A vibration winglet device, control method and system

Abstract

The application discloses a vibrating winglet device, a control method and a system, relates to the field of wings, and the vibrating winglet device is characterized in that the vibrating winglet device comprises a main wing, a vibrating winglet and a steering engine, the main wing is suitable for fixing various structural parts of the vibrating winglet device, the vibrating winglet is fixed above the main wing, the vibrating winglet is suitable for freely rotating around a rotating shaft, and the rotating shaft is driven to rotate by the steering engine and is connected with a movable wing tip. Since the vibrating winglet device adopts the idea of guiding the movement of the vibrating winglet based on the results of stability analysis, the vibrating winglet can not only weaken the strength of the wing tip vortex but also accelerate the dissipation of the wing tip vortex, thereby achieving a better drag reduction effect than the conventional winglet. Since the variable wing tip winglet is adopted, the movable wing tip device changes the wing tip vortex structure at the wing tip, causes the flow to change, and thereby changes the corresponding aerodynamic performance and reduces the drag. Not only can the drag be reduced, but the engine noise of the airplane can also be reduced, and the service life of the engine is prolonged.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of wings, in particular to a vibrating winglet device, control method and system. BACKGROUND

[0002] When the aircraft is flying, the pressure difference between the upper and lower surfaces of the wing will produce a wing tip vortex. This large-scale vortex structure will bring problems such as induced drag and wake encounter, affecting the flight safety of the aircraft and the take-off and landing frequency of the airport. In order to weaken this influence, wing tip vortices are usually used to weaken the strength of the wing tip vortices, such as the double forked knife winglet of B737max and the like. With the development of technology, the wing tip vortices have reached a limit in weakening the strength of the wing tip vortices for drag reduction. Therefore, people further begin to study vibrating winglet devices that can further promote the dissipation of the wing tip vortices on the basis of weakening the strength of the wing tip vortices. The vibrating winglet promotes the rapid dissipation of the wing tip vortices by making the wing tip vortices swing with a certain amplitude to promote the growth of the wing tip vortices. The dominant frequency of the wing tip vortices that can make the wing tip vortices dissipate is often in a very narrow bandwidth. Due to the lack of mechanism research, the existing vibrating winglets are often difficult to accurately find the appropriate vibration frequency.

[0003] Therefore, the skilled in the art is committed to developing a vibrating winglet device. SUMMARY

[0004] In view of the above defects of the prior art, the technical problem to be solved by the present application is to make up for the difficulty of the traditional vibrating winglet in finding the accurate vibration frequency.

[0005] To achieve the above-mentioned purpose, the present application provides a vibrating winglet device, control method and system.

[0006] In the first aspect of the present application, a vibrating winglet device is provided, comprising a main wing, a vibrating winglet and a steering engine. The main wing is suitable for fixing the parts of the vibrating winglet device. The vibrating winglet is fixed above the main wing and is suitable for freely rotating around the rotating shaft. The steering engine is connected to drive the rotating shaft with a moving wing tip.

[0007] In the second aspect of the present application, a vibrating winglet control method is provided, comprising: inputting the disturbance amplitude and frequency of the wing tip vortex into a synchronizer, and the synchronizer controls the steering engine to drive the vibrating winglet to vibrate according to the corresponding amplitude and frequency.

[0008] In some embodiments of the first aspect, the main wing part adopts a flat plate wing with a winglet.

[0009] In some embodiments of the first aspect, the main wing is selected as NACA0020, and ABS plastic and aluminum alloy are used to process the main wing, the chord length of the main wing is 25 cm, the aspect ratio of the main wing is 2, and the vibration aileron part is controlled by a steering engine to control the movement of the wing tip.

[0010] In some embodiments of the first aspect, the shaft connected to the wing tip is driven to rotate by a motor, and the movement of the wing tip is driven and controlled by an Adrino control board, and the driving voltage of the selected steering engine is 4.8V / 7.4V, and the corresponding rotation speed is 0.22 / 60 degrees or 0.18 / 60 degrees.

[0011] In some embodiments of the second aspect, the method for obtaining the disturbance of the wing tip vortex comprises: obtaining the disturbance of the wing tip vortex by performing stability analysis on the Batchelor vortex model.

