| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 21 | Active aircraft pylon noise control system | US13214481 | 2011-08-22 | US09022311B2 | 2015-05-05 | Russell H. Thomas; Michael J Czech; Alaa A. Elmiligui |
| An active pylon noise control system for an aircraft includes a pylon structure connecting an engine system with an airframe surface of the aircraft and having at least one aperture to supply a gas or fluid therethrough, an intake portion attached to the pylon structure to intake a gas or fluid, a regulator connected with the intake portion via a plurality of pipes, to regulate a pressure of the gas or fluid, a plenum chamber formed within the pylon structure and connected with the regulator, and configured to receive the gas or fluid as regulated by the regulator, and a plurality of injectors in communication with the plenum chamber to actively inject the gas or fluid through the plurality of apertures of the pylon structure. | ||||||
| 22 | METHOD AND APPARATUS FOR CONTROLLING FLOW ABOUT A TURRET | US12842534 | 2010-07-23 | US20120018004A1 | 2012-01-26 | Alan Z. Ullman |
| Methods and apparatus are provided to control flow separation of an ambient flow along a surface and about a turret, such as by reducing flow separation aft of the turret. By reducing flow separation, the resulting turbulence may be similarly reduced such that the performance of a system, such as a laser system, housed by the turret may be improved. To reduce flow separation, a motive flow may be provided by ejector nozzles that open through the surface and are positioned proximate to and aft of the turret relative to the ambient flow. The motive flow has a greater velocity than the ambient flow to thereby create a region aft of the turret of reduced pressure relative to an ambient pressure. Within this region of reduced pressure aft of the turret, a portion of the ambient flow mixes with the motive flow, thereby reducing or eliminating flow separation. | ||||||
| 23 | Method for creating an aeronautic sound shield having gas distributors arranged on the engines, wings, and nose of an aircraft | US11288052 | 2005-11-14 | US07407131B1 | 2008-08-05 | Stephen Corda; Mark Stephen Smith; David Daniel Myre |
| The present invention blocks and/or attenuates the upstream travel of acoustic disturbances or sound waves from a flight vehicle or components of a flight vehicle traveling at subsonic speed using a local injection of a high molecular weight gas. Additional benefit may also be obtained by lowering the temperature of the gas. Preferably, the invention has a means of distributing the high molecular weight gas from the nose, wing, component, or other structure of the flight vehicle into the upstream or surrounding air flow. Two techniques for distribution are direct gas injection and sublimation of the high molecular weight solid material from the vehicle surface. The high molecular weight and low temperature of the gas significantly decreases the local speed of sound such that a localized region of supersonic flow and possibly shock waves are formed, preventing the upstream travel of sound waves from the flight vehicle. | ||||||
| 24 | Modification of fluid flow about bodies and surfaces through virtual aero-shaping of airfoils with synthetic jet actuators | US10094194 | 2002-03-08 | US06644598B2 | 2003-11-11 | Ari Glezer; Michael Amitay |
| The present invention involves a system for altering the aerodynamic shape and/or fluid flow about a solid body. The preferred embodiment comprises an obstruction disposed on the solid body and extending outwardly from the solid body into the fluid flowing over the solid body and a synthetic jet actuator embedded in the solid body such that said fluid flowing over the solid body encounters the obstruction before the synthetic jet actuator. The synthetic jet actuator includes a jet housing defined by walls, the jet housing having an internal chamber with a volume of fluid and an opening in the jet housing connecting the chamber to an external environment having the fluid, and a volume changing means for periodically changing the volume within the internal chamber so that a series of fluid vortices are generated and projected in the external environment out from the opening of the jet housing. A synthetic jet stream is formed by the fluid vortices entraining the fluid of the external environment and is projected outwardly from the solid body. The fluid flowing over the solid body contacts the synthetic jet stream forming a recirculation region, thereby modifying both the flow field and the pressure distribution and similarly modifying both the lift and drag characteristics of the solid body. | ||||||
| 25 | Movable surface plane | US10187953 | 2002-07-03 | US06622973B2 | 2003-09-23 | Ahmed Z. Al-Garni; Amro M. Al-Qutub |
