A self-powered autonomous vibration suppression method for large flexible solar panels

Abstract

The application provides a self-powered autonomous vibration suppression method for a large flexible solar panel, and belongs to the field of spacecraft structures and vibration control. The method solves the problem that, in the prior art, when the size of the solar panel is large, the multi-channel signal acquisition and power supply line design consume a large amount of satellite power and control interface resources. The method comprises the following steps: installing an autonomous vibration suppression device on a large flexible solar panel; converting solar energy into electric energy and storing the electric energy in a battery for power supply; converting structural strain energy generated by vibration of the large flexible solar panel into electric energy and storing the electric energy in the battery through the inverse piezoelectric effect of a piezoelectric fiber sheet; and supplying power to a bidirectional piezoelectric actuator; under the power supply of the battery, the bidirectional piezoelectric actuator suppresses deformation and vibration of the large flexible solar panel according to local strain information on the large flexible solar panel. The method is mainly used for large flexible solar panels.

Description

TECHNICAL FIELD

[0001] The present application belongs to the field of spacecraft structure and vibration control, and particularly relates to a self-powered autonomous vibration suppression method for a large flexible solar panel. BACKGROUND

[0002] With the development of the satellite industry, the need for high energy of the communication load and SAR radar imaging load with large power consumption, the size of the satellite solar panel is increasingly large, and the size requirement of the solar panel has reached dozens of square meters or even hundreds of square meters. The flexible vibration suppression of the large flexible panel has become a complex engineering problem, and improper suppression can cause the vibration of the whole satellite and affect the stability of the satellite.

[0003] The existing main method is still to perform modal analysis on the panel on the ground, to design satellite control parameters according to the structure frequency, to make the control system avoid the structure resonance frequency, and to avoid exciting the structure vibration. This method faces the problem that when the panel size is very large, the hinge is more, and the base frequency is low, the ground cannot effectively perform physical test to obtain accurate structure characteristic information, and when the design parameters do not match the actual situation, the structure vibration problem is easily caused in orbit.

[0004] With the popularization and application of intelligent materials, the piezoelectric effect of piezoelectric ceramics and other materials can be used as a sensor to collect the vibration information of the panel, and can also be used as an actuator to generate force to offset the disturbance torque generated when the panel vibrates. However, this method has the problem that all piezoelectric actuators arranged on the panel need power supply and control of the single machine in the satellite, and when the panel size is large, the multi-channel signal acquisition and power supply line design consume a lot of satellite power and control interface resources. SUMMARY

[0005] Therefore, the present application aims to provide a self-powered autonomous vibration suppression method for a large flexible solar panel, so as to solve the problem in the prior art that all piezoelectric actuators arranged on the panel need power supply and control of the single machine in the satellite, and when the panel size is large, the multi-channel signal acquisition and power supply line design consume a lot of satellite power and control interface resources.

[0006] To achieve the above-mentioned purpose, the present application adopts the following technical scheme:

[0007] A self-powered autonomous vibration suppression method for a large flexible solar panel, comprising the following steps:

[0008] Step 1: installing an autonomous vibration suppression device on the large flexible solar panel;

[0009] Step 2: recovering solar energy and structure strain energy through the flexible solar panel and piezoelectric fiber sheet in the autonomous vibration suppression device;

[0010] Step 3: The flexible solar panel converts solar energy into electrical energy stored in the battery to power the bidirectional piezoelectric actuator in the self-contained vibration suppression device;

[0011] Step 4: When the sailboard is not facing the sun for a long time, the piezoelectric fiber sheet converts the structural strain energy generated by the vibration of the large flexible solar sail into electrical energy through the inverse piezoelectric effect and stores it in the battery to power the bidirectional piezoelectric actuator.

[0012] Step 5: Under the power of the battery, the bidirectional piezoelectric actuator extends or shortens according to the local strain information on the large flexible solar sail to generate an opposite force, suppressing the deformation and vibration of the large flexible solar sail.

[0013] Further, the self-contained vibration suppression device further comprises a mounting base and a base plate, both ends of the base plate are provided with a mounting base, the bidirectional piezoelectric actuator is installed between the two mounting bases, the battery is installed outside the mounting base, the flexible solar panel is installed outside the bidirectional piezoelectric actuator, and the piezoelectric fiber sheet is installed above the base plate.

[0014] Further, a piezoelectric strain sensor is installed below the base plate, and the piezoelectric strain sensor is used to collect local strain information on the large flexible solar sail.

[0015] Further, both ends of the bidirectional piezoelectric actuator are connected with the mounting base through a spherical hinge.

