Electromagnetic non-contact wing forced vibration dynamic loading device

Abstract

The invention belongs to the technical field of wing mechanical loading tests, and particularly relates to an electromagnetic non-contact wing forced vibration dynamic loading device. An upper driving coil shell and a lower driving coil shell are installed on a frame body, and a wing containing space is formed between the upper driving coil shell and the lower driving coil shell; the driving coil is connected with a power supply, and the driving coil is arranged in the upper driving coil shell and / or the lower driving coil shell; the wing position adjusting mechanism is mounted on the frame body; the wing is located in the wing containing space, one end of the wing is connected with the wing position adjusting mechanism through a mechanical sensor, and when the wing is made of a non-metal material, a load coil is installed on the wing and connected with a power source; the control system is connected with the power supply and the mechanical sensor and used for controlling current output by the power supply according to signals fed back by the mechanical sensor. The device can simulate the surface acting force of air on the wing 4, and can be used for the mechanical loading test of the aircraft wing.

Description

Technical Field

[0001] The present application belongs to the technical field of wing mechanical loading test, and in particular relates to an electromagnetic non-contact wing forced vibration dynamic loading device. Background Art

[0002] The dynamic response of metals and composite materials under complex stress environments has always been a concern of scholars. Especially with the development of my country's aerospace and national defense industry, more and more working environments require metal materials to be loaded with high strain rates and multiple, cyclic loading, such as continuous vibration cycle fatigue of wings. Therefore, it is of great significance to study the dynamic mechanical behavior of metal materials under complex loading conditions.

[0003] Conventional testing methods are to load a certain point, such as using a hydraulic rod to pull a certain point on the wing to deform the wing. This method is difficult to achieve distributed force loading control, which is very different from the aerodynamic distribution of the wing. In addition, the structural response speed of the hydraulic pressure is low, which is difficult to meet the current aircraft simulation requirements for complex loads.

[0004] Therefore, it is desired to have a technical solution to overcome or at least alleviate at least one of the above-mentioned defects of the prior art. Summary of the invention

[0005] The purpose of the present application is to provide an electromagnetic non-contact wing forced vibration dynamic loading device to solve at least one problem existing in the prior art.

[0006] The technical solution of this application is:

[0007] An electromagnetic non-contact wing forced vibration dynamics loading device, comprising:

[0008] A frame, on which an upper drive coil housing and a lower drive coil housing are mounted, and a wing accommodating space is provided between the upper drive coil housing and the lower drive coil housing;

[0009] A driving coil, wherein the driving coil is connected to a power source and comprises one or two groups of driving coils, wherein:

[0010] When the drive coil includes a group, the drive coil is installed in the upper drive coil housing or the lower drive coil housing;

[0011] When the driving coils include two groups, the two groups of driving coils are installed in the upper driving coil housing and the lower driving coil housing respectively;

[0012] A wing position adjustment mechanism, wherein the wing position adjustment mechanism is mounted on the frame;

[0013] A wing, wherein the wing is located in the wing accommodation space, one end of the wing is connected to the wing position adjustment mechanism through a mechanical sensor, and when the wing is made of non-metallic material, a load coil is installed on the wing, and the load coil is connected to the power supply;

[0014] A control system, wherein the control system is connected to the power supply and the mechanical sensor respectively, and is used to control the current output by the power supply according to the signal fed back by the mechanical sensor.

[0015] In at least one embodiment of the present application, the driving coil is in a flat shape, a flat cylinder or a flat rectangle.

[0016] In at least one embodiment of the present application, the driving coil includes an axial core and a plurality of turns of conductive wire wound around the axial core in the same direction, and insulating material is disposed between each turn of conductive wire.

[0017] In at least one embodiment of the present application, the shaft core is made of ferromagnetic material.

[0018] In at least one embodiment of the present application, when the driving coils include two groups, a repulsive force is generated between the two groups of driving coils.

[0019] In at least one embodiment of the present application, a cooling fan and a drive coil fixing frame are provided in the upper drive coil housing and the lower drive coil housing.

[0020] In at least one embodiment of the present application, the wing position adjustment mechanism adopts a screw structure, and the up-down, front-back, and left-right positions of the wing are adjusted by rotating the screw by a handle.

[0021] In at least one embodiment of the present application, the wing position adjustment mechanism is provided with a self-locking mechanism for fixing the wing at a certain position in the wing accommodating space.

[0022] In at least one embodiment of the present application, the load coil is wound by a flexible wire, a flexible insulating material is provided between each turn of the flexible wire, and the load coil is fixed to the wing by glue, tape or screws.

