Passive spacecraft solar array flexible vibration suppression device and spacecraft

Abstract

The present invention provides a passive spacecraft solar wing flexible vibration suppression device and a spacecraft, comprising: a metal bracket, a first damping module and a second damping module; the two ends of the metal bracket are respectively connected to the first damping module and the second damping module; a spacecraft is installed on one side surface of the metal bracket, and a solar wing is installed on the other side surface. The present invention utilizes the shear deformation of the damping module to achieve the dissipation of the kinetic energy of the solar wing without consuming the energy of the spacecraft.

Description

Technical Field

[0001] The present invention relates to a flexible vibration suppression device, and more particularly to a passive flexible vibration suppression device for a solar wing of a spacecraft and a spacecraft. Background Art

[0002] The solar wing is a power generation device of a spacecraft, providing power for the spacecraft. After being deployed in orbit, the solar wing is a flexible structure and will generate low-frequency flexible vibrations under disturbances such as thermal shock and spacecraft attitude changes. Since the solar wing has a large inertial mass after deployment, the flexible vibrations of the solar wing will have an adverse impact on the attitude stability and pointing accuracy of the spacecraft. In the space environment, due to the lack of air damping, the vibration energy of the solar wing is mainly dissipated through the structural material damping of the solar wing. The structural material damping of the solar wing itself is usually small, so generally the low-frequency flexible vibrations of the solar wing will last for a long time. To reduce the influence of the flexible vibrations of the solar wing on the spacecraft attitude stability and pointing accuracy, it is necessary to suppress the flexible vibrations of the solar wing, thereby reducing the duration of the flexible vibrations of the solar wing.

[0003] Active control technology is currently widely used to suppress the flexible vibration of solar panels. The active suppression device of the flexible vibration of solar panels usually uses actuators and sensors to form a closed-loop control system. For example, the patent "A method for suppressing the vibration of satellite solar panels using a solid micro-thruster array" (CN107719705 A) uses multiple solid micro-thrusters as actuators and uses vibration sensors to collect vibration signals for closed-loop control; the patent "A method and device for active control of low-modal vibration of space sailboard structure based on morphological perception" (CN101051217 A) The vibration form of the sailboard structure is sensed in real time using a fiber Bragg grating sensor network, and a control strategy is generated based on the sensed structural vibration information, and a shape memory alloy spring is used as an actuator for closed-loop control; the patent "An adaptive vibration control method based on sailboard flexible deformation measurement (CN102880049A)" obtains the deformation displacement of the sailboard root, the middle position of the sailboard, and the end of the sailboard at the current moment, calculates the attitude angular velocity of the spacecraft at the current moment, and the expected attitude angular velocity, and calculates the attitude angular velocity deviation based on the attitude information at the current moment to determine the adaptive control amount of the spacecraft, and realizes the adaptive vibration control of the spacecraft based on the sailboard flexible deformation measurement through PID; the patent "A vibration self-suppressing solar sailboard based on suspension rope tension measurement (CN106773706A)" uses suspension rope tension and acceleration sensors to feedback the flexible vibration of the solar wing, and controls the motor to achieve suspension rope extension and retraction according to the control algorithm, thereby controlling the tension of the suspension rope, and then controlling the flexible vibration of the solar wing. The solar wing flexible vibration suppression device based on the active control principle will require additional power during operation, increasing the energy consumption of the spacecraft. At the same time, the active flexible vibration suppression device usually requires multiple drivers for distributed control, which invisibly increases the weight of the solar wing, increases the complexity of the solar wing system, and reduces the reliability of the solar wing. Summary of the invention

[0004] In view of the defects in the prior art, an object of the present invention is to provide a passive spacecraft solar wing flexible vibration suppression device and a spacecraft.

[0005] A passive spacecraft solar wing flexible vibration suppression device provided by the present invention includes: a metal bracket, a first damping module and a second damping module;

[0006] Two ends of the metal bracket are respectively connected to the first damping module and the second damping module;

[0007] The spacecraft is installed on one side of the metal bracket, and the solar wing is installed on the other side.

[0008] Preferably, the metal bracket comprises: a first metal bracket and a second metal bracket;

[0009] The first metal bracket is connected to the second metal bracket;

[0010] The spacecraft is installed on one side of the first metal bracket facing away from the second metal bracket;

[0011] The solar wing is installed on one side of the second metal bracket facing away from the first metal bracket.