[0012] In some embodiments of the second aspect, the method for obtaining the Batchelor vortex model comprises: uploading the flow field information to a computer, and performing Batchelor vortex fitting on the flow field information by the computer to obtain the Batchelor vortex model.

[0013] In some embodiments of the second aspect, the method for obtaining the flow field information comprises: collecting and recording the flow field information by a NI controller.

[0014] In some embodiments of the second aspect, the stability analysis on the Batchelor vortex model is according to the formula: wherein A is the amplitude of the disturbance, ω is the frequency of the disturbance, qr(y,z) is the shape function of the disturbance, indicating the specific form of the disturbance, and G(x) represents the energy of the disturbance, is the phase of the disturbance.

[0015] In the third aspect of the present application, a vibration aileron control system is provided, comprising a NI controller, a computer and a synchronizer, the NI controller is adapted to collect and record flow field information and upload the flow field information to the computer, the computer is adapted to perform Batchelor vortex fitting on the flow field information to obtain a Batchelor vortex model, and the synchronizer is adapted to control the steering engine to drive the vibration aileron to vibrate according to the corresponding amplitude and frequency according to the disturbance of the wing tip vortex.

[0016] The vibration aileron device provided by the present application has at least the following beneficial effects:

[0017] 1. Since the present application uses the results based on stability analysis to guide the movement of the vibration aileron, the vibration aileron can not only weaken the strength of the wing tip vortex, but also accelerate the dissipation of the wing tip vortex, thereby achieving better drag reduction effect than the traditional aileron.

[0018] 2. Because the present invention utilizes modified wingtip winglets, the movable wingtip device modifies the wingtip vortex structure, causing changes in the flow, thereby changing the corresponding aerodynamic performance and reducing drag. This not only reduces drag but also reduces aircraft engine noise and extends engine life.

[0019] 3. The background of the present invention is based on large-sized fixed-wing aircraft such as wide-body passenger aircraft. In fact, this vibrating winglet can also be used in drones. Existing research has shown that vibrating winglets can effectively increase the payload of drones, increase flight range, improve flight performance, and bring higher flight benefits.

[0020] The concept, specific structure and technical effects of the present invention will be further described below in conjunction with the accompanying drawings to fully understand the purpose, characteristics and effects of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Figure 1 1 is a schematic structural diagram of a vibrating winglet in an embodiment of the present invention;

[0022] Figure 2 1 is a graph showing the optimal vibration frequency of the vibrating winglet obtained based on stability analysis at different wind speeds in an embodiment of the present invention.

[0023] Description of reference numerals:

[0024] 1. Main wing; 2. Vibrating winglet; 3. Servo; 4. NI controller; 5. Computer. DETAILED DESCRIPTION

[0025] The following describes several preferred embodiments of the present invention with reference to the accompanying drawings to make its technical content clearer and easier to understand. The present invention can be embodied in many different forms of embodiments, and the scope of protection of the present invention is not limited to the embodiments mentioned herein.

[0026] In the drawings, components with identical structures are denoted by the same reference numerals, and components with similar structures or functions are denoted by similar reference numerals. The size and thickness of each component shown in the drawings are arbitrary and are not limited by the present invention. For clarity, the thickness of components in some places in the drawings is appropriately exaggerated.

[0027] like Figure 1 As shown, in embodiment 1 of the present invention, a vibrating winglet device for promoting rapid dissipation of wing wake vortex is provided, comprising a main wing 1, a vibrating winglet 2, and a servo 3. The main wing 1 is suitable for fixing various parts of the vibrating winglet device. A vibrating winglet 2 is fixed above the main wing 1. The vibrating winglet 2 is suitable for freely rotating around a rotating shaft and is driven by the servo 3 to rotate a shaft connected to a moving wingtip.

[0028] In some embodiments of embodiment 1, the main wing part adopts a wingletted flat plate wing.

[0029] In some embodiments of embodiment 1, the main wing is selected as NACA0020, and ABS plastic and aluminum alloy are adopted to process the main wing, the chord length is 25 cm, the aspect ratio is 2, and the oscillating winglet part adopts a rudder to control the wingtip movement.

[0030] In some embodiments of embodiment 1, the shaft connected to the wingtip is driven to rotate by a motor, and the wingtip is driven to move by an Adrino control board. The driving voltage of the selected rudder is 4.8V / 7.4V, and the corresponding rotating speed is 0.22 / 60 degrees or 0.18 / 60 degrees.

