• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    PLASMA-ASSISTED SYNTHETIC JET ACTUATOR AND METHOD FOR IMPROVING AERODYNAMIC PROPERTIES OF AN AERODYNAMIC STRUCTURE A plasma-assisted synthetic jet device, an aircraft including a plasma-assisted synthetic jet device, and a method of improving aerodynamic properties for provide airflow control in an aerodynamic structure by ionizing one or more gases exiting through an orifice of the synthetic jet device disposed in the aerodynamic structure.
    公开号:BR102014033062B1
    申请号:R102014033062-3
    申请日:2014-12-30
    公开日:2022-01-25
    发明作者:Dejan Nikic
    申请人:The Boeing Company；
    IPC主号:
    专利说明:

    [001] The present description relates to aerodynamic structures and, more specifically, to improved aerodynamic properties of aerodynamic structures using airflow control. FUNDAMENTALS OF THE INVENTION
    [002] The performance of aerodynamic structures basically depends on the lift and drag forces created on the surface of the structures in response to the passage of airflow. Mechanically fixed surfaces can be selectively included in aerodynamic surfaces, such as rotor blades, wings, engine inlets, fan blades, nozzles, etc., in order to change local aerodynamic properties and thereby achieve desired aerodynamic properties for these aerodynamic structures. Additionally, movable control surfaces, such as flaps, leading edge hyperlift devices, elevator decrease devices, ailerons, elevators, and rudders, can be included on or on aerodynamic surfaces in order to dynamically change the geometry. of the aerodynamic surface, thus altering the aerodynamic properties of the structure.
    [003] In addition to the various mechanical devices included in aerodynamic structures, aerodynamic properties of structures can also be altered causing effects on the flow of passing air. These effects can be generated by various actuation devices arranged on or on the surface or aerodynamic device. SUMMARY
    [004] One embodiment provides a synthetic jet actuator that includes an aerodynamic structure with an aerodynamic surface and forming a hole through the aerodynamic surface. The synthetic jet actuator also includes one or more walls forming a chamber within the aerodynamic structure and adjacent to the aerodynamic surface, wherein the chamber is in fluid communication with a neighboring environment through the orifice. The synthetic jet actuator also includes an ionization device disposed in the orifice and configured to ionize chamber gases exiting the orifice.
    [005] Another embodiment provides an aircraft that includes a thrust source and one or more lift surfaces configured to generate a lift force when coupled to the thrust source. The aircraft also includes at least one synthetic jet actuator configured to provide airflow control on an aerodynamic surface of the aircraft, the aerodynamic structure having an aerodynamic surface and forming a hole through the aerodynamic surface. The synthetic jet actuator includes one or more walls forming a chamber within the aerodynamic structure and adjacent to the aerodynamic surface, wherein the chamber is in fluid communication with an surrounding environment through the orifice. The synthetic jet actuator also includes an ionization device disposed in the orifice and configured to ionize chamber gases exiting the orifice.
    [006] Another embodiment provides a method for flying an aircraft which includes using a source of thrust to generate a lift force on one or more lift surfaces of the aircraft, and providing airflow control in an aerodynamic structure of the aircraft by ionization of one or more gases leaving a synthetic jet actuator arranged in the aerodynamic structure.
    [007] The invention may involve a plasma-assisted synthetic jet actuator that may include an aerodynamic structure with an aerodynamic surface and forming a hole through the aerodynamic surface; one or more walls forming a chamber within the aerodynamic structure and adjacent to the aerodynamic surface, wherein the chamber is in fluid communication with a surrounding environment through the orifice; and an ionization device disposed in the orifice and configured to ionize one or more chamber gases exiting the orifice. A pressure differential between the chamber and the surrounding environment can cause one or more gases from the chamber to exit through the orifice. The plasma-assisted synthetic jet actuator may also include a gas propulsion device configured to propel one or more gases from the chamber through the orifice. The gas propulsion device may be a piezoelectrically actuated diaphragm. The ionization device and the gas propulsion device may be the same device. The ionization device may include first and second electrodes disposed on opposite sides of the aerodynamic surface. The plasma-assisted synthetic jet actuator of claim 6 further comprises an insulating layer configured to at least partially cover one of the first and second electrodes. The ionized chamber gases may be steerable using at least one of an actuation device configured to pivot the plasma-assisted synthetic jet actuator and one or more electromagnets adjacent to the plasma-assisted synthetic jet actuator. The plasma-assisted synthetic jet actuator may also include a first power supply providing a first signal to the gas propulsion device, and a second power supply providing a second signal to the ionization device, wherein the first signal is synchronized with the second sign. A pulse of the second signal may be delayed a predetermined amount from a pulse of the first signal, the predetermined amount based on an amount of time for a volume of one or more propelled chamber gases to reach the orifice.
    [008] The invention may involve an aircraft which may include a source of thrust; one or more lift surfaces configured to generate a lift force when coupled to the thrust source; and at least one plasma-assisted synthetic jet actuator configured to provide airflow control on an aerodynamic surface of the aircraft, the aerostructure having an aerodynamic surface and forming a hole through the aerodynamic surface, and the aerodynamically assisted synthetic jet actuator plasma comprising: one or more walls forming a chamber within the aerodynamic structure and adjacent the aerodynamic surface, wherein the chamber is in fluid communication with a surrounding environment through the orifice; and an ionization device disposed in the orifice and configured to ionize one or more chamber gases exiting through the orifice. The plasma-assisted synthetic jet actuator may also include a gas propulsion device configured to propel one or more gases from the chamber through the orifice. The at least one plasma-assisted synthetic jet actuator may be configured to augment at least one or more aircraft control surfaces. The synthetic jet actuator may also include a first power supply providing a first signal to the gas propulsion device, and a second power supply providing a second signal to the ionization device, wherein the first signal is synchronized with the second signal. .