[0012] Preferably, the spacecraft and the solar wing are installed in the middle of the metal bracket;

[0013] The first damping module and the second damping module are respectively installed at both ends of the metal bracket through a plurality of second screws.

[0014] Preferably, the first damping module includes: a first long spring plate connecting block, a first short spring plate connecting block, a first damping rubber, and a first spring plate group;

[0015] The first long spring plate connecting block is arranged parallel to one side of the first short spring plate connecting block;

[0016] Both ends of the first long spring plate connecting block are connected to both ends of the first short spring plate connecting block through the first spring plate group;

[0017] The first long spring plate connecting block, the first short spring plate connecting block, and the first spring plate group enclose a trapezoid and form a first trapezoidal cavity inside the trapezoid;

[0018] The first damping rubber is filled in the first trapezoidal cavity.

[0019] Preferably, the first spring plate group includes: a first spring plate, a second spring plate, a third spring plate, and a fourth spring plate;

[0020] The first spring plate and the second spring plate are installed on one side of the first long spring plate connecting block and the first short spring plate connecting block, and the third spring plate and the fourth spring plate are installed on the other side of the first long spring plate connecting block and the first short spring plate connecting block;

[0021] Both ends of the first spring plate and the second spring plate are respectively connected to the first long spring plate connecting block and the first short spring plate connecting block through a plurality of first screws;

[0022] Both ends of the third spring plate and the fourth spring plate are respectively connected to the first long spring plate connecting block and the first short spring plate connecting block through a plurality of the first screws;

[0023] The first spring plate is parallel to the second spring plate, and the third spring plate is parallel to the fourth spring plate.

[0024] Preferably, the second damping module includes: a second long spring piece connecting block, a second short spring piece connecting block, a second damping rubber, and a second spring piece group;

[0025] The second long spring piece connecting block is arranged parallel to one side of the second short spring piece connecting block;

[0026] Both ends of the second long spring piece connecting block are connected to both ends of the second short spring piece connecting block through the second spring piece group;

[0027] The second long spring piece connecting block, the second short spring piece connecting block, and the second spring piece group enclose a trapezoid and form a second trapezoidal cavity inside the trapezoid;

[0028] The second damping rubber is filled in the second trapezoidal cavity.

[0029] Preferably, the second spring piece group includes: a fifth spring piece, a sixth spring piece, a seventh spring piece, and an eighth spring piece;

[0030] The fifth spring piece and the sixth spring piece are installed on one side of the second long spring piece connecting block and the second short spring piece connecting block, and the seventh spring piece and the eighth spring piece are installed on the other side of the second long spring piece connecting block and the second short spring piece connecting block;

[0031] Both ends of the fifth spring piece and the sixth spring piece are respectively connected to the second long spring piece connecting block and the second short spring piece connecting block through a plurality of the first screws;

[0032] Both ends of the seventh spring piece and the eighth spring piece are respectively connected to the second long spring piece connecting block and the second short spring piece connecting block through a plurality of the first screws;

[0033] The fifth spring piece is parallel to the sixth spring piece, and the seventh spring piece is parallel to the eighth spring piece.

[0034] Preferably, the two sides of the metal bracket are mirror-symmetrical about the midline;

[0035] The first damping module and the second damping module are mirror-symmetrical about the midline of the metal bracket.

[0036] Preferably, the first long spring piece connecting block and the second long spring piece connecting block are fixedly installed at both ends of the first metal bracket;

[0037] The first short spring piece connecting block and the second short spring piece connecting block are fixedly installed at both ends of the second metal bracket;

[0038] The first long spring piece connecting block is longer than the first short spring piece connecting block, and the second long spring piece connecting block is longer than the second short spring piece connecting block.

[0039] Preferably, a spacecraft adopts the passive spacecraft solar wing flexural vibration suppression device.

[0040] Preferably, the first spring piece, the second spring piece, the third spring piece, the fourth spring piece, the fifth spring piece, the sixth spring piece, the seventh spring piece and the eighth spring piece are exactly the same.

