Vortex generator, aircraft, and control method for an aircraft

Abstract

The embodiment of the present application discloses a vortex generator, an aircraft and a control method of the aircraft, wherein the vortex generator comprises a flow guide, a driver, a detector and a controller. The flow guide is arranged on the fuselage of the aircraft and is used to form a vortex in the airflow flowing on the surface of the fuselage. The driver is used to drive the flow guide to move relative to the fuselage, so as to adjust the height of the flow guide protruding from the surface of the fuselage. The detector is used to obtain a predetermined parameter, and the predetermined parameter represents the thickness of the boundary layer formed by the airflow on the surface of the fuselage. The controller is used to obtain the thickness of the boundary layer according to the predetermined parameter, so as to control the driver to adjust the protruding height of the flow guide to match the thickness of the boundary layer. The embodiment of the present application can improve the effect of the vortex generator.

Description

Technical Field

[0001] This application relates to the technical field of aircraft, and particularly to an eddy current generator, an aircraft, and a method for controlling the aircraft. Background Technology

[0002] Eddy current generators can be applied to lifting surfaces such as aircraft wings and tails that require delayed separation. They are devices that delay aircraft stall angle of attack, increase maximum lift coefficient, and optimize aircraft takeoff and landing performance.

[0003] The vortex generator includes a guide vane protruding from the fuselage surface, which causes vortices to form in the airflow passing over the fuselage surface. The protrusion height of the guide vane is closely related to the thickness of the boundary layer formed by the airflow on the fuselage surface. Currently, the protrusion height of the guide vane is a fixed value.

[0004] The thickness of the boundary layer formed by airflow on the fuselage surface varies under different environments, and the effectiveness of existing vortex generators needs to be improved. Summary of the Invention

[0005] Embodiments of this application provide an eddy current generator, an aircraft, and a control method for the aircraft, thereby improving the performance of the eddy current generator.

[0006] To address the aforementioned technical problems, embodiments of this application disclose the following technical solutions:

[0007] On one hand, a vortex generator is provided, comprising a guide element, a actuator, a detector, and a controller. The guide element is movably mounted on the fuselage of an aircraft, causing vortices to form in the airflow passing over the fuselage surface. The actuator moves the guide element relative to the fuselage to adjust the height of the guide element protruding from the fuselage surface. The detector acquires predetermined parameters characterizing the thickness of the boundary layer formed by the airflow on the fuselage surface. The controller is connected to both the actuator and the detector, and is used to obtain the boundary layer thickness based on the predetermined parameters, thereby controlling the actuator to adjust the protrusion height of the guide element to match the boundary layer thickness.

[0008] In addition to one or more of the features disclosed above, or as an alternative, the detection element is disposed on the guide element. The controller is also used to control the driver to move the detection element so that the height of the detection element protruding from the surface of the fuselage gradually increases, and to obtain predetermined parameters corresponding to different protrusion heights of the detection element. In response to multiple predetermined parameters satisfying a predetermined relationship, the protrusion height of the detection element corresponding to one of the predetermined parameters is used as the thickness of the boundary layer.

[0009] In addition to one or more of the features disclosed above, or alternatively, the predetermined parameter is the static pressure of the airflow. The controller, in response to a ratio of the latter predetermined parameter to the former predetermined parameter being less than a first predetermined value, uses the protrusion height of the sensor corresponding to the latter predetermined parameter as the thickness of the boundary layer.

[0010] In addition to one or more of the features disclosed above, or as an alternative, the first predetermined value is 98%.

[0011] In addition to one or more of the features disclosed above, or as an alternative, the predetermined parameter is the airflow velocity. The controller responds to multiple predetermined parameters gradually increasing to a first fixed value and then ceasing to change, taking the protrusion height of the detection element corresponding to the predetermined parameter closest to the second fixed value as the thickness of the boundary layer, and the ratio of the second fixed value to the first fixed value is the second predetermined value.

[0012] In addition to one or more of the features disclosed above, or as an alternative, the second predetermined value is 99%.

[0013] In addition to one or more of the features disclosed above, or as an alternative, when the eddy current generator is mounted on the fuselage, the detection element is located at the end of the guide that is away from the fuselage.

[0014] In addition to one or more of the features disclosed above, or alternatively, the eddy current generator also includes a transmission element rotatably mounted on the fuselage about its own axis. The transmission element is in a transmission engagement with a guide element, such that when the transmission element rotates about its own axis, it can drive the guide element to move along the axis. A driver is connected to the transmission element and drives its rotation, thereby causing the guide element to move relative to the fuselage.

[0015] In addition to one or more of the features disclosed above, or as an alternative, the transmission component is a screw, which is threadedly connected to the guide component, and the driver is a motor, the output shaft of which is coaxially connected to the screw.

[0016] On the other hand, an aircraft is also provided, which includes a fuselage and a vortex generator, wherein the vortex generator is disposed on the fuselage and the vortex generator is any of the aforementioned vortex generators.