    [009] The invention may involve a method for improving aerodynamic properties of an aerodynamic structure which may include providing airflow control in the aerodynamic structure by ionizing one or more gases exiting through an orifice formed in an aerodynamic surface of the aerodynamic structure. . Airflow control may be provided by a plasma-assisted synthetic jet actuator which may include one or more walls forming a chamber within the aerodynamic structure and adjacent to the aerodynamic surface, wherein the chamber is in fluid communication with a surrounding environment. back through the hole; and an ionization device disposed in the orifice and configured to ionize one or more chamber gases exiting through the orifice. The method may also include propelling one or more gases from the chamber through the orifice using a gas propulsion device.
    [0010] Aerodynamic structure may be included in an aircraft, and where airflow control is used at least to augment one or more of the aircraft's control surfaces. The aerodynamic structure may be an input from an aircraft jet engine. The plasma-assisted synthetic jet actuator may also include a gas propulsion device coupled to a first power source, and an ionization device coupled to a second power source, wherein a first signal provided by the first power source is synchronized with a second signal provided by the second power supply.
    [0011] The features, functions and advantages that have been discussed can be achieved independently in various embodiments or can be combined in other embodiments as well, the additional details of which can be seen with reference to the following description and drawings. BRIEF DESCRIPTION OF THE DRAWINGS
    [0012] In order that the manner in which the aforementioned features of the present description may be understood in detail, a more particular description of the description, summarized herein, may be had by referring to embodiments, some of which are illustrated in the accompanying drawings. It should be noted, however, that the accompanying drawings only illustrate typical embodiments of this description and therefore should not be considered as limiting its scope, as the description may admit other equally effective embodiments.
    [0013] Fig. 1 illustrates a cross-sectional view of an aerodynamic structure in an air stream, in accordance with embodiments described herein.
    [0014] Figs. 2A-2C illustrate synthetic jet devices, in accordance with embodiments described herein.
    [0015] Fig. 3 illustrates a controller for synthetic jet devices, in accordance with embodiments described herein.
    [0016] Fig. 4A illustrates an aircraft configured to include synthetic jet devices, in accordance with embodiments described herein.
    [0017] Figs. 4B and 4C illustrate configurations for synthetic jet devices in an aerodynamic structure, in accordance with embodiments described herein.
    [0018] For ease of understanding, equal reference numbers have been used, where possible, to designate identical elements that are common to the figures. It is contemplated that elements described in one embodiment may be beneficially used in other embodiments without specific citation. The illustrations referred to herein are not to be understood as drawn to scale unless specifically noted otherwise. Also, drawings are often simplified and details or components are omitted for clarity of presentation and explanation. The drawings and discussion serve to explain principles discussed below, where like designations denote like elements. DETAILED DESCRIPTION OF THE INVENTION
    [0019] To provide better airflow control in aerodynamic structures, various actuation devices (described in more detail below) can be included in or on aerodynamic structures. By controlling the propulsion of gases from the chambers of the actuation devices (i.e., controlling the volumetric flow rate, direction, etc.), and additionally selectively ionizing the propelled gases, better control of airflow close to the devices can be achieved. acting. By the ionization of the propelled gases, a larger plasma can be formed near the aerodynamic surfaces, which, in turn, causes a greater force of attraction in the passing air stream. As a result, aerodynamic structures that include these actuation devices can present greater aerodynamic performance, such as lower drag force, greater flow adherence, low noise and reduced turbulent wake. Consequently, aerodynamic structures may be less prone to lift losses and may have lower lift losses, and may be able to operate at greater angles of attack without inducing lift losses. Propelled ionized gases can provide superior performance at supersonic or hypersonic speeds.
    [0020] Fig. 1 illustrates a cross-sectional view of an aerodynamic structure in an air stream, in accordance with embodiments described herein. For example, the aerodynamic structure 100 could represent a device in operation, such as an aircraft wing, an aircraft horizontal or vertical stabilizer, or other surface in flight, or it could represent a device fixed in a wind tunnel and coupled in appropriate instrumentation or in an experimental setting. Of course, the aerodynamic structure 100 need not be limited to aerospace applications, but could represent devices used in countless other contexts, such as high-performance automotive transport or other commercial or personal transport, wind power generation, etc. As shown, aerodynamic structure 100 is disposed in an environment around 115. Environment around 115 includes a fluid that generally surrounds aerodynamic structure 100 such as atmospheric air; of course, the environment may include other gases or liquids. The aerodynamic structure 100 is shown as an airfoil 110, although similar principles can certainly be applied to devices with different sizes, shapes or configurations. As shown, airflow 130 passes over and under airfoil 110 from left to right. Airflow 130 is generally laminar (i.e. smooth), but airflow 130 could also include portions of turbulent flow. As the airflow passes over and under the airfoil, the interaction produces aerodynamic forces in various directions, such as lift force components 112 and drag force 114.
    [0021] The airflow interaction additionally creates a boundary layer 120 of air, in which the air velocity is gradually reduced from a free-flow velocity (i.e., the velocity at points where aerodynamic structure does not affect airflow). of air) to approximately zero velocity at the surface of the aerodynamic structure 110. The size and shape of the boundary layer 120 is related to the aerodynamic properties of the structure, as well as the velocity of the airflow; thus, by changing the size and/or shape of the contour layer, the amount of drag force created by the structure can also be changed.
