KR102655972B1 - Yoke using Viscoelastic Tape and Folding-type Solar Panels using the same - Google Patents

Abstract

The present embodiments include a deployable solar panel mounted on a satellite orbiting a planet, including a solar panel mounted on the outside of the satellite to convert light energy into electrical energy and a yoke interconnecting the satellite and the solar panel, the yoke proposes a deployable solar panel in which reinforcement is laminated on both sides of the base connecting the satellite and the solar panel to attenuate vibration transmitted to the solar panel.

Description

Yoke with viscoelastic properties and foldable solar panels using the same {Yoke using Viscoelastic Tape and Folding-type Solar Panels using the same}

The present invention relates to a yoke and a deployable solar panel using the same, and particularly to a yoke having viscoelastic properties and a deployable solar panel using the same.

The content described in this section simply provides background information for this embodiment and does not constitute prior art.

Satellites that perform Earth observation require rapid maneuvering and rapid attitude stabilization to obtain as many observations as possible in a limited time in one orbit. In order to improve the mobility and stability of satellites, the structure must be designed to be lightweight and have sufficient rigidity at the same time.

The satellite's solar panel is mounted on the outside of the satellite and has a large moment of inertia, so it is one of the factors that greatly affects attitude control. Also, in the case of the deployable solar panel applied to secure a sufficient power area, it is folded and stored during launch. After launch, it is deployed on orbit, and it is difficult to design it to be lightweight because it focuses on high-strength design to withstand the launch vibration and shock that occurs during deployment. Meanwhile, as the recent satellite development trend is toward smaller and lighter satellites, existing rigidity-securing design techniques have limitations, such as the occurrence of vibration in large flexible structures.

Embodiments of the present invention were developed to solve the above problems, and require a short deployment stabilization time by applying a layered superelastic shape memory alloy. The main purpose of the invention is to efficiently reduce external disturbance (vibration/shock) without increasing the weight and size in all fields requiring compact/light design.

Other unspecified objects of the present invention can be additionally considered within the scope that can be easily inferred from the following detailed description and its effects.

According to one aspect of this embodiment, the present invention relates to a deployable solar panel mounted on a satellite orbiting a planet, a solar panel mounted outside the satellite to convert light energy into electrical energy, and the satellite and the solar panel. It proposes a deployable solar panel comprising a yoke that interconnects, wherein the yoke is laminated with reinforcement on both sides of the base connecting the satellite and the solar panel to attenuate vibration transmitted to the solar panel. .

Preferably, the yoke includes the base having a superelastic effect and the reinforcing part that dampens vibration input from the outside, and the reinforcing part includes a constraint layer made of the same material as the base and a damping part that forms viscoelastic properties. It is characterized by comprising a layer.

Preferably, the reinforcing part is characterized in that a plurality of restraining layers are cross-stacked and fixed on both sides of the base using a damping layer that forms the viscoelastic properties to damp vibration against microscopic vibrations below the critical stress. .

Preferably, the yoke improves rigidity and damping performance by adjusting the number of stacks of the constraint layer and the damping layer.

Preferably, when the vibration response in the form of bending behavior that occurs when vibration is transmitted is a large displacement greater than the critical stress of the base, a phase change to restore the original shape occurs and the yoke exhibits a damping effect to absorb vibration, and the yoke exhibits a damping effect to absorb vibration. In the case of a small displacement below the stress, the vibration is attenuated by friction between a damping layer forming viscoelastic properties and a restraining layer made of the same material as the base.

Preferably, the base is formed of superelastic shape memory alloy (SMA, Shape Memory Alloy).

According to another embodiment of the present invention, the present invention provides a yoke for interconnecting a satellite and the solar panel, a base connecting one end of the satellite and one end of the solar panel, and the base having a superelastic effect. and a reinforcing part that dampens vibration input from the outside, wherein the reinforcing part includes a constraint layer made of the same material as the base and a damping layer that forms viscoelastic properties.

Preferably, the yoke improves rigidity and damping performance by adjusting the number of stacks of the constraint layer and the damping layer, and uses a damping layer that forms the viscoelastic properties to form a plurality of constraint layers on both sides of the base. It is characterized by being cross-stacked and fixed.

Preferably, when the vibration response in the form of bending behavior that occurs when vibration is transmitted is a large displacement greater than the critical stress of the base, a phase change to restore the original shape occurs and the yoke exhibits a damping effect to absorb vibration, and the yoke exhibits a damping effect to absorb vibration. In the case of a small displacement below the stress, the vibration is attenuated by friction between a damping layer forming viscoelastic properties and a restraining layer made of the same material as the base.

Preferably, the yoke applies uniform pressure when stacking a restraining layer made of the same material as the base of the reinforcement part and a damping layer forming viscoelastic properties on both sides of the base connecting the satellite and the solar panel. It is characterized in that it further includes at least one adhesive hole that enables adhesion.

Preferably, the base and the confinement layer are formed of superelastic shape memory alloy (SMA, Shape Memory Alloy).