[0017] On the other hand, a control method for an aircraft is also provided. The method includes: acquiring predetermined parameters via a sensor, the predetermined parameters characterizing the thickness of a boundary layer formed by airflow on the fuselage surface of the aircraft; obtaining the boundary layer thickness based on the predetermined parameters; controlling the actuator to move a guide relative to the fuselage based on the boundary layer thickness, such that the actuator drives a guide to move relative to the fuselage, and the height of the guide protruding from the fuselage surface matches the boundary layer thickness. The guide is movably mounted on the fuselage of the aircraft, causing vortices to form in the airflow flowing over the fuselage surface.

[0018] In addition to one or more of the features disclosed above, or as an alternative, the step of obtaining predetermined parameters through the detection element includes: controlling the actuator to move the flow guide, thereby causing the height of the detection element protruding from the fuselage surface to gradually increase. Predetermined parameters are obtained at different protrusion heights of the detection element. The step of obtaining the boundary layer thickness based on the predetermined parameters includes: in response to multiple predetermined parameters satisfying a predetermined relationship, using the protrusion height of the detection element corresponding to one of the predetermined parameters as the thickness of the boundary layer.

[0019] In addition to one or more of the features disclosed above, or as an alternative, in response to multiple predetermined parameters satisfying a predetermined relationship, the step of using the protrusion height of the detector corresponding to one of the predetermined parameters as the thickness of the boundary layer includes: in response to the ratio of a later predetermined parameter to an earlier predetermined parameter being greater than a first predetermined value, using the protrusion height of the detector corresponding to the later predetermined parameter as the thickness of the boundary layer. Wherein, the predetermined parameter is the static pressure of the airflow.

[0020] In addition to one or more of the features disclosed above, or as an alternative, the first predetermined value is 98%.

[0021] In addition to one or more of the features disclosed above, or as an alternative, in response to multiple predetermined parameters satisfying a predetermined relationship, the step of using the protrusion height of the detector corresponding to one of the predetermined parameters as the thickness of the boundary layer includes: in response to the multiple predetermined parameters gradually increasing to a first fixed value and then no longer changing, using the protrusion height of the detector corresponding to the predetermined parameter closest to a second fixed value as the thickness of the boundary layer, wherein the ratio of the second fixed value to the first fixed value is a second predetermined value. Wherein, the predetermined parameter is the airflow velocity.

[0022] In addition to one or more of the features disclosed above, or as an alternative, the second predetermined value is 99%.

[0023] One of the above technical solutions has the following advantages or beneficial effects:

[0024] In the eddy current generator, a sensor acquires predetermined parameters, the controller determines the boundary layer thickness based on these parameters, and then controls the actuator to adjust the protrusion height of the guide component to match the boundary layer thickness. Thus, the protrusion height of the guide component can adaptively adjust according to the boundary layer thickness, thereby improving the effectiveness of the eddy current generator. Attached Figure Description

[0025] The technical solution and other beneficial effects of this application will become apparent from the following detailed description of specific embodiments in conjunction with the accompanying drawings.

[0026] Figure 1This is a structural schematic diagram of an embodiment of the aircraft of this application;

[0027] Figure 2 This is a three-dimensional structural schematic diagram of an embodiment of the eddy current generator of this application;

[0028] Figure 3 This is a cross-sectional schematic diagram of an vortex generator protruding from the fuselage surface in one embodiment of the aircraft of this application;

[0029] Figure 4 This is a cross-sectional schematic diagram of an vortex generator protruding from the fuselage surface in one embodiment of the aircraft of this application;

[0030] Figure 5 This is a three-dimensional structural schematic diagram of an embodiment of the eddy current generator of this application;

[0031] Figure 6 This is a flowchart of an embodiment of the control method for the aircraft of this application;

[0032] Figure 7 This is a flowchart of an embodiment of the control method for the aircraft of this application.

[0033] Figure 8 This is a flowchart of an embodiment of the control method for the aircraft of this application;

[0034] Figure 9 This is a flowchart of an embodiment of the control method for the aircraft of this application.

[0035] Explanation of reference numerals in the attached drawings: 100-Aircraft; 200-Fuselage; 201-Wing; 203-Vertical tail; 205-Horizontal tail; 207-Fuselage surface; 209-Accommodation slot; 211-Shielding component; 213-Elastic component; 300-Vortex generator; 301-Flow guide component; 303-Actuator; 305-Detection component; 307-Controller; 309-Transmission component; 311-Sloping surface; 400-Airflow; 401-Boundary layer; 403-Main flow zone; 405-Boundary point. Detailed Implementation

[0036] To make the objectives, technical solutions, and beneficial effects of this application clearer, the following detailed description, in conjunction with the accompanying drawings and specific embodiments, further illustrates this application. It should be understood that the specific embodiments described in this specification are merely for explaining this application and are not intended to limit it.

[0037] In the description of this application, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," and "counterclockwise," etc., indicating orientation or positional relationships based on the orientation or positional relationships shown in the accompanying drawings, are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this application. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, features defined with "first" and "second" may explicitly or implicitly include one or more of the stated features. In the description of this application, "a plurality of" means two or more, unless otherwise explicitly specified.