    [0022] Figs. 2A-2C illustrate synthetic jet devices, in accordance with embodiments described herein. Synthetic jet devices 200, 280, 298 can generally be included in an aerodynamic structure 202 and operated to affect a contour layer 120, thereby providing reduced drag and other improvements in aerodynamic performance. The effect of synthetic jet devices on the contour layer 120 can generally be reflected by a reduction in the height of the contour layer both locally (i.e., close to the synthetic jet device) and along at least a portion of the structure. aerodynamics. Synthetic jet devices are further configured to ionize gases propelled by a chamber, and can thereby have a greater effect (and provide better control) of the flow of air passing 130. Various elements in Figs. 2A-2C share common reference numbers; unless otherwise indicated, the elements may operate or behave in the same or substantially similar manner.
    [0023] The synthetic jet device 200 includes one or more walls 205 forming a chamber 210. The shape and position of the one or more walls can be selected in order to form the chamber 210 with a desired shape and/or volume; for example, the walls may be shaped round (from a top view) to form a cylindrical chamber, or the walls may be formed at right angles to form a rectangular chamber. Of course, the walls 205 can have a non-uniform profile, such as being tapered from top to bottom (or vice versa). The volume of chamber 210 can be selected so as to optimize the performance characteristics of the synthetic jet device; the shape of the chamber 210 may also be selected to optimize performance, and may additionally take into account practical considerations (i.e., limitations associated with placement of the synthetic jet device within the aerodynamic structure 202).
    [0024] The synthetic jet device 200 includes a piezoelectrically actuated diaphragm 215, which is physically coupled to one or more walls 205 and forms an outline of the chamber 210. A power supply 220 is coupled to the piezoelectrically actuated diaphragm 215 and configured to cause the diaphragm to oscillate in an up and down motion (as shown by the adjacent arrows). Of course, the direction and/or frequency of oscillation may vary depending on the orientation of the diaphragm and/or the synthetic jet device 200. The oscillation of the diaphragm causes pressure changes within the chamber 210, which in turn causes air to flow. out of synthetic jet device 200 is alternately sucked in and propelled from chamber 210 through orifice 225 (air movement is represented by arrows 230).
    [0025] By controlling the frequency and magnitude of diaphragm oscillations (and based on current airflow conditions 130), the aerodynamic performance of a particular surface or device can be improved. To provide this control, the power supply 220 can generally be an alternating current (AC) power supply, and can be configured to generate any viable signal to supply the diaphragm, such as a sine wave, square wave, ramp, serrated, etc. The power supply 220 can be further configured to use pulse width modulation (PWM) to supply a signal with a desired duty cycle to the diaphragm. The power supply 220 may be arranged within the aerodynamic structure 202.
    [0026] In alternative embodiments, diaphragm 215 may be actuated using different means; for example, using electrostatic, electromagnetic, hydraulic or pneumatic means. In another embodiment, a piston assembly may be used in place of the diaphragm. The piston assembly can form a seal with the walls 205 and provide the desired pressure changes within the chamber 210 to operate the synthetic jet device.
    [0027] Synthetic jet device 200 is positioned adjacent to an aerodynamic surface 235, and may include one or more top walls 240 coupled to walls 205; one or more top walls 240 may form part of the aerodynamic surface 235 and may be formed from the same material as the rest of the aerodynamic surface 235, or may alternatively be formed from a different material. If the upper wall(s) 240 are not included, the walls 205 can be directly coupled to the aerodynamic surface 235, such that the aerodynamic surface 235 forms an outline of the chamber 210.
    [0028] In an alternative embodiment, the synthetic jet device 200 may be established from an aerodynamic surface 235, thereby providing a selected depth or thickness of the aerodynamic surface material between the synthetic jet device 200 and the surrounding environment 115 .
    [0029] In order to affect the airflow 130 moving in the environment around 115, the synthetic jet device 200 is in fluid communication with the environment around 115 through an orifice 225 which is formed through the aerodynamic surface 235. Additionally, or alternatively. the orifice may be formed through one or more top walls 240 of the synthetic jet device 200. The orifice 225 can be of any desired shape and size, and can be selected so as to optimize the performance characteristics of the synthetic jet device. In one embodiment, the orifice is circular (seen in a top view), and may have a fixed diameter between about ten (10) microns and about one hundred (100) microns. In other embodiments, the size of the orifice may be mechanically adjustable to control the velocity of fluid flowing through it. For example, the orifice could include a motorized valve coupled to a power supply, an adjustable plug, and/or a movable cover assembly disposed adjacent the orifice.
    [0030] The synthetic jet device 200 additionally includes an ionization device 250 disposed in the orifice 225. The ionization device 250 may comprise any type of device capable of ionizing air or other gases, which includes devices configured to produce electric or magnetic fields. suitable for ionization. As shown, the ionization device 250 includes a surface electrode 255 and an inner electrode 260, and each electrode 255, 260 is coupled to a power supply 265. The electrodes may be of any viable shape and size, and may be constructed from any viable conductive material. In one embodiment, the electrodes may be constructed of a copper foil. In other embodiments, electrode materials may be selected for conductive, structural and/or other properties; Exemplary materials may include graphite, carbon, titanium, brass, silver, platinum, and so on. To allow the electrodes 255, 260 to generate the desired electric or magnetic fields and to avoid electrical shorts, the aerodynamic surface 235 and/or upper wall(s) 240 may be constructed of a dielectric (or at least significantly less conductive) material. than the material selected for electrodes 255, 260). Consistent with desirable general aerodynamic properties, some embodiments may provide an aerodynamic surface 235 and/or upper wall(s) 240 that are constructed of carbon fiber, carbon fiber reinforced polymer, or other composite materials with a strength ratio. for proper weight. Of course, the streamlined surface 235 and top wall(s) 240 can be constructed of different materials.
