A solar wing active vibration suppression device and method based on piezoelectric drive

Abstract

The present invention discloses a piezoelectric-driven solar wing active vibration suppression device and method, comprising two piezoelectric vibration suppression modules and a connecting rod; the piezoelectric vibration suppression module comprises a pre-tightening bolt, a pre-tightening rod, a support rod, a piezoelectric actuation module and a piezoelectric sensing module; the stud of the pre-tightening bolt passes through the countersunk through hole of the pre-tightening rod, the piezoelectric actuation module and the threaded hole of the support rod in sequence, and is threadedly connected to the piezoelectric actuation module to compress the piezoelectric actuation module. The piezoelectric actuation module comprises N piezoelectric actuation units; the piezoelectric actuation unit comprises 8 double-partitioned piezoelectric ceramic sheets stacked in sequence. When working, the piezoelectric actuation module is stimulated by the application of an excitation signal to produce a vibration type opposite to the disturbed vibration direction of the solar wing, thereby achieving the effect of active vibration suppression. The present invention has the advantages of a wide range of applications, good vibration control effect, strong versatility, and broad application prospects.

Description

Technical Field

[0001] The present invention relates to the fields of piezoelectric actuation and mechanical vibration control, and in particular to a piezoelectric-driven solar wing active vibration suppression device and method. Background Art

[0002] As an important component of space structures and spacecraft, solar wings carry the main energy source of spacecraft and space structures. However, solar wings will inevitably produce vibrations of different modes due to factors such as attitude adjustment and debris impact in the space working environment. The solar wing structure lacks vibration control modules or damping, and cannot suppress its disturbed vibrations, resulting in frequent failures or even damage of solar wings in the space environment due to disturbed vibrations.

[0003] At present, there are two methods for vibration control of solar wings: passive control and active control. Passive control, such as dampers and vibration isolators, has poor vibration suppression effects and cannot effectively suppress vibrations in different directions and of different vibration types of solar wings. Active control currently used is cumbersome and complex in structure, and cannot suppress vibrations of different types. Existing vibration suppression technologies are difficult to effectively suppress vibrations of solar wing structures due to poor adaptability and low vibration suppression rates. Summary of the invention

[0004] The technical problem to be solved by the present invention is to address the defects involved in the background technology and provide a piezoelectric-driven solar wing active vibration suppression device and method, which can suppress different vibration types.

[0005] The present invention adopts the following technical solutions to solve the above technical problems:

[0006] A piezoelectric-driven solar wing active vibration suppression device comprises a first piezoelectric vibration suppression module, a second piezoelectric vibration suppression module and a connecting rod;

[0007] The first piezoelectric vibration suppression module and the second piezoelectric vibration suppression module have the same structure, and both include a pre-tightening bolt, a pre-tightening rod, a support rod, a piezoelectric actuation module and a piezoelectric sensing module;

[0008] The pre-tightening bolt comprises a nut and a stud;

[0009] The support rod and the preload rod are regular prisms or cylinders with the same cross-sectional shape, a threaded hole matching the preload bolt is provided at the center of one end face of the support rod, and a countersunk through hole matching the preload bolt is provided at the center of one end face of the preload rod;

[0010] The piezoelectric actuation module includes N piezoelectric actuation units;

[0011] The piezoelectric actuating unit comprises 8 double-partition piezoelectric ceramic sheets; the double-partition piezoelectric ceramic sheets are in the shape of a regular polygon or a circle, with a through hole in the center for the pre-tightening bolt to pass through, polarized along the thickness direction, and the polarization boundary line of the double-partition piezoelectric ceramic sheets is a straight line passing through the center of the circle; the double-partition piezoelectric ceramic sheets comprise a first partition and a second partition, and the polarization directions of the first partition and the second partition are opposite; the 8 double-partition piezoelectric ceramic sheets are stacked in sequence, wherein the polarization boundary lines of the first, second, fifth, and sixth double-partition piezoelectric ceramic sheets are coplanar, the polarization boundary lines of the third, fourth, seventh, and eighth double-partition piezoelectric ceramic sheets are coplanar, and the polarization boundary lines of the first and third double-partition piezoelectric ceramic sheets are perpendicular to each other; the polarization directions of the 2i-1th double-partition piezoelectric ceramic sheet and the 2ith double-partition piezoelectric ceramic sheet are opposite, i is an integer greater than or equal to 1 and less than or equal to 4; the polarization directions of the first and fifth double-partition piezoelectric ceramic sheets are the same, and the polarization directions of the third and seventh double-partition piezoelectric ceramic sheets are the same;

[0012] The N piezoelectric actuating units are stacked in sequence, and the polarization boundary lines of the first double-partitioned piezoelectric ceramic sheets of the N piezoelectric actuating units are coplanar and have the same polarization direction;

