A locking and releasing mechanism based on shape memory reversible adhesive

Abstract

This invention relates to the field of aerospace technology, and particularly to a locking and releasing mechanism based on shape memory reversible adhesive. An embodiment of this invention provides a locking and releasing mechanism based on reversible adhesive for locking and releasing aerospace devices. The aerospace device has a groove, and the locking and releasing mechanism is disposed in the groove. The locking and releasing mechanism includes a spring, a piston, and shape memory polymer reversible adhesive. The piston is set within the groove by the spring, and the shape memory polymer reversible adhesive is disposed on the surface of the piston away from the spring. When locking is required, multiple pistons located on different aerospace devices are brought together by the shape memory polymer reversible adhesive, thereby achieving the locking function. When releasing is required, the shape memory polymer reversible adhesive is heated, causing it to lose its dry tack, releasing the pistons on the different aerospace devices, thereby achieving the release function. This invention provides a locking and releasing mechanism that is simple in structure, small in size, low in impact, lightweight, and low in cost.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and in particular to a locking and releasing mechanism based on shape memory reversible adhesive. Background Technology

[0002] Larger components in spacecraft, such as solar cells and antennas, cannot be placed directly on satellite platforms. Therefore, these large components must be folded up to reduce their volume. Locking and releasing devices are used to fold up these large components. They are used to fold up large components before the spacecraft reaches its designated orbit, and then released after the spacecraft is launched into its designated orbit.

[0003] In related technologies, most spacecraft locking and releasing devices use pyrotechnics such as explosive bolts. Although such devices have high reliability, the explosion during the process can cause a significant impact on the system, especially when used on small platforms such as small satellites. The impact can have a great impact on the attitude and control of the spacecraft platform. In addition, pyrotechnics are generally for single use and cannot be tested to ensure that they can work properly before use. Summary of the Invention

[0004] This invention provides a locking and releasing mechanism based on shape memory reversible adhesive, which is simple in structure, small in size, low in impact, light in weight and low in cost.

[0005] This invention provides a locking and releasing mechanism based on shape memory reversible adhesive for locking and releasing aerospace devices. The aerospace device is provided with a groove, and the locking and releasing mechanism is disposed in the groove. The locking and releasing mechanism includes a spring, a piston, and shape memory polymer reversible adhesive. The piston is set in the groove by the spring, and the shape memory polymer reversible adhesive is disposed on the surface of the piston away from the spring.

[0006] When locking is required, the multiple pistons located on different aerospace devices are bonded together by the shape memory polymer reversible adhesive, thereby achieving the locking function. At this time, the spring is in a stretched state.

[0007] When release is required, the shape memory polymer reversible adhesive is heated to make it lose its dry tack, and the pistons on different aerospace devices are released under the stretching action of the spring, thereby realizing the release function;

[0008] A heating film is provided in the groove, and electricity is applied to the heating film to provide heat to the shape memory polymer reversible adhesive.

[0009] In one possible design, pulleys are provided on both sides of the piston to reduce resistance so that the spring can pull the piston open.

[0010] In one possible design, the piston is one of a circle, a square, or a rectangle.

[0011] In one possible design, the material used to prepare the shape memory polymer reversible adhesive is a thermosetting shape memory polymer. When the temperature is below the glass transition temperature, the shape memory polymer reversible adhesive is in a rigid state, and the pull-out force of the shape memory polymer reversible adhesive on the substrate is 10-200 N / cm. 2 When the temperature is below the glass transition temperature, the shape memory reversible adhesive is in a flexible state, the dry tack is reduced, the peel strength is not greater than 0.1 MPa, and in the locked state, the spring provides a peel force greater than 0.1 MPa.

[0012] In one possible design, the material used to prepare the shape memory reversible adhesive includes at least one of shape memory epoxy resin and shape memory polyurethane.

[0013] In one possible design, the aerospace device includes solar panels, two of which are connected by a deformable hinge. The deformable hinge is made of shape memory material and includes a first shape and a second shape. The first shape is U-shaped and the second shape is straight. By driving the deformable hinge to change from the first shape to the second shape, the two folded solar panels are opened.

[0014] In one possible design, the deformable hinge is provided with the heating film, which provides heat to the deformable hinge to drive its deformation.

[0015] In one possible design, the deformable hinge is a curved structure, and two clamps are provided at both ends of the deformable hinge, with the two clamps respectively fixed to the two solar panels.

[0016] In one possible design, the deformable hinge is made of a shape memory polymer composite material, which includes a polymer matrix and a reinforcement.