    [0031] In several embodiments, each electrode may be attached adjacent to the aerodynamic surface or on the upper wall(s), and may have an opening that corresponds to the size and position of the hole 225. In one embodiment, each electrode may be ring-shaped, with a circular opening. Surface electrode 255 may be protected from ambient conditions around 115 by including an insulating layer 268 configured to at least partially cover the surface electrode. The material of insulating layer 268 can be selected based on its thickness or other aerodynamic properties; as the insulating layer 268 extends into the environment around 115 out of the aerodynamic surface 235, too great a thickness can cause an undesirable change in the aerodynamic properties of the aerodynamic surface 235 (e.g. a large thickness tends to create additional drag force ). Examples of insulating layer 268 may include an insulating tape or layer(s) of a film coating or paint. The material of the insulating layer can basically be selected on the basis of its dielectric properties (i.e. its ability to withstand operating stresses at a desired thickness or size), and can also be selected for its thermal, chemical or mechanical resistance properties. In one embodiment, the insulating layer can be a Kapton® tape or film (a registered trademark of E.l. du Pont of Nemours and Company); other insulating layer materials may include polyimides, polyamides, polyamide-imides, polyetheretherketones, or other polymers with suitable properties.
    [0032] In alternative embodiments, the surface electrode may be fully or partially embedded beneath the aerodynamic surface, thereby reducing (or eliminating) the effects caused by its profile on the aerodynamic surface. For example, top wall(s) 240 may include a recess of a suitable size and shape to receive the surface electrode adjacent to the aerodynamic surface 235. To protect the surface electrode from ambient conditions, the surface electrode could be completely enclosed in the material of the top wall(s) 240 or aerodynamic surface 235, or the size (e.g. depth) of the recess could be selected to additionally include an insulating layer 268 beneath the aerodynamic surface, as protecting the surface electrode while minimizing any profile on the aerodynamic surface.
    [0033] As shown, the insulating layer 268 extends only to the side edges of the hole 225. In other embodiments, however, the size of the opening in the electrodes 255, 260 can vary with respect to the size of the hole 225; for example, the surface electrode 255 may have an opening that is larger than the hole 225. In such an embodiment, the insulating layer 268 may be formed all over the surface electrode 255, thus completely shielding the surface electrode 255 from the surface electrode 255. environment around 115 without changing the size of hole 225. The electrode opening can be any feasible size, limited by the ability to generate the electric or magnetic fields necessary to ionize propelled gases. Because the electrodes 255, 260 are generally aligned with each other (i.e., with little or no lateral displacement), greater ionization efficiency can be obtained during operation as a greater fraction of the electric field lines can be used to ionization.
    [0034] Electrodes 255, 260 are coupled to the power supply 265, which have parameters (e.g. frequency and magnitude) selected that are capable of ionizing gases as they are propelled from the synthetic jet device 200 into the surrounding environment 115 The ionized propelled gases can form a plasma 270 adjacent or close to the synthetic jet device 200, which will generally attract airflow 130 to the aerodynamic surface 235. The power supply 265 is generally an AC power supply ( AC) and similar to the above-described power supply 220, and can be configured to generate any viable signal (e.g., sine wave, square wave, PWM, etc.) to provide electrodes 255, 260 to ionize the propelled gases.
    [0035] In some embodiments, the signals provided to both the piezoelectrically actuated diaphragm 215 and the electrodes 255, 260 may be a common signal. One embodiment can provide a common signal using either a single power supply (such as the 220 power supply and the 265 power supply). Another embodiment may provide power supplies 220 and 265 as separate entities, but synchronize their respective outputs so that essentially the same signal is provided.
    [0036] In other embodiments, the signals provided to the piezoelectrically actuated diaphragm 215 and to the electrodes 255, 260 may differ, but may be selected to provide better performance of the synthetic jet device 200. For example, the signal provided to the piezoelectricity 215 may be selected to propel gases from the chamber at a particular volumetric flow rate and/or cyclic frequency through orifice 225. The signal provided to electrodes 255, 260 may ideally be synchronized to the signal provided to piezoelectrically actuated diaphragm 215; for example, the signal provided to the electrodes may be delayed (i.e., phase shifted) by a predetermined amount, such that pulses provided at electrodes 255, 260 are coordinated to ionize a greater amount of air which is propelled through orifice 225. In other words, a volume of air is propelled by a piezoelectrically actuated diaphragm 215 in response to the signal pulse provided by the power supply 220. Instead of pulsing the power supply 265 at the same time as the power supply 220, pulses from power supply 265 may be selectively delayed to reflect the amount of time required for the propelled volume to physically reach orifice 225. And, by applying ionizing pulses to electrodes 255, 260 as relatively greater amounts of air arrive at orifice 225 , greater ionization efficiency can be achieved (i.e., more ionization occurs for the amount of power delivered to the synthetic jet device 200).