[0023] The invention has at least the following beneficial technical effects:

[0024] The electromagnetic non-contact wing forced vibration dynamic loading device of the present application adopts electromagnetic force loading method, relies on electromagnetic field to generate electromagnetic driving force, can quickly and accurately adjust the size of electromagnetic force according to the current waveform, realize high-frequency response of force loading and rapid changes of tension and compression, and meet the needs of loading complex loads on various materials. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a schematic diagram of an electromagnetic non-contact wing forced vibration dynamic loading device according to one embodiment of the present application;

[0026] Figure 2 It is a schematic diagram of the assembly of the driving coil and the load coil according to one embodiment of the present application;

[0027] Figure 3 It is a schematic diagram of the assembly of a drive coil and a drive coil housing according to one embodiment of the present application.

[0028] in:

[0029] 1-frame; 2-driving coil; 3-load coil; 4-wing; 5-power supply; 6-wing position adjustment mechanism; 7-mechanical sensor; 8-upper driving coil housing; 9-cooling fan; 10-driving coil fixing frame; 11-lower driving coil housing; 12-control system. DETAILED DESCRIPTION

[0030] In order to make the purpose, technical scheme and advantages of the implementation of this application clearer, the technical scheme in the embodiment of this application will be described in more detail below in conjunction with the drawings in the embodiment of this application. In the drawings, the same or similar reference numerals throughout represent the same or similar elements or elements with the same or similar functions. The described embodiments are part of the embodiments of this application, not all of them. The embodiments described below with reference to the drawings are exemplary and are intended to be used to explain this application, and should not be construed as limitations on this application. Based on the embodiments in this application, all other embodiments obtained by ordinary technicians in this field without making creative work are within the scope of protection of this application. The embodiments of this application are described in detail below in conjunction with the drawings.

[0031] In the description of the present application, it should be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the scope of protection of the present application.

[0032] The following is combined with Figures 1 to 3 This application is described in further detail.

[0033] The present application provides an electromagnetic non-contact wing forced vibration dynamic loading device, comprising: a frame 1, a drive coil 2, a wing position adjustment mechanism 6, a wing 4 and a control system 12.

[0034] Specifically, Figure 1 As shown, the frame 1 is mainly used for supporting, and can support the drive coil 2 and the wing position adjustment mechanism 6. The frame 1 has supporting parts in the upper and lower areas of the wing 4, which are used to install the upper drive coil housing 8 and the lower drive coil housing 11, and there is a wing accommodating space between the upper drive coil housing 8 and the lower drive coil housing 11; the wing position adjustment mechanism 6 is also placed on the frame 1; after structural design, the power supply 5 can also be placed on the frame 1 to reduce the occupied space, and the power supply 5 can also be placed separately in other positions without affecting its function of providing current to the coil.

[0035] In the preferred embodiment of the present application, the structural shape of the frame 1 is not limited, and the materials used should be able to bear the weight of the system and have a certain strength, including steel, copper, aluminum, plastic, etc. The frame 1 is installed with the corresponding drive coil housing through the extended support frame in the upper and lower areas of the wing 4, which can support the drive coil 2. The size of the support frame has a large area covering the wing 4, thereby supporting a large area of ​​the drive coil 2 to provide a large area of ​​electromagnetic force.

[0036] like Figure 1-3 As shown, the drive coil 2 is connected to the power supply 5, and the power supply 5 can output a large current to the drive coil 2. When the current flows through the drive coil 2, an electromagnetic field with a large area can be formed within the range covering the wing 4. The drive coil 2 includes one group or two groups, wherein when the drive coil 2 includes one group, the drive coil 2 is installed in the upper drive coil housing 8 or the lower drive coil housing 11; when the drive coil 2 includes two groups, the two groups of drive coils 2 are installed in the upper drive coil housing 8 and the lower drive coil housing 11 respectively. It can be understood that each group can include one drive coil 2 or multiple drive coils 2. The number of drive coils 2 included in each group is appropriately selected according to the size of the wing 4, and each drive coil 2 is fixed to the frame 1 using an upper drive coil housing 8 or a lower drive coil housing 11.

[0037] In a preferred embodiment of the present application, the shape of the driving coil 2 is flat, and can be a flat cylinder or a flat rectangle, and the change in shape does not affect the function of the driving coil 2. The flat shape can cover a larger range of the wing 4 structure, thereby providing a larger area of ​​electromagnetic force to the wing 4 and realizing surface force loading.

[0038] In this embodiment, the driving coil 2 includes an axis core and a plurality of turns of wire wound on the axis core in the same direction, and insulating material is arranged between each turn of wire. In order to facilitate winding the coil, there is an axis core at the center of the coil, and the wire can be wound on the axis core. The axis core can be made of ferromagnetic material to improve magnetic conductivity, and the axis core can also be made of insulating material without affecting its function of generating a strong magnetic field.