[0017] In one possible design, the reinforcement comprises at least one of carbon fiber, glass fiber, Kevlar fiber, and aramid fiber.

[0018] Compared with the prior art, the present invention has at least the following beneficial effects:

[0019] To avoid the locking and releasing mechanism occupying space on the spacecraft, a groove is provided on the surfaces where the spacecraft fit together in the locked state, and the locking and releasing mechanism is housed in the groove. A piston is placed in the groove and fixed thereby by a spring. When force is applied to the spring, the piston is located in the center of the groove. A shape memory polymer reversible adhesive is applied to the piston's outer surface. Pulling the piston stretches the spring, and then the two pistons are bonded together by the shape memory polymer reversible adhesive. Once the two pistons are bonded, the locking function of the spacecraft is achieved. Furthermore, by fixing the piston to the spacecraft with the spring, this design allows for a certain degree of displacement of the spacecraft in the locked state, enabling it to adapt to the complex motion environment during spaceflight. If a rigid locking mechanism were used, the spacecraft would be subjected to greater sudden forces during spaceflight, posing a risk of breakage. When releasing the spacecraft, the piston quickly retracts into the groove under the spring's pull, without affecting the overall shape of the spacecraft, and the piston will not detach and become space debris.

[0020] It should be noted that, compared to locking and releasing mechanisms made of pyrotechnic materials, the product provided in this application can be repeatedly tested on the ground to test its locking and releasing effect, and the release has virtually no impact or generates minimal impact, making aerospace devices safer. Attached Figure Description

[0021] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0022] Figure 1 This is a schematic diagram of the locking and releasing mechanism based on reversible adhesive in the locking state according to an embodiment of the present invention;

[0023] Figure 2 This is a schematic diagram of the structure of a locking and releasing mechanism based on reversible adhesive in the released state according to an embodiment of the present invention;

[0024] Figure 3 This is a schematic diagram of a lockable and releaseable solar panel provided in an embodiment of the present invention;

[0025] Figure 4 This is a schematic diagram of another lockable and releaseable solar panel structure provided in an embodiment of the present invention;

[0026] Figure 5 This is a schematic diagram of a deformable hinge provided in an embodiment of the present invention.

[0027] In the picture:

[0028] 1-Piston; 2-Spring; 3-Shape memory polymer reversible adhesive; 4-Pulley; 5-Solar panel; 6-Deformable hinge; 7-Clamp. Detailed Implementation

[0029] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are some embodiments of the present invention, but not all embodiments. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the scope of protection of the present invention.

[0030] In the description of the embodiments of the present invention, unless otherwise expressly specified and limited, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance; unless otherwise specified or stated, the term "multiple" refers to two or more; the terms "connected," "fixed," etc., should be interpreted broadly. For example, "connected" can be a fixed connection, a detachable connection, an integral connection, or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand the specific meaning of the above terms in the present invention according to the specific circumstances.

[0031] In this specification, it should be understood that the directional terms such as "upper" and "lower" used in the description of the embodiments of the present invention are used to describe the angles shown in the accompanying drawings and should not be construed as limiting the embodiments of the present invention. Furthermore, in the context, it should also be understood that when it is mentioned that one element is connected "upper" or "lower" to another element, it can be directly connected to the other element "upper" or "lower," or indirectly connected to the other element "upper" or "lower" through an intermediate element.

[0032] like Figures 1 to 5 As shown, this embodiment of the invention provides a locking and releasing mechanism based on shape memory reversible adhesive for locking and releasing aerospace devices. The aerospace device is provided with a groove, and the locking and releasing mechanism is disposed in the groove. The locking and releasing mechanism includes a spring 2, a piston 1 and shape memory polymer reversible adhesive 3. The piston 1 is set in the groove by the spring 2, and the shape memory polymer reversible adhesive 3 is disposed on the surface of the piston 1 away from the spring 2.

[0033] When locking is required, multiple pistons 1 located on different aerospace devices are bonded together by shape memory polymer reversible adhesive 3 to achieve the locking function. At this time, the spring 2 is in a stretched state.

[0034] When release is required, the shape memory polymer reversible adhesive 3 is heated, causing the shape memory polymer reversible adhesive 3 to lose its dry stickiness. Under the stretching action of the spring, the pistons on different aerospace devices are released, thereby realizing the release function.

[0035] A heating film is installed inside the groove, and electricity is supplied to the heating film to provide heat for the shape memory polymer reversible adhesive 3.

