A piezoelectric servo structure

Abstract

The present invention provides a piezoelectric servo structure, which relates to the technical field of rudder wings of aerospace aircraft. The piezoelectric servo structure includes a servo cabin housing, and a fixed mounting seat is fixedly connected to the bottom end of the servo cabin housing. The fixed mounting seat is used to fix the rudder wing in the servo cabin housing. The rudder wing includes a base, a set screw, a rudder wing housing, a piezoelectric sheet, a torsion spring, and a rotating shaft. The rotating shaft is connected to the base through a rotating shaft connecting member. The set screw applies a force to fix the piezoelectric sheet. The rudder wing housing is fixed through the cooperation of the rotating shaft and a rotating shaft clamping member. By utilizing the fact that after the piezoelectric sheet generates deformation under a certain voltage, it pushes the deflection of the rudder wing inside the rudder wing housing, so as to achieve the purpose of deflecting the servo rudder surface. The structure is simple, easy to miniaturize, has a fast response speed, high response accuracy, high electromechanical coupling coefficient, and strong anti-interference ability. It has the advantages of simple structure, light weight, and fast response speed.

Description

Technical Field

[0001] The present invention relates to the technical field of aerospace vehicle rudder wings, and specifically to a piezoelectric actuator structure. Background Technique

[0002] Chinese Patent Publication No. CN114562918A discloses a micro electric folding actuator, including a support device, a transmission device and a folding device, which realizes the compactness and reliability of the transmission device. The modular design facilitates installation and debugging. At the same time, the folding function of the small actuator is realized, with high reliability and simple structure. Traditional actuators include many transmission units such as an actuator controller, a servo power amplifier, a DC servo motor, and a reduction mechanism, which occupy a large space and are not easy to miniaturize. Moreover, there are problems such as narrow control bandwidth and low precision. In addition, the mechanical structure of traditional actuators is complex, and the control system of traditional actuators is easily affected by external electromagnetic interference, which affects its safety and reliability. Therefore, in order to meet the development requirements of the aerospace industry, it is urgent to research, develop and apply new principles, new materials and new structures of aircraft actuators. Summary of the Invention

[0003] Aiming at the deficiencies of the prior art, the present invention provides a piezoelectric actuator structure, a rudder wing structure based on the inverse piezoelectric effect. Compared with the traditional motor-driven rudder wing structure, it has the advantages of simple structure, light weight, and fast response speed.

[0004] To achieve the above objectives, the present invention is realized through the following technical solutions: A piezoelectric actuator structure, including a rudder cabin housing, the bottom end of the rudder cabin housing is fixedly connected with a fixed mount, and the fixed mount is used to fix the rudder wing in the rudder cabin housing. The rudder wing includes a base, a set screw, a rudder wing housing, a piezoelectric sheet, a torsion spring, and a rotating shaft. The base is connected to the fixed mount through a pin. The torsion spring cooperates with the pin and the fixed mount for the rudder wing to unfold. The rotating shaft is connected to the base through a rotating shaft connecting piece. The set screw applies a force to fix the piezoelectric sheet. The rudder wing housing is fixed through cooperation with the rotating shaft and a rotating shaft clamping part.

[0005] Preferably, the fixed mount uses a bolt connection method to fix the rudder wing in the rudder cabin housing. [[ID=2I]]

[0006] Preferably, it further includes a bearing, and the bearing is used to connect the rudder wing housing and the base to bear the radial load when the rudder wing deflects, making the rudder wing deflection action smoother.

[0007] Preferably, the rotating shaft and the metal rod are used to fix the position of the rudder wing and play a limiting role.

[0008] Preferably, one end of the piezoelectric sheet is provided with a piezoelectric sheet extension, and the piezoelectric sheet extension is used to amplify the deflection size of the piezoelectric sheet.

[0009] Preferably, a thimble is embedded inside the piezoelectric sheet extension, and the thimble is used to reduce the contact area between the end of the piezoelectric sheet extension and the inner groove member of the rudder wing housing.

[0010] Preferably, a limiting mechanism is installed on the rotating shaft fixture when the rudder wing is not deployed, so that the rudder wing is retracted into the rudder machine housing.

[0011] Preferably, a piezoelectric servo structure includes a rudder machine housing. A fixed mount is fixedly connected to the bottom end of the rudder machine housing. The fixed mount is used to fix the rudder wing inside the rudder machine housing. The rudder wing includes a base, a pressing sheet, a set screw, a rudder wing housing, a piezoelectric sheet, a torsion spring, a bearing, and a rudder wing end connector. The base is connected to the fixed mount through a pin. The torsion spring cooperates with the pin and the fixed mount for the deployment of the rudder wing. The base is used to fix the piezoelectric sheet and the pressing sheet. The pressing sheet is arranged between the set screw and the piezoelectric sheet. The rudder wing housing is arranged outside the piezoelectric sheet and is the driving surface of the rudder wing. The rotating shaft is connected to the base through a rotating shaft connector. The set screw applies a force to the pressing sheet to fix the piezoelectric sheet. The rudder wing end connector cooperates with a metal rod to fix the position of the rudder wing and play a limiting role.