[0031] In embodiment 2 of the present application, a winglet control method is provided, comprising: inputting the disturbance amplitude and frequency of the wingtip vortex into a synchronizer 6, and the synchronizer 6 controls the rudder 3 to drive the winglet 2 to vibrate according to the corresponding amplitude and frequency.

[0032] As shown in Figure 1 and Figure 2 In some embodiments of embodiment 2, the method for obtaining the disturbance of the wingtip vortex comprises: obtaining the disturbance of the wingtip vortex by performing stability analysis on the Batchelor vortex model.

[0033] In some embodiments of embodiment 2, the method for obtaining the Batchelor vortex model comprises: uploading the flow field information to a computer 5, and obtaining the Batchelor vortex model by performing Batchelor vortex fitting on the flow field information by the computer 5.

[0034] In some embodiments of embodiment 2, the method for obtaining the flow field information comprises: obtaining the flow field information by collecting and recording through an NI controller 4.

[0035] In some embodiments of embodiment 2, the stability analysis on the Batchelor vortex model is according to the formula: wherein A is the amplitude of the disturbance, ω is the frequency of the disturbance, qr(y, z) is the shape function of the disturbance, indicating the specific form of the disturbance, and G(x) represents the energy of the disturbance, is the phase of the disturbance.

[0036] In embodiment 3 of the present invention, a control system for a vibrating winglet is provided, including an NI controller 4, a computer 5, and a synchronizer 6. The NI controller 4 is suitable for collecting and recording flow field information and uploading the flow field information to the computer 5. The computer 5 is suitable for performing Batchelor vortex fitting on the flow field information to obtain a Batchelor vortex model. The synchronizer 6 is suitable for controlling the servo 3 to drive the vibrating winglet to vibrate according to the corresponding amplitude and frequency based on the disturbance of the wingtip vortex.

[0037] The beneficial effects of the vibrating winglet device of the present invention are as follows:

[0038] 1. Since the present invention adopts the idea of ​​guiding the movement of the vibrating winglet 2 based on the results of stability analysis, the vibrating winglet 2 can not only weaken the strength of the wingtip vortex, but also accelerate the dissipation of the wingtip vortex, achieving a better drag reduction effect than traditional winglets.

[0039] 2. Because the present invention utilizes a modified wingtip winglet 2, the movable wingtip device modifies the wingtip vortex structure, causing changes in the flow, thereby changing the corresponding aerodynamic performance and reducing drag. This not only reduces drag but also reduces aircraft engine noise and extends engine life.

[0040] 3. The background of the invention is based on large-sized fixed-wing aircraft such as wide-body passenger aircraft. In fact, this vibrating winglet can also be used in drones. Existing research has shown that the vibrating winglet 2 can effectively increase the payload of drones, increase flight range, improve flight performance, and bring higher flight benefits.

[0041] like Figure 1 As shown, in embodiment 4 of the present invention, a vibrating winglet device is provided to promote the rapid dissipation of the wake vortex, and a method for guiding the vibration of the vibrating winglet in combination with the stability analysis results is provided, which includes a vibrating winglet device and a control system. The vibrating winglet device includes: a main wing 1, a vibrating winglet 2, and a servo 3. Among them, the main wing 1 is used to fix the various parts of the vibrating winglet structure, and the vibrating winglet 2 is fixed above the main wing 1. The vibrating winglet 2 can rotate freely around the rotating shaft and is driven by the servo 3 to rotate the shaft connected to the movable wingtip.

[0042] The control system includes: NI controller 4, computer 5, synchronizer 6. Before the embodiment, it is necessary to transmit the flow velocity measurement data to the NI controller 4, the NI controller 4 collects and records the flow field data and uploads it to the computer 5, and the computer 5 first performs Batchelor vortex fitting on the flow field information. The Batchelor vortex model is as follows:

[0043]

[0044] By performing stability analysis on the Batchelor vortex model, the optimal perturbation of the wingtip vortex at this time can be obtained. The perturbation formula is as follows:

[0045] f q (x,y,z,t)=Aωq r (y,z)G(x)sin(ωt+φ)

[0046] Where A is the amplitude of the disturbance, ω is the frequency of the disturbance, and q r (y, z) is the shape function of the disturbance, representing its specific form. G(x) represents the energy of the disturbance, and φ is the phase of the disturbance. These data can be calculated using stability analysis methods. The main factors affecting the operation of the vibrating winglet are the corresponding A and ω in the formula. The former determines the amplitude of the winglet's vibration, and the latter determines the frequency of the winglet's vibration. The disturbance corresponding to A and ω is input to synchronizer 6, which controls servo 3 to drive the vibrating winglet to vibrate according to the corresponding amplitude and frequency.