[0036] To avoid the locking and releasing mechanism occupying space on the aerospace components, a groove is provided on the surfaces of the components that are in contact with each other when locked. The locking and releasing mechanism is housed in this groove. A piston 1 is placed in the groove and fixed thereby by a spring 2. When force is applied to the spring 2, the piston 1 is located in the center of the groove. A shape memory polymer reversible adhesive 3 is applied to the surface of the piston 1 facing outwards from the groove. Pulling the piston 1 stretches the spring 2, and then the two pistons 1 are bonded together by the shape memory polymer reversible adhesive 3. After the two pistons 1 are bonded together, the locking function of the aerospace components is achieved. In addition, by fixing the piston 1 to the aerospace components with the spring 2, this arrangement allows for a certain degree of displacement of the aerospace components when the pistons 1 of different aerospace components are bonded together, thus enabling them to adapt to the complex motion environment during spaceflight. If a rigid locking mechanism were used, the aerospace components would be subjected to greater sudden forces during spaceflight, posing a risk of damage or breakage. When releasing the spacecraft, piston 1 will quickly retract into the groove under the pull of spring 2, without affecting the overall shape of the spacecraft. At the same time, piston 1 will not fall off and become space debris.

[0037] It should be noted that, compared to locking and releasing mechanisms made of pyrotechnic materials, the product provided in this application can be repeatedly tested on the ground to test its locking and releasing effect, and the release has virtually no impact or generates minimal impact, making aerospace devices safer.

[0038] In some embodiments of the present invention, pulleys 4 are provided on both sides of the piston 1. The pulleys 4 are used to reduce resistance so that the spring 2 can pull the piston 1 open.

[0039] In this embodiment, the pulley 4 includes a pin and a roller. On the one hand, the pulley 4 can reduce the resistance to the sliding of the piston 1, making it easier for the spring 2 to pull the piston 1 open. On the other hand, it prevents the piston 1 from sliding and damaging the groove.

[0040] In some embodiments of the present invention, the piston 1 is one of a circle, a square, or a rectangle.

[0041] In some embodiments of the present invention, the material for preparing the shape memory polymer reversible adhesive 3 is a thermosetting shape memory polymer. When the temperature is below the glass transition temperature, the shape memory polymer reversible adhesive 3 is in a rigid state, and the pull-out force of the shape memory polymer reversible adhesive 3 on the substrate is 10-200 N / cm2. When the temperature is below the glass transition temperature, the shape memory reversible adhesive is in a flexible state, the dry tack is reduced, and the peel strength is not greater than 0.1 MPa. In the locked state, the spring 2 provides a peel force greater than 0.1 MPa.

[0042] In some embodiments of the present invention, the materials used to prepare the shape memory reversible adhesive include at least one of shape memory epoxy resin and shape memory polyurethane.

[0043] In some embodiments of the present invention, the aerospace device includes a solar panel 5, and two solar panels 5 are connected by a deformable hinge 6. The deformable hinge 6 is made of shape memory material and includes a first shape and a second shape. The first shape is U-shaped and the second shape is straight. By driving the deformable hinge 6 to change from the first shape to the second shape, the two folded solar panels 5 are opened.

[0044] In this embodiment, the aerospace device can be a solar panel 5. A locking and releasing mechanism and a deformable hinge 6 are used to achieve controllable locking and releasing of the solar panel 5. Specifically, a deformable hinge 6, made of shape memory material and possessing deformability, connects two solar panels 5. The first shape and second shape of the deformable hinge 6 are U-shaped and straight, respectively. When the deformable hinge 6 is in the first shape, the two solar panels 5 are folded and fitted together, driving the deformable hinge 6 to deform into the straight second shape. During the deformation process, the deformable hinge 6 releases and opens the two solar panels. The deformable hinge 6 has a simple structure, a gentle and slow deformation process, low impact, light weight, and low cost. During the deformation of the hinge 6 into the second shape, the shape memory polymer reversible adhesive 3 is heated to remove its dry tack, allowing the solar panel 5 to open in conjunction with the deformable hinge 6.

[0045] The specific steps are as follows:

[0046] Before satellite launch, a pre-stressed tension is applied to spring 2 in the groove to generate tensile stress. The strong dry adhesion of the shape memory polymer reversible adhesive 3 balances the stress of spring 2 to achieve locking. The deformable hinge 6 is initially straight. Under heating, its stiffness decreases, causing it to bend 180° to form a U-shape. Subsequently, the temperature is reduced to maintain the U-shaped bending state to keep the solar panels folded up.