[0038] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, the terms "installation," "connection," and "joining" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection, a direct connection, or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0039] In this application, unless otherwise expressly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0040] At high angles of attack, aircraft wings experience significant wing separation on their upper surface. Adding a vortex generator (guide) before this separation introduces energy into the boundary layer of the airflow, delaying wing separation and thus mitigating stall and increasing the maximum lift coefficient. Based on empirical formulas and accumulated data, the vortex generator protruding from the wing typically exhibits the most significant effect when its height is a certain multiple of the boundary layer thickness (e.g., 1.2 times). Since the boundary layer thickness varies under different operating conditions, the protrusion height of the vortex generator needs to be adjusted to accommodate these variations. In the embodiments described below, the boundary layer thickness is obtained, and the protrusion height of the vortex generator is adjusted accordingly to achieve the optimal effect.

[0041] Please see Figure 1 . Figure 1 This is a structural schematic diagram of one embodiment of the aircraft 100 of this application.

[0042] In some embodiments, the aircraft 100 includes a fuselage 200 and a vortex generator 300, the vortex generator 300 being disposed on the fuselage 200. The aircraft 100 can be a passenger aircraft, a firefighting aircraft, or a fighter jet. Specifically, the fuselage 200 includes a main fuselage body 217 and wings 201, a vertical tail 203, and a horizontal tail 205 respectively disposed on the main fuselage body 217. The vortex generator 300 can be disposed on the main fuselage body 217, the wings 201, the vertical tail 203, or the horizontal tail 205.

[0043] Please see Figure 2 and Figure 3 . Figure 2 This is a three-dimensional structural schematic diagram of an embodiment of the eddy current generator 300 of this application. Figure 3 This is a cross-sectional schematic diagram of an embodiment of the aircraft 100 of this application, showing a vortex generator 300 protruding from the fuselage surface 207.

[0044] In some embodiments, the vortex generator 300 includes a guide member 301, a driver 303, a detector 305, and a controller 307. The guide member 301 is movably disposed on the fuselage 200 of the aircraft 100, causing vortices to form in the airflow 400 flowing over the fuselage surface 207. The driver 303 drives the guide member 301 to move relative to the fuselage 200 to adjust the height H1 of the guide member 301 protruding from the fuselage surface 207. The detector 305 acquires predetermined parameters characterizing the thickness T of the boundary layer 401 formed by the airflow 400 on the fuselage surface 207. The controller 307 is controlled and connected to both the driver 303 and the detector 305, and is used to obtain the thickness T of the boundary layer 401 based on the predetermined parameters, thereby controlling the driver 303 to adjust the protrusion height H1 of the guide member 301 to match the thickness T of the boundary layer 401.

[0045] Specifically, in some embodiments, the fuselage 200 has a receiving slot 209 to receive the vortex generator 300. During the cruise phase of the aircraft 100, the actuator 303 drives the guide vane 301 to retract into the fuselage 200. During the takeoff or landing phase of the aircraft 100, the actuator 303 drives the guide vane 301 to protrude from the fuselage surface 207.

[0046] Specifically, the flow guide 301 can move along a predetermined direction F to protrude from the fuselage surface 207, and can move in the opposite direction of the predetermined direction F to retract into the fuselage 200. The specific shape of the flow guide 301 can refer to existing related designs, and this application does not limit it.

[0047] Please refer to the following: Figure 4 . Figure 4 This is a cross-sectional schematic diagram of an embodiment of the aircraft 100 of this application, showing a vortex generator 300 protruding from the fuselage surface 207.

[0048] In some embodiments, to avoid the formation of a depression between the guide member 301 and the inner wall surface of the receiving groove 209, thereby ensuring that the surface of the body 207 is flat, the shielding member 211 is slidably fitted to the body 200 along direction D, and the elastic member 213 applies an elastic force to the shielding member 211 along direction D, so that the shielding member 211 elastically presses against the guide member 301.

[0049] Specifically, the guide member 301 has an inclined surface 311, which is inclined relative to a predetermined direction F. The blocking member 211 elastically abuts against the inclined surface 311, blocking the recess formed between the inner wall of the receiving groove 209 and the inclined surface 311. The elastic member 213 can be a spring. The two ends of the elastic member 213 elastically abut against the body 200 and the blocking member 211 along the direction D, respectively.

[0050] The blocking member 211 and the inclined surface 311 form a transmission engagement structure. When the guide member 301 moves along the predetermined direction F, the blocking member 211, driven by the guide member 301, moves in the opposite direction D and compresses the elastic member 213. When the guide member 301 moves in the opposite direction F, the blocking member 211 moves along the direction D under the elastic force of the elastic member 213. The blocking member 211 always abuts against the inclined surface 311, so that the receiving groove 209 is always closed.

[0051] Specifically, airflow 400 flows along direction D over fuselage surface 207. Airflow 400 includes a main flow region 403 and a boundary layer 401 attached to fuselage surface 207. Boundary layer 401 and main flow region 403 have a boundary 405.

[0052] In some embodiments, the eddy current generator 300 further includes a transmission member 309, which is rotatably mounted on the body 200 about its own axis. The transmission member 309 is in a transmission engagement with the guide member 301, so that when the transmission member 309 rotates about its own axis, it can drive the guide member 301 to move along the axis. A driver 303 is connected to the transmission member 309 and is used to drive the transmission member 309 to rotate, thereby driving the guide member 301 to move relative to the body 200. In some embodiments, the transmission member 309 is a screw, which is threadedly connected to the guide member 301. The driver 303 is a motor, and the output shaft of the motor is coaxially connected to the screw.

