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

Abstract

The invention 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 problem that in the prior art, 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. According to the method, an autonomous vibration suppression device is installed on a large flexible solar panel, the flexible solar panel converts solar energy into electric energy and stores the electric energy in a battery for power supply, and piezoelectric fiber sheets convert structural strain energy generated by vibration of the large flexible solar panel into electric energy and stores the electric energy in the battery through the inverse piezoelectric effect to supply power to a bidirectional piezoelectric actuator. Under the power supply of the battery, the bidirectional piezoelectric actuator inhibits the deformation and vibration of the large flexible solar panel according to the local strain information on the large flexible solar panel. The flexible solar panel is mainly used for large flexible solar panels.

Description

Technical Field

[0001] The invention belongs to the field of spacecraft structure and vibration control, and in particular relates to a self-powered autonomous vibration suppression method for a large flexible solar sail panel. Background Art

[0002] With the development of the satellite industry, high-power communication payloads and SAR radar imaging payloads require high energy, and the size of satellite solar panels has become increasingly large. The size requirement of solar panels has reached dozens or even hundreds of square meters. The flexible vibration suppression of large flexible panels has become a complex engineering problem. Improper suppression will cause vibration of the entire satellite and affect the stability of the satellite.

[0003] The main existing method is to conduct modal analysis on the sailboard on the ground, design satellite control parameters according to the structural frequency, so that the control system avoids the structural resonance frequency, thereby avoiding exciting structural vibration. The problem faced by this method is that when the sailboard is large in size, has many hinges, and has a low fundamental frequency, it is no longer possible to conduct effective physical experiments on the ground to obtain accurate structural characteristic information. When the design parameters do not match the actual ones, it is easy to cause structural vibration problems in orbit.

[0004] With the popularization and application of smart materials, the piezoelectric effect of materials such as piezoelectric ceramics can be used as sensors to collect vibration information of sailboards, and can also be used as actuators to generate force to offset the interference torque generated when the sailboard vibrates. However, the problem with this method is that all piezoelectric actuators arranged on the sailboard require power supply and control from a single unit on the satellite. When the sailboard is large in size, multi-channel signal acquisition and power supply line design consume a lot of resources such as satellite power and control interfaces. Summary of the invention

[0005] In view of this, the present invention aims to propose a self-powered autonomous vibration suppression method for large flexible solar panels, so as to solve the problem that all piezoelectric actuators arranged on the panels in the prior art need to be powered and controlled by a single unit on the satellite, and when the panels are large in size, multi-channel signal acquisition and power supply line design consume a great deal of resources such as satellite power and control interfaces.

[0006] To achieve the above object, the present invention adopts the following technical solutions:

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

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

[0009] Step 2: Recover solar energy and structural strain energy through flexible solar panels and piezoelectric fiber sheets in the autonomous vibration suppression device;

[0010] Step 3: The flexible solar panel converts solar energy into electrical energy and stores it in the battery, which powers the bidirectional piezoelectric actuator in the autonomous 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 sailboard into electrical energy through the inverse piezoelectric effect and stores it in the battery to power the bidirectional piezoelectric actuator;

[0012] Step 5: Under battery power supply, the bidirectional piezoelectric actuator extends or shortens according to the local strain information on the large flexible solar panel, generating forces in opposite directions to suppress the deformation and vibration of the large flexible solar panel.

[0013] Furthermore, the autonomous vibration suppression device also includes a mounting base and a substrate, the two ends of the substrate are equipped with mounting bases, the bidirectional piezoelectric actuator is installed between the two mounting bases, the battery is installed on the outside of the mounting base, the flexible solar panel is installed on the outside of the bidirectional piezoelectric actuator, and the piezoelectric fiber sheet is installed above the substrate.

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

[0015] Furthermore, both ends of the bidirectional piezoelectric actuator are connected to the mounting base through a ball joint.

[0016] Furthermore, the bidirectional piezoelectric actuator includes a first piezoelectric ceramic stack, a second piezoelectric ceramic stack, a telescopic 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 to the inside of the shell, and the other end is connected to the telescopic unit, one end of the second piezoelectric ceramic stack is connected to the telescopic unit, and the other end is connected to the shell end cover, the shell end cover is connected to the shell, the end of the shell away from the shell end cover is connected to the ball joint, and the outer side of the telescopic unit is connected to the ball joint through the connecting end cover.

[0017] Furthermore, the end surfaces of the first piezoelectric ceramic stack and the second piezoelectric ceramic stack connected to the telescopic unit are both hemispherical, and are in contact with and fit with the spherical groove at the center of the telescopic unit.

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

[0019] Compared with the prior art, the present invention has the following beneficial effects:

[0020] 1. The present invention takes advantage of the installation on the solar sail panel and can effectively overcome the problem of external power supply by adhering a flexible solar panel to the device.

[0021] 2. The present invention utilizes the piezoelectric inverse effect to design a vibration energy recovery device, thereby ensuring energy supply in emergency situations where the sail is not aligned with the sun for a long period of time, and suppressing the vibration of a large flexible sailboard.

[0022] 3. The present invention does not require external power supply, nor does it require onboard computer control. It has high integration and autonomy and can be installed on a large scale on large flexible solar panels. It has great engineering significance for improving control accuracy and ensuring spacecraft stability. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings:

[0024] Figure 1 It is a structural schematic diagram of the autonomous vibration suppression device of the present invention;

[0025] Figure 2 It is a cross-sectional view of the autonomous vibration suppression device described in the present invention.

[0026] In the figure:

[0027] 1-flexible solar panel, 2-bidirectional piezoelectric actuator, 3-piezoelectric fiber sheet, 4-clamp, 5-mounting base, 6-battery, 7-ball joint, 8-substrate, 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

[0028] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely explain the technical solutions in the embodiments of the present invention. It should be noted that the embodiments of the present invention 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 invention, not all of the embodiments.