[0041] Preferably, the first damping module and the second damping module increase the bending stiffness and reduce the shear stiffness through a trapezoidal structure.

[0042] Preferably, the second metal bracket is connected to the root of the solar wing.

[0043] Compared with the prior art, the present invention has the following beneficial effects:

[0044] 1. The present invention utilizes the shear deformation of the damping module to achieve the kinetic energy dissipation of the solar wing without consuming the energy of the spacecraft.

[0045] 2. In the present invention, when the damping module undergoes shear deformation, its bending stiffness does not change significantly. Therefore, the present invention has no obvious influence on the stiffness of the solar wing and does not significantly reduce the fundamental frequency of the solar wing.

[0046] 3. The present invention utilizes the large shear deformation of the damping rubber to achieve high reliability of passive energy consumption.

[0047] 4. The present invention is installed at the root of the solar wing, without the need for structural modification of the solar wing, and can be applied to different forms of spacecraft solar wings.

[0048] 5. In the present invention, the spring piece is detachable, and the overall stiffness and damping characteristics of the present invention can be conveniently changed by changing the thickness of the spring piece, which is convenient for adaptive adjustment for different solar wings.

[0049] 6. The structure of the present invention is simple, with low requirements for processing and manufacturing, and is convenient for miniaturization and lightweight design. BRIEF DESCRIPTION OF THE DRAWINGS

[0050] By reading the detailed description of the non-limiting embodiments with reference to the following drawings, other features, objects and advantages of the present invention will become more obvious:

[0051] Figure 1 It is a three-dimensional structure schematic diagram of the flexural vibration suppression device;

[0052] Figure 2 It is a partial exploded structure schematic diagram of the flexural vibration suppression device;

[0053] Figure 3 is the exploded view of the first damping module;

[0054] Figure 4 is the exploded view of the second damping module;

[0055] Figure 5 is the schematic diagram when the flexible vibration suppression device is used and installed;

[0056] Figure 6 is the schematic diagram of the lateral comparison before and after the deformation of the damping module.

[0057] As shown in the figure:

[0058] Specific embodiments

[0059] The present invention will be described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that those of ordinary skill in the art can make several changes and improvements without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0060] Embodiment 1

[0061] As Figure 1 and Figure 5 shown, this embodiment includes: a metal bracket, a first damping module 10, and a second damping module 20; both ends of the metal bracket are respectively connected to the first damping module 10 and the second damping module 20, a spacecraft is installed on one side surface of the metal bracket, and a solar wing is installed on the other side surface. The spacecraft and the solar wing are installed in the middle of the metal bracket, and the first damping module 10 and the second damping module 20 are respectively installed at both ends of the metal bracket through a plurality of second screws 42. The metal bracket includes: a first metal bracket 1 and a second metal bracket 2; the first metal bracket 1 is connected to the second metal bracket 2, the spacecraft is installed on the side of the first metal bracket 1 facing away from the second metal bracket 2, and the solar wing is installed on the side of the second metal bracket 2 facing away from the first metal bracket 1.

[0062] As Figure 3As shown in the figure, the first damping module 10 includes: a first long spring plate connecting block 11, a first short spring plate connecting block 12, a first damping rubber 13, and a first spring plate group; the first long spring plate connecting block 11 is arranged in parallel on one side of the first short spring plate connecting block 12, both ends of the first long spring plate connecting block 11 are connected to both ends of the first short spring plate connecting block 12 through the first spring plate group, the first long spring plate connecting block 11, the first short spring plate connecting block 12, and the first spring plate group enclose a trapezoid and form a first trapezoidal cavity inside the trapezoid, and the first damping rubber 13 is filled in the first trapezoidal cavity. The first spring plate group includes: a first spring plate 14, a second spring plate 15, a third spring plate 16, and a fourth spring plate 17; the first spring plate 14 and the second spring plate 15 are installed on one side of the first long spring plate connecting block 11 and the first short spring plate connecting block 12, the third spring plate 16 and the fourth spring plate 17 are installed on the other side of the first long spring plate connecting block 11 and the first short spring plate connecting block 12, both ends of the first spring plate 14 and the second spring plate 15 are respectively connected to the first long spring plate connecting block 11 and the first short spring plate connecting block 12 through a plurality of first screws 41, both ends of the third spring plate 16 and the fourth spring plate 17 are respectively connected to the first long spring plate connecting block 11 and the first short spring plate connecting block 12 through a plurality of first screws 41, the first spring plate 14 is parallel to the second spring plate 15, and the third spring plate 16 is parallel to the fourth spring plate 17.