According to another embodiment of the present invention, the present invention relates to a method of manufacturing a deployable solar panel using a solar panel deployable satellite orbiting a planet, the base having a superelastic effect on both sides of the base, and an input from the outside. A step of creating a yoke by seating a reinforcing part that dampens vibration, and interconnecting a satellite orbiting the planet and a solar panel mounted on the outside of the satellite to convert light energy into electrical energy through the yoke, , the step of generating the yoke is an unfolded solar system characterized in that the yoke is created by seating a reinforcing part created by cross-lamination of a restraining layer made of the same material as the base and a damping layer forming viscoelastic properties, on the base. We propose a method of manufacturing a battery panel.

As described above, according to the embodiments of the present invention, the present invention has the effect of enabling a lightweight design by minimizing the required rigidity of the solar panel in line with the development trend of lightweight/miniaturization of satellites with high damping yoke of solar panels.

Even if the effects are not explicitly mentioned here, the effects described in the following specification and their potential effects expected by the technical features of the present invention are treated as if described in the specification of the present invention.

1 to 3 are diagrams showing a deployable solar panel using a yoke having viscoelastic properties according to an embodiment of the present invention.
Figure 4 is a flowchart showing a method of manufacturing a deployable solar panel using a yoke with viscoelastic properties according to an embodiment of the present invention.
Figures 5 to 11 are diagrams showing experimental results according to the type of yoke in a deployable solar panel according to an embodiment of the present invention.

Hereinafter, embodiments of the present invention will be described in detail with reference to the attached drawings. The advantages and features of the present invention and methods for achieving them will become clear by referring to the embodiments described in detail below along with the accompanying drawings. However, the present invention is not limited to the embodiments disclosed below and may be implemented in various different forms. The present embodiments are merely intended to ensure that the disclosure of the present invention is complete and to provide common knowledge in the technical field to which the present invention pertains. It is provided to fully inform those who have the scope of the invention, and the present invention is only defined by the scope of the claims. Like reference numerals refer to like elements throughout the specification.

Unless otherwise defined, all terms (including technical and scientific terms) used in this specification may be used with meanings that can be commonly understood by those skilled in the art to which the present invention pertains. Additionally, terms defined in commonly used dictionaries are not interpreted ideally or excessively unless clearly specifically defined.

The terms used in this application are only used to describe specific embodiments and are not intended to limit the invention. The singular terms include plural expressions, unless the context clearly dictates otherwise. In this application, terms such as “comprise” or “have” are intended to designate the presence of features, numbers, steps, operations, components, parts, or combinations thereof described in the specification, but are not intended to indicate the presence of one or more other features. It should be understood that this does not exclude in advance the possibility of the existence or addition of elements, numbers, steps, operations, components, parts, or combinations thereof.

Terms containing ordinal numbers, such as second, first, etc., may be used to describe various components, but the components are not limited by the terms. The above terms are used only for the purpose of distinguishing one component from another. For example, the second component may be referred to as the first component without departing from the scope of the present invention, and similarly, the first component may also be referred to as the second component. The term and/or includes any of a plurality of related stated items or a combination of a plurality of related stated items.

The present invention relates to a yoke having viscoelastic properties and a deployable solar panel using the same.

Satellites that perform Earth observation require rapid maneuvering and rapid attitude stabilization to obtain as many observations as possible in a limited time in one orbit. In order to improve the mobility and stability of satellites, the structure must be designed to be lightweight and have sufficient rigidity at the same time. The satellite's solar panel is mounted on the outside of the satellite and has a large moment of inertia, so it is one of the factors that greatly affects attitude control. In addition, in the case of deployable solar panels used to secure sufficient power area, they are folded and stored at launch and then deployed in orbit after launch. In order to withstand the launch vibration and shock generated during deployment, the focus is on high-strength design. Therefore, lightweight design is difficult. Meanwhile, the size of solar panels is increasing in order to secure sufficient power due to the advancement of satellite missions. In order to apply them to high-mobility satellites, it is necessary to effectively attenuate vibrations occurring in large flexible structures by departing from the existing design to secure stability through securing rigidity. The need for new structural designs that can do this is emerging.

Among the structures of conventional satellite solar panels, the deployment-fixed type is a design that increases deployment rigidity by fixing the deployed solar panel to the satellite and a support beam or using a highly rigid hinge to connect the panels, thereby reducing the posture stabilization time for video shooting. It is short and widely applied to optical satellites that require high mobility. In addition, since solar panel design relies on applying support beams and increasing the rigidity of the structure to satisfy the minimum required stiffness of the satellite, there are limits to satellite lightweighting. In addition, existing support beams cannot be applied to solar tracking type deployment-rotation solar panels, and the rigid body vibration of the solar panel due to micro-vibration generated from the solar panel rotation actuator acts as a cause of deterioration of the orientation performance of high-precision satellites. Additionally, this problem becomes more apparent in the case of microsatellites that are equipped with solar panels that are relatively large in size compared to the main body to meet power requirements.

Therefore, in order to solve the above-mentioned problem, the deployable solar panel 10 can be designed to be compact and lightweight through vibration isolation through the application of the high-stiffness, high-damping yoke 200, and low-cost development can be achieved by alleviating incoming vibration conditions. It may be possible.