[0012] Working principle: The realization of the angle deflection of the rudder wing housing in the servo structure is that when the piezoelectric sheet is deformed under a certain voltage, it pushes the deflection of the rudder wing inside the rudder wing housing, so as to achieve the purpose of the deflection of the servo rudder surface. Among them, the cooperation of the pressing sheet, the base and the set screw fixes the piezoelectric sheet, so that the piezoelectric sheet bends and deforms at the other end, thereby applying a certain force to the rudder wing housing and pushing the rudder wing to deflect. In addition, the cooperation of the bearing makes the deflection of the rudder wing smoother.

[0013] The present invention provides a piezoelectric servo structure. It has the following beneficial effects:

[0014] 1. The rudder wing structure of the present invention based on the inverse piezoelectric effect uses the piezoelectric sheet to be deformed under a certain voltage and then pushes the deflection of the rudder wing inside the rudder wing housing, so as to achieve the purpose of the deflection of the servo rudder surface. The structure is simple, easy to miniaturize, has a fast response speed, high response accuracy, high electromechanical coupling coefficient, strong anti-interference ability, and can operate normally in a certain high-temperature environment.

[0015] 2. The rudder wing structure of the present invention based on the inverse piezoelectric effect has the advantages of simple structure, light weight, and fast response speed compared with the traditional motor-driven rudder wing structure.

[0016] 3. The pressing piece, base and set screw of the present invention cooperate to fix the piezoelectric sheet, causing the piezoelectric sheet to bend and deform at the other end, thereby exerting a certain force on the rudder wing housing and pushing the rudder wing to deflect. In addition, the cooperation of the bearing makes the deflection process of the rudder wing smoother.

[0017] 4. The rudder wing structure of the present invention can replace most of the existing rudder wing structures driven by motors. After the piezoelectric sheet deforms under a certain voltage, it pushes the deflection of the rudder wing inside the rudder wing housing, thereby achieving the purpose of deflecting the rudder surface of the servo. It can have more application scenarios in new missiles and smart weapons, and also has more application scenarios in various new aircraft, and can replace most of the existing rudder wing structures driven by motors. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic structural diagram of a specific embodiment of the present invention;

[0019] Figure 2 It is a schematic structural diagram of another specific embodiment of the present invention;

[0020] Figure 3 It is a schematic diagram of the rudder wing structure test of the present invention;

[0021] Figure 4 It is a schematic diagram of the piezoelectric sheet structure test of the present invention.

[0022] Among them, 1. Rudder nacelle housing; 2. Fixed mount; 3. Pin; 4. Base; 5. Pressing piece; 6. Set screw; 7. Rudder wing housing; 8. Piezoelectric sheet; 9. Torsion spring; 10. Bearing; 11. Rudder wing end connector; 12. Rotating shaft connector; 13. Piezoelectric sheet extension; 14. Thimble; 15. Rotating shaft clip; 16. Rotating shaft. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0023] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0024] Embodiment 1:

[0025] As Figure 1As shown in the figure, an embodiment of the present invention provides a piezoelectric servo structure, which includes a servo cabin housing 1. A fixed mount 2 is fixedly connected to the bottom end of the servo cabin housing 1. The fixed mount 2 is used to fix the rudder wing in the servo cabin housing 1. The rudder wing includes a base 4, a set screw 6, a rudder wing housing 7, a piezoelectric sheet 8, a torsion spring 9, and a rotating shaft 16. The base 4 is connected to the fixed mount 2 through a pin 3. The torsion spring 9 cooperates with the pin 3 and the fixed mount 2 to be used for the deployment of the rudder wing. The rotating shaft 16 is connected to the base 4 through a rotating shaft connecting member 12. The set screw 6 applies a force to fix the piezoelectric sheet 8. The rudder wing housing 7 is fixed through the cooperation of the rotating shaft 16 and a rotating shaft clamping member 15.

[0026] In some specific embodiments, the fixed mount 2 uses a bolt connection method to fix the rudder wing in the servo cabin housing 1.

[0027] In some specific embodiments, it further includes a bearing 10. The bearing 10 is used to connect the rudder wing housing 7 and the base 4, and is used to bear the radial load when the rudder wing deflects, making the deflection action of the rudder wing smoother.

[0028] The rotating shaft 16 and the metal rod are used to fix the position of the rudder wing and play a limiting role.

