14 keeps the arm 13 aligned with the relative wind direction W, and when the angle of attack of the retreating blade increases, rotation of the blade relatively to rod 12 opens the valve so that an air jet 10a is discharged from slot 10, to increase the lift of the blade and delay the onset of stall by energising the boundary layer. In an alternative, the rod 13 has two masses, one at each end so that the rod remains parallel to the tip path plane by gyroscopic effect as the rotor rotates. In either embodiment, power consumption is minimized by discharging compressed air only when needed. The compressor may be driven from the gearbox of an engine driving the rotor shaft. | ||||||
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