The deployable solar panel (10) has high rigidity and short stabilization time, so it can be applied to the deployment mechanism of solar panels and antennas of high-speed reconnaissance satellites. Due to the short stabilization time, more images can be captured under the same conditions. It has the advantage of being able to take pictures.

The deployable solar panel 10 can be designed to be lightweight by minimizing the required rigidity of the solar panel in line with the development trend of lightweight/miniaturization of satellites with high damping yoke of solar panels.

The deployable solar panel (10) is a mechanical technology using vibration reduction characteristics and can be widely used in all defense and civil fields, including space, aviation, and ground platforms. In particular, it requires a short deployment stabilization time while having high structural rigidity. It can be used in the deployment drive unit.

In addition, the deployable solar panel (10) can be used to minimize required rigidity by efficiently reducing external disturbance (vibration/shock) without increasing the weight and size in all fields requiring small/light design. You can.

1 to 3 are diagrams showing a deployable solar panel using a yoke having viscoelastic properties according to an embodiment of the present invention.

Referring to FIGS. 1 to 3 , the deployable solar panel 10 includes a satellite 100, a yoke 200, and a solar panel 300. Here, the yoke 200 includes a base 210, a confinement layer 222, and an attenuation layer 224. The deployable solar panel 10 may omit some of the various components exemplarily shown in FIGS. 1 to 3 or may additionally include other components.

Figure 1 is a diagram showing a deployable solar panel using a yoke having viscoelastic properties according to an embodiment of the present invention, and Figure 2 is a diagram showing a solar panel assembled with a yoke having viscoelastic properties according to an embodiment of the present invention. 1 is a diagram showing a partially enlarged view of the shape and the yoke, and FIG. 3 is an exemplary diagram showing a partially enlarged view of the second shape and the yoke in which a yoke with viscoelastic properties according to an embodiment of the present invention is assembled.

According to an embodiment of the present invention, the deployable solar panel 10 using a yoke with viscoelastic properties improves the damping ability of the yoke 200, which is a structural interface connecting the solar panel 300 and the satellite 100. By improving the damping ability and damage to solar panels caused by environmental vibrations input from the outside, damage to solar panels and deterioration of satellite maneuvering performance caused by environmental vibrations input from the outside can be resolved.

Satellite body 100 may orbit around a planet. Specifically, the satellite 100 is an artificial device launched to orbit a planet such as the Earth, and is artificially placed to orbit the planet.

By maintaining an appropriate speed according to the altitude, the satellite 100 can stay in orbit around the planet without falling to the ground, and continues its orbital motion without falling to the ground or being thrown out of the planet's gravitational sphere into outer space. Should be.

The solar panel 300 is mounted on the outside of the satellite 100 and can convert light energy into electrical energy.

The yoke 200 may connect the satellite 100 and the solar panel 300 to each other.

Referring to FIG. 2, the yoke 200 and the solar panel 300 are connected to each other by cell connection interfaces 410 and 420, and may be connected through a simple mechanical structure, but are not limited to what is shown.

Referring to FIG. 3, the yoke 200 and the solar panel 300 may be connected to each other by a screw fastening method without a separate connection interface as shown in FIG. 2. Here, the yoke 200 may have at least two holes formed in a portion connected to the solar panel 300, and the holes are formed in portions corresponding to the holes formed in the solar panel 300 to use a screw fastening method. It can be formed to be fixed through.

The yoke 200, a high-damping laminated structure utilizing shape memory alloy and viscoelastic effect, has mechanical properties that allow for short vibration stabilization time and easy control of the deployment mechanism.

According to one embodiment of the present invention, the deployable solar panel 10 using a yoke with viscoelastic properties has excellent vibration damping performance and elastic properties compared to general metal in order to improve the damping ability of the physical properties of the base 210. Elastic shape memory alloy (SMA, Shape Memory Alloy) can be applied.

According to one embodiment of the present invention, the deployable solar panel 10 has a restraining layer 222 made of the same material as the yoke 200 on both sides of the yoke 200 to improve the damping ability of the yoke 200 itself. A damping layer 224 laminated with viscoelastic tape was applied.

In addition, the deployable solar panel 10 has a simple manufacturing process and low cost when manufacturing the yoke 200, and has superior vibration reduction performance compared to conventional metal reinforcement materials, which has the effect of reducing costs.

The yoke 200 can attenuate vibration transmitted to the solar panel 300 by stacking reinforcement parts 220 on both sides of the base 210 that connects the satellite 100 and the solar panel 300.

The yoke 200 may include a base 210 that has a superelastic effect and a reinforcement portion 220 that dampens vibration input from the outside.

The base 210 can connect the satellite 100 and the solar panel 300. The base 210 may be implemented as a structure.

Structure 210 may be formed of superelastic shape memory alloy (SMA).

According to an embodiment of the present invention, the structure 210 may be formed of an alloy that has sufficient rigidity and a superelastic effect, and thus may have an insulating effect greater than a critical strain even on its own.