[0053] In some other embodiments, the flow guide 301 is slidably fitted onto the body 200 along a predetermined direction F. The driver 303 is a linear motor. The driving end of the linear motor is connected to the flow guide 301 and drives the flow guide 301 to move.

[0054] The specific method by which the driver 303 adjusts the protrusion height H1 of the guide 301 is not limited to the examples above.

[0055] Specifically, in Figure 2 In the diagram, control connections are indicated by dashed lines. These connections can be wired or wireless. Wired connections are, for example, electrical connections via wires. Wireless connections are, for example, Bluetooth communication connections.

[0056] Specifically, Figure 2 In the illustrated embodiment, there are two detection elements 305. The two detection elements 305 may detect the same or different parameters. For example, one detection element 305 may be used to obtain flow rate, while the other may be used to obtain static pressure. The two detection elements 305 can mutually verify each other, improving the detection effect. The number of detection elements 305 may also be one, or three or more.

[0057] like Figure 4 As shown, in some embodiments, the detection element 305 is used to obtain static pressure. The flow guide 301 has a plurality of static pressure measuring holes 215 (two in the figure), which are disposed on the surface of the flow guide 301 facing away from the body 200. The detection element 305 corresponds one-to-one with the static pressure measuring hole 215, and each detection element 305 is embedded in the flow guide 301 and obtains static pressure through the corresponding static pressure measuring hole 215. Figure 4 In the illustrated embodiment, there are two detection elements 305. In other embodiments, the number of detection elements 305 may be one or more. When there are multiple detection elements 305, the controller 307 will only be triggered to execute the corresponding control action when the detection results of multiple detection elements 305 all meet the predetermined specifications. If the boundary layer measurement is performed by measuring static pressure, then the method of measuring static pressure is preferred. Figure 4 The structure shown.

[0058] Multiple airflow guides 301 are typically installed on the fuselage 200.

[0059] In some embodiments, a plurality of vortex generators 300 are provided on the fuselage 200, and a controller 307 in each vortex generator 300 controls the movement of the guide member 301.

[0060] Please see Figure 5 . Figure 5 This is a three-dimensional structural schematic diagram of one embodiment of the vortex generator 300 of this application. In other embodiments, in the vortex generator 300, a controller 307 can control the movement of multiple guide elements 301. In some embodiments, the multiple guide elements 301 controlled by the same controller 307 are all distributed on the fuselage body 217. In some embodiments, the multiple guide elements 301 controlled by the same controller 307 are all distributed on the wing 201. In some embodiments, the multiple guide elements 301 controlled by the same controller 307 are all distributed on the horizontal tail 205. In some embodiments, the multiple guide elements 301 controlled by the same controller 307 are distributed in a dispersed manner on the fuselage body 217, wing 201, vertical tail 203, and horizontal tail 205.

[0061] In some embodiments, the controller 307 adjusts the height of the guide member 301 based on the boundary layer thickness measured at the location of the guide member 301, and accumulates data. Subsequently, the controller 307 uses the accumulated data to optimize and find the best combination of multiple guide member 301 protrusion heights.

[0062] In some embodiments, the correspondence between the thickness T of the boundary layer 401 and the protrusion height H1 of the flow guide 301 is pre-stored in the controller 307. After obtaining the thickness T of the boundary layer 401, the controller 307 looks up the corresponding protrusion height H1 of the flow guide 301 according to the correspondence. This correspondence can be set and adjusted as needed. In some embodiments, the ratio of the protrusion height H1 of the flow guide 301 to the thickness T of the boundary layer 401 is 1.2.

[0063] In one application scenario, during the takeoff or landing phase of the aircraft 100, the detection element 305 acquires predetermined parameters, and the controller 307 obtains the thickness T of the boundary layer 401 through these parameters. Based on the thickness T of the boundary layer 401, the controller 307 controls the actuator 303 to adjust the protrusion height H1 of the guide element 301 to match the thickness T of the boundary layer 401, achieving optimal delay in separation and increased lift. During the cruise phase of the aircraft 100, the controller 307 controls the actuator 303 to retract the guide element 301 into the fuselage 200.

[0064] In this embodiment, the protrusion height H1 of the guide member 301 can be adaptively adjusted according to the thickness T of the boundary layer 401, thereby improving the effect of the eddy current generator 300.

[0065] The difficulty in adjusting the protrusion height H1 of the guide vane 301 to match the thickness T of the boundary layer 401 lies in the following: 1. The thickness T of the boundary layer 401 of the aircraft 100 during flight is difficult to measure accurately, and there are currently few measurement methods available. 2. The matching relationship between the thickness T of the boundary layer 401 and the protrusion height H1 of the guide vane 301 needs to be obtained through empirical formulas or modeling with a large amount of data.

[0066] The following details the scheme for obtaining the thickness T of the boundary layer 401 through predetermined parameters in the embodiments of this application.

[0067] In some embodiments, the detection element 305 is disposed on the flow guide 301. Specifically, in some embodiments, when the eddy current generator 300 is mounted on the fuselage 200, the detection element 305 is located at the end of the flow guide 301 opposite to the fuselage 200.