    [0037] Additionally, in some embodiments, the power supply 265 may be configured to provide ionizing pulses to the electrodes 255, 260 only during a selected portion of the signal cycle that is provided to the piezoelectrically actuated diaphragm 215. For example, the supply The power supply unit 265 may change its signal output so as not to ionize gases during periods in which the piezoelectrically actuated diaphragm 215 oscillates in one direction and draws air from the surrounding environment 115 into the chamber 210. During this period, the power supply 265 may not provide an output signal (i.e., zero volts) to electrodes 255, 260, or may instead provide a modified output signal, perhaps with a lower amplitude and/or frequency that is calculated to not ionize any of the gases. being drawn into chamber 210. This may prevent unnecessary damage or wear to the synthetic jet device caused by the formation of a plasma within the chamber itself, and may further improve the ionization efficiency of the synthetic jet device.
    [0038] As described herein, embodiments may provide power supplies 220 and 265 as separate power supplies, or as a single power supply. The power supply or supplies may be coupled to a synchronization module configured to selectively shift or otherwise tune the signals that are provided to piezoelectrically actuated diaphragm 215 and electrodes 255, 260. Functions provided by the synchronization module may be achieved through any viable device, such as using hardware components (an application-specific integrated circuit, or analog circuitry) and/or software.
    [0039] Referring now to a modality represented in Fig. 2B. a synthetic jet device 280 is provided which includes several components common with other embodiments described above. Synthetic jet device 280 also includes a bottom wall 285 that can be attached to walls 205 in closure chamber 210; in one embodiment, the bottom wall 285, walls 205 and top wall(s) 240 may be formed as a single unit. A gas source 290 may be in fluid communication with chamber 210 to provide one or more gases to be propelled and/or ionized. A flow controller 295 may be arranged between the gas source 290 and the chamber 210 to control the flow of gas delivered to the chamber. The gas source may include one or more gases selected for their ionizing capacity, such as argon, helium, etc.
    [0040] As gases provided in chamber 210 approach the ionization device 250, for example along a path shown by arrow 297, the ionization device 250 may ionize the gases in a manner similar to that described above. Gases may be propelled through chamber 210 towards orifice 225, and finally through orifice, as atoms of the gases are attracted using the electric or magnetic fields generated by power supply 265 and electrodes 255, 260. In another mode, shown in Fig. 2C, a synthetic jet device 298 can use the ionization device 250 to propel atmospheric air atoms without a separate gas source.
    [0041] Of course, in all embodiments, a pressure differential can exist between the chamber 210 and the surrounding environment 115. For example, the air flow velocity 130 can cause a lower air pressure in the surrounding environment relative to pressure inside the chamber. This pressure differential may be beneficially used to supplement the propulsion provided by the various gas propulsion devices described herein, or, in other embodiments, the pressure differential may be used as the sole source of propulsion.
    [0042] Modalities can achieve additional airflow control allowing synthetic jet devices 200, 280, 298 to be steerable. For example, the upper wall(s) 240 may be comprised of a flexible material, such as rubber, and the walls 205 or the lower wall 285 may be physically connected at one or more further actuation devices configured to pivot the synthetic jet device while physical couplings between aerodynamic surface 235, walls 205 and top wall are maintained. Additionally, or alternatively, the walls (i.e. the top walls, walls and/or bottom wall) of the synthetic jet devices may be suitably shaped and/or arranged within the aerodynamic structure to allow for targeting movement by the actuation devices. Actuation devices may include one or more electromechanical or pneumatic devices physically coupled to the synthetic jetting device at discrete points or areas, or coupled to a pivoting surface adjacent to the synthetic jetting device (e.g. a generally flat surface coupled by below the bottom wall 285). Of course, different synthetic jet devices can be directed together or independently.
    [0043] Additionally, or alternatively, a steering function can be performed using one or more electromagnets adjacent or in proximity to the synthetic jet devices and, for example, arranged within the aerodynamic structure and coupled to a power supply. Where appropriate, power signals are applied to electromagnets, the generated magnetic fields can influence (i.e., can both attract and repel) the ionized particles exiting the orifice of synthetic jet devices, and thereby selectively drive the direction of the output. .
    [0044] Regardless of the configuration selected to achieve the steering functions, the opening of the top wall(s) 240 of the steerable synthetic jet device may remain at least partially aligned with the orifice to allow propelled gases are ionized and leave the chamber.
    [0045] By controlling the propulsion of gases from chamber 210 (controlling volumetric flow, direction, etc.), synthetic jet devices 200, 280, 298 can provide better control of airflow beyond the aerodynamic surface 235 , thus providing better aerodynamic properties.
    [0046] In general, the size of a formed plasma 190 will be proportional to its ability to attract airflow 130; that is, by forming a larger plasma, a greater effect on airflow control can be realized. Providing propelled gases may tend to support the formation of a larger plasma, which may additionally attract airflow 130. As a result, synthetic jet devices 200, 280, 298 may achieve greater penetration into the boundary layer (in other words, reduce the boundary layer on which drag forces occur), which results in less drag. Additionally, the attraction of airflow 130 to the aerodynamic surface 235 may provide greater adherence of flow to the aerodynamic surface; this in general makes the aerodynamic structure less prone to lift speed losses and can decrease lift speed for the structure. Similarly, the greater adherence of flow in the aerodynamic structure can allow greater angles of attack without loss of lift, which can be beneficial for military aircraft or other high-performance applications. Synthetic jet devices 200, 280, 298 may be particularly well suited for use in the subsonic, supersonic and hypersonic speed range, whereas devices that do not use propelled ionized gases may generally be suitable for use only at subsonic speeds.