[0047] Considering that it is difficult to directly obtain the vortex model with existing aircraft measurement technology, the empirical curve of vibration frequency and incoming flow velocity is obtained through ground experiments, such as Figure 2 As shown, in actual use, the corresponding vibration frequency can be directly determined by the incoming flow velocity and the empirical curve.

[0048] In some embodiments of the present invention, the vibrating winglet device body includes a main wing portion and a vibrating winglet portion. The main wing portion adopts a flat wing with winglets, and the main wing is selected as NACA0020 and is made of ABS plastic and aluminum alloy, with a chord length of 25 cm and an aspect ratio of 2. The vibrating winglet portion uses a servo to control the movement of the moving wingtip. The shaft connected to the moving wingtip is driven by a motor to rotate, and the movement of the moving wingtip is driven by an Adrino control board to drive the control servo. The selected driving voltage for the driving servo is 4.8V / 7.4V, corresponding to a rotation speed of 0.22 / 60 degrees or 0.18 / 60 degrees.

[0049] Determining the optimal vibration frequency of the vibrating winglet requires fitting the Batchelor vortex model based on the flow field information. This can be achieved through: (1) using multiple five-hole probes to obtain the velocities of the wake vortex in different directions; (2) using PIV experimental observations to obtain the velocities of the wake vortex in different directions, and other flow field observation techniques.

[0050] The control system includes a computer, an NI controller, and a synchronizer. The NI controller collects and records flow field data and uploads it to the computer. The computer extracts the Batchelor vortex model from the flow velocity measurements, performs stability analysis, and determines the corresponding vibration frequency of the vibrating winglet. This triggers the synchronizer, which controls the vibrating winglet to vibrate at the specified frequency.

[0051] The preferred embodiments of the application have been described above in detail. It should be understood that modifications and variations to the preferred embodiments could be made by those skilled in the art without departing from the spirit and scope of the application. Accordingly, it is intended that there be included within the scope of the application, all such modifications and variations as would be apparent to those skilled in the art upon reading this disclosure. It is intended to obtain for the inventors such patent rights as are available in any country on the world.

Claims

1. A method of controlling a vibration winglet, characterized by, The method for obtaining the disturbance of the wingtip vortex comprises: obtaining the disturbance of the wingtip vortex by performing stability analysis on the Batchelor vortex model. The method for obtaining the disturbance of the wingtip vortex comprises: obtaining the disturbance of the wingtip vortex by performing stability analysis on the Batchelor vortex model. The stability analysis on the Batchelor vortex model is according to the formula: The method for obtaining the Batchelor vortex model comprises: uploading the flow field information to a computer, and obtaining the Batchelor vortex model by performing Batchelor vortex fitting on the flow field information by the computer. where A is the amplitude of the perturbation, ω is the frequency of the perturbation, q r (y,z) is a shape function of the perturbation, representing the specific form of the perturbation, G(x) represents the energy of the perturbation, is the phase of the perturbation.

2. The method of vibration flap control according to claim 1, characterized in that The method for obtaining the flow field information comprises: obtaining the flow field information by acquisition and recording by an NI controller.

3. The method of vibration flap control according to claim 2, wherein The system comprises an NI controller, a computer and a synchronizer, the NI controller is adapted to acquire and record the flow field information and upload the flow field information to the computer, the computer is adapted to perform Batchelor vortex fitting on the flow field information to obtain the Batchelor vortex model, and the synchronizer is adapted to control the servo motor to drive the oscillating wing to vibrate according to the corresponding amplitude and frequency according to the disturbance of the wingtip vortex, and the computer performs stability analysis on the Batchelor vortex model according to the following formula:

4. A control system for a vibrating winglet, characterized in that ​ where A is the amplitude of the perturbation, ω is the frequency of the perturbation, q r (y,z) is a shape function of the perturbation, representing the specific form of the perturbation, G(x) represents the energy of the perturbation, is the phase of the perturbation.

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