[0013] The stud of the pre-tightening bolt passes through the countersunk through hole of the pre-tightening rod, the through hole of each double-partitioned piezoelectric ceramic sheet of the N piezoelectric actuating units in the piezoelectric actuating module, and then is threadedly connected to the threaded hole of the support rod to press each double-partitioned piezoelectric ceramic sheet of the N piezoelectric actuating units in the piezoelectric actuating module;

[0014] The side wall of the support rod close to one end of the piezoelectric actuation module is evenly provided with first to fourth mounting grooves in the circumferential direction;

[0015] The piezoelectric sensing module includes first to fourth piezoelectric sensors; the first to fourth piezoelectric sensors are arranged in the first to fourth mounting grooves in a one-to-one correspondence, and are used to sense the magnitude of the force at their locations;

[0016] The first piezoelectric sensor is located on the angular bisector plane of the first partition of the first double-partition piezoelectric ceramic piece in the piezoelectric actuating unit, on the angular bisector plane of the first partition of the third double-partition piezoelectric ceramic piece in the piezoelectric actuating unit of the second piezoelectric sensor, on the angular bisector plane of the second partition of the first double-partition piezoelectric ceramic piece in the piezoelectric actuating unit of the third piezoelectric sensor, and on the angular bisector plane of the second partition of the third double-partition piezoelectric ceramic piece in the piezoelectric actuating unit of the fourth piezoelectric sensor;

[0017] One end of the support rod in the first piezoelectric vibration suppression module and the second piezoelectric vibration suppression module away from the piezoelectric actuation module is fixedly connected to the solar wing, so that the support rods of the first piezoelectric vibration suppression module and the second piezoelectric vibration suppression module are coplanar with the solar wing, and the second and fourth piezoelectric sensors in the first piezoelectric vibration suppression module are coplanar with the solar wing, and the second and fourth piezoelectric sensors in the second piezoelectric vibration suppression module are coplanar with the solar wing;

[0018] One end of the connecting rod is fixedly connected to the pre-tightening rod of the first piezoelectric vibration suppression module, and the other end is fixedly connected to the pre-tightening rod of the second piezoelectric vibration suppression module, and the connecting rod is connected to the spacecraft through a bracket; the pre-tightening rods of the first piezoelectric vibration suppression module and the second piezoelectric vibration suppression module are symmetrical about the mid-section of the connecting rod, and the pre-tightening rods of the first piezoelectric vibration suppression module and the second piezoelectric vibration suppression module are not parallel to each other.

[0019] The present invention also discloses a working method of the piezoelectric driven solar wing active vibration suppression device, comprising the following steps:

[0020] For each piezoelectric actuating unit in the first piezoelectric vibration suppression module and the second piezoelectric vibration suppression module, the upper end surfaces of the two partitions of the first, third, fifth and seventh double-partition piezoelectric ceramic pieces are grounded, the lower end surfaces of the two partitions of the second, fourth, sixth and eighth double-partition piezoelectric ceramic pieces are grounded, the lower end surfaces of the first partitions of the first and fifth double-partition piezoelectric ceramic pieces are connected to the driving signal A, the upper end surfaces of the first partitions of the second and sixth double-partition piezoelectric ceramic pieces are connected to the driving signal A, the lower end surfaces of the second partitions of the first and fifth double-partition piezoelectric ceramic pieces are connected to the driving signal B, the upper end surfaces of the second partitions of the second and sixth double-partition piezoelectric ceramic pieces are connected to the driving signal B, the lower end surfaces of the first partitions of the third and seventh double-partition piezoelectric ceramic pieces are connected to the driving signal C, the upper end surfaces of the first partitions of the fourth and eighth double-partition piezoelectric ceramic pieces are connected to the driving signal C, the lower end surfaces of the second partitions of the third and seventh double-partition piezoelectric ceramic pieces are connected to the driving signal D, and the upper end surfaces of the second partitions of the fourth and eighth double-partition piezoelectric ceramic pieces are connected to the driving signal D;

[0021] The driving signal A has the same frequency, consistent phase and the same positive and negative as the sensing signal emitted by the first piezoelectric sensor; the driving signal B has the same frequency, consistent phase and the opposite positive and negative as the sensing signal emitted by the second piezoelectric sensor; the driving signal C has the same frequency, consistent phase and the opposite positive and negative as the sensing signal emitted by the third piezoelectric sensor; the driving signal D has the same frequency, consistent phase and the same positive and negative as the sensing signal emitted by the fourth piezoelectric sensor; that is, the driving signals A, B, C, and D are respectively amplified signals of the sensing signals of the first, second, third, and fourth piezoelectric sensors.