[0068] The controller 307 is also used to control the driver 303 to move the detection element 305 so that the height H2 of the detection element 305 protruding from the surface 207 of the body gradually increases, and to obtain the predetermined parameters at different protrusion heights H2 of the detection element 305. In response to multiple predetermined parameters satisfying a predetermined relationship, the protrusion height H2 of the detection element 305 corresponding to one of the predetermined parameters is used as the thickness T of the boundary layer 401.

[0069] In this embodiment, the detection element 305 is moved from the boundary layer 401 to the main flow region 403, so that the detection element 305 passes through the dividing point 405, and the position of the dividing point 405 is obtained by changing predetermined parameters. The distance between the dividing point 405 and the fuselage surface 207 is also the thickness T of the boundary layer 401.

[0070] In some embodiments, the thickness T of the boundary layer 401 is measured by measuring the change in static pressure, based on the principle that the static pressure within the boundary layer 401 remains constant. The details are as follows.

[0071] In this embodiment, the predetermined parameter is the static pressure of the airflow 400. Correspondingly, the detection element 305 is a pressure sensor. In response to a ratio of the latter predetermined parameter to the former predetermined parameter being less than a first predetermined value, the controller 307 uses the protrusion height H2 of the detection element 305 corresponding to the latter predetermined parameter as the thickness T of the boundary layer 401. In some embodiments, the first predetermined value is 98%.

[0072] Please see Figure 6 . Figure 6 This is a flowchart of an embodiment of the control method for the aircraft 100 of this application.

[0073] In one embodiment, to obtain the thickness T of the boundary layer 401, the control method of the aircraft 100 includes the following steps.

[0074] Step S501: Control driver 303 drives detection element 305 to protrude from the body surface 207 to a predetermined position.

[0075] Specifically, since the detection element 305 is disposed on the flow guide 301, the driver 303 drives the flow guide 301 to extend out of the body 200, thereby causing the flow guide 301 to drive the detection element 305 to extend out of the body 200. When the detection element 305 is located at the predetermined position, its height H2 protruding from the surface 207 of the body is, for example, 0.2 mm.

[0076] Step S503: Obtain the static pressure value collected by the test piece 305.

[0077] Specifically, in some embodiments, the detection element 305 continuously collects static pressure values, and when the detection element 305 is located at a predetermined position, the controller 307 records the currently collected static pressure value. In other embodiments, when the detection element 305 is located at the predetermined position, the controller controls the detection element 305 to operate, collect static pressure values, and the controller 307 records the currently collected static pressure value.

[0078] Step 505: Control the driver 303 to drive the detection element 305 to continue extending outward a predetermined distance.

[0079] Specifically, the predetermined distance is, for example, 0.5 mm. Outward refers to the direction away from the fuselage surface 207.

[0080] Step 507: Obtain the static pressure value collected by the test piece 305.

[0081] Specifically, the controller 307 records the static pressure value collected by the detection element 305 at the current position.

[0082] Step 509: Determine whether the ratio of the current static pressure value to the previous static pressure value is less than the first predetermined value. If yes, proceed to the next step; otherwise, return to step 505.

[0083] Specifically, in some embodiments, the first predetermined value is 98%. If the ratio of the currently obtained static pressure value to the previously obtained static pressure value is less than the first predetermined value, then the current position of the detection element 305 is at the boundary 405. If the ratio of the currently obtained static pressure value to the previously obtained static pressure value is not less than the first predetermined value, then the current position of the detection element 305 is still at the boundary layer 401, and steps 505 to 509 are repeated.

[0084] Step 511: Record the protrusion height H2 of the test piece 305 corresponding to the currently obtained static pressure value.

[0085] Specifically, the protrusion height H2 of the current detection element 305 can be obtained from the predetermined position and predetermined distance of the detection element 305. The protrusion height H2 of the current detection element 305 is also the thickness T of the boundary layer 401.

[0086] The above control method obtains the thickness T of the boundary layer 401 by gradually increasing the protrusion height H2 of the detection element 305. In other embodiments, the thickness T of the boundary layer 401 is obtained by gradually decreasing the protrusion height H2 of the detection element 305. Details are as follows.

[0087] Please see Figure 7 . Figure 7 This is a flowchart of an embodiment of the control method for the aircraft 100 of this application.

[0088] In one embodiment, to obtain the thickness T of the boundary layer 401, the control method of the aircraft 100 includes the following steps.

[0089] Step S701: Control driver 303 drives detection element 305 to protrude from the body surface 207 to a predetermined position.

[0090] Specifically, when the detection element 305 is in the predetermined position, the protrusion height H2 of the detection element 305 is much greater than the possible thickness T of the boundary layer 401 under the current operating condition. For example, the possible thickness T of the boundary layer 401 under the current operating condition is 3 mm, and the predetermined position is configured such that the protrusion height H2 of the detection element 305 is 5 mm.

[0091] Step S703: Obtain the static pressure value collected by the test piece 305.

[0092] Step 705: Control the driver 303 to drive the detection element 305 to retract inward by a predetermined distance.

[0093] Specifically, the predetermined distance is, for example, 0.5 mm. "Inward" refers to the direction toward the fuselage surface 207.

[0094] Step 707: Obtain the static pressure value collected by the test piece 305.