Since the structure 210 generates a damping effect for large displacements exceeding the critical stress of SMA, in order to dampen micro vibrations below the critical stress, a laminate containing a restraining layer 222 made of SMA material using a viscoelastic tape is placed on both sides. can be combined Specifically, when the vibration response in the form of bending behavior that occurs when vibration is transmitted to the yoke 200 is a large displacement greater than the critical stress of the SMA, a phase change to restore the original shape occurs and a damping effect to absorb vibration is exhibited. The small displacement may be able to attenuate vibration through friction between the laminated body of the damping layer 224 implemented with viscoelastic double-sided tape and the constraint layer 222 implemented with a SMA thin plate. Here, the viscoelastic tape has a viscoelastic material and may be a variety of materials capable of adhering the constraint layer 222 implemented with laminated SMA thin plates.

Critical stress represents the maximum strain that an object can withstand without being destroyed. Bending behavior is a force that acts when a certain force is applied, and can represent the force that acts as vibration occurs.

In addition, large displacement means that the displacement of the object changing its position is large, which can indicate a case where it is greater than the critical stress, while small displacement means that the displacement of the object changing its position is small, and can indicate a case that is less than the critical stress.

Phase change can indicate that a substance exhibits different states depending on temperature and pressure.

The reinforcing part 220 may have an insulating function focused on micro-strain through the insulating effect due to friction of several layers while stacking the damping layer 222 with viscoelastic properties. At this time, the material of each of the constraint layer 222 and the damping layer 224 may be any material with a function suitable for each purpose, and the thickness and size may also be implemented without limitation.

The stiffness and damping ability of the yoke 200 increase depending on the number of the constraint layer 222 and the damping layer 224 stacked, and the number of stacks can be adjusted as needed.

According to an embodiment of the present invention, the yoke 200 having viscoelastic properties is made of a laminated superelastic shape memory alloy (SMA), and the structure 210 and the structure 210 made of SMA material having a superelastic effect. It is a laminate in which a restraining layer 222 of the same material is laminated using a damping layer 224 with a viscoelastic effect. Here, the constraint layer 222 may be implemented as a thin plate laminate, and the damping layer 224 may be implemented as a viscoelastic tape.

According to one embodiment of the present invention, when applying SMA alone, the yoke 200, which has viscoelastic properties, can expect a damping effect due to phase change only when a large displacement exceeding the critical stress occurs, so a small amount of stress less than the critical stress can be expected. In order to attenuate vibration, thin plates made of SMA material can be laminated on both sides of the yoke main structure 210 made of SMA material using viscoelastic tape. Here, the thin plate may represent the confinement layer 222.

Referring to FIGS. 2 and 3 , the reinforcement portion 220 includes a confinement layer 222 and an attenuation layer 224 . The reinforcement unit 220 may omit some of the various components exemplarily shown in FIGS. 2 and 3 or may additionally include other components.

The reinforcement portion 220 is laminated on both sides of the structure 210 and can attenuate the vibration transmitted to the solar panel 300 by attenuating the vibration transmitted to the structure 210.

The reinforcement portion 220 may be formed by stacking a plurality of constraint layers 222 and attenuation layers 224, and the damping layers 224 and attenuation layers 210 may be alternately stacked and fixed.

The reinforcing part 220 has a high damping ability realized through viscoelastic properties, and can solve problems such as damage to the solar panel 300 and deterioration of the maneuvering performance of the satellite 100 by attenuating the vibration of the satellite 100 in a vibration environment. .

The reinforcement portion 220 may be a structure made of various viscoelastic materials that have a damping ability to dissipate vibration transmitted to the structure 210. Here, damping is the ability to attenuate vibration, and vibration can be reduced by dissipating the vibration energy transmitted to the structure 210.

The reinforcement portion 220 is fixed by multiple cross-stacked restraint layers 222 on both sides of the structure 210 using a damping layer 224 that forms viscoelastic properties to dampen microscopic vibrations below the critical stress. It can be.

According to one embodiment of the present invention, the thickness of the laminated thin plates of the reinforcement portion 220 is several mm or less, which has the advantage of minimizing the increase in weight/volume compared to conventional metal reinforcement materials, making space and aviation electronic equipment smaller and lighter. Implementation is possible. Here, the laminated thin plates are a constraint layer 222 and an attenuation layer 224.

The confinement layer 222 may be made of the same material as the structure 210. As the structure 210 and the constraint layer 222 are made of the same material, the properties of the vibration frequency transmitted to each are formed to be the same, thereby effectively attenuating vibration. Here, the structure 210 can be manufactured inexpensively by being light and thin, and the constraint layer 222 implemented with the same material as the structure 210 can also be manufactured inexpensively by being light and thin.

According to one embodiment of the present invention, the structure 210 and the constraint layer 222 are preferably implemented with FR-4, a material made of glass fiber and epoxy, but are not necessarily limited thereto.

According to one embodiment of the present invention, the confinement layer 222 may be implemented with a material different from that of the structure 210, and the bending behavior of the structure 210 may be sufficiently required to implement high damping. Accordingly, if the constraint layer 222 is made of a high-rigidity material, the effect may be greatly reduced.

According to one embodiment of the present invention, the confinement layer 222 may be formed as the thinnest layer possible. Specifically, the reinforcement portion 220 can bond the constraint layer 222, which is formed as thin as possible, in several layers through the attenuation layer 224, and the constraint layer ( 222) can be formed as the thinnest layer possible, but is not necessarily limited to this.