[0022] Compared with the prior art, the present invention adopts the above technical solution and has the following technical effects:

[0023] 1. The present invention has a compact structure and adopts a piezoelectric ceramic sheet "sandwich" structure, so that active excitation can induce vibrations of different modes of the structure, thereby being able to control vibrations of different modes. The present invention has a simple structure, great application value and a wide range of applications;

[0024] 2. The present invention makes full use of the direct piezoelectric effect and the inverse piezoelectric effect of piezoelectric materials to detect vibration types and actively suppress vibrations, and gives full play to the advantages of piezoelectric materials such as strong electromechanical coupling characteristics, fast response, light weight and anti-electromagnetic interference;

[0025] 3. The present invention adopts a two-partition form of a piezoelectric ceramic sheet, so that the present invention can apply a control signal separately, and can solve the problem of suppressing different vibration types. The present invention is powerful and reliable, and is suitable for application in solar wing structures. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] Figure 1 It is a schematic diagram of the structure of the present invention in cooperation with a solar wing;

[0027] Figure 2 It is a schematic diagram of the structure and polarization direction distribution of the piezoelectric actuation module in the present invention;

[0028] Figure 3 It is a schematic diagram of the excitation signal interface of the piezoelectric actuation module in the present invention;

[0029] Figure 4 It is a schematic diagram of the deformation type of the solar wing under disturbed vibration of the present invention;

[0030] Figure 5 It is a schematic diagram of the change of the sensing signal of the piezoelectric sensing module under the longitudinal vibration mode of the present invention;

[0031] Figure 6 It is a schematic diagram of the excitation signal application method and vibration suppression principle in the longitudinal vibration mode of the present invention;

[0032] Figure 7 It is a schematic diagram of the change of the sensing signal of the piezoelectric sensing module under the bending vibration mode of the present invention;

[0033] Figure 8 It is a schematic diagram of the excitation signal application method and vibration suppression principle in the bending vibration mode of the present invention;

[0034] Fig. 9 It is a schematic diagram of the change of the sensing signal of the piezoelectric sensing module of the present invention under the shaking head vibration mode;

[0035] Fig.10 It is a schematic diagram of the excitation signal application method and the vibration suppression principle in the head shaking vibration mode of the present invention.

[0036] In the figure, 1-solar wing, 2-piezoelectric actuation module, 3-piezoelectric sensor on the support rod, 4-connecting rod, 5-pre-tightening bolt. DETAILED DESCRIPTION

[0037] The technical solution of the present invention is further described in detail below in conjunction with the accompanying drawings:

[0038] The present invention can be implemented in many different forms and should not be considered to be limited to the embodiments described herein. On the contrary, these embodiments are provided to make this disclosure thorough and complete, and will fully express the scope of the present invention to those skilled in the art. In the accompanying drawings, components are enlarged for clarity.

[0039] like Figure 1 As shown, the present invention discloses a piezoelectric-driven solar wing active vibration suppression device, comprising a first piezoelectric vibration suppression module, a second piezoelectric vibration suppression module and a connecting rod;

[0040] The first piezoelectric vibration suppression module and the second piezoelectric vibration suppression module have the same structure, and both include a pre-tightening bolt, a pre-tightening rod, a support rod, a piezoelectric actuation module and a piezoelectric sensing module;

[0041] The pre-tightening bolt comprises a nut and a stud;

[0042] The support rod and the preload rod are regular prisms or cylinders with the same cross-sectional shape, a threaded hole matching the preload bolt is provided at the center of one end face of the support rod, and a countersunk through hole matching the preload bolt is provided at the center of one end face of the preload rod;

[0043] The piezoelectric actuation module includes N piezoelectric actuation units;

[0044] like Figure 2 As shown, the piezoelectric actuating unit comprises 8 double-partition piezoelectric ceramic sheets; the double-partition piezoelectric ceramic sheets are in the shape of regular polygons or circles, with a through hole in the center for the pre-tightening bolt to pass through, polarized along the thickness direction, and the polarization boundary line of the double-partition piezoelectric ceramic sheets is a straight line passing through the center of the circle; the double-partition piezoelectric ceramic sheets comprise a first partition and a second partition, and the polarization directions of the first partition and the second partition are opposite; the 8 double-partition piezoelectric ceramic sheets are stacked in sequence, wherein the polarization boundary lines of the first, second, fifth, and sixth double-partition piezoelectric ceramic sheets are coplanar, the polarization boundary lines of the third, fourth, seventh, and eighth double-partition piezoelectric ceramic sheets are coplanar, and the polarization boundary lines of the first and third double-partition piezoelectric ceramic sheets are perpendicular to each other; the polarization directions of the 2i-1th double-partition piezoelectric ceramic sheet and the 2ith double-partition piezoelectric ceramic sheet are opposite, i is an integer greater than or equal to 1 and less than or equal to 4; the polarization directions of the first and fifth double-partition piezoelectric ceramic sheets are the same, and the polarization directions of the third and seventh double-partition piezoelectric ceramic sheets are the same;