[0039] It can be understood that when the drive coil 2 includes two groups, one is located in the area above the wing 4, and the other is located in the area below the wing 4, when current is simultaneously passed through the drive coils 2, the two groups of drive coils 2 can generate magnetic fields with opposite directions of the central magnetic field to enhance the electromagnetic force formed in the load coil 3, that is, the two groups of drive coils 2 generate magnetic fields in opposite directions, and there is a repulsive force between the two groups of drive coils 2. The current in the drive coil 2 can change in size and direction, and the current in the two groups of drive coils 2 can change at the same time. The two groups of drive coils 2 can be a series circuit structure or a parallel circuit structure. After changing the size and direction of the current in the drive coil 2, the size and direction of the magnetic field will also change accordingly, and thus the size and direction of the electromagnetic force will also change accordingly.

[0040] Advantageously, if Figure 3 As shown, in this embodiment, the drive coil 2 is placed inside the drive coil housing and fixed to the upper drive coil housing 8 or the lower drive coil housing 11 through a drive coil fixing frame 10. In order to enhance heat dissipation, a cooling fan 9 can be installed around the drive coil housing.

[0041] Further, such as Figure 1-2 As shown, the wing position adjustment mechanism 6 is installed on the frame 1, which is used to support the wing 4 and adjust the position of the wing 4. The wing 4 is located in the wing accommodation space between the upper drive coil housing 8 and the lower drive coil housing 11. There is a certain gap between the wing 4 and the drive coil 2. One end of the wing 4 is connected to the wing position adjustment mechanism 6 through a mechanical sensor 7, wherein one end of the wing 4 is fixed on the mechanical sensor 7, and the other end is in a free state; the mechanical sensor 7 is fixed on the wing position adjustment mechanism 6, and can measure the real-time force condition of the wing 4. When the wing 4 is a metal material with ferromagnetism, there is no need to fix the load coil 3 on the wing 4, and the wing mechanical response can be driven non-contactly only by the drive coil 2. When the wing 4 is a non-metallic material, a load coil 3 is installed on the wing 4, and the load coil 3 is connected to the power supply 5. When current is respectively passed through the driving coil 2 and the load coil 3, a load force is generated between the two through the interaction between the electromagnetic field and the current. Under the action of the electromagnetic force, the wing 4 will be deformed, causing the free end of the wing 4 to bend downward or upward, thereby carrying out mechanical testing of the wing 4.

[0042] In a preferred embodiment of the present application, the wing position adjustment mechanism 6 adopts a screw structure. The up and down height, front and back, and left and right positions of the wing 4 can be adjusted by rotating the screw by the handle. At the same time, a self-locking mechanism is provided on the wing position adjustment mechanism 6, which can fix the wing 4 at a certain position in the wing accommodating space.

[0043] In a preferred embodiment of the present application, the load coil 3 is wound by a flexible wire, a flexible insulating material is arranged between each turn of the flexible wire, and the load coil 3 is fixed to the wing 4 by glue, tape or screws. Figure 2 As shown, in this embodiment, the load coil 3 is fixed under the wing 4. When current is passed through the load coil 3, the current interacts with the magnetic field generated by the drive coil 2 to generate an electromagnetic force in the load coil 3. The magnitude and direction of the electromagnetic force can be changed according to the magnitude and direction of the current in the load coil 3. The load coil 3 is made of a thinner and softer material, and can change its shape with the shape of the wing 4. It is a flexible deformable material and can be tightly installed on the surface of the flat or curved wing 4.

[0044] The control system 12 is connected to the power supply 5 and the mechanical sensor 7 respectively. The mechanical sensor 7 can measure the magnitude of the electromagnetic force on the wing 4 in real time, and output the measurement data to the control system 12 through the wire. The control system 12 can process, analyze and store the measurement data. The control system 12 can control the current output by the power supply 5 according to the signal fed back by the mechanical sensor 7. Under the drive of the control system 12, the power supply 5 provides accurate and adjustable current for the drive coil 4 and the load coil 3. The power supply 5 inputs alternating current and outputs direct current. The positive and negative poles of the power supply 5 are respectively connected to the positive and negative poles of the drive coil 2 and the load coil 3, thereby providing current to the coil. The wire of the drive coil 2 is thicker and can withstand a larger current. The wire of the load coil 3 is thinner and withstands a smaller current. The power supply 5 can output a larger direct current and a smaller alternating current. Under the action of the control system 12, the power supply 5 can adjust the magnitude change of the current and the direction change of the current. The magnitude and direction of the current flowing through the drive coil 4 and the load coil 3 are controlled by controlling the power supply 5 through the control system 12, thereby controlling the magnitude and direction of the electromagnetic force. The current flowing through the driving coil 4 and the load coil 3 can be designed to have a desired waveform, thereby controlling the waveform of the electromagnetic force.