The damping layer 224 may form viscoelastic properties. Additionally, the damping layer 224 may be implemented as a viscoelastic tape. Here, the viscoelastic tape is the damping layer 224, and can represent a tape that exhibits liquid properties and solid properties simultaneously when force is applied to an object.

The viscoelastic tape has a viscoelastic material and may be of various materials that can adhere the laminated constraint layer 222. Preferably, the viscoelastic tape is implemented as 3M966, which is used for various materials that require high adhesion, heat resistance, moisture resistance, solvent resistance, etc. Here, in addition to the above-mentioned properties, the 3M966 tape satisfies the outgassing characteristics of space application standards and is a product with a track record of space mission application (space heritage). It must meet the outgassing standards in order to be used in space. You can.

Therefore, a plurality of yokes 200 of the deployable solar panel 10 are stacked, and the reinforcing portion 220 connects the structure 210 with a tape having viscoelastic properties, resulting in a vibration response in the form of bending behavior that occurs when vibration is transmitted. Vibration can be effectively attenuated due to friction between the viscoelastic double-sided tape and the structure 210.

The yoke 200 can improve its rigidity and damping performance by adjusting the number of stacks of the constraint layer 222 and the damping layer 224.

According to one embodiment of the present invention, the number of stacks of the constraint layer 222 and the attenuation layer 224 may vary depending on the environment and needs in which the deployable solar panel 10 or the yoke 200 is used.

The stiffness and damping capacity of the yoke 200 increases depending on the number of restraint layers 222 and damping layers 224, and the number of restraint layers 222 and damping layers 224 can be adjusted as needed. You can.

When the vibration response in the form of bending behavior that occurs when vibration is transmitted is greater than the critical stress of the structure 210, the yoke 200 exhibits a damping effect to absorb vibration by causing a phase change to restore the original shape, and the critical stress In the case of small displacements below, vibration may be attenuated by friction between the damping layer 224, which has viscoelastic properties, and the constraint layer 222, which is made of the same material as the structure 210.

According to one embodiment of the present invention, the damping performance of the yoke 200 of the deployable solar panel 10 is improved as the number of stacks of the reinforcement portion 220 increases, and the number of stacks is increased as necessary. It can be used by adjusting .

According to one embodiment of the present invention, the shape of the reinforcement portion 200 will be implemented as shown in Figure 3 in order to minimize the weight and volume while alleviating the vibration of the structure 210 with high damping characteristics implemented by friction. You can.

According to one embodiment of the present invention, the yoke 200 of the deployable solar panel 10 can be fixed by connecting the structure 210 and the constraint layer 222 through the attenuation layer 224, and is necessarily limited to this. It doesn't work.

Referring to FIG. 2, the yoke 200 is formed in a polygonal shape and can connect the satellite 100 and the solar panel 300. At this time, the yoke 200 is formed in an integrated polygonal shape, and may be connected to the solar panel 300 on the side opposite to the part connected to the satellite 100. At this time, the yoke 200 may be connected to the solar panel 300 through the battery connection interfaces 410 and 420, and may be connected to the satellite 100 through the satellite connection interface 430.

Additionally, the deployable solar panel 10 may have an empty space surrounded by the satellite 100, the yoke 200, and the solar panel 300. At this time, the empty space may be formed in a polygonal shape. For example, in FIG. 2, a hexagonal empty space may be formed, and in FIG. 3, a square-shaped empty space may be formed. Here, the empty space has the effect of reducing the weight of the yoke 200 and minimizing unnecessary mass due to the low required rigidity.

According to one embodiment of the present invention, the yoke 200 may be connected to the solar panel 300 at both ends in the width direction and may be connected to the satellite 100 at one end. This is because the solar panel 300 is thin and has a large area, so a moment may occur if it is fixed in the center or only on one side. Specifically, when the yoke 200 is connected to the center of the solar panel 300 and the satellite 100, or is fixed to one side in the width direction of the solar panel 300 and connected to the satellite 100. , there is a problem that a bending moment occurs when vibration enters, and to prevent this, the yoke 200 can connect both sides in the width direction of the solar panel 300 and one side of the satellite 100. .

Referring to FIG. 3, the yoke 200 may include a first yoke 202 and a second yoke 204. At this time, the first yoke 202 and the second yoke 204 may be connected to each other through the yoke connection portion 404. Specifically, the first yoke 202 and the second yoke 204 are each formed in a square shape and are coupled to the yoke connection portion 404 at one end by a screw fastening method, and may be formed in the same shape. At this time, the yoke connection part 404 may be connected to the satellite 100 and the satellite connection part 402.

The satellite connection part 402 is connected to one side of the yoke connection part 404, and the part connected to the satellite 100 may vary depending on the shape of the satellite 100.

According to one embodiment of the present invention, the first yoke 202 and the second yoke 204 may be fixed to form a polygonal shape when assembled with the yoke connection portion 404 and the solar panel 300, respectively. For example, the yoke 200 is located between the satellite 100 and the solar panel 300, and has a first yoke on both sides centered on the yoke connection portion 404 positioned to correspond to the central portion of the solar panel 300. (202) and the second yoke (204) may be formed to be assembled. At this time, the first yoke 202 and the second yoke 204 are each connected to one side of the yoke connection portion 404 formed at a position corresponding to the center of the solar panel 300, and the opposite side is connected to the solar panel 300. ) can be connected to both ends of the width direction. Accordingly, the first yoke 202 and the second yoke 204 can connect the satellite 100 and the solar panel 300 to form a polygonal shape.