[0063] As Figure 4 shown in the figure, the second damping module 20 includes: a second long spring plate connecting block 21, a second short spring plate connecting block 22, a second damping rubber 23, and a second spring plate group; the second long spring plate connecting block 21 is arranged in parallel on one side of the second short spring plate connecting block 22, both ends of the second long spring plate connecting block 21 are connected to both ends of the second short spring plate connecting block 22 through the second spring plate group, the second long spring plate connecting block 21, the second short spring plate connecting block 22, and the second spring plate group enclose a trapezoid and form a second trapezoidal cavity inside the trapezoid, and the second damping rubber 23 is filled in the second trapezoidal cavity. The second spring plate group includes: a fifth spring plate 24, a sixth spring plate 25, a seventh spring plate 26, and an eighth spring plate 27; the fifth spring plate 24 and the sixth spring plate 25 are installed on one side of the second long spring plate connecting block 21 and the second short spring plate connecting block 22, the seventh spring plate 26 and the eighth spring plate 27 are installed on the other side of the second long spring plate connecting block 21 and the second short spring plate connecting block 22, both ends of the fifth spring plate 24 and the sixth spring plate 25 are respectively connected to the second long spring plate connecting block 21 and the second short spring plate connecting block 22 through a plurality of first screws 41, both ends of the seventh spring plate 26 and the eighth spring plate 27 are respectively connected to the second long spring plate connecting block 21 and the second short spring plate connecting block 22 through a plurality of first screws 41, the fifth spring plate 24 is parallel to the sixth spring plate 25, and the seventh spring plate 26 is parallel to the eighth spring plate 27.

[0064] As shown Figure 2 in the figure, the metal bracket is mirror-symmetrical on both sides of the center line, and the first damping module 10 and the second damping module 20 are mirror-symmetrical along the center line of the metal bracket. The first long spring piece connecting block 11 and the second long spring piece connecting block 21 are fixedly installed at both ends of the first metal bracket 1, and the first short spring piece connecting block 12 and the second short spring piece connecting block 22 are fixedly installed at both ends of the second metal bracket 2. The first long spring piece connecting block 11 is longer than the first short spring piece connecting block 12, and the second long spring piece connecting block 21 is longer than the second short spring piece connecting block 22.

[0065] Embodiment 2

[0066] Embodiment 2 is a preferred example of Embodiment 1.

[0067] As shown Figures 1 to 5 in the figure, this embodiment includes: a first metal bracket 1, a second metal bracket 2, a first damping module 10, a second damping module 20, a first screw 41, and a second screw 42. The first damping module 10 and the second damping module 20 are respectively connected to the first metal bracket 1 and the second metal bracket 2 by four second screws 42 at both ends.

[0068] The first damping module 10 includes: a first long spring piece connecting block 11, a first short spring piece connecting block 12, a first damping rubber 13, a first spring piece 14, a second spring piece 15, a third spring piece 16, a fourth spring piece 17, and a first screw 41. The first spring piece 14, the second spring piece 15, the third spring piece 16, and the fourth spring piece 17 are respectively connected to the first long spring piece connecting block 11 and the first short spring piece connecting block 12 by sixteen screws 41. The first damping rubber 13 is filled into the first trapezoidal cavity formed by the first spring piece 14, the second spring piece 15, the third spring piece 16, the fourth spring piece 17, the first long spring piece connecting block 11, and the first short spring piece connecting block 12.

[0069] The second damping module 20 includes: a second long spring piece connecting block 21, a second short spring piece connecting block 22, a second damping rubber 23, a fifth spring piece 24, a sixth spring piece 25, a seventh spring piece 26, an eighth spring piece 27, and a first screw 41. The fifth spring piece 24, the sixth spring piece 25, the seventh spring piece 26, and the eighth spring piece 27 are respectively connected to the second long spring piece connecting block 21 and the second short spring piece connecting block 22 by sixteen first screws 41. The second damping rubber 23 is filled into the second trapezoidal cavity formed by the fifth spring piece 24, the sixth spring piece 25, the seventh spring piece 26, the eighth spring piece 27, the second long spring piece connecting block 21, and the second short spring piece connecting block 22.