[0016] Further, the bidirectional piezoelectric actuator comprises a first piezoelectric ceramic stack, a second piezoelectric ceramic stack, an extension unit, a shell, a connecting end cover and a shell end cover, the first piezoelectric ceramic stack and the second piezoelectric ceramic stack are symmetrically arranged, one end of the first piezoelectric ceramic stack is connected with the inside of the shell, the other end is connected with the extension unit, one end of the second piezoelectric ceramic stack is connected with the extension unit, the other end is connected with the shell end cover, the shell end cover is connected with the shell, one end of the shell away from the shell end cover is connected with the spherical hinge, and the outer side of the extension unit is connected with the spherical hinge through the connecting end cover.

[0017] Further, the connecting end faces of the first piezoelectric ceramic stack and the second piezoelectric ceramic stack and the extension unit are all semispherical and are in contact with the spherical groove at the center of the extension unit.

[0018] Further, the battery is fixed on the mounting base by a clamp.

[0019] Compared with the prior art, the beneficial effects of the present application are:

[0020] 1. The present application utilizes the advantages of the solar sail by adhering a flexible solar panel on the device, which can effectively overcome the problem of external power supply.

[0021] 2、The application uses the piezoelectric inverse effect to design a vibration energy recovery device, ensures the energy supply in the long-term emergency situation without the sun, and can suppress the vibration of the large flexible solar panel.

[0022] 3、The application does not need external power supply, and does not need on-board computer control, has high integration and autonomy, can be installed on a large flexible solar panel in a large scale, has great engineering significance for improving control precision and ensuring the stability of the spacecraft. BRIEF DESCRIPTION OF DRAWINGS

[0023] The drawings constituting a part of the application are used to provide further understanding of the application, the schematic embodiments of the application and the description thereof are used to explain the application, and do not constitute improper limitation on the application. In the drawings:

[0024] Fig. 1 It is a structural schematic view of the autonomous vibration suppression device described in the application.

[0025] Fig. 2 It is a sectional view of the autonomous vibration suppression device described in the application.

[0026] In the drawings:

[0027] 1-flexible solar panel, 2-bidirectional piezoelectric actuator, 3-piezoelectric fiber sheet, 4-clip, 5-mounting base, 6-battery, 7-spherical hinge, 8-base plate, 9-piezoelectric strain sensor, 201-first piezoelectric ceramic stack, 201-second piezoelectric ceramic stack, 203- telescopic unit, 204-outer shell, 205-connection end cover, 206-outer shell end cover. DETAILED DESCRIPTION

[0028] The technical solutions in the embodiments of the application will be clearly and completely described below with reference to the drawings in the embodiments of the application. It should be noted that the embodiments in the application and the features in the embodiments can be combined with each other without conflict, and the described embodiments are only part of the embodiments of the application, not all the embodiments.

[0029] Specific embodiment 1: see Figs. 1-2 This embodiment is described,

[0030] A self-powered autonomous vibration suppression method for a large flexible solar panel, which comprises the following steps:

[0031] Step 1: installing the autonomous vibration suppression device on the large flexible solar panel;

[0032] Step 2: recovering solar energy and structural strain energy through the flexible solar panel 1 and the piezoelectric fiber sheet 3 in the autonomous vibration suppression device;

[0033] Step 3: Flexible solar panel 1 converts solar energy into electrical energy stored in battery 6 to power bidirectional piezoelectric actuator 2 in the self-oscillation damping device;

[0034] Step 4: When the sail panel is not facing the sun for a long time, piezoelectric fiber sheet 3 converts the structural strain energy generated by the vibration of the large flexible solar sail into electrical energy through the inverse piezoelectric effect and stores it in battery 6 to power bidirectional piezoelectric actuator 2.

[0035] Step 5: Under the power of battery 6, bidirectional piezoelectric actuator 2 extends or shortens according to the local strain information collected from the large flexible solar sail, generating an opposite force to suppress the deformation and vibration of the large flexible solar sail.

[0036] Considering the characteristics of the large flexible solar sail, which is long-term facing the sun and prone to vibration, the device is provided with a flexible solar panel 1 and a piezoelectric fiber sheet 3 arranged to recover solar energy and structural strain energy, respectively. The flexible solar panel 1 is adhered to the outer shell 204 of the bidirectional piezoelectric actuator 2 to convert solar energy into electrical energy stored in battery 6 to power the bidirectional piezoelectric actuator 2. When the sail panel is not facing the sun for a long time, the piezoelectric fiber sheet 3 can convert the strain energy generated by the vibration of the large flexible solar sail into electrical energy through the inverse piezoelectric effect and store it in battery 6 to ensure the normal operation of the entire system. Under the power of battery 6, bidirectional piezoelectric actuator 2 extends or shortens according to the local strain information collected from the large flexible solar sail, generating an opposite force to suppress the deformation and vibration of the large flexible solar sail.