[0095] Step 709: Determine whether the ratio of the previously obtained static pressure value to the currently obtained static pressure value is less than a first predetermined value. If yes, proceed to the next step; otherwise, return to step 705.

[0096] Specifically, in some embodiments, the first predetermined value is 98%. If the ratio of the previously obtained static pressure value to the currently obtained static pressure value is less than the first predetermined value, then the current position of the detection element 305 is at the boundary 405.

[0097] Step 711: Record the protrusion height H2 of the test piece 305 corresponding to the static pressure value obtained in the previous test.

[0098] Specifically, the protrusion height H2 of the detection element 305 corresponding to the previously obtained static pressure value can be obtained from the predetermined position and predetermined distance of the detection element 305. The protrusion height H2 of the detection element 305 corresponding to the previously obtained static pressure value is also the thickness T of the boundary layer 401.

[0099] In one application scenario, adopt Figure 6 The control method shown obtains the thickness T of the boundary layer 401, and after the operating conditions change, the control actuator 303 drives the detection element 305 to retract into the machine body, and then uses the method again. Figure 6 The control method shown yields the thickness T of the boundary layer 401.

[0100] In another application scenario, the following is adopted: Figure 6 The control method shown obtains the thickness T of the boundary layer 401, and after the operating conditions change, it adopts... Figure 7 The control method shown yields the thickness T of the boundary layer 401.

[0101] In other embodiments, the gas velocity within the boundary layer 401 is measured using a laser Doppler velocimetry method. Based on the definition of the boundary layer 401, the location of the 99% mainstream velocity region 403 is defined as the boundary of the boundary layer 401, and the thickness T of the boundary layer 401 is measured accordingly. Details are as follows.

[0102] In some embodiments, the predetermined parameter is the flow velocity of the airflow 400. Correspondingly, the detection element 305 is a Doppler velocimeter. In response to multiple predetermined parameters gradually increasing to a first fixed value and then ceasing to change, the controller 307 uses the protrusion height H2 of the detection element 305 corresponding to the predetermined parameter closest to the second fixed value as the thickness T of the boundary layer 401. The ratio of the second fixed value to the first fixed value is a second predetermined value. In some embodiments, the second predetermined value is 99%.

[0103] Please see Figure 8 . Figure 8 This is a flowchart of an embodiment of the control method for the aircraft 100 of this application.

[0104] In one embodiment, to obtain the thickness T of the boundary layer 401, the control method of the aircraft 100 includes the following steps.

[0105] Step S601: Control driver 303 drives detection element 305 to protrude from the body surface 207 to a predetermined position.

[0106] Specifically, since the detection element 305 is disposed on the flow guide 301, the driver 303 drives the flow guide 301 to extend out of the body 200, thereby causing the flow guide 301 to drive the detection element 305 to extend out of the body 200. When the detection element 305 is located at a predetermined position, its height protruding from the surface 207 of the body is, for example, 0.2 mm.

[0107] Step S603: Obtain the flow rate of the airflow 400 collected by the detection component 305.

[0108] Specifically, in some embodiments, the detector 305 is constantly collecting flow rate data, and when the detector 305 is at a predetermined position, the controller 307 records the currently collected flow rate. In other embodiments, when the detector 305 is at the predetermined position, the controller 305 is activated to collect flow rate data, and the controller 307 records the currently collected flow rate.

[0109] Step 605: Control the driver 303 to drive the detection element 305 to continue extending outward a predetermined distance.

[0110] Specifically, the predetermined distance is, for example, 0.5 mm. Outward refers to the direction away from the fuselage surface 207.

[0111] Step 607: Obtain the flow rate collected by the test piece 305.

[0112] Specifically, the controller 307 records the flow rate collected by the detector 305 at the current location.

[0113] Step 609: Determine whether the current obtained flow rate is greater than the previous obtained flow rate. If yes, return to step S605; otherwise, proceed to the next step.

[0114] In the airflow 400, the velocity gradually increases along the normal direction of the fuselage surface 207, and then remains unchanged in the mainstream region 403. If the currently obtained velocity is greater than the previously obtained velocity, then the current detection element 305 is still within the boundary layer 401. If the currently obtained velocity is not greater than the previously obtained velocity, then the current detection element 305 is located in the mainstream region 403.

[0115] Step 611: The current flow rate is a first fixed value. Multiply the first fixed value by a second predetermined value to obtain a second fixed value.

[0116] Specifically, in some embodiments, the second predetermined value is 99%. That is, the position where the flow rate reaches 99% of the flow rate in the mainstream region 403 is designated as the boundary 405.

[0117] Step 613: Obtain the protrusion height H2 of the detection element 305 corresponding to the flow rate closest to the second fixed value.

[0118] Specifically, this step obtains the thickness T of the boundary layer 401.

[0119] Similarly, in the control method for obtaining the thickness T of the boundary layer 401 by detecting the flow rate, the thickness T of the boundary layer 401 can also be obtained by gradually reducing the protrusion height H2 of the detection element 305. The details are as follows.

[0120] Please see Figure 9 . Figure 9 This is a flowchart of an embodiment of the control method for the aircraft 100 of this application.

[0121] In one embodiment, to obtain the thickness T of the boundary layer 401, the control method of the aircraft 100 includes the following steps.