Compared to the existing integrated, single-material yoke, a certain thickness must be maintained to maintain minimum rigidity. According to one embodiment of the present invention, the yoke 200 of the present invention has a large damping effect and does not require great rigidity, so it can be assembled thinly and used, and while the yoke 200 is used as an integrated piece, the first yoke 202 ) and the second yoke (204) can be used separately to maximize the damping effect.

Therefore, referring to FIGS. 2 and 3, the yoke 200 is formed in a structure in which the base 210, the confinement layer 222, and the attenuation layer 224 are stacked together to form the satellite 100 and the solar panel 300. It can be implemented to connect and form a polygonal shape.

Figure 4 is a flowchart showing a method of manufacturing a deployable solar panel using a yoke with viscoelastic properties according to an embodiment of the present invention. The manufacturing method of the deployable solar panel is performed to manufacture the deployable solar panel, and descriptions that overlap with the detailed description of the deployable solar panel will be omitted.

The manufacturing method of a high-damping multilayer printed circuit board using viscoelastic properties includes the steps of creating a yoke by seating a structure with a hyperelastic effect on both sides of the structure and a reinforcement part that dampens vibration input from the outside (S410), and creating a yoke around the planet. The diagram includes a step (S420) of interconnecting the satellite and the solar panel mounted on the outside of the satellite to convert light energy into electrical energy through a yoke.

The step (S510) of creating a yoke by seating a structure with a superelastic effect on both sides of the structure and a reinforcing part that dampens vibration input from the outside includes a constraint layer made of the same material as the structure and a damping layer that forms viscoelastic properties. A yoke can be created by seating the reinforcing parts created by cross-lamination into the structure.

In Figure 4, it is shown that each process is executed sequentially, but this is only an illustrative explanation, and those skilled in the art can change the order shown in Figure 4 and execute it without departing from the essential characteristics of the embodiments of the present invention. Alternatively, it may be applied through various modifications and modifications, such as executing one or more processes in parallel or adding other processes.

Figures 5 to 11 are diagrams showing experimental results according to the type of yoke in a deployable solar panel according to an embodiment of the present invention.

Figure 5 is a diagram showing a test configuration for deriving a second test result according to the number of layers of the reinforcing part of the yoke having viscoelastic properties according to an embodiment of the present invention, and Figure 6 is a non-contact diagram according to an embodiment of the present invention. This is a diagram showing the configuration of the exciter.

Referring to FIG. 5, the yoke characteristic test consists of a yoke 200 and a solar panel 300, and for the test, a gravity compensation device 20, a displacement sensor 21, and a non-contact vibration exciter 22. , a power amplifier 23, a function generator 24, an oscilloscope 25, a power supply 26, and a processor 28. The configuration of the yoke characteristic test may omit some components or additionally include other components among the various components shown as examples.

The gravity compensation device (0g Compensation Device) 20 is a device for compensating for 0g, the gravity of space, and can enable experiments to be conducted in an environment such as space.

The displacement sensor 21 can measure the distance or position that an object has moved.

Noncontact Vibration Exciter (22) can generate vibration without contact.

The power amplifier 23 can supply power.

The function generator 24 can generate frequencies with arbitrary waveforms.

The oscilloscope 25 can output changes in input voltage and show changes so that changes can be observed.

The power supply (Power Supply) 26 can supply the voltage and current necessary to operate the experiment.

The processor 28 may receive the experimental results, provide the experimental results, and provide results calculated from the experimental results. For example, the processor 28 may be implemented as a PC, but is not necessarily limited thereto.

Referring to FIG. 6, the Noncontact Vibration Exciter (22) includes a permanent magnet (27) and a solenoid coil (29).

Permanent Magnet (27) refers to a magnet that maintains a strong magnetization state for a long time.

Solenoid coil (29) represents a uniformly wound long cylindrical coil.

Figure 7 is a diagram showing yokes for testing yoke characteristics according to an embodiment of the present invention.

Figure 7 (a) shows a first yoke made of aluminum, Figure 7 (b) shows a yoke made of SMA material, and Figure 7 (c) shows a yoke made of SMA material forming multiple layers, Figure 7(d) shows the specifications of the first yoke, second yoke, and third yoke.

Yoke property tests can be performed for each yoke material.

Referring to FIG. 7, the first yoke may be made of an aluminum material, the second yoke may be made of an SMA material having a superelastic effect, and the third yoke may be made of an SMA material having a superelastic effect that forms multiple layers. It can be done.

Referring to (d) of FIG. 7, the first yoke is made of aluminum and may be formed as layer 0. Additionally, the first yoke may be formed to have a thickness of 1.1 mm and a dimension of 249 x 249 x 1.1 mm. This is only an example used in the following experiment and is not limited thereto.

The second yoke is made of superelastic SMA and can be formed as a zero layer. Additionally, the second yoke may be formed to have a thickness of 1.5 mm and a dimension of 249 x 249 x 1.5 mm. This is only an example used in the following experiment and is not limited thereto.