[0045] The N piezoelectric actuating units are stacked in sequence, and the polarization boundary lines of the first double-partitioned piezoelectric ceramic sheets of the N piezoelectric actuating units are coplanar and have the same polarization direction;

[0046] The stud of the pre-tightening bolt passes through the countersunk through hole of the pre-tightening rod, the through hole of each double-partitioned piezoelectric ceramic sheet of the N piezoelectric actuating units in the piezoelectric actuating module, and then is threadedly connected to the threaded hole of the support rod to press each double-partitioned piezoelectric ceramic sheet of the N piezoelectric actuating units in the piezoelectric actuating module;

[0047] The side wall of the support rod close to one end of the piezoelectric actuation module is evenly provided with first to fourth mounting grooves in the circumferential direction;

[0048] The piezoelectric sensing module includes first to fourth piezoelectric sensors; the first to fourth piezoelectric sensors are arranged in the first to fourth mounting grooves in a one-to-one correspondence, and are used to sense the magnitude of the force at their locations;

[0049] The first piezoelectric sensor is located on the angular bisector plane of the first partition of the first double-partition piezoelectric ceramic piece in the piezoelectric actuating unit, on the angular bisector plane of the first partition of the third double-partition piezoelectric ceramic piece in the piezoelectric actuating unit of the second piezoelectric sensor, on the angular bisector plane of the second partition of the first double-partition piezoelectric ceramic piece in the piezoelectric actuating unit of the third piezoelectric sensor, and on the angular bisector plane of the second partition of the third double-partition piezoelectric ceramic piece in the piezoelectric actuating unit of the fourth piezoelectric sensor;

[0050] One end of the support rod in the first piezoelectric vibration suppression module and the second piezoelectric vibration suppression module away from the piezoelectric actuation module is fixedly connected to the solar wing, so that the support rods of the first piezoelectric vibration suppression module and the second piezoelectric vibration suppression module are coplanar with the solar wing, and the second and fourth piezoelectric sensors in the first piezoelectric vibration suppression module are coplanar with the solar wing, and the second and fourth piezoelectric sensors in the second piezoelectric vibration suppression module are coplanar with the solar wing;

[0051] One end of the connecting rod is fixedly connected to the pre-tightening rod of the first piezoelectric vibration suppression module, and the other end is fixedly connected to the pre-tightening rod of the second piezoelectric vibration suppression module, and the connecting rod is connected to the spacecraft through a bracket; the pre-tightening rods of the first piezoelectric vibration suppression module and the second piezoelectric vibration suppression module are symmetrical about the mid-section of the connecting rod, and the pre-tightening rods of the first piezoelectric vibration suppression module and the second piezoelectric vibration suppression module are not parallel to each other.

[0052] The present invention also discloses a working method of the piezoelectric driven solar wing active vibration suppression device, comprising the following steps:

[0053] For each piezoelectric actuating unit in the first piezoelectric vibration suppression module and the second piezoelectric vibration suppression module, the upper end surfaces of the two partitions of the first, third, fifth and seventh double-partition piezoelectric ceramic pieces are grounded, the lower end surfaces of the two partitions of the second, fourth, sixth and eighth double-partition piezoelectric ceramic pieces are grounded, the lower end surfaces of the first partitions of the first and fifth double-partition piezoelectric ceramic pieces are connected to the driving signal A, the upper end surfaces of the first partitions of the second and sixth double-partition piezoelectric ceramic pieces are connected to the driving signal A, the lower end surfaces of the second partitions of the first and fifth double-partition piezoelectric ceramic pieces are connected to the driving signal B, the upper end surfaces of the second partitions of the second and sixth double-partition piezoelectric ceramic pieces are connected to the driving signal B, the lower end surfaces of the first partitions of the third and seventh double-partition piezoelectric ceramic pieces are connected to the driving signal C, the upper end surfaces of the first partitions of the fourth and eighth double-partition piezoelectric ceramic pieces are connected to the driving signal C, the lower end surfaces of the second partitions of the third and seventh double-partition piezoelectric ceramic pieces are connected to the driving signal D, and the upper end surfaces of the second partitions of the fourth and eighth double-partition piezoelectric ceramic pieces are connected to the driving signal D. Figure 3 As shown;

[0054] The driving signal A has the same frequency, consistent phase and the same positive and negative as the sensing signal emitted by the first piezoelectric sensor; the driving signal B has the same frequency, consistent phase and the opposite positive and negative as the sensing signal emitted by the second piezoelectric sensor; the driving signal C has the same frequency, consistent phase and the opposite positive and negative as the sensing signal emitted by the third piezoelectric sensor; the driving signal D has the same frequency, consistent phase and the same positive and negative as the sensing signal emitted by the fourth piezoelectric sensor; that is, the driving signals A, B, C, and D are respectively amplified signals of the sensing signals of the first, second, third, and fourth piezoelectric sensors.