    [0047] Fig. 3 illustrates a controller for synthetic jet devices, in accordance with embodiments described herein. Controller 300 may be employed as a part of a general aircraft flight control arrangement. Controller 300 can be employed using computing hardware separate from a main controller, or the functionality described here can be incorporated as part of a main controller. Controller 300 can be used, for example, with the above-described synthetic jet devices 200, 280, 298. The controller 300 generally includes one or more computer processors 310, a memory 330, and an input/output (I/O) interface 350.
    [0048] The controller 300 can be coupled via the I/O interface 350 to one or more sensors 360, which can generally provide data to the controller, and can be used to complete a control feedback circuit. 360 sensors can be configured to measure one or more parameters of the surrounding environment, aerodynamic structure or synthetic jet device, such as various temperatures, flow, air velocity, humidity, pressure, electric or magnetic fields, voltage, current and so on. The controller 300 may also be configured to receive user input 370 over the I/O interface 350, for example, using an application programming interface (API). Data received from sensors 360 may be stored in memory 330 as sensor data 335, and user inputs 370 may be stored as set points or performance metrics 340 which generally reflect a desired operation of the aerodynamic structure.
    [0049] Based on 335 sensor data and 340 performance metrics/setpoints, the controller 300 can be configured to calculate or otherwise determine an optimal employment of synthetic jet devices. An optimization function such as this may include determining which of the synthetic jet devices to operate, at what levels to operate (i.e., magnitude of signal power, frequency and/or gas delivered to the synthetic jet devices), direction(s) to drive the output of synthetic jet devices, and so on. The optimization function may occur substantially continuously, or may be performed at intervals by the processor 310.
    [0050] Controller 300 is further configured to provide control signals 380 to the various components of synthetic jet devices. Control signals 380 may be responsive to the determined optimal employment of synthetic jet devices, or may reflect user-fed setpoints or performance metrics 340. For example, signals from power supply 382 may be used to optimally control the output. provided by power sources 220, 265. In some embodiments, control signals may be transmitted to the gas sources (gas source signal 384) or flow controller 295; these signals could indicate, among other things, the selection, amounts and distribution of gases to be provided in chamber 210 for propulsion and ionization. Controller 300 may also be configured to provide direction control signals 388 to one or more actuators (or electromagnets) configured to change the direction of gases propelled by synthetic jet devices, generally as described herein.
    [0051] Fig. 4A illustrates an aircraft configured to include synthetic jet devices, in accordance with embodiments described herein. Overall, synthetic jet devices 200, 280, 298 can be included in aircraft 400 anywhere smoother or better controlled airflow is desired. For example, synthetic jet devices 200, 280, 298 may be provided along the leading edge and/or trailing edge (or essentially any other desired position) of aircraft bearing surfaces such as the wings 410, and may be used to augment or completely replace traditional control surfaces such as llapes, leading edge hypersustainers, ailerons, elevator decrements, small wings, etc. Embodiments may include synthetic jet devices arranged in approximately corresponding positions on opposite sides of each wing 410.
    [0052] Synthetic jet devices 200, 280, 298 may be provided along the leading edge and/or trailing edge (or essentially any other desired position) of the horizontal stabilizer 420 or vertical stabilizer 430, and may be used to augment or completely replace traditional control surfaces such as rudders, elevators, etc. Embodiments may include synthetic jet devices arranged in approximately corresponding positions on opposite sides of the fin 420, or on the fin 430.
    [0053] Synthetic jet devices 200, 280, 298 may also be included in an air intake of jet engines 440, which are the source of thrust for aircraft 400. Smoothing the airflow provided in jet engines can result in more stable and/or more efficient operation of jet engines and, as described herein, may allow extended operation of jet engines (eg, beyond rated limits, at least temporarily).
    [0054] Synthetic jet devices 200, 280, 298 may also be included anywhere along the fuselage 450. The synthetic jet devices may advantageously be placed adjacent or close to protruding auxiliary aircraft components, such as antennas. and which generally decrease the aerodynamic properties of the aircraft (i.e. create additional drag). For example, one or more synthetic jet devices could be arranged in front or behind (with respect to the direction of airflow) the landing gear 460 to provide smoother airflow after the landing gear when deployed, and thus better general aerodynamic properties for the aircraft. Synthetic jets could also be selectively turned off or not used when the landing gear is retracted, that is, when compensation for landing gear effects is unnecessary.
    [0055] Although the 400 aircraft is represented as a commercial aircraft, the principles and methods can be similarly applied to personal aircraft, sport aircraft, military aircraft, etc. The synthetic jet devices described here can be embedded in fixed or moving surfaces (eg, the rotor blades of a helicopter), still providing similar advantages. Still further, the principles and methods described herein can also be applied in other aerodynamic fields, such as high-performance automotive or other commercial or personal transportation field, wind power generation, etc.
    [0056] Figs. 4B and 4C illustrate configurations for synthetic jet devices in an aerodynamic structure, in accordance with embodiments described herein. The 470 assembly includes an aerodynamic surface 230 and four (4) synthetic jet devices 475 arranged in a single row. Synthetic jet devices 475 may be the same, or may operate in a substantially similar manner, to the synthetic jet devices 200, 280, 298 described above. For simplicity, the aerodynamic surface 235 adjacent to each of the synthetic jet devices 475 is shown to be the same width as the synthetic jet devices; however, the surface may extend in such a way that the synthetic jet devices are enveloped by the aerodynamic surface. These settings are provided as non-limiting examples only; of course, any number of synthetic jet devices can be used, in any viable arrangement or arrangement, such as a multi-row and column arrangement, a mismatched row and column arrangement, a radial arrangement, and so on. Each of the synthetic jet devices includes an orifice 225 through which gases from the chamber are propelled. In one embodiment, surface electrodes 255 corresponding to each of the synthetic jet devices are included as a single strip electrode that is shared by multiple synthetic jet devices (in this case, a strip electrode corresponding to the entire row) and with openings corresponding to the holes of each synthetic jet device 475. For ease of display, the strip electrode is illustrated in an exploded view; normally, the strip electrode is disposed adjacent the synthetic jet devices and/or the aerodynamic surface 235. The surface electrode 255 is coupled to the power supply 265, which, in turn, is coupled to an internal electrode 260 (not shown) disposed in each of the synthetic jet devices 475.