[0037] By taking advantage of the installation on the solar sail, the problem of external power supply can be effectively overcome by adhering a flexible solar panel 1 to the device. The vibration energy recovery device is designed using the inverse piezoelectric effect to ensure energy supply in emergency situations when the sail panel is not facing the sun for a long time, and to suppress the vibration of the large flexible sail panel without the need for external power supply and on-board computer control. The device has high integration and autonomy and can be installed on a large flexible solar sail on a large scale, which has great engineering significance in improving control accuracy and ensuring the stability of the spacecraft.

[0038] Specific implementation method 2: refer to Figs. 1-2 This implementation method, the self-oscillation damping device further comprises a mounting base 5 and a base plate 8, both ends of the base plate 8 are provided with a mounting base 5, the bidirectional piezoelectric actuator 2 is installed between the two mounting bases 5, the battery 6 is installed on the outside of the mounting base 5, the flexible solar panel 1 is installed on the outside of the bidirectional piezoelectric actuator 2, the piezoelectric fiber sheet 3 is installed above the base plate 8, and the battery 6 is fixed on the mounting base 5 by a clamp 4.

[0039] Specific implementation method 3: refer to Figs. 1-2To illustrate this embodiment, a piezoelectric strain sensor 9 is installed under the substrate 8. The piezoelectric strain sensor 9 is used to collect local strain information on the large flexible solar panel. When powered by the battery 6, the bidirectional piezoelectric actuator 2 extends or shortens according to the local strain information collected by the piezoelectric strain sensor 9 arranged parallel to the surface of the large flexible solar panel, generating a force in the opposite direction to suppress the deformation and vibration of the large flexible solar panel.

[0040] Specific implementation 4: See Figs. 1-2 To illustrate this embodiment, both ends of the bidirectional piezoelectric actuator 2 are connected to the mounting base 5 through a ball joint 7. The bidirectional piezoelectric actuator 2 is connected to the mounting base 5 through the ball joint 7, and the mounting base 5 is fixed to the large flexible solar sail panel. The ball 7 connection ensures that the bidirectional piezoelectric actuator 2 is only subjected to axial force but not bending moment and torque, thereby avoiding bending of the bidirectional piezoelectric actuator 2 and ensuring that the actuator can extend and retract normally.

[0041] Specific implementation 5: See Figs. 1-2 To illustrate this embodiment, the bidirectional piezoelectric actuator 2 includes a first piezoelectric ceramic stack 201, a second piezoelectric ceramic stack 202, a telescopic unit 203, a housing 204, a connecting end cap 205, and a housing end cap 206. The first piezoelectric ceramic stack 201 and the second piezoelectric ceramic stack 202 are symmetrically arranged. One end of the first piezoelectric ceramic stack 201 is connected to the interior of the housing 204, and the other end is connected to the telescopic unit 203. One end of the second piezoelectric ceramic stack 202 is connected to the telescopic unit 203, and the other end is connected to the housing end cap 206. The housing end cap 206 is connected to the housing 204. The end of the housing 204 away from the housing end cap 206 is connected to the ball joint 7. The outer side of the telescopic unit 203 is connected to the ball joint 7 via the connecting end cap 205. The end surfaces of the first piezoelectric ceramic stack 201 and the second piezoelectric ceramic stack 202 connected to the telescopic unit 203 are both hemispherical and both contact and cooperate with the spherical groove at the center of the telescopic unit 203.

[0042] One end of the first piezoelectric ceramic stack 201 is flat and installed in the bottom groove of the shell 204, and the other end face is hemispherical and contacts and cooperates with the spherical groove at the center of the telescopic unit 203. One end of the second piezoelectric ceramic stack 202 is flat and installed in the installation groove of the shell end cover 206, and the other end face is hemispherical and contacts and cooperates with the spherical groove at the center of the telescopic unit 203. The shell end cover 206 is fixed to the shell 204 by threads. Two holes are provided on the shell end cover 205, and the diameters are the same as the diameters of the two rods on the telescopic unit 203. The holes on the shell end cover 205 are aligned with the diameters of the two rods on the telescopic unit 203. The rod cooperates to ensure that the telescopic unit 203 can only perform linear motion along the axial direction of the bidirectional actuator 2. When the first piezoelectric ceramic stack 201 is extended under external control, the telescopic unit 203 is pushed out, thereby extending the bidirectional actuator 2. Conversely, when the second piezoelectric ceramic stack 202 is extended under external control, the telescopic unit 203 is retracted, thereby shortening the bidirectional actuator 2. The second piezoelectric ceramic stack 201 and the second piezoelectric ceramic stack 202 are in spherical contact with the telescopic unit 203, ensuring that the telescopic unit only bears axial force but not bending moment, thereby preventing the telescopic unit from getting stuck.