| Movable surface planes include opposed independently movable endless surfaces over the majority of opposite sides of the planes. By moving one surface in the same direction as the fluid flow about the plane, and the opposite surface in a direction opposite the fluid flow, the flow is accelerated across the surface moving in the same direction to produce a lesser pressure, and retarded across the surface moving in the opposite direction to produce a greater pressure. The net result is a force urging the plane toward the surface moving in the direction of ambient fluid flow. The two surfaces of the present invention may be operated independently of one another, to move in the same or opposite directions and to have the same or different velocities. The movable surfaces are porous and communicate with ductwork within the structure, to provide fluid flow through the surfaces for boundary layer control. | ||||||
| 26 | Boundary layer control of aerodynamic airfoils | US09718397 | 2000-11-24 | US06488238B1 | 2002-12-03 | Lorenzo Battisti |
| Boundary layer control of a structural element in a fluid stream is achieved by the following operations: providing in such structural element at least one region equipped with micro porous structure by an electroforming technique; having a fluid stream flow through the external surface of the said at least one region, inwards or outwards with respect to the environment in which that element is placed. | ||||||
| 27 | Aircraft weapons bay high frequency acoustic suppression apparatus | US09973175 | 2001-10-05 | US06446904B1 | 2002-09-10 | Michael J. Stanek |
| An aircraft weapons bay high frequency acoustic suppression apparatus is disclosed. The apparatus includes an extendable spoiler retractably received within an aircraft weapons bay. An injector unit is received within the spoiler for injecting high frequency pulses of pressurized gas into the airstream. The injector unit includes a resonance tube in outlet fluid communication with an nozzle. The pulsating output of the resonance tube perturbs the flow of pressurized gas in the nozzle, effectively breaking it up into discrete slugs or pulses which then exit the nozzle and enter the airstream. The high frequency perturbation of the airflow across the weapons bay, created by the aircraft weapons bay high frequency acoustic suppression apparatus of the present invention effectively suppresses undesirable acoustic resonance within the open weapons bay. | ||||||
| 28 | Piezoelectric actuators for circulation controlled rotorcraft | US09641699 | 2000-08-18 | US06425553B1 | 2002-07-30 | James E. Smith; John L. Loth; Robert P. M. Craven; Robert Bond |
| A dynamic fluid control surface, e.g., a rotor blade of a helicopter, having a blowing slot extending the entire length of the leading and trailing edges of the dynamic fluid control surface, an internal chamber containing a pressurized fluid, e.g., air, and one or more piezoelectric actuators positioned along the length of the blowing slots and connected to the internal chamber. The piezoelectric actuators are controlled by a computer system to regulate the flow of fluid released through the blowing slot. There may be one or more blowing slots on either just the trailing edge of a dynamic fluid control surface or on both the leading edge and the trailing edge of the dynamic fluid control surface. | ||||||
| 29 | Synthetic jet actuators for mixing applications | US869587 | 1997-06-05 | US6056204A | 2000-05-02 | Ari Glezer; John W. Wiltse |
| The first preferred embodiment of an improved fluid mixing system comprises a synthetic jet actuator aligned perpendicular to a primary fluid flow. When the synthetic jet actuator is driven at a very high frequency, small scale mixing of the primary fluid flow can be effectively controlled. A second preferred embodiment for a mixing system comprises at least one synthetic jet actuator attached to the housing of a primary jet such that the direction of the synthetic jet flow will be parallel to the direction of the primary jet flow. If the two jets are allowed to operate at the same time, the synthetic jet actuator will have the effect of more effectively mixing the primary jet into the ambient fluid. Another embodiment of an improved mixing system comprises a synthetic jet actuator situated in a closed volume. The fluid flow created by the synthetic jet actuator in the closed volume will greatly aid mixing of the fluids in the chamber without injecting any new matter into the chamber. | ||||||
| 30 | Synthetic jet actuators for modifiying the direction of fluid flows | US869716 | 1997-06-05 | US5988522A | 1999-11-23 | Ari Glezer; Barton L. Smith |