[0055] like Figure 4 As shown, the disturbed vibration types of the solar wing that are most easily excited are longitudinal vibration, bending vibration and the shaking motion of the solar wing. When the piezoelectric sensing module sends out a sensing signal, it indicates that the solar wing structure is vibrating mechanically. Whether it is the longitudinal vibration of the solar wing, the bending vibration of the solar wing structure, or the shaking motion of the solar wing, at this time, A, B, C and D driving signals are given respectively; the piezoelectric actuation module is stimulated by the driving signal to generate an excitation vibration, and the excitation vibration has the same frequency and phase as the disturbed vibration of the structure, and the direction is opposite, which has the effect of vibration suppression, and the first round of vibration suppression is performed; the first round of vibration suppression ends with the end of the piezoelectric sensing signal, that is, when the excitation vibration and the disturbed vibration are completely offset, the support rod reaches a force balance state, the first round of vibration suppression ends, the excitation signal is zero, and the piezoelectric actuation module has no excitation vibration;

[0056] If the piezoelectric sensor does not send out a sensing signal after the first round of vibration suppression, it means that the disturbed vibration of the structure disappears or is reduced to the point where it cannot generate a sensing signal after the first round of vibration suppression, and the vibration suppression is completed at this time;

[0057] If the piezoelectric sensor sends out a sensing signal again after the first round of vibration suppression, it means that the disturbance of the structure is still continuing and the structure is still experiencing disturbed vibration; at this time, a second round of vibration suppression is carried out, and drive signals A, B, C and D are given respectively; the piezoelectric actuator module generates excitation vibration again to suppress the disturbed vibration of the structure; when the piezoelectric sensing signal is zero again, the excitation signal is zero, the excitation vibration ends, and the second round of vibration suppression is completed; then, based on whether the sensing signal occurs or not, it is determined whether to repeat the vibration suppression.

[0058] The piezoelectric-driven solar wing active vibration suppression device can suppress longitudinal vibration, bending vibration and head shaking vibration, and is not limited by the order of the mode. The specific vibration types are described in detail below:

[0059] 1) When the sensing signals of the first, second, third and fourth piezoelectric sensors in the first and second piezoelectric vibration suppression modules have the same positive and negative, the same frequency, the same phase and the same peak value, it means that the support rod vibrates longitudinally and the solar wing is disturbed to produce longitudinal vibration, such as Figure 5 As shown. At this time, A, B, C and D driving signals are given to the first and second piezoelectric vibration suppression modules respectively, and the first piezoelectric vibration suppression module and the second piezoelectric vibration suppression module are excited by the driving signals to generate excited longitudinal vibrations. When the solar wing is disturbed by longitudinal vibrations that cause the entire structure and its support rods to axially extend, the excited vibrations generated by the first piezoelectric vibration suppression module and the second piezoelectric vibration suppression module will cause the support rods to axially shorten, and the displacements of the two vibrations will cancel each other out, thus achieving a vibration suppression effect; when the solar wing is disturbed by vibrations that cause the entire structure and its support rods to axially shorten, the excited vibrations generated by the first piezoelectric vibration suppression module and the second piezoelectric vibration suppression module will cause the support rods to axially extend, and the displacements of the two vibrations will cancel each other out, thus achieving a vibration suppression effect as well, as shown. Figure 6 shown.

[0060] 2) When the sensing signals of the piezoelectric sensors are as follows, the sensing signals of the first piezoelectric sensor in the first piezoelectric vibration suppression module and the third piezoelectric sensor in the second piezoelectric vibration suppression module have the same positive and negative, the same frequency, the same phase and the same peak value, and the sensing signals of the third piezoelectric sensor in the first piezoelectric vibration suppression module and the first piezoelectric sensor in the second piezoelectric vibration suppression module have the same positive and negative, the same frequency, the same phase and the same peak value, and at the same time, there is no obvious sensing signal from other piezoelectric sensors, it means that the support rod has bending vibration, such as Figure 7As shown, the solar wing is disturbed and produces longitudinal vibration. At this time, the first and second piezoelectric vibration suppression modules are given A and C driving signals respectively, and the B and D driving signals are zero. The first piezoelectric vibration suppression module and the second piezoelectric vibration suppression module are excited by the driving signal to produce excited bending vibration. When the support rod of the first piezoelectric vibration suppression module bends to the left within the plane of the solar wing, and the support rod of the second piezoelectric vibration suppression module bends to the right within the plane of the solar wing, the first piezoelectric vibration suppression module is excited by the driving signal to bend to the right, and the second piezoelectric vibration suppression module is excited to bend to the left, and the displacement of the disturbed vibration deformation and the exciting vibration deformation is offset, thereby achieving a vibration suppression effect; when the support rod of the first piezoelectric vibration suppression module bends to the right within the plane of the solar wing, and the support rod of the second piezoelectric vibration suppression module bends to the left within the plane of the solar wing, the first piezoelectric vibration suppression module is excited by the driving signal to bend to the left, and the second piezoelectric vibration suppression module is excited to bend to the right, and the displacement of the disturbed vibration deformation and the exciting vibration deformation is offset, thereby also achieving a vibration suppression effect. Figure 8 shown.