[0070] The first damping rubber 13 is identical to the second damping rubber 23, the first long spring plate connecting block 11 is identical to the second long spring plate connecting block 21, and the first short spring plate connecting block 12 is identical to the second short spring plate connecting block 22. The first spring plate group serves as the hypotenuse of the trapezoidal first damping module 10, the first long spring plate connecting block 11 forms the long side of the trapezoidal first damping module 10, and the first short spring plate connecting block 12 forms the short side of the trapezoidal first damping module 10. The second spring plate group serves as the hypotenuse of the trapezoidal second damping module 20, the second long spring plate connecting block 21 forms the long side of the trapezoidal second damping module 20, and the second short spring plate connecting block 22 forms the short side of the trapezoidal second damping module 20. The bending stiffness and shear stiffness of the first damping module 10 and the second damping module 20 can be adjusted by the stiffness of the spring plates.

[0071] The working principle of the present invention is as follows:

[0072] After the solar panel is deployed in orbit, the solar panel will generate low-frequency flexible vibrations under the excitation of thermal shock or spacecraft attitude adjustment. This example is installed between the solar panel and the spacecraft. The first metal bracket 1 is connected to the spacecraft, and the second metal bracket 2 is connected to the root of the solar panel. When the solar panel generates flexible vibrations, the solar panel will generate a large bending moment on this embodiment at its root. The bending moment exerted on this device by the flexible vibrations of the solar panel will be transmitted to the first damping module 10 and the second damping module 20 through the second metal bracket 2, and then the first damping module 10 and the second damping module 20 will generate shear deformation. The first damping rubber 13 and the second damping rubber 23 in the first damping module 10 and the second damping module 20 will generate shear deformation along with the first damping module 10 and the second damping module 20, thereby consuming the vibration energy of the solar panel and enabling the flexible vibrations of the solar panel to stop quickly.

[0073] In this embodiment, the first damping module 10 and the second damping module 20 adopt a trapezoidal configuration. The trapezoidal configuration can ensure that the first damping module 10 and the second damping module 20 have a large bending stiffness, and at the same time can effectively reduce their shear stiffness. Therefore, this embodiment as a whole has a large bending stiffness and a small shear stiffness. Since this embodiment serves as the mounting surface of the solar panel, the large bending stiffness of this embodiment ensures that the fundamental frequency of the solar panel does not decrease significantly, while the low shear stiffness ensures that this embodiment can generate a large shear deformation when the solar panel vibrates, thereby effectively dissipating the vibration energy of the solar panel and achieving the suppression of the flexible vibrations of the solar panel.

[0074] Those skilled in the art know that in addition to implementing the system and its various devices, modules, and units provided by the present invention in the form of pure computer-readable program code, the method steps can be logically programmed to enable the system and its various devices, modules, and units provided by the present invention to be implemented in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers, etc. to achieve the same functions. Therefore, the system and its various devices, modules, and units provided by the present invention can be considered as a kind of hardware component, and the devices, modules, and units included therein for implementing various functions can also be regarded as the structures within the hardware component; the devices, modules, and units for implementing various functions can also be regarded as either software modules for implementing the method or structures within the hardware component.

[0075] In the description of the present application, it should be understood that the orientation or positional relationship indicated by the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present application and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present application.

