Self-powered autonomous vibration suppression device for large flexible solar panel

Abstract

The utility model provides a self-powered autonomous vibration suppression device for a large flexible solar panel, and belongs to the field of spacecraft structures and vibration control. The problem that when the size of a sailboard is large, multi-channel signal collection and power supply circuit design greatly consume resources such as satellite power and control interfaces is solved. The device comprises a flexible solar panel, a bidirectional piezoelectric actuator, a piezoelectric fiber plate, mounting bases, a battery and a substrate, the mounting bases are mounted at two ends of the substrate, the bidirectional piezoelectric actuator is mounted between the two mounting bases, the battery is mounted on the outer side of the mounting base, the flexible solar panel is mounted on the outer side of the bidirectional piezoelectric actuator, and the piezoelectric fiber plate is mounted on the outer side of the bidirectional piezoelectric actuator. And the piezoelectric fiber plate is arranged above the substrate. The vibration suppression device is mainly used for vibration suppression of large flexible solar panels.

Description

TECHNICAL FIELD

[0001] The utility model belongs to the field of spacecraft structure and vibration control, especially relates to a kind of self-powered autonomous vibration suppression device for large flexible solar panel. BACKGROUND

[0002] With the development of satellite industry, the need of high energy of large-power consumption communication load and SAR radar imaging load, the size of satellite solar panel is more and more huge, the size requirement of solar panel has reached dozens of square meters or even hundreds of square meters, the flexible vibration suppression of large flexible panel becomes 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 means is still to carry out 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, so as to avoid exciting the structure vibration, the problem of this method is that when the panel size is very large, the hinge is more, and the base frequency is low, the ground cannot effectively carry out 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 at the same time, it can also be used as an actuator to generate force to offset the disturbance torque generated when the panel vibrates, however, the problem of this method is that all piezoelectric actuators arranged on the panel need power supply and control of single machine in the satellite, when the panel size is large, multi-channel signal acquisition and power supply line design consume a lot of satellite power and control interface resources. UTILITY MODEL CONTENTS

[0005] Therefore, the utility model aims at providing a kind of self-powered autonomous vibration suppression device for large flexible solar panel to solve the problem that all piezoelectric actuators arranged on the panel need power supply and control of single machine in the satellite, when the panel size is large, multi-channel signal acquisition and power supply line design consume a lot of satellite power and control interface resources.

[0006] To achieve the above purpose, the utility model adopts the following technical scheme:

[0007] A kind of self-powered autonomous vibration suppression device for large flexible solar panel, including flexible solar panel, bidirectional piezoelectric actuator, piezoelectric fiber sheet, mounting base, battery and substrate, the both ends of the substrate are equipped with mounting base, the bidirectional piezoelectric actuator is installed between two mounting bases, the battery is installed on the outside of mounting base, the flexible solar panel is installed on the outside of bidirectional piezoelectric actuator, and the piezoelectric fiber sheet is installed above the substrate.

[0008] Further, a piezoelectric strain sensor is installed below the substrate.

[0009] Further, both ends of the bidirectional piezoelectric actuator are connected with the mounting base through a spherical hinge.

[0010] Further, the spherical hinge is connected with the mounting base through a bolt.

[0011] Further, the bidirectional piezoelectric actuator comprises a first piezoelectric ceramic stack, a second piezoelectric ceramic stack, an expansion 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 expansion unit, one end of the second piezoelectric ceramic stack is connected with the expansion 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 outside of the expansion unit is connected with the spherical hinge through the connecting end cover.

[0012] Further, the connecting end faces of the first piezoelectric ceramic stack and the second piezoelectric ceramic stack and the expansion unit are all semispherical and are in contact with the spherical groove at the center of the expansion unit.

[0013] Further, the battery is fixed on the mounting base through a clamp.

[0014] Further, the substrate is connected with the large flexible solar sail through a bolt.

[0015] Compared with the prior art, the utility model has the advantages that:

[0016] 1. The utility model utilizes the advantage of being installed on the solar sail, adheres the flexible solar panel on the device, and effectively overcomes the problem of external power supply.

[0017] 2. The utility model utilizes the piezoelectric inverse effect to design a vibration energy recovery device, ensures the energy supply in the emergency situation of not facing the sun for a long time, and can inhibit the vibration of the large flexible sail.