[0061] 3) When the sensing signals of the piezoelectric sensors are as follows, the sensing signals of the first piezoelectric sensor in the first piezoelectric vibration suppression module and the first piezoelectric sensor in the second piezoelectric vibration suppression module have the same positive and negative, the same frequency, the same phase, but the peak values ​​are not equal, and the sensing signals of the third piezoelectric sensor in the first piezoelectric vibration suppression module and the third piezoelectric sensor in the second piezoelectric vibration suppression module have the same positive and negative, the same frequency, the same phase, but the peak values ​​are not equal, and at the same time, there is no obvious sensing signal from other piezoelectric sensors, it means that the support rod is bending and vibrating, and the solar wing is being disturbed to produce bending vibration in the plane. At this time, the first and second piezoelectric vibration suppression modules are given A and C driving signals respectively, and the B and D driving signals are zero. The first piezoelectric vibration suppression module and the second piezoelectric vibration suppression module are excited by the driving signals to produce excited bending vibration. When the support rods of the first and second piezoelectric vibration suppression modules are bent to the left within the plane of the solar wing, the first and second piezoelectric vibration suppression modules are excited by the driving signal to produce bending deformation to the right, and the displacement of the disturbed vibration deformation and the exciting vibration deformation offset each other, thereby achieving a vibration suppression effect; when the support rods of the first and second piezoelectric vibration suppression modules are bent to the right within the plane of the solar wing, the first and second piezoelectric vibration suppression modules are excited by the driving signal to produce bending deformation to the left, and the displacement of the disturbed vibration deformation and the exciting vibration deformation offset each other, thereby also achieving a vibration suppression effect.

[0062] 4) When the sensing signals of the piezoelectric sensors are as follows, the sensing signals of the second piezoelectric sensor in the first piezoelectric vibration suppression module and the second piezoelectric sensor in the second piezoelectric vibration suppression module are of the same positive and negative, the same frequency, the same phase and the same peak value, and the sensing signals of the fourth piezoelectric sensor in the first piezoelectric vibration suppression module and the fourth piezoelectric sensor in the second piezoelectric vibration suppression module are of the same positive and negative, the same frequency, the same phase and the same peak value, and at the same time, when there is no obvious sensing signal from other piezoelectric sensors, it means that the support rod is undergoing bending vibration, and the solar wing is being disturbed to produce bending vibration in the normal direction. At this time, the first and second piezoelectric vibration suppression modules are given B and D driving signals respectively, and the A and C driving signals are zero. The first piezoelectric vibration suppression module and the second piezoelectric vibration suppression module are excited by the driving signals to produce excited bending vibration in the normal direction of the solar wing. When the support rods of the first and second piezoelectric vibration suppression modules undergo bending deformation in the positive direction of the normal line of the solar wing plane, the first and second piezoelectric vibration suppression modules are excited by the driving signal to generate bending deformation in the negative direction of the normal line of the solar wing plane, and the displacement of the disturbed vibration deformation and the exciting vibration deformation offset each other, thereby achieving a vibration suppression effect; when the support rods of the first and second piezoelectric vibration suppression modules undergo bending deformation in the negative direction of the normal line of the solar wing plane, the first and second piezoelectric vibration suppression modules are excited by the driving signal to generate bending deformation in the positive direction of the normal line of the solar wing plane, and the displacement of the disturbed vibration deformation and the exciting vibration deformation offset each other, thereby also achieving a vibration suppression effect.

[0063] 5) When the sensing signals of the piezoelectric sensors are as follows, the sensing signals of the second piezoelectric sensor in the first piezoelectric vibration suppression module and the fourth piezoelectric sensor in the second piezoelectric vibration suppression module are of the same positive and negative, the same frequency, the same phase and the same peak value, and the sensing signals of the fourth piezoelectric sensor in the first piezoelectric vibration suppression module and the second piezoelectric sensor in the second piezoelectric vibration suppression module are of the same positive and negative, the same frequency, the same phase and the same peak value, and when there is no obvious sensing signal from other piezoelectric sensors, it means that the support rod is in bending vibration, and the solar wing is being disturbed to produce axial torsional vibration. At this time, the first and second piezoelectric vibration suppression modules are given B and D driving signals respectively, and the A and C driving signals are zero. The first piezoelectric vibration suppression module and the second piezoelectric vibration suppression module are excited by the driving signals to produce the excited bending vibration in the normal direction of the solar wing plane. When the support rod of the first piezoelectric vibration suppression module bends in the positive direction of the normal line of the solar wing plane, and the support rod of the second piezoelectric vibration suppression module bends in the negative direction of the normal line of the solar wing plane, the first piezoelectric vibration suppression module is excited by the driving signal to produce a bending deformation in the negative direction of the normal line of the solar wing plane, and the second piezoelectric vibration suppression module is excited by the driving signal to produce a bending deformation in the positive direction of the normal line of the solar wing plane. The displacement of the disturbed vibration deformation and the exciting vibration deformation offset each other, thereby achieving a vibration suppression effect. The same applies to the opposite direction, which also achieves a vibration suppression effect.