[0076] The specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Without conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A passive spacecraft solar wing flexible vibration suppression device, characterized in that Including: A metal bracket, a first damping module (10), and a second damping module (20); Both ends of the metal bracket are respectively connected to the first damping module (10) and the second damping module (20); A spacecraft is installed on one side of the metal bracket, and a solar wing is installed on the other side; The metal bracket includes: a first metal bracket (1) and a second metal bracket (2); The first metal bracket (1) is connected to the second metal bracket (2); The spacecraft is installed on the side of the first metal bracket (1) facing away from the second metal bracket (2); The solar wing is installed on the side of the second metal bracket (2) facing away from the first metal bracket (1); The spacecraft and the solar wing are installed in the middle of the metal bracket; The first damping module (10) and the second damping module (20) are respectively installed at both ends of the metal bracket through a plurality of second screws (42); The first damping module (10) includes: a first long spring piece connecting block (11), a first short spring piece connecting block (12), a first damping rubber (13), and a first spring piece group; The first long spring piece connecting block (11) is arranged parallel to one side of the first short spring piece connecting block (12); Both ends of the first long spring piece connecting block (11) are connected to both ends of the first short spring piece connecting block (12) through the first spring piece group; The first long spring piece connecting block (11), the first short spring piece connecting block (12), and the first spring piece group enclose a trapezoid and form a first trapezoidal cavity inside the trapezoid; The first damping rubber (13) is filled in the first trapezoidal cavity; The second damping module (20) includes: a second long spring piece connecting block (21), a second short spring piece connecting block (22), a second damping rubber (23), and a second spring piece group; The second long spring piece connecting block (21) is arranged parallel to one side of the second short spring piece connecting block (22); Both ends of the second long spring piece connecting block (21) are connected to both ends of the second short spring piece connecting block (22) through the second spring piece group; The second long spring piece connecting block (21), the second short spring piece connecting block (22), and the second spring piece group enclose a trapezoid and form a second trapezoidal cavity inside the trapezoid; The second damping rubber (23) is filled in the second trapezoidal cavity.

2. The passive spacecraft solar wing flexible vibration suppression device according to claim 1, wherein The first spring piece group includes: a first spring piece (14), a second spring piece (15), a third spring piece (16), and a fourth spring piece (17); The first spring piece (14) and the second spring piece (15) are installed on one side of the first long spring piece connecting block (11) and the first short spring piece connecting block (12), and the third spring piece (16) and the fourth spring piece (17) are installed on the other side of the first long spring piece connecting block (11) and the first short spring piece connecting block (12); Both ends of the first spring piece (14) and the second spring piece (15) are respectively connected to the first long spring piece connecting block (11) and the first short spring piece connecting block (12) through a plurality of first screws (41); Both ends of the third spring piece (16) and the fourth spring piece (17) are respectively connected to the first long spring piece connection block (11) and the first short spring piece connection block (12) by a plurality of the first screws (41); The first spring piece (14) is parallel to the second spring piece (15), and the third spring piece (16) is parallel to the fourth spring piece (17).

3. The passive spacecraft solar wing flexible vibration suppression device according to claim 1, characterized in that, The second spring piece group includes: a fifth spring piece (24), a sixth spring piece (25), a seventh spring piece (26), and an eighth spring piece (27); The fifth spring piece (24) and the sixth spring piece (25) are installed on one side of the second long spring piece connection block (21) and the second short spring piece connection block (22), and the seventh spring piece (26) and the eighth spring piece (27) are installed on the other side of the second long spring piece connection block (21) and the second short spring piece connection block (22); Both ends of the fifth spring piece (24) and the sixth spring piece (25) are respectively connected to the second long spring piece connection block (21) and the second short spring piece connection block (22) by a plurality of the first screws (41); Both ends of the seventh spring piece (26) and the eighth spring piece (27) are respectively connected to the second long spring piece connection block (21) and the second short spring piece connection block (22) by a plurality of the first screws (41); The fifth spring piece (24) is parallel to the sixth spring piece (25), and the seventh spring piece (26) is parallel to the eighth spring piece (27).

4. The passive spacecraft solar wing flexible vibration suppression device according to claim 1, characterized in that: The metal bracket is mirror-symmetrical on both sides of the midline; The first damping module (10) and the second damping module (20) are mirror-symmetrical along the midline of the metal bracket.

5. The passive spacecraft solar array flexible vibration suppression device according to claim 1, characterized in that: The first long spring piece connection block (11) and the second long spring piece connection block (21) are fixedly installed at both ends of the first metal bracket (1); The first short spring piece connection block (12) and the second short spring piece connection block (22) are fixedly installed at both ends of the second metal bracket (2); The first long spring piece connection block (11) is longer than the first short spring piece connection block (12), and the second long spring piece connection block (21) is longer than the second short spring piece connection block (22).

6. A spacecraft, characterized in that: The spacecraft adopts the passive spacecraft solar wing flexural vibration suppression device according to any one of claims 1-5.

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