    [0057] Referring now to the modality illustrated in Fig. 4C, assembly 490 includes aerodynamic surface 235 and two (2) synthetic jet devices 475 arranged in a row. In this embodiment, a separate surface electrode 255 is provided on each synthetic jet device 475. Although depicted here as circular electrodes with a circular opening corresponding to the size of the hole 225, the surface electrodes 255 may alternatively be of any viable shape and size, as previously discussed. Surface electrodes 255 are each coupled to a power supply 265, which in turn is coupled to an inner electrode 260 (not shown) disposed in each of the synthetic jet devices 475. Although power supplies are shown 265, alternative embodiments may provide a single power supply 265 coupled to multiple surface electrodes 255.
    [0058] Descriptions of the various embodiments of the present description have been presented for purposes of illustration, but should not be exhaustive or limited to the embodiments described. Many modifications and variations will be apparent to those skilled in the art without departing from the scope and spirit of the described embodiments. The terminology used here has been chosen to better explain the principles of the modalities, the practical application or technical improvement over technologies found on the market, or to allow those skilled in the art to understand the modalities described herein.
    [0059] As those skilled in the art will appreciate, aspects of the present disclosure may be conceived as a system, method or computer program product. Thus, aspects of the present description may take the form of a fully hardware modality, a fully software modality (including firmware, resident software, microcode, etc.) or a modality combining software and hardware aspects that can all in general be referred to herein as a '■'circuit', 'module' or 'system'. In addition, aspects of the present disclosure may take the form of a computer program product conceived on one or more computer-readable media with computer-readable program code embedded therein.
    [0060] Any combination of one or more computer readable media may be used. Computer readable media may be computer readable signal media or computer readable storage media. A computer readable storage medium may be, for example, but not limited to, an electronic, magnetic, optical, electromagnetic, infrared or semiconductor system, apparatus or device, or any suitable combination of those described. More specific examples (a non-exhaustive list) of computer-readable storage media would include the following: an electrical connection with one or more wires, a portable computer floppy disk, a hard disk, a random access memory (RAM), a memory read-only memory (ROM), an erasable programmable read-only memory (EPROM or flash memory), an optical pound, a portable compact disc read-only memory (CD-ROM), an optical storage device, a storage device magnetic, or any suitable combination of those described. In the context of this document, a computer readable storage medium can be any tangible medium that can contain, or store a program for use by, or related to, a system, apparatus, or instruction execution device.
    [0061] A computer-readable signal medium may include a propagated data signal with computer-readable program code embedded therein, for example, in the baseband or as part of a carrier wave. A propagated signal such as this can take a variety of forms, including, but not limited to, electromagnetic, optical, or any suitable combination of these. A computer-readable signal media may be any computer-readable media that is not computer-readable storage media and that can communicate, propagate, or transport a program for use by an instruction-executing system, apparatus, or device, or related with these.
    [0062] Program code conceived on computer-readable media may be transmitted using any appropriate media, including, but not limited to, wireless, wired, fiber optic cable, RF, etc., or any suitable combination thereof.
    [0063] Computer program code to perform operations for aspects of the present description may be written in any combination of one or more programming languages, including an object-oriented programming language such as Java, Smalltalk, C++ or similar and conventional procedural programming languages, such as "C" programming language or similar programming languages. The program code may run completely on the user's computer, partially on the user's computer, as a standalone software package, partially on the user's computer and partially on a remote computer, or completely on the remote computer or server. In this scenario, the remote computer can be connected to the user's computer through any type of network, including a local area network (LAN) or wide area network (WAN), or the connection can be made to an external computer ( for example, over the Internet using an Internet Service Provider).
    [0064] Aspects of the present description are described herein with reference to flowchart illustrations and/or block diagrams of methods, apparatus (systems) and computer program products in accordance with embodiments of the description. It is understood that each block of the flowchart illustrations and/or block diagram, and combinations of blocks in the flowchart illustrations and/or block diagrams, may be implemented by computer program instructions. Such computer program instructions may be provided to a processor of a general purpose computer, special purpose computer, or other programmable data processing apparatus to produce a machine in such a way that the instructions which it will execute by means of the processor of the computer or other programmable data processing apparatus, create means for implementing the functions/acts specified in the block or blocks of the flowchart and/or block diagram.
    [0065] Such computer program instructions may also be stored on computer-readable media that may direct a computer, other programmable data processing apparatus, or other devices to function in a particular manner, such that the stored instructions on computer readable media produce an article of manufacture including instructions that implement the function/act specified in the block or blocks of the flowchart and/or block diagram.
    [0066] Computer program instructions may also be loaded into a computer, other programmable data processing apparatus, or other devices to cause a series of operational steps to be performed on the computer, other programmable apparatus, or other devices to produce a computer-implemented process such that instructions executing on the computer or other programmable apparatus provide processes for implementing the functions/acts specified in the block or blocks of the flowchart and/or block diagram.