[0029] One end of the piezoelectric sheet 8 is provided with a piezoelectric sheet extension 13. The piezoelectric sheet extension 13 is used to amplify the deflection size of the piezoelectric sheet 8.

[0030] A thimble 14 is embedded inside the piezoelectric sheet extension 13. The thimble 14 is used to reduce the contact area between the end of the piezoelectric sheet extension 13 and the inner groove member of the rudder wing housing 7.

[0031] In the piezoelectric servo structure of this embodiment, a limiting mechanism is installed by the rotating shaft clamping member 15 when the rudder wing is not deployed, so that the rudder wing is retracted into the servo cabin housing 1.

[0032] The piezoelectric intelligent structure utilizes the inverse piezoelectric effect of piezoelectric materials. By applying an excitation electric field, the piezoelectric materials generate mechanical deformation, thereby realizing various expected motions. Technical solution for rudder wing deflection: The realization of the angle deflection of the rudder wing housing 7 in the servo structure is that after the piezoelectric sheet 8 is deformed under a certain voltage, it pushes the deflection of the rudder wing inside the rudder wing housing 7, so as to achieve the purpose of the deflection of the servo rudder surface. Among them, the cooperation of the pressing piece 5, the base 4 and the set screw 6 fixes the piezoelectric sheet 8, so that the piezoelectric sheet 8 bends and deforms at the other end, thereby applying a certain force to the rudder wing housing 7 and pushing the rudder wing to deflect. In addition, the cooperation of the bearing 10 makes the deflection process of the rudder wing smoother. It can replace most of the existing rudder wing structures driven by motors and has many application scenarios in new missiles and smart weapons, and also has many application scenarios in various new aircraft.

[0033] Embodiment 2:

[0034] Reference Figures 2-4 For the piezoelectric servo structure of this embodiment, it includes a servo cabin housing 1. A fixed mount 2 is fixedly connected to the bottom end of the servo cabin housing 1. The fixed mount 2 is used to fix the rudder wing in the servo cabin housing 1. The rudder wing includes a base 4, a pressing piece 5, a set screw 6, a rudder wing housing 7, a piezoelectric sheet 8, a torsion spring 9, a bearing 10, and a rudder wing end connector 11. The base 4 is connected to the fixed mount 2 through a pin 3. The torsion spring 9 cooperates with the pin 3 and the fixed mount 2 for the deployment of the rudder wing. The base 4 is used to fix the piezoelectric sheet 8 and the pressing piece 5. The pressing piece 5 is arranged between the set screw 6 and the piezoelectric sheet 8. The rudder wing housing 7 is arranged outside the piezoelectric sheet 8 and is the driving surface of the rudder wing. The rotating shaft 16 is connected to the base 4 through a rotating shaft connector 12. The set screw 6 applies a force to the pressing piece 5 to fix the piezoelectric sheet 8. The rudder wing end connector 11 cooperates with the metal rod to fix the position of the rudder wing and plays a limiting role.

[0035] The difference between this Embodiment 2 and the above Embodiment 1 is that: the airfoil of the rudder wing housing 7 is different. Figure 2 It is on the smaller side of the 0020 type. Figure 1 It is on the larger side of the 0040 type; the structural form of the rotating shaft is different. Figure 2 In [reference], the rotating shaft and the rudder wing housing 7 are integrated. Figure 1 In [reference], the rotating shaft 16 and the rudder wing housing 7 are separated and are two different components. Figure 2 The piezoelectric sheet 8 in [reference] does not have a piezoelectric sheet extension 13. Figure 1 In [reference], it has a piezoelectric sheet extension.

[0036] The present invention is based on a piezoelectric intelligent structure. The piezoelectric intelligent structure utilizes the inverse piezoelectric effect of piezoelectric materials. By applying an exciting electric field, the piezoelectric materials generate mechanical deformation, thereby achieving various expected motions. The realization of the angle deflection of the rudder wing housing 7 in the servo structure is that after the piezoelectric sheet 8 is deformed under a certain voltage, it pushes the deflection of the rudder wing inside the rudder wing housing 7, thereby achieving the purpose of the deflection of the servo rudder surface. Among them, the cooperation of the pressing piece 5, the base 4, and the set screw 6 fixes the piezoelectric sheet 8, making the piezoelectric sheet 8 bend and deform at the other end, thereby applying a certain force to the rudder wing housing 7 and pushing the rudder wing to deflect. In addition, the cooperation of the bearing 10 makes the deflection process of the rudder wing smoother.

[0037] In some specific embodiments:

[0038] Servo cabin housing 1: The position where the servo structure is installed and fixed.

[0039] Fixed mount 2: Fixes the rudder wing in the servo cabin housing 1, and the connection method adopted is bolt connection.