| In a first preferred embodiment for an improved synthetic jet actuator, the orifice shape is altered by either a flap or adjusting the housing walls. If the flap is deployed outward from the wall just above the orifice of a synthetic jet actuator, the synthetic jet flow will be vectored upward, toward the flap. Similarly, if the upper wall forming the orifice is moved outward from the jet chamber interior with respect to an opposing wall forming the orifice, the flow will also vector upward. In the second preferred embodiment of an improved synthetic jet actuator, an opening in addition to the orifice, may be formed in one or more walls of the housing. A louver is aligned with the opening in the housing and permits fluid flow in only one direction, either into the chamber or out of the chamber. When the louver permits fluid flow into the chamber, the jet actuator can operate at high speeds since fluid can enter the chamber through a greater surface area. Another preferred embodiment for an improved synthetic jet actuator comprises two concentric tubular sections normal to an outside surface of a solid body). In operation, the innermost section is connected to a vacuum device and constantly pulls fluid down its length from the ambient fluid above the outer surface. Meanwhile, the outer section ejects fluid into the ambient environment by pulses. Such an operation will cause a synthetic fluid jet to form above the constant suction synthetic jet actuator. | ||||||
| 31 | Modifications of fluid flow about bodies and surfaces with synthetic jet actuators | US869374 | 1997-06-05 | US5957413A | 1999-09-28 | Ari Glezer; Barton L. Smith; Mark A. Trautman |
| The present invention involves a system for altering the aerodynamic shape and/or fluid flow field about a solid body. The preferred embodiment comprises a synthetic jet actuator embedded in a solid body, with the jet orifice built into the body surface. The synthetic jet actuator generates a series of fluid vortices emanating from the orifice so as to entrain fluid external to the actuator chamber and form a synthetic jet stream. A recirculating flow region is formed along the solid body surface about the synthetic jet orifice. As a result the apparent aerodynamic shape of the body is altered. Consequently, if the solid body is placed in a fluid flow field, the entire fluid flow field is altered by the operation of the synthetic jet actuator. | ||||||
| 32 | Drag reduction method and surface | US341565 | 1989-04-21 | US5133519A | 1992-07-28 | Robert E. Falco |
| Rearward facing microsteps (11, 12, 20, 21) are provided in a wall surface (10, 10a, 10b, 19, 19a, 19b) to reduce shear friction drag caused by wall surface bounded turbulent shear flows. Microsteps combined with phased tangential flow injection adjacent the microsteps are also described. These reduce the drag caused by eddy currents. The surface is useful in any setting where turbulent flow occurs to create eddy currents such as airplanes, boats, vehicles, conduits and the like. | ||||||
| 33 | Lift-producing machine or device | US385184 | 1989-07-26 | US5031859A | 1991-07-16 | John T. Cunningham |
| A thrust-producing device comprises a body having a surface and a periphery and disposed in a first fluid; a generator for imparting energy to a second fluid; and a distributor connected to the generator, disposed adjacent the surface, for distributing the second fluid in a first stream over and adjacent the surface for blanketing and enclosing at least a portion of the surface with the first stream and causing the first stream to be initially sufficiently unattached to the surface to define a closed volume between the surface and the first stream. The distributor imparts sufficient velocity to the first stream for permitting a substantial portion of the first stream to reach beyond at least a portion of the body periphery and to partially evacuate by entrainment the volume and to create a low pressure within the volume relative to a pressure of the first fluid and to generate a second stream within the volume; whereby at least a substantial portion of the first stream is deflected angularly and around at least a portion of the body by the dynamic interaction of the first stream with the first fluid and the second stream and the low pressure within the closed volume, and whereby the at least a substantial portion of the first stream entrains a portion of the first fluid to produce a combined resultant fluid flow which proceeds angularly and around at least a portion of the body, thereby creating a resultant thrust force acting on the body.A method for producing thrust for a body is also disclosed. | ||||||
| 34 | Low drag surface | US662983 | 1984-09-20 | US4955565A | 1990-09-11 | John F. Coplin |
| A low drag surface comprises at its upstream edge, an intermittent linear vortex producing means which extends transverse to the flow over the surface and produces a succession of rolling vortices extending transverse to said flow. The vortices move across the surface and reduce drag in the manner of roller bearings. In preferred embodiments the vortex producing means is mechanical, in the form of an oscillating part or fluid dynamic, in the form of a nozzle arrangement. | ||||||
| 35 | Rag control for powered lift aircraft | US536739 | 1983-09-28 | US4895323A | 1990-01-23 | Fred W. May |