The third yoke is formed of a restraining layer 222 and FR-4 made of a material made of glass fiber and epoxy, or of FR-4 made of a material made of glass fiber and epoxy and a superelastic SMA, and has 2, 4, or 6 layers. can be formed. Additionally, the second yoke may be formed with a thickness of 2.1 mm, 2.7 mm, and 3.1 mm for each layer, and may be formed with a dimension of 249 This is only an example used in the following experiment and is not limited thereto.

The yoke shown in FIG. 7 is only an example for the following yoke characteristic test and is not limited to this.

Yoke characteristic tests include free damping test, sine sweep test, and temperature test.

Figure 8 is a diagram showing the results of a free decay test according to an embodiment of the present invention.

Figure 8 (a) is a diagram showing displacement over time according to an embodiment of the present invention, and Figure 8 (b) is a diagram showing initial displacement according to an embodiment of the present invention. This is a diagram showing the damping ratio.

The free damping test has a displacement application condition of 1 cm to 4 cm.

Referring to Figure 8, the free damping test is the result of the free damping test for each first yoke, second yoke, and third yoke, and it can be seen that the damping performance improves as the number of stacks of the yoke applied with SMA increases compared to the yoke applied with aluminum. You can.

In addition, based on the 4cm displacement application condition, it can be seen that in the case of the third yoke (stacked in six layers), the damping ratio is improved by about 4.6 times compared to the first yoke.

Figures 9 and 10 are diagrams showing the results of the Sine Sweep test according to an embodiment of the present invention.

The Sine Sweep test refers to a test that is performed in a specific frequency range by increasing or decreasing the excitation frequency according to a given amplitude.

The Sine Sweep test has a frequency application condition of 1Hz to 15Hz.

Figure 9 is a diagram showing the results of the first Sine Sweep test according to an embodiment of the present invention.

Figure 9 (a) is a diagram showing displacement according to time according to an embodiment of the present invention, and Figure 9 (b) is a diagram showing displacement according to frequency (Frequency) according to an embodiment of the present invention. This is a drawing showing displacement.

Referring to FIG. 9, the first Sine Sweep test confirms that the displacement in both the first and second modes decreases as the number of stacks of the third yoke increases compared to the second yoke.

In particular, in the case of the second mode, it can be seen that the displacement of the third yoke (stacked with 6 layers) is reduced by about 6.8 times compared to the second yoke (stacked with 0 layers).

Figure 10 is a diagram showing the results of a second Sine Sweep test according to an embodiment of the present invention.

Figure 10 (a) is a diagram showing the modal frequency according to the type of yoke according to an embodiment of the present invention, and Figure 10 (b) is a diagram showing the modal frequency according to the type of yoke according to an embodiment of the present invention. This is a diagram showing modal damping.

Modal means following a certain 'mode'.

Referring to Figure 10, it can be seen that the values of modal frequency and modal damping improve as the number of stacks increases.

In particular, in the case of the second mode, it can be seen that the modal damping value of the third yoke (stacked with 6 layers) is improved by about 10 times compared to the second yoke (stacked with 0 layers).

Figure 11 is a diagram showing the results of a temperature test according to an embodiment of the present invention.

The temperature test has a temperature condition of -25℃ to 55℃ and a displacement of 4 cm.

Referring to Figure 11, due to the characteristics of viscoelastic materials and superelastic shape memory alloy (SMA), some changes in properties depending on temperature are observed, but the damping ratio of the 6-layer lamination condition is about 1.6 times higher than that of the 2-layer lamination condition at all test temperatures. You can check it.

Therefore, it can be experimentally proven (free damping, sine sweep, temperature test) that the superelastic SMA layered yoke structure of the present invention is effective in reducing vibration in elastic mode for solar panels.

In addition, it can be confirmed that the deployable solar panel 10 has high damping characteristics under the same displacement conditions compared to the yoke applied to a general metal material (Al), and from the Sine Sweep results, it has excellent damping characteristics for the secondary mode of the solar panel. It can be observed, and from the temperature test results, it can be confirmed that as the number of layers increases, higher damping performance is realized within the same temperature range.

Even though all the components constituting the embodiments of the present invention described above are described as being combined or operated in combination, the present invention is not necessarily limited to these embodiments. That is, as long as it is within the scope of the purpose of the present invention, all of the components may be operated by selectively combining one or more of them.

The above description is merely an illustrative explanation of the technical idea of the present invention, and various modifications, changes, and substitutions can be made by those skilled in the art without departing from the essential characteristics of the present invention. will be. Accordingly, the embodiments disclosed in the present invention and the accompanying drawings are not intended to limit the technical idea of the present invention, but are for illustrative purposes, and the scope of the technical idea of the present invention is not limited by these embodiments and the attached drawings. . The scope of protection of the present invention should be interpreted in accordance with the claims below, and all technical ideas within the equivalent scope should be construed as being included in the scope of rights of the present invention.