[0040] Pin 3: The connecting part between the base 4 and the fixed mount 2.

[0041] Torsion spring 9: The torsion spring 9 cooperates with the pin 3 and the fixed mounting seat 2 for the deployment of the rudder wing.

[0042] Base 4: The piezoelectric sheet 8 and the pressing sheet 5 are fixed in position.

[0043] Pressing sheet 5: It is arranged between the set screw 6 and the piezoelectric sheet 8. The piezoelectric sheet 8 is a piezoelectric bimorph, which prevents the piezoelectric bimorph from being damaged due to stress concentration caused by the direct pressing of the set screw 6 on the piezoelectric bimorph.

[0044] Rudder wing housing 7: The driving surface of the rudder wing design.

[0045] Rudder wing end connector 11: It cooperates with the rotating shaft 16 to fix the position of the rudder wing, plays a limiting role, and prevents the rudder wing from falling off.

[0046] Set screw 6: Applies a force to the pressing sheet 5 to fix the piezoelectric sheet 8.

[0047] Bearing 10: It is mainly used to bear the radial load when the rudder wing deflects, making the deflection action of the rudder wing smoother.

[0048] Rotating shaft 16: Serves as the fulcrum for the deflection of the rudder wing.

[0049] Rotating shaft connector 12: Connects the rotating shaft 16 and fixes the rotating shaft 16 on the base 4.

[0050] Rotating shaft clip 15: Cooperates with the rotating shaft 16 to fix the rudder wing housing 7, plays a limiting role, and prevents the rudder wing housing 7 from falling off.

[0051] Piezoelectric sheet extension 13: Plays the role of extending the piezoelectric sheet 8 and amplifying the deflection size of the piezoelectric sheet 8.

[0052] Ejector pin 14: It is embedded in the piezoelectric sheet extension 13, reduces the contact area between the end of the piezoelectric sheet extension 13 and the inner groove part of the rudder wing housing 7. At the same time, the ejector pin 14 can be made of a material with higher hardness and greater rigidity to improve the accuracy of the piezoelectric sheet 8 driving the rudder wing housing 7.

[0053] Rotating shaft clip 15: Installs a limiting mechanism when the rudder wing is not deployed, so that the rudder wing is retracted into the rudder engine housing 1.

[0054] Although the embodiments of the present invention have been shown and described, for those of ordinary skill in the art, it can be understood that various changes, modifications, substitutions, and variations can be made to these embodiments without departing from the principle and spirit of the present invention. The scope of the present invention is defined by the appended claims and their equivalents.

Claims

1. A piezoelectric servo structure, comprising a servo cabin housing (1), characterized in that: A fixed mounting base (2) is fixedly connected to the bottom end of the rudder nacelle housing (1). The fixed mounting base (2) is used to fix the rudder wing within the rudder nacelle housing (1). The rudder wing includes a base (4), a set screw (6), a rudder wing housing (7), a piezoelectric sheet (8), a torsion spring (9), and a rotating shaft (16). The base (4) is connected to the fixed mounting base (2) through a pin (3). The torsion spring (9) cooperates with the pin (3) and the fixed mounting base (2) for the deployment of the rudder wing. The rotating shaft (16) is connected to the base (4) through a rotating shaft connecting member (12). The set screw (6) applies a force to fix the piezoelectric sheet (8). The rudder wing housing (7) is fixed through the cooperation of the rotating shaft (16) and a rotating shaft clamping member (15). One end of the piezoelectric sheet (8) is provided with a piezoelectric sheet extension member (13). The piezoelectric sheet extension member (13) is used to amplify the deflection magnitude of the piezoelectric sheet (8). A thimble (14) is embedded inside the piezoelectric sheet extension member (13). The thimble (14) is used to reduce the contact area between the end of the piezoelectric sheet extension member (13) and the inner groove member of the rudder wing housing (7).

2. The piezoelectric servo structure according to claim 1, wherein: The fixed mounting base (2) uses a bolt connection method to fix the rudder wing within the rudder nacelle housing (1).

3. A piezoelectric servo structure according to claim 1, characterized in that: It further includes a bearing (10). The bearing (10) is used to connect the rudder wing housing (7) and the base (4) and bear the radial load during the deflection of the rudder wing, making the deflection action of the rudder wing smoother.

4. A piezoelectric servo structure according to claim 1, characterized in that: The rotating shaft (16) and the metal rod are used to fix the position of the rudder wing and play a limiting role.

5. A piezoelectric servo structure according to claim 1, characterized in that: The rotating shaft clamping member (the limiting mechanism is installed when the rudder wing is not deployed, so that the rudder wing is retracted into the rudder nacelle housing (1).

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