[0029] Specific implementation 1: See Figure 1-2 To explain this embodiment,

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

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

[0032] Step 2: Recover 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: The flexible solar panel 1 converts solar energy into electrical energy and stores it in the battery 6 to power the bidirectional piezoelectric actuator 2 in the autonomous vibration suppression device;

[0034] Step 4: When the sailboard is not facing 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 sailboard into electrical energy through the inverse piezoelectric effect and stores it in the battery 6 to power the bidirectional piezoelectric actuator 2;

[0035] 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.

[0036] Taking into account the characteristics of large-scale flexible solar panels facing the sun for a long time and being prone to vibration, the device is provided with flexible solar panels 1 and piezoelectric fiber sheets 3, which can respectively recycle solar energy and structural strain energy. The flexible solar panel 1 is adhered to the housing 204 of the bidirectional piezoelectric actuator 2, and converts solar energy into electrical energy and stores it in the battery 6 to supply power to the bidirectional piezoelectric actuator 2. When the panel is not facing the sun for a long time, the piezoelectric fiber 3 can convert the strain energy generated by the vibration of the large-scale flexible solar panel into electrical energy through the inverse piezoelectric effect, and store it in the battery 6 to ensure that the entire system can work normally. Under the power supply of the battery 6, the bidirectional piezoelectric actuator 2 stretches or shortens according to the local strain information collected from the large-scale flexible solar panel, generates a force in the opposite direction, and suppresses the deformation and vibration of the large-scale flexible solar panel.

[0037] Taking advantage of the installation on the solar sail panel, by adhering the flexible solar panel 1 on the device, the problem of external power supply can be effectively overcome. The vibration energy recovery device is designed using the piezoelectric inverse effect to ensure the energy supply in the emergency situation of long-term non-sun orientation, and the vibration of the large flexible sail panel can be suppressed. No external power supply is required, and no on-board computer control is required. It has high integration and autonomy, and can be installed on a large scale on large flexible solar sail panels. It has great engineering significance for improving control accuracy and ensuring the stability of spacecraft.

[0038] Specific implementation method 2: See Figure 1-2 To illustrate this embodiment, the autonomous vibration suppression device also includes a mounting base 5 and a substrate 8, the mounting base 5 is mounted on both ends of the substrate 8, 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 the battery 6 is fixed to the mounting base 5 by a clamp 4.

[0039] Specific implementation method 3: See Figure 1-2To illustrate this embodiment, a piezoelectric strain sensor 9 is installed under the substrate 8, and 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 stretches or shrinks according to the local strain information collected by the piezoelectric strain sensor 9 arranged parallel to the surface of the large flexible solar panel, thereby generating a force in the opposite direction and suppressing the deformation and vibration of the large flexible solar panel.

[0040] Specific implementation method 4: See Figure 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. 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 Figure 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 cover 205 and a housing 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 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. The outer side of the telescopic unit 203 is connected to the ball joint 7 through the connecting end cover 205. 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 both are in contact with 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 connected to the ends of the telescopic unit 203. The rod cooperates to ensure that the telescopic unit 203 can only make a 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. On the contrary, 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 cooperate with the telescopic unit 203 through spherical contact, which ensures 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 only used to help explain the present invention. The specific embodiments do not describe all the details in detail, nor do they limit the invention to the specific embodiments described. According to the content of this specification, many modifications and changes can be made. This specification selects and specifically describes these embodiments in order to better explain the principles and practical applications of the present invention, so that those skilled in the art can understand and use the present invention well.

Claims

1. A self-powered autonomous vibration suppression method for large flexible solar panels, characterized in that: It includes the following steps: Step 1: Install the autonomous vibration suppression device on the large flexible solar sail panel; Step 2: Recover 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 a battery (6) to power the bidirectional piezoelectric actuator (2) in the autonomous vibration suppression device; Step 4: When the solar panel is not facing 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 panel into electrical energy through the inverse piezoelectric effect and stores it in the battery (6), thereby supplying power to the bidirectional piezoelectric actuator (2); Step 5: Under the power supply of the battery (6), the bidirectional piezoelectric actuator (2) stretches or contracts 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. A self-powered autonomous vibration suppression method for a large flexible solar sail panel according to claim 1, characterized in that: The autonomous vibration suppression device also includes a mounting base (5) and a substrate (8), wherein mounting bases (5) are mounted at both ends of the substrate (8), 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), and the piezoelectric fiber sheet (3) is mounted above the substrate (8).

3. A self-powered autonomous vibration suppression method for a large flexible solar sail panel according to claim 2, characterized in that: A piezoelectric strain sensor (9) is installed below the substrate (8), and the piezoelectric strain sensor (9) is used to collect local strain information on a large flexible solar sail panel.

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

5. A self-powered autonomous vibration suppression method for a large flexible solar sail panel according to claim 4, 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); 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 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 a 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).

6. A self-powered autonomous vibration suppression method for a large flexible solar sail panel according to claim 5, characterized in that: 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 are in contact with and fit with the spherical groove at the center of the telescopic unit (203).

7. A self-powered, autonomous vibration suppression method for a large flexible solar sail panel according to claim 2, characterized in that: The battery (6) is fixed on the mounting base (5) via a clamp (4).

8. A self-powered, autonomous vibration suppression method for a large flexible solar sail panel according to claim 4, characterized in that: The ball joint (7) is connected to the mounting base (5) via bolts.

9. A self-powered, autonomous vibration suppression method for a large flexible solar sail panel according to claim 2, characterized in that: The base plate (8) is connected to the large flexible solar sail panel via bolts.

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