[0122] Step S901: Control driver 303 drives detection element 305 to protrude from the body surface 207 to a predetermined position.

[0123] Specifically, when the detection element 305 is in the predetermined position, the protrusion height H2 of the detection element 305 is much greater than the possible thickness T of the boundary layer 401 under the current operating condition. For example, the possible thickness T of the boundary layer 401 under the current operating condition is 3 mm, and the predetermined position is configured such that the protrusion height H2 of the detection element 305 is 5 mm.

[0124] Step S903: Obtain the flow rate of the airflow 400 collected by the detection component 305.

[0125] Step 905: Control the driver 303 to drive the detection element 305 to retract inward by a predetermined distance.

[0126] Specifically, the predetermined distance is, for example, 0.5 mm. "Inward" refers to the direction toward the fuselage surface 207.

[0127] Step 907: Obtain the flow rate collected by the test piece 305.

[0128] Step 909: Determine whether the previously obtained flow rate is greater than the currently obtained flow rate. If not, return to step S905; otherwise, proceed to the next step.

[0129] Step 911: The previously obtained flow rate is a first fixed value. Multiply the first fixed value by a second predetermined value to obtain a second fixed value.

[0130] The second predetermined value is 99%. The point where the flow rate reaches 99% of the flow rate in the main flow region 403 is designated as the dividing point 405.

[0131] Step 913: Obtain the protrusion height H2 of the detection element 305 corresponding to the flow rate closest to the second fixed value.

[0132] Specifically, this step obtains the thickness T of the boundary layer 401.

[0133] In one application scenario, adopt Figure 8 The control method shown obtains the thickness T of the boundary layer 401, and after the operating conditions change, the control actuator 303 drives the detection element 305 to retract into the machine body, and then uses the method again. Figure 8 The control method shown yields the thickness T of the boundary layer 401.

[0134] In another application scenario, the following is adopted: Figure 8 The control method shown obtains the thickness T of the boundary layer 401, and after the operating conditions change, it adopts... Figure 9 The control method shown yields the thickness T of the boundary layer 401.

[0135] This application also provides a control method for an aircraft 100. The control method for the aircraft 100 can be referred to the various embodiments of the aircraft 100 and the vortex generator 300 described above.

[0136] Please see Figure 2 and Figure 3 .

[0137] The control method for the aircraft 100 includes the following steps: acquiring predetermined parameters via a detection element 305, the predetermined parameters characterizing the thickness T of the boundary layer 401 formed by the airflow 400 on the fuselage surface 207 of the aircraft 100. Obtaining the thickness T of the boundary layer 401 based on the predetermined parameters. Controlling the actuator 303 to move relative to the fuselage 200, causing the actuator 303 to move the guide element 301, and ensuring that the height H1 of the guide element 301 protruding from the fuselage surface 207 matches the thickness T of the boundary layer 401. The guide element 301 is movably mounted on the fuselage 200 of the aircraft 100, causing vortices to form in the airflow 400 flowing over the fuselage surface 207.

[0138] In some embodiments, the step of obtaining predetermined parameters through the detection element 305 includes: controlling the actuator 303 to move the flow guide 301, thereby causing the detection element 305 disposed on the flow guide 301 to move, and thus gradually increasing the height H2 of the detection element 305 protruding from the body surface 207. Predetermined parameters are obtained at different protrusion heights H2 of the detection element 305 through the detection element 305. The step of obtaining the thickness T of the boundary layer 401 based on the predetermined parameters includes: in response to multiple predetermined parameters satisfying a predetermined relationship, using the protrusion height H2 of the detection element 305 corresponding to one of the predetermined parameters as the thickness T of the boundary layer 401.

[0139] In some embodiments, in response to multiple predetermined parameters satisfying a predetermined relationship, the step of using the protrusion height H2 of the detection element 305 corresponding to one of the predetermined parameters as the thickness T of the boundary layer 401 includes: in response to the ratio of a later predetermined parameter to a previous predetermined parameter being greater than a first predetermined value, using the protrusion height H2 of the detection element 305 corresponding to the later predetermined parameter as the thickness T of the boundary layer 401. Wherein, the predetermined parameter is the static pressure of the airflow 400.

[0140] In some embodiments, the first predetermined value is 98%.

[0141] In some embodiments, in response to multiple predetermined parameters satisfying a predetermined relationship, the step of using the protrusion height H2 of the detection element 305 corresponding to one of the predetermined parameters as the thickness T of the boundary layer 401 includes: in response to the multiple predetermined parameters gradually increasing to a first fixed value and then no longer changing, using the protrusion height H2 of the detection element 305 corresponding to the predetermined parameter closest to a second fixed value as the thickness T of the boundary layer 401, wherein the ratio of the second fixed value to the first fixed value is a second predetermined value. Wherein, the predetermined parameter is the flow velocity of the airflow 400.

[0142] In some embodiments, the second predetermined value is 99%.

[0143] In summary, the vortex generator, aircraft, and control method for the aircraft provided in this application allow the protrusion height of the guide element to be adaptively adjusted according to the thickness of the boundary layer, thereby improving the effectiveness of the vortex generator.