| A wing (2) has a trailing edge at which jet flow is deflected downwardly to provide lift. A retractable member (4, 4') has a sharp forward edge (6, 6'). When deployed, member (4, 4') extends along at least a portion of the span (preferably substantially the entire span) of the wing (2) at the leading edge of wing (2). Member (4, 4') projects forwardly and upwardly from wing (2). Member (4, 4') causes flow around wing (2) rearwardly of itself to separate from wing (2) to reduce suction and leading edge thrust. Preferably, reattachment of flow is induced at a location spaced rearwardly from member (4, 4'). A jet of high velocity gas is blown along wing (2) in a generally spanwise direction. This induces reattachment to maintain trailing edge thrust so that jet deflection at the trailing edge will efficiently provide lift during a short distance landing. | ||||||
| 36 | Mono-element combined supercritical high lift airfoil | US444555 | 1982-11-26 | US4457480A | 1984-07-03 | Robert J. Englar; Gregory G. Huson |
| A multi-purpose mono-element airfoil is disclosed for aerodynamic vehicles and devices. The multi-purpose mono-element highlift airfoil when utilized in an aerodynamic application provides a combined no-moving-parts high lift and cruise airfoil which in conjunction with a plenum, upon pressure initiation, causes pressurized air to issue from a slot tanget to the airfoil surface and remains attached to the airfoil's shaped trailing edge, providing a controlled resultant force or thrust. Upon application to hydrodynamic vehicles, the multi-purpose mono-elements airfoil is placed in the freestream and provides turning or pitching forces to the vehicle without any deflection of itself or any mechanical components. | ||||||
| 37 | Method and structure for airfoil thrust and lift control | US718739 | 1976-08-30 | US4391424A | 1983-07-05 | Otto E. Bartoe, Jr. |
| 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. Also, an outboard independent portion of each gate may optionally be interconnected to the controls to move in a progressive manner and thus provide a powerful rolling torque, particularly at low airspeeds. | ||||||
| 38 | Mono-element combined supercritical high lift airfoil | US238265 | 1981-02-25 | US4387869A | 1983-06-14 | Robert J. Englar; Gregory G. Huson |
| A multi-purpose mono-element airfoil is disclosed for aerodynamic and hydrodynamic vehicles and devices. The multipurpose mono-element highlift airfoil when utilized in an aerodynamic application provides a combined no-moving-parts high lift and cruise airfoil which in conjunction with a plenum, upon pressure initiation, causes pressurized air to issue from a slot tangent to the airfoil surface and remains attached to the airfoil's shaped trailing edge, providing a controlled resultant force of thrust. Upon application to hydrodynamic vehicles, the multi-purpose mono-element airfoil is placed in the freestream and provides turning or pitching forces to the vehicle without any deflection of itself or any mechanical components. | ||||||
| 39 | Method of and apparatus for controlling flow attachment to the wing and flap surfaces of an upper surface blowing type aircraft | US429658 | 1973-12-28 | US3971534A | 1976-07-27 | Charles A. Grotz |
| A method of controlling flow attachment to the wing and flap surfaces of an upper surface blowing type aircraft by horizontally controlling the divergence of the jet exhaust of the aircraft engines to control the vertical thickness of the exhaust is disclosed. In addition to controlling the thickness of the exhaust, control of the divergent exhaust also provides control over the outward velocity component of the exhaust which further provides control over flow attachment by controlling the flow of ambient air under the jet exhaust. In one form, the apparatus of the invention comprises one or more side panels, located at the end of the engine exhaust nozzle, adjacent to the surface of the wing. When the panels are moved outwardly, openings are formed which allow the exhaust to horizontally diverge. When the panels are moved inwardly, the openings are closed and the exhaust is no longer diverted and thinned. In an alternate form, the apparatus of the invention comprises movable vanes mounted on the wing, slightly rearwardly of the end of the exhaust nozzle. The vanes are movable so as to either divert the exhaust outwardly and thin it, or to be aligned with the exhaust stream to have little or no effect on the exhaust whereby it remains unthinned. | ||||||
| 40 | Boundary layer control means | US3604661D | 1969-09-25 | US3604661A | 1971-09-14 | MAYER ROBERT ALFRED JR |
| A vehicle movable through a fluid supporting medium includes an active system for controlling the layer of said fluid over at least a portion of the vehicle exterior surface. Parallel slots through the surface permit fluid under pressure to issue over the surface to reduce drag and improve lift and/or propulsion.
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