[0018] 3. The utility model 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 sail on a large scale, has great engineering significance for improving control accuracy and ensuring the stability of the spacecraft. DRAWINGS

[0019] The drawings forming a part of this application provide further understanding of the present application, and the illustrative embodiments thereof, with their descriptions, serve to explain the application without implying any unnecessary limitation of the application. In the drawings:

[0020] Fig. 1 A structural schematic view of a self-powered autonomous vibration suppression device for a large flexible solar panel according to the present application is shown in the figure.

[0021] Fig. 2 A sectional view of a self-powered autonomous vibration suppression device for a large flexible solar panel according to the present application is shown in the figure.

[0022] In the figure:

[0023] 1 - flexible solar panel, 2 - bidirectional piezoelectric actuator, 3 - piezoelectric fiber sheet, 4 - clamp, 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 - housing, 205 - connecting end cover, 206 - housing end cover. DETAILED DESCRIPTION

[0024] The technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application. It should be noted that the embodiments in the present 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 present application, not all the embodiments.

[0025] Specific implementation 1: see Figs. 1-2 The present application provides a self-powered autonomous vibration suppression device for a large flexible solar panel, characterized in that it 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 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 base plate 8 is connected to the large flexible solar panel through bolts.

[0026] The autonomous vibration suppression device is installed on the large flexible solar sail, solar energy and structural strain energy are recovered through the flexible solar panel 1 and the piezoelectric fiber sheet 3 in the autonomous vibration suppression device, the flexible solar panel 1 converts the solar energy into electrical energy and stores the electrical energy in the battery 6 to supply power to the bidirectional piezoelectric actuator 2, when the sail is not pointed at 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 into electrical energy through the inverse piezoelectric effect and stores the electrical energy in the battery 6 to supply power to the bidirectional piezoelectric actuator 2, under the power supply of the battery 6, the bidirectional piezoelectric actuator 2 extends or shortens according to the local strain information collected from the large flexible solar sail, and generates an opposite force to suppress the deformation and vibration of the large flexible solar sail.

[0027] By virtue of the advantages of the installation on the solar sail, the external power supply problem can be effectively overcome by adhering the flexible solar panel 1 to the device, the vibration energy recovery device is designed by using the piezoelectric inverse effect, the energy supply in the emergency situation of long-term non-pointing at the sun is ensured, and the vibration of the large flexible sail can be suppressed, without the need for external power supply and on-board computer control, the device has high integration and autonomy, can be installed on a large flexible solar sail on a large scale, and has great engineering significance for improving control accuracy and ensuring spacecraft stability.

[0028] Specific embodiment 2: see Figs. 1-2 In this embodiment, the piezoelectric strain sensor 9 is installed below the substrate 8, and is used to collect local strain information on the large flexible solar sail, under the power supply of 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 sail, and generates an opposite force to suppress the deformation and vibration of the large flexible solar sail.

[0029] Specific embodiment 3: see Figs. 1-2The two ends of the bidirectional piezoelectric actuator 2 are connected to the mounting base 5 through the ball hinge 7, the bidirectional piezoelectric actuator 2 is connected to the mounting base 5 through the ball hinge 7, the ball hinge 7 is connected to the mounting base 5 through a bolt, the mounting base 5 is fixed to the large flexible solar panel, and the ball hinge 7 connection ensures that the bidirectional piezoelectric actuator 2 only bears axial force and does not bear bending moment and torque, thereby avoiding the bending of the bidirectional piezoelectric actuator 2 and ensuring that the actuator can normally stretch and retract.

[0030] Specific embodiment 4: see Figs. 1-2 The bidirectional piezoelectric actuator 2 includes a first piezoelectric ceramic stack 201, a second piezoelectric ceramic stack 202, a telescopic unit 203, a shell 204, a connecting end cover 205, and a shell end cover 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 inside of the shell 204, 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, the other end is connected to the shell end cover 206, the shell end cover 206 is connected to the shell 204, one end of the shell 204 away from the shell end cover 206 is connected to the ball hinge 7, the outer side of the telescopic unit 203 is connected to the ball hinge 7 through the connecting end cover 205, and the connecting end faces of the first piezoelectric ceramic stack 201 and the second piezoelectric ceramic stack 202 and the telescopic unit 203 are all semispherical and are in contact with the spherical groove at the center of the telescopic unit 203.