[0064] 6) When the sensing signal of the piezoelectric sensor is as follows, when the phases of the sensing signals generated by the first, second, third and fourth piezoelectric sensors in the first and second piezoelectric vibration suppression modules differ by π / 2 respectively, it means that the support rod vibrates in the shaking motion mode, such as Fig. 9 As shown, the solar wing is being disturbed to produce vibrations in the shaking motion mode. At this time, the first and second piezoelectric vibration suppression modules are given A, B, C and D driving signals respectively, and the first piezoelectric vibration suppression module and the second piezoelectric vibration suppression module are excited by the driving signals to produce an excited shaking motion. The vibration suppression principle is similar to the suppression principle of bending vibration, but the excitation timing differs by π / 2, which plays a role in suppressing the vibration of the shaking motion mode. Fig.10 shown.

[0065] The present invention adopts a piezoelectric sandwich structure and utilizes the inverse piezoelectric effect of piezoelectric materials to generate excitation vibration. By adjusting the excitation signal, the excitation vibration can be adjusted to the same frequency, the same phase and the opposite displacement as the disturbed vibration, thereby playing a vibration suppression role. At the same time, the vibrations of different modes generated by the disturbance of the solar wing can be effectively suppressed by the present invention. The present invention has the advantages of a wide range of applications, good vibration control effect, strong versatility, etc., and has broad application prospects.

[0066] It will be understood by those skilled in the art that, unless otherwise defined, all terms (including technical and scientific terms) used herein have the same meaning as generally understood by those skilled in the art in the art to which the present invention belongs. It should also be understood that terms such as those defined in common dictionaries should be understood to have meanings consistent with the meanings in the context of the prior art, and will not be interpreted with idealized or overly formal meanings unless defined as herein.

[0067] The specific implementation methods described above further illustrate the objectives, technical solutions and beneficial effects of the present invention in detail. It should be understood that the above description is only a specific implementation method of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the scope of protection of the present invention.