10: Deployable solar panel
100: Satellite body
200: York
210: base
220: reinforcement part
222: Restraint layer
224: Attenuation layer
300: solar panel

Claims (13)

In a deployable solar panel mounted on a satellite orbiting a planet,
A solar panel mounted outside the satellite to convert light energy into electrical energy; and
It includes a yoke that interconnects the satellite and the solar panel,
The yoke has reinforcement parts laminated on both sides of the base connecting the satellite and the solar panel to attenuate vibration transmitted to the solar panel,
The yoke includes a first yoke and a second yoke respectively connected to both sides of a yoke connection portion connected to the satellite through a satellite connection portion at a position corresponding to the center of the solar panel,
The first yoke and the second yoke have opposite sides connected to the yoke connection part connected to both ends in the width direction of the solar panel, and are assembled with the solar panel and the yoke connection part by screwing each other, and are installed on the inside. A deployable solar panel characterized by being implemented in a polygonal form forming an empty space. According to paragraph 1,
The yoke is,
It includes the base having a superelastic effect and the reinforcement part that dampens vibration input from the outside,
The reinforcement part,
a restraint layer made of the same material as the base; and
A deployable solar panel comprising an attenuating layer that forms viscoelastic properties. According to paragraph 2,
The reinforcement part,
A deployable solar panel, characterized in that a plurality of restraining layers are cross-stacked and fixed on both sides of the base using a damping layer that forms the viscoelastic properties to attenuate vibration against microscopic vibrations below the critical stress. According to paragraph 2,
The yoke is,
A deployable solar panel, characterized in that rigidity and damping performance are improved by adjusting the number of stacks of the constraint layer and the damping layer. According to paragraph 2,
The yoke is,
When the vibration response in the form of bending behavior that occurs when vibration is transmitted is a large displacement greater than the critical stress of the base, a phase change to restore the original shape occurs, showing a damping effect to absorb vibration,
In the case of a small displacement below the critical stress, a deployable solar panel characterized in that vibration is attenuated by friction between a damping layer forming viscoelastic properties and a restraining layer made of the same material as the base. According to paragraph 2,
The yoke is,
Connected to the satellite at a position corresponding to the center of the solar panel, connected to the solar panel at both ends in the width direction of the solar panel,
Forming an empty space surrounded by the satellite, the yoke, and the solar panel,
A deployable solar panel, characterized in that the empty space is formed in a polygonal shape. delete According to paragraph 1,
The base is,
A deployable solar panel characterized by being formed of superelastic shape memory alloy (SMA, Shape Memory Alloy). In the yoke that interconnects the satellite and the solar panel,
a base connecting one end of the satellite and one end of the solar panel; and
It includes the base having a superelastic effect and a reinforcing part that dampens vibration input from the outside,
The reinforcement portion includes a constraint layer made of the same material as the base; and a damping layer that forms viscoelastic properties,
The yoke includes a first yoke and a second yoke respectively connected to both sides of a yoke connection portion connected to the satellite through a satellite connection portion at a position corresponding to the center of the solar panel,
The first yoke and the second yoke have opposite sides connected to the yoke connection part connected to both ends in the width direction of the solar panel, and are assembled with the solar panel and the yoke connection part by screwing each other, and are installed on the inside. A yoke characterized by being implemented in a polygonal form forming an empty space. According to clause 9,
The yoke is,
Rigidity and damping performance are improved by adjusting the number of stacks of the constraint layer and the damping layer, and a plurality of constraint layers are cross-stacked and fixed on both sides of the base using the damping layer that forms the viscoelastic properties,
A yoke, wherein the base and the confinement layer are formed of superelastic shape memory alloy (SMA, Shape Memory Alloy). According to clause 9,
The yoke is,
If the vibration response in the form of bending behavior that occurs when the vibration is transmitted is a large displacement greater than the critical stress of the base, a phase change to restore the original shape occurs, showing a damping effect to absorb vibration, and if the small displacement is less than the critical stress, A yoke characterized in that vibration is damped by friction between a damping layer forming viscoelastic properties and a restraining layer made of the same material as the base. According to clause 9,
The yoke is,
Connected to the satellite at a position corresponding to the center of the solar panel, connected to the solar panel at both ends in the width direction of the solar panel,
Forming an empty space surrounded by the satellite, the yoke, and the solar panel,
A yoke wherein the empty space is formed in a polygonal shape. In the method of manufacturing a deployable solar panel using a solar panel deployable satellite orbiting a planet,
Creating a yoke by seating reinforcing parts that dampen vibration input from the outside on both sides of a base having a superelastic effect; and
Comprising the step of interconnecting a satellite revolving around a planet and a solar panel mounted outside the satellite to convert light energy into electrical energy through the yoke,
The step of creating the yoke is by seating the reinforcing part created by cross-lamination of a restraining layer made of the same material as the base and a damping layer forming viscoelastic properties on the base, at a position corresponding to the center of the solar panel. Generating a yoke including a first yoke and a second yoke respectively connected to both sides of the yoke connection connected to the satellite through the satellite connection,
The first yoke and the second yoke have opposite sides connected to the yoke connection part connected to both ends in the width direction of the solar panel, and are assembled with the solar panel and the yoke connection part by screwing each other, and are installed on the inside. A method of manufacturing a deployable solar panel, characterized in that it is implemented in a polygonal form forming an empty space.

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