[0031] One end of the first piezoelectric ceramic stack 201 is a plane and is installed in the groove at the bottom of the shell 204, the other end is semispherical and is in contact with the spherical groove at the center of the telescopic unit 203, one end of the second piezoelectric ceramic stack 202 is a plane and is installed in the mounting groove of the shell end cover 206, the other end is semispherical and is in contact with the spherical groove at the center of the telescopic unit 203, the shell end cover 206 is fixed to the shell 204 through threads, two holes are formed in the shell end cover 205 and have the same diameter as the two rods of the telescopic unit 203, the holes in the shell end cover 205 are matched with the rods of the telescopic unit 203, so that the telescopic unit 203 can only move linearly along the axial direction of the bidirectional actuator 2, when the first piezoelectric ceramic stack 201 is controlled to elongate, the telescopic unit 203 is pushed out, so that the bidirectional actuator 2 is elongated, on the contrary, when the second piezoelectric ceramic stack 202 is controlled to elongate, the telescopic unit 203 is retracted, so that the bidirectional actuator 2 is shortened, the second piezoelectric ceramic stack 201 and the second piezoelectric ceramic stack 202 are in contact with the telescopic unit 203 through the spherical surface, so that the telescopic unit only bears axial force and does not bear bending moment, thereby preventing the telescopic unit from being stuck.

[0032] The above disclosed embodiments of the present application are only used for helping to explain the present application. The embodiments do not describe all the details and do not limit the present application to the described embodiments. According to the content of the present application, many modifications and changes can be made. The present application selects and specifically describes these embodiments in order to better explain the principles and practical applications of the present application, so that the skilled in the art can well understand and utilize the present application.

Claims

1. A self-powered autonomous vibration suppression device for large flexible solar panels, characterized by: The application relates to a flexible solar panel (1), a bidirectional piezoelectric actuator (2), a piezoelectric fiber sheet (3), a mounting base (5), a battery (6) and a base plate (8), both ends of the base plate (8) are provided with the mounting base (5), the bidirectional piezoelectric actuator (2) is arranged between the two mounting bases (5), the battery (6) is arranged outside the mounting base (5), the flexible solar panel (1) is arranged outside the bidirectional piezoelectric actuator (2), and the piezoelectric fiber sheet (3) is arranged above the base plate (8).

2. A self-powered autonomous vibration suppression device for large flexible solar panels according to claim 1, characterized in that: A piezoelectric strain sensor (9) is arranged below the base plate (8).

3. The self-powered autonomous vibration suppression device for large flexible solar panels of claim 1, wherein: Both ends of the bidirectional piezoelectric actuator (2) are connected with the mounting base (5) through a spherical hinge (7).

4. The self-powered autonomous vibration suppression device for large flexible solar panels of claim 3, wherein: The spherical hinge (7) is connected with the mounting base (5) through a bolt.

5. The self-powered autonomous vibration suppression device for large flexible solar panels of claim 3, wherein: The bidirectional piezoelectric actuator (2) comprises a first piezoelectric ceramic stack (201), a second piezoelectric ceramic stack (202), a telescopic unit (203), a shell (204), a connecting end cover (205) and a shell end cover (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 with the inside of the shell (204), the other end is connected with the telescopic unit (203), one end of the second piezoelectric ceramic stack (202) is connected with the telescopic unit (203), the other end is connected with the shell end cover (206), the shell end cover (206) is connected with the shell (204), one end of the shell (204) away from the shell end cover (206) is connected with the spherical hinge (7), and the outside of the telescopic unit (203) is connected with the spherical hinge (7) through the connecting end cover (205).

6. A self-powered autonomous vibration suppression device for large flexible solar panels according to claim 5, characterized in that: The connecting end faces of the first piezoelectric ceramic stack (201) and the second piezoelectric ceramic stack (202) and the telescopic unit (203) are all semispherical and are in contact with a spherical groove at the center of the telescopic unit (203).

7. The self-powered autonomous vibration suppression device for large flexible solar panels of claim 1, wherein: The battery (6) is fixed on the mounting base (5) through a clamp (4).

8. The self-powered autonomous vibration suppression device for large flexible solar panels of claim 1, wherein: The base plate (8) is connected with a large flexible solar panel through a bolt.

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