Claims

1. A piezoelectric-driven solar wing active vibration suppression device, characterized in that: It comprises a first piezoelectric vibration suppression module, a second piezoelectric vibration suppression module and a connecting rod; The first piezoelectric vibration suppression module and the second piezoelectric vibration suppression module have the same structure, and both include a pre-tightening bolt, a pre-tightening rod, a support rod, a piezoelectric actuation module and a piezoelectric sensing module; The pre-tightening bolt comprises a nut and a stud; The support rod and the preload rod are regular prisms or cylinders with the same cross-sectional shape, a threaded hole matching the preload bolt is provided at the center of one end face of the support rod, and a countersunk through hole matching the preload bolt is provided at the center of one end face of the preload rod; The piezoelectric actuation module includes N piezoelectric actuation units; The piezoelectric actuating unit comprises 8 double-partition piezoelectric ceramic sheets; the double-partition piezoelectric ceramic sheets are in the shape of a regular polygon or a circle, with a through hole in the center for the pre-tightening bolt to pass through, polarized along the thickness direction, and the polarization boundary line of the double-partition piezoelectric ceramic sheets is a straight line passing through the center of the circle; the double-partition piezoelectric ceramic sheets comprise a first partition and a second partition, and the polarization directions of the first partition and the second partition are opposite; the 8 double-partition piezoelectric ceramic sheets are stacked in sequence, wherein the polarization boundary lines of the first, second, fifth, and sixth double-partition piezoelectric ceramic sheets are coplanar, the polarization boundary lines of the third, fourth, seventh, and eighth double-partition piezoelectric ceramic sheets are coplanar, and the polarization boundary lines of the first and third double-partition piezoelectric ceramic sheets are perpendicular to each other; the polarization directions of the 2i-1th double-partition piezoelectric ceramic sheet and the 2ith double-partition piezoelectric ceramic sheet are opposite, i is an integer greater than or equal to 1 and less than or equal to 4; the polarization directions of the first and fifth double-partition piezoelectric ceramic sheets are the same, and the polarization directions of the third and seventh double-partition piezoelectric ceramic sheets are the same; The N piezoelectric actuating units are stacked in sequence, and the polarization boundary lines of the first double-partitioned piezoelectric ceramic sheets of the N piezoelectric actuating units are coplanar and have the same polarization direction; The stud of the pre-tightening bolt passes through the countersunk through hole of the pre-tightening rod, the through hole of each double-partitioned piezoelectric ceramic sheet of the N piezoelectric actuating units in the piezoelectric actuating module, and then is threadedly connected to the threaded hole of the support rod to press each double-partitioned piezoelectric ceramic sheet of the N piezoelectric actuating units in the piezoelectric actuating module; The side wall of the support rod close to one end of the piezoelectric actuation module is evenly provided with first to fourth mounting grooves in the circumferential direction; The piezoelectric sensing module includes first to fourth piezoelectric sensors; the first to fourth piezoelectric sensors are arranged in the first to fourth mounting grooves in a one-to-one correspondence, and are used to sense the magnitude of the force at their locations; The first piezoelectric sensor is located on the angular bisector plane of the first partition of the first double-partition piezoelectric ceramic piece in the piezoelectric actuating unit, on the angular bisector plane of the first partition of the third double-partition piezoelectric ceramic piece in the piezoelectric actuating unit of the second piezoelectric sensor, on the angular bisector plane of the second partition of the first double-partition piezoelectric ceramic piece in the piezoelectric actuating unit of the third piezoelectric sensor, and on the angular bisector plane of the second partition of the third double-partition piezoelectric ceramic piece in the piezoelectric actuating unit of the fourth piezoelectric sensor; One end of the support rod in the first piezoelectric vibration suppression module and the second piezoelectric vibration suppression module away from the piezoelectric actuation module is fixedly connected to the solar wing, so that the support rods of the first piezoelectric vibration suppression module and the second piezoelectric vibration suppression module are coplanar with the solar wing, and the second and fourth piezoelectric sensors in the first piezoelectric vibration suppression module are coplanar with the solar wing, and the second and fourth piezoelectric sensors in the second piezoelectric vibration suppression module are coplanar with the solar wing; One end of the connecting rod is fixedly connected to the pre-tightening rod of the first piezoelectric vibration suppression module, and the other end is fixedly connected to the pre-tightening rod of the second piezoelectric vibration suppression module, and the connecting rod is connected to the spacecraft through a bracket; the pre-tightening rods of the first piezoelectric vibration suppression module and the second piezoelectric vibration suppression module are symmetrical about the mid-section of the connecting rod, and the pre-tightening rods of the first piezoelectric vibration suppression module and the second piezoelectric vibration suppression module are not parallel to each other.

2. The working method of the piezoelectric driven solar wing active vibration suppression device according to claim 1 is characterized in that: The following steps are involved: For each piezoelectric actuating unit in the first piezoelectric vibration suppression module and the second piezoelectric vibration suppression module, the upper end surfaces of the two partitions of the first, third, fifth and seventh double-partition piezoelectric ceramic pieces are grounded, the lower end surfaces of the two partitions of the second, fourth, sixth and eighth double-partition piezoelectric ceramic pieces are grounded, the lower end surfaces of the first partitions of the first and fifth double-partition piezoelectric ceramic pieces are connected to the driving signal A, the upper end surfaces of the first partitions of the second and sixth double-partition piezoelectric ceramic pieces are connected to the driving signal A, the lower end surfaces of the second partitions of the first and fifth double-partition piezoelectric ceramic pieces are connected to the driving signal B, the upper end surfaces of the second partitions of the second and sixth double-partition piezoelectric ceramic pieces are connected to the driving signal B, the lower end surfaces of the first partitions of the third and seventh double-partition piezoelectric ceramic pieces are connected to the driving signal C, the upper end surfaces of the first partitions of the fourth and eighth double-partition piezoelectric ceramic pieces are connected to the driving signal C, the lower end surfaces of the second partitions of the third and seventh double-partition piezoelectric ceramic pieces are connected to the driving signal D, and the upper end surfaces of the second partitions of the fourth and eighth double-partition piezoelectric ceramic pieces are connected to the driving signal D; The driving signal A has the same frequency, consistent phase and the same positive and negative as the sensing signal emitted by the first piezoelectric sensor; the driving signal B has the same frequency, consistent phase and the opposite positive and negative as the sensing signal emitted by the second piezoelectric sensor; the driving signal C has the same frequency, consistent phase and the opposite positive and negative as the sensing signal emitted by the third piezoelectric sensor; the driving signal D has the same frequency, consistent phase and the same positive and negative as the sensing signal emitted by the fourth piezoelectric sensor; that is, the driving signals A, B, C, and D are respectively amplified signals of the sensing signals of the first, second, third, and fourth piezoelectric sensors.

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