[0043] The specific embodiments of the present invention disclosed above are intended only to help illustrate the present invention. The specific embodiments do not describe all details in detail, nor do they limit the invention to the specific embodiments described. Numerous modifications and variations are possible based on the contents of this specification. These embodiments are selected and described in detail in this specification to better explain the principles and practical applications of the present invention, thereby enabling those skilled in the art to better understand and utilize the present invention.

Claims

1. A self-powered, autonomous vibration suppression method for a large flexible solar panel, characterized by: The invention comprises an autonomous vibration suppression device, wherein the autonomous vibration suppression device comprises a flexible solar panel (1), a bidirectional piezoelectric actuator (2), a piezoelectric fiber sheet (3), a mounting base (5), a battery (6) and a substrate (8), wherein both ends of the substrate (8) are mounted with mounting bases (5), the bidirectional piezoelectric actuator (2) is mounted between the two mounting bases (5), the battery (6) is mounted on the outside of the mounting base (5), the flexible solar panel (1) is mounted on the outside of the bidirectional piezoelectric actuator (2), the piezoelectric fiber sheet (3) is mounted above the substrate (8), and a piezoelectric strain sensor (9) is mounted below the substrate (8), wherein the piezoelectric strain sensor (9) is used to collect local strain information on the large flexible solar panel; The self-powered autonomous vibration suppression method comprises the following steps: Step 1: Install the autonomous vibration suppression device on the large flexible solar sail panel; Step 2: Recovering solar energy and structural strain energy through the flexible solar panel (1) and the piezoelectric fiber sheet (3) in the autonomous vibration suppression device; Step 3: The flexible solar panel (1) converts solar energy into electrical energy and stores it in the battery (6), which powers the bidirectional piezoelectric actuator (2) in the autonomous vibration suppression device; Step 4: When the sail panel is not aligned with the sun for a long time, the piezoelectric fiber sheet (3) converts the structural strain energy generated by the vibration of the large flexible solar sail panel into electrical energy through the inverse piezoelectric effect and stores it in the battery (6), which supplies power to the bidirectional piezoelectric actuator (2); Step 5: Under the power supply of the battery (6), the bidirectional piezoelectric actuator (2) extends or shortens according to the local strain information on the large flexible solar sail panel, generating forces in opposite directions to suppress the deformation and vibration of the large flexible solar sail panel.

2. The self-powered, autonomous vibration suppression method for a large flexible solar sail panel according to claim 1, characterized in that: Both ends of the bidirectional piezoelectric actuator (2) are connected to the mounting base (5) via a ball joint (7).

3. The self-powered, autonomous vibration suppression method for a large flexible solar panel according to claim 2, characterized in that: The bidirectional piezoelectric actuator (2) comprises a first piezoelectric ceramic stack (201), a second piezoelectric ceramic stack (202), a telescopic unit (203), a housing (204), a connecting end cover (205) and a housing end cover (206), wherein the first piezoelectric ceramic stack (201) and the second piezoelectric ceramic stack (202) are symmetrically arranged, one end of the first piezoelectric ceramic stack (201) is connected to the interior of the housing (204), and the other end is connected to the telescopic unit (203), one end of the second piezoelectric ceramic stack (202) is connected to the telescopic unit (203), and the other end is connected to the housing end cover (206), the housing end cover (206) is connected to the housing (204), one end of the housing (204) away from the housing end cover (206) is connected to the ball joint (7), and the outer side of the telescopic unit (203) is connected to the ball joint (7) via the connecting end cover (205).

4. The self-powered, autonomous vibration suppression method for a large flexible solar panel according to claim 3, characterized in that: The connecting end surfaces of the first piezoelectric ceramic stack (201) and the second piezoelectric ceramic stack (202) and the telescopic unit (203) are both hemispherical, and are in contact with and fit the spherical groove at the center of the telescopic unit (203).

5. The self-powered, autonomous vibration suppression method for a large flexible solar panel according to claim 1, characterized in that: The battery (6) is fixed on the mounting base (5) via a clamp (4).

6. The self-powered, autonomous vibration suppression method for a large flexible solar sail panel according to claim 2, characterized in that: The ball joint (7) is connected to the mounting base (5) via bolts.

7. The self-powered, autonomous vibration suppression method for a large flexible solar panel according to claim 1, characterized in that: The base plate (8) is connected to the large flexible solar sail panel via bolts.

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