[0144] The above steps are provided only to help understand the method, structure, and core ideas of this application. Those skilled in the art can make various improvements and modifications to this application without departing from its principles, and these improvements and modifications also fall within the scope of protection of the claims.

Claims

1. An eddy current generator, characterized in that, include: A flow guide is used to be movably mounted on the fuselage of the aircraft and to create vortices in the airflow passing over the surface of the fuselage. A driver for driving the flow guide to move relative to the fuselage to adjust the height of the flow guide protruding from the surface of the fuselage; A detection element is disposed on the air guide; the detection element is used to acquire predetermined parameters, the predetermined parameters being characterized by the thickness of the boundary layer formed by the airflow on the fuselage surface. A controller, which is connected to both the driver and the detection element, is used to obtain the thickness of the boundary layer based on the predetermined parameters, thereby controlling the driver to adjust the protrusion height of the guide element to match the thickness of the boundary layer. The controller is also used to control the driver to move the detection element so that the height of the detection element protruding from the surface of the machine body gradually increases, and to obtain the predetermined parameters corresponding to different protrusion heights of the detection element. In response to multiple predetermined parameters satisfying a predetermined relationship, the protrusion height of the detection element corresponding to one of the predetermined parameters is used as the thickness of the boundary layer.

2. The eddy current generator as described in claim 1, characterized in that, The predetermined parameter is the static pressure of the airflow; The controller responds to the fact that the ratio of the latter predetermined parameter to the former predetermined parameter is less than a first predetermined value, and uses the protrusion height of the detection element corresponding to the latter predetermined parameter as the thickness of the boundary layer.

3. The eddy current generator as described in claim 2, characterized in that, The first predetermined value is 98%.

4. The eddy current generator as described in claim 1, characterized in that, The predetermined parameter is the flow rate of the airflow; The controller responds to the fact that multiple predetermined parameters gradually increase to a first fixed value and then no longer change, and takes the protrusion height of the detection element corresponding to the predetermined parameter that is closest to the second fixed value as the thickness of the boundary layer, and the ratio of the second fixed value to the first fixed value is the second predetermined value.

5. The eddy current generator as described in claim 4, characterized in that, The second predetermined value is 99%.

6. The eddy current generator as described in claim 1, characterized in that, When the eddy current generator is installed on the fuselage, the detection element is located at the end of the guide element away from the fuselage.

7. The eddy current generator as described in claim 1, characterized in that, Also includes: A transmission component is rotatably mounted on the machine body about its own axis. The transmission component is in transmission cooperation with the guide component so that when the transmission component rotates about its own axis, it can drive the guide component to move along the axis. The driver is connected to the transmission component and is used to drive the transmission component to rotate, thereby driving the guide component to move relative to the body through the transmission component.

8. The eddy current generator as described in claim 7, characterized in that, The transmission component is a screw, which is threadedly connected to the guide component. The driver is a motor, and the output shaft of the motor is coaxially connected to the screw.

9. An aircraft, characterized in that, include: body; A vortex generator is disposed on the fuselage, and the vortex generator is any one of the vortex generators described in claims 1 to 8.

10. A control method for an aircraft, characterized in that, The control method is applied to the eddy current generator according to any one of claims 1 to 8, comprising: The actuator is controlled to move the flow guide and the detection element disposed on the flow guide, thereby gradually increasing the height of the detection element protruding from the fuselage surface; the predetermined parameters corresponding to different protrusion heights of the detection element are obtained through the detection element, and the predetermined parameters characterize the thickness of the boundary layer formed by the airflow on the fuselage surface of the aircraft. In response to multiple predetermined parameters satisfying a predetermined relationship, the protrusion height of the detection element corresponding to one of the predetermined parameters is taken as the thickness of the boundary layer; The actuator is controlled to move the airflow guide relative to the fuselage, and the height of the airflow guide protruding from the fuselage surface matches the thickness of the boundary layer. The airflow guide is movably mounted on the fuselage of the aircraft and causes vortices to form in the airflow flowing over the fuselage surface.

11. The control method for the aircraft as described in claim 10, characterized in that, The step of using the protrusion height of the detection element corresponding to one of the predetermined parameters as the thickness of the boundary layer in response to a predetermined relationship among multiple predetermined parameters includes: In response to the fact that the ratio of the latter predetermined parameter to the former predetermined parameter is less than a first predetermined value, the protrusion height of the detection element corresponding to the latter predetermined parameter is taken as the thickness of the boundary layer. Wherein, the predetermined parameter is the static pressure of the airflow.

12. The control method for the aircraft as described in claim 11, characterized in that, The first predetermined value is 98%.

13. The control method for the aircraft as described in claim 10, characterized in that, The step of using the protrusion height of the detection element corresponding to one of the predetermined parameters as the thickness of the boundary layer in response to a predetermined relationship among multiple predetermined parameters includes: In response to the fact that multiple predetermined parameters gradually increase to a first fixed value and then no longer change, the protrusion height of the detection element corresponding to the predetermined parameter that is closest to the second fixed value is taken as the thickness of the boundary layer, and the ratio of the second fixed value to the first fixed value is the second predetermined value. Wherein, the predetermined parameter is the flow rate of the airflow.

14. The control method for the aircraft as described in claim 13, characterized in that, The second predetermined value is 99%.

Images