    [0067] The flowchart and block diagrams in the figures illustrate the architecture, functionality and operation of possible implementations of systems, methods and computer program products in accordance with various embodiments of the present description. In this regard, each block in the flowchart or block diagrams may represent a module, segment or portion of instructions, which comprises one or more executable instructions for implementing the specified logic function(s). In some alternative implementations, the functions noted in the block may occur out of the order noted in the figures. For example, two blocks shown in succession can, in fact, run substantially simultaneously, or the blocks can sometimes be run in reverse order, depending on the functionality involved. It is also noted that each block in the illustration of the block diagrams and/or flowchart, and combinations of blocks in the illustration of the block diagrams and/or flowchart, can be implemented by systems based on special-purpose hardware to perform the functions or specified acts or perform special-purpose combinations of hardware and computer instructions.
    [0068] While the disclosure is directed to embodiments of the present description, other embodiments and additional embodiments of the description may be conceived without departing from its basic scope, and its scope is determined by the following claims.
    权利要求:
    Claims (12)
    [0001]
    1. Plasma-assisted synthetic jet actuator (200, 280, 298), characterized in that it comprises: an aerodynamic structure (100, 202) having an aerodynamic surface and forming an orifice (225) through the aerodynamic surface; one or more walls (205) forming a chamber (210) within the aerodynamic structure and adjacent to the aerodynamic surface, wherein the chamber is in fluid communication with a surrounding environment (115) through the orifice (225); and an ionization device (250) disposed in the orifice (225) and configured to ionize one or more chamber gases exiting through the orifice (225).
    [0002]
    2. Plasma-assisted synthetic jet actuator, according to claim 1, characterized in that a pressure differential between the chamber (210) and the surrounding environment (115) causes one or more gases to exit the chamber through hole (225).
    [0003]
    3. Plasma-assisted synthetic jet actuator according to any one of claims 1 to 2, characterized in that it additionally comprises a gas propulsion device configured to propel one or more gases from the chamber through the orifice.
    [0004]
    4. Plasma-assisted synthetic jet actuator, according to claim 3, characterized in that the ionization device and the gas propulsion device are the same device.
    [0005]
    5. Plasma-assisted synthetic jet actuator, according to any one of claims 1 to 4, characterized in that the ionization device comprises first and second electrodes arranged on opposite sides of the aerodynamic surface.
    [0006]
    6. Plasma-assisted synthetic jet actuator according to any one of claims 1 to 5, characterized in that the ionized chamber gases are steerable using at least one of an actuation device configured to pivot the synthetic jet actuator plasma-assisted and one or more electromagnets adjacent to the plasma-assisted synthetic jet actuator.
    [0007]
    7. Plasma-assisted synthetic jet actuator, according to claim 3, characterized in that it additionally comprises a first power supply providing a first signal to the gas propulsion device, and a second power supply providing a second signal to the ionization device, where the first signal is synchronized with the second signal.
    [0008]
    8. Method for improving aerodynamic properties of an aerodynamic structure (100, 202), characterized in that it comprises: providing airflow control in the aerodynamic structure (100, 202) by ionizing one or more gases exiting through a hole (225) formed in an aerodynamic surface of the aerodynamic structure (100, 202). wherein airflow control is provided by a plasma-assisted synthetic jet actuator (200, 280, 298), comprising: one or more walls (205) forming a chamber (210) within the aerodynamic structure (100, 202 ) and adjacent to the aerodynamic surface, wherein the chamber (210) is in fluid communication with a surrounding environment (115) through the orifice (225); and an ionization device (250) disposed in the orifice (225) and configured to ionize one or more chamber gases exiting through the orifice (225).
    [0009]
    Method according to claim 8, characterized in that it further comprises propelling one or more gases from the chamber through the orifice (225) using a gas propulsion device.
    [0010]
    10. Method according to claim 8 or 9, characterized in that the aerodynamic structure (100, 202) is included in an aircraft, and in which the airflow control is used to at least increase one or more aircraft control surfaces.
    [0011]
    11. Method according to any one of claims 8 to 10, characterized in that the aerodynamic structure (100, 202) is an input of an aircraft jet engine.
    [0012]
    Method according to any one of claims 8 to 11, characterized in that the plasma-assisted synthetic jet actuator additionally comprises a gas propulsion device coupled to a first power supply, and an ionization device coupled to a second power supply, wherein a first signal provided by the first power supply is synchronized with a second signal provided by the second power supply.
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    同族专利:
    公开号 | 公开日
    EP2913266A1|2015-09-02|
    BR102014033062A2|2016-05-31|
    CA2870937A1|2015-08-21|
    AU2014262214B2|2018-03-29|
    CA2870937C|2018-03-27|
    EP2913266B1|2016-10-26|
    CN104859843A|2015-08-26|
    US9637224B2|2017-05-02|
    CN104859843B|2019-04-12|
    US20150239552A1|2015-08-27|
    AU2014262214A1|2015-09-10|
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    法律状态:
    2016-05-31| B03A| Publication of a patent application or of a certificate of addition of invention [chapter 3.1 patent gazette]|
    2018-10-30| B06F| Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]|
    2020-04-07| B06U| Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]|
    2021-11-23| B09A| Decision: intention to grant [chapter 9.1 patent gazette]|
    2022-01-25| B16A| Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]|Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 30/12/2014, OBSERVADAS AS CONDICOES LEGAIS. |
    优先权:
    申请号 | 申请日 | 专利标题
    US14/186,760|US9637224B2|2014-02-21|2014-02-21|Plasma-assisted synthetic jets for active air flow control|
    US14/186760|2014-02-21|
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