[0045] The electromagnetic non-contact wing forced vibration dynamic loading device of the present application fixes the driving coil 2 on the frame 1, located above and / or below the wing 4, and the load coil 3 is arranged on the wing 4. The control system 12 controls the power supply 5 to pass an adjustable current into the driving coil 2 and the load coil 3 respectively, so as to form a strong magnetic field at the wing 4. The current in the load coil 3 interacts with the strong magnetic field to generate an electromagnetic force, thereby forming an electromagnetic force of surface loading on the wing 4, simulating the aerodynamic force on the wing 4, and generating a load force through the interaction between the electromagnetic field and the current. The magnitude and direction of the force are related to the magnitude and direction of the current, and the magnitude of the electromagnetic force can be adjusted quickly and accurately according to the current waveform, so as to achieve a high-frequency response of the force loading and a rapid change of tension and compression. At the same time, the control system 12 is used to control the power supply 5 to quickly adjust the required loading force and force waveform, with a high dynamic mechanical response, meeting the requirements of various test conditions.

[0046] The electromagnetic non-contact wing forced vibration dynamic loading device of the present application can realize non-contact mechanical loading of the wing 4, can simulate the surface force of air on the wing 4, and can be used for mechanical loading tests of aircraft wings; it can control the current size with high precision, thereby controlling the electromagnetic force size and direction of the electromagnetic force, and has a higher response frequency.

[0047] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. An electromagnetic non-contact wing forced vibration dynamics loading device, characterized in that: include: A frame (1), an upper drive coil housing (8) and a lower drive coil housing (11) being mounted on the frame (1), and a wing accommodating space being provided between the upper drive coil housing (8) and the lower drive coil housing (11); A driving coil (2), wherein the driving coil (2) is connected to a power source (5), and the driving coil (2) includes one or two groups, wherein: When the drive coil (2) includes a group, the drive coil (2) is installed in the upper drive coil housing (8) or the lower drive coil housing (11); When the drive coil (2) includes two groups, the two groups of drive coils (2) are respectively installed in the upper drive coil housing (8) and the lower drive coil housing (11); A wing position adjustment mechanism (6), wherein the wing position adjustment mechanism (6) is mounted on the frame (1); A wing (4), the wing (4) being located in the wing accommodation space, one end of the wing (4) being connected to the wing position adjustment mechanism (6) via a mechanical sensor (7), and when the wing (4) is made of a non-metallic material, a load coil (3) is installed on the wing (4), and the load coil (3) is connected to the power supply (5); A control system (12), wherein the control system (12) is connected to the power supply (5) and the mechanical sensor (7) respectively, and is used to control the current output by the power supply (5) according to the signal fed back by the mechanical sensor (7).

2. The electromagnetic non-contact wing forced vibration dynamic loading device according to claim 1, characterized in that: The driving coil (2) is in a flat shape, a flat cylindrical shape or a flat rectangular shape.

3. The electromagnetic non-contact wing forced vibration dynamics loading device according to claim 2, characterized in that: The driving coil (2) comprises an axial core and a plurality of turns of conductive wires wound around the axial core in the same direction, with insulating material being arranged between the turns of conductive wires.

4. The electromagnetic non-contact wing forced vibration dynamic loading device according to claim 3, characterized in that: The shaft core is made of ferromagnetic material.

5. The electromagnetic non-contact wing forced vibration dynamic loading device according to claim 4, characterized in that: When the driving coil (2) includes two groups, a repulsive force is generated between the two groups of driving coils (2).

6. The electromagnetic non-contact wing forced vibration dynamics loading device according to claim 5, characterized in that: A cooling fan (9) and a drive coil fixing frame (10) are provided in the upper drive coil housing (8) and the lower drive coil housing (11).

7. The electromagnetic non-contact wing forced vibration dynamic loading device according to claim 1, characterized in that: The wing position adjustment mechanism (6) adopts a screw rod structure, and the upper and lower, front and rear, and left and right positions of the wing (4) are adjusted by rotating the screw rod with a handle.

8. The electromagnetic non-contact wing forced vibration dynamics loading device according to claim 7, characterized in that: The wing position adjustment mechanism (6) is provided with a self-locking mechanism for fixing the wing (4) at a certain position in the wing accommodation space.

9. The electromagnetic non-contact wing forced vibration dynamic loading device according to claim 1, characterized in that: The load coil (3) is wound by a flexible wire, and a flexible insulating material is arranged between each turn of the flexible wire. The load coil (3) is fixed to the wing (4) by glue, tape or screws.

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