[0047] After the satellite enters orbit, the satellite platform receives the command to deploy the solar panels. The shape memory polymer reversible adhesive 3 heating film receives the heating command and begins to heat up. The shape memory polymer reversible adhesive 3 undergoes a phase change and its dry tack decreases. The pre-tension force of the spring 2 pulls the shape memory polymer reversible adhesive 3 open to release the solar panel 5.

[0048] When the heating film of the deformable hinge 6 receives a heating command, its temperature rises, causing it to gradually return from a U-shaped contracted state to a straight state, thus driving the solar panel to unfold.

[0049] It should be noted that shape memory polymer reversible adhesive 3 exhibits high dry tack when the temperature is below the glass transition temperature. However, after heat treatment, when the temperature of shape memory polymer reversible adhesive 3 exceeds the glass transition temperature, its dry tack decreases.

[0050] Understandably, the groove is located at the corner away from the deformable hinge 6, so that the piston 1 can generate a larger torque after being bonded by the shape memory polymer reversible adhesive 3.

[0051] It should be noted that when the shape memory material is a shape memory polymer composite material or a shape memory polymer, the deformation temperature of the shape memory material is the glass transition temperature.

[0052] In some embodiments of the present invention, the deformable hinge 6 is provided with a heating film, which is used to provide heat to the deformable hinge 6 to drive its deformation.

[0053] In some embodiments of the present invention, the deformable hinge 6 is a curved structure, and two clamps 7 are provided at both ends of the deformable hinge 6, which are respectively fixed on two solar panels 5.

[0054] In this embodiment, the curved structure of the deformable hinge 6 is more convenient to deform into a straight line or a U-shape.

[0055] In some embodiments of the present invention, the deformable hinge 6 is made of a shape memory polymer composite material, which includes a polymer matrix and a reinforcement.

[0056] In some embodiments of the present invention, the reinforcing material includes at least one of carbon fiber, glass fiber, Kevlar fiber and aramid fiber.

[0057] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, and not to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features; and these modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A locking and releasing mechanism based on shape memory reversible adhesive, characterized in that, For locking and releasing aerospace devices, the aerospace devices are provided with grooves, the locking and releasing mechanism is provided in the grooves, the locking and releasing mechanism includes a spring (2), a piston (1) and a shape memory polymer reversible adhesive (3), the piston (1) is set in the groove by the spring (2), and the shape memory polymer reversible adhesive (3) is provided on the surface of the piston (1) away from the spring (2); When locking is required, the pistons (1) located on different aerospace devices are bonded together by the shape memory polymer reversible adhesive (3) to achieve the locking function. At this time, the spring (2) is in a stretched state. When release is required, the shape memory polymer reversible adhesive (3) is heated to make the shape memory polymer reversible adhesive (3) lose its dry stickiness, and the pistons on different aerospace devices are released under the stretching action of the spring, thereby realizing the release function; A heating film is provided in the groove, and electricity is supplied to the heating film to provide heat to the shape memory polymer reversible adhesive (3).

2. The locking and releasing mechanism according to claim 1, characterized in that, The piston (1) is provided with pulleys (4) on both sides. The pulleys (4) are used to reduce resistance so that the spring (2) can pull the piston (1) open.

3. The locking and releasing mechanism according to claim 1, characterized in that, The piston can be one of the following: round, square, or rectangular.

4. The locking and releasing mechanism according to claim 1, characterized in that, The materials used to prepare the shape memory reversible adhesive include at least one of shape memory epoxy resin and shape memory polyurethane.

5. The locking and releasing mechanism according to claim 1, characterized in that, The aerospace device includes a solar panel (5), and two solar panels (5) are connected by a deformable hinge (6). The deformable hinge (6) is made of shape memory material. The deformable hinge (6) includes a first shape and a second shape. The first shape is U-shaped and the second shape is straight. By driving the deformable hinge (6) to change from the first shape to the second shape, the two folded solar panels (5) are opened.

6. The locking and releasing mechanism according to claim 5, characterized in that, The deformable hinge (6) is provided with the heating film, which is used to provide heat to the deformable hinge (6) to drive its deformation.

7. The locking and releasing mechanism according to claim 5, characterized in that, The deformable hinge (6) has a curved surface structure, and two clamps (7) are provided at both ends of the deformable hinge (6). The two clamps (7) are respectively fixed on the two solar panels (5).

8. The locking and releasing mechanism according to claim 5, characterized in that, The deformable hinge (6) is made of shape memory polymer composite material, which includes a polymer matrix and a reinforcement.

9. The locking and releasing mechanism according to claim 8, characterized in that, The reinforcing material includes at least one of carbon fiber, glass fiber, Kevlar fiber, and aramid fiber.

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