CN116534287A - A locking and releasing mechanism based on shape memory reversible glue - Google Patents

Abstract

The invention relates to the field of aerospace technology, in particular to a locking and releasing mechanism based on shape memory reversible glue. An embodiment of the present invention provides a locking and releasing mechanism based on reversible glue, which is used for locking and releasing aerospace devices. The aerospace device is provided with a groove, and the locking and releasing mechanism is arranged in the groove. The locking and releasing mechanism includes a spring, a piston and Shape memory polymer reversible glue, the piston is set in the groove by the spring, and the shape memory polymer reversible glue is set on the surface of the piston away from the spring; when it needs to be locked, multiple pistons respectively located on different aerospace devices pass through the shape The memory polymer reversible glue is bonded to realize the locking function; when it needs to be released, the shape memory polymer reversible glue is heated to make the shape memory polymer reversible glue lose its dry viscosity, and the pistons on different aerospace devices are released to realize the release function. The invention can provide a locking and releasing mechanism with simple mechanism, small volume, small impact, light weight and low cost.

Description

A locking and releasing mechanism based on shape memory reversible glue

technical field

The invention relates to the field of aerospace technology, in particular to a locking and releasing mechanism based on shape memory reversible glue.

Background technique

The larger mechanisms in the spacecraft cannot be placed directly on the satellite platform, such as solar cells, antennas and other structures, so large mechanisms must be folded to reduce the occupied volume. The locking and releasing device is a device for retracting large mechanisms , before the spacecraft reaches the predetermined orbit, the locking and releasing device is used to gather the large structure, and the locking and releasing device is used to release the large structure after the spacecraft is launched to the predetermined orbit.

In related technologies, most of the spacecraft locking and releasing devices use explosive bolts and other pyrotechnics. Although this kind of device has high reliability, the explosion in the process will cause a greater impact on the system, especially for small satellites, etc. On a small-mass platform, the impact will have a great impact on the attitude and control of the satellite platform. At the same time, pyrotechnics are generally one-time use, and it is not allowed to test whether they can work normally before use.

Contents of the invention

Embodiments of the present invention provide a locking and releasing mechanism based on shape memory reversible glue, which can provide a locking and releasing mechanism with simple mechanism, small volume, small impact, light weight and low cost.

An embodiment of the present invention provides a locking and releasing mechanism based on shape memory reversible glue, which is used for locking and releasing aerospace devices. The aerospace device is provided with a groove, the locking and releasing mechanism is arranged in the groove, and the lock The tight release mechanism includes a spring, a piston and a shape memory polymer reversible glue, the piston is set in the groove by a spring, and the shape memory polymer reversible glue is arranged on the surface of the piston away from the spring;

When locking is required, a plurality of the pistons respectively located on different aerospace devices are pasted by the shape memory polymer reversible glue, and then the locking function is realized, and the spring is in a stretched state at this time;

When release is required, the shape memory polymer reversible adhesive is heated to make the shape memory polymer reversible adhesive lose its dry viscosity, 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 the heating film is energized to provide heat for the shape memory polymer reversible glue.

In a possible design, pulleys are provided on both sides of the piston, and the pulleys are used to reduce resistance so that the spring pulls the piston apart.

In a possible design, the piston is one of circular, square and rectangular.

In a possible design, the preparation material of the shape memory polymer reversible adhesive is a thermosetting shape memory polymer. When the temperature is lower than the glass transition temperature, the shape memory polymer reversible adhesive is in a rigid state, and the shape memory polymer reversible The pullout force of the glue on the substrate is 10-200N/cm ² , when the temperature is lower than the glass transition temperature, the shape memory reversible glue is in a flexible state, the dry viscosity is reduced, and the peel strength is not more than 0.1MPa. The spring provides a peeling force greater than 0.1MPa.

In a possible design, the preparation material of the shape-memory reversible glue includes at least one of shape-memory epoxy resin and shape-memory polyurethane.

In a possible design, the aerospace device includes a solar panel, and the two solar panels are connected by a deformed hinge, the deformed hinge is made of a shape memory material, and the deformed hinge includes a first shape and The second shape, the first shape is U-shape, the second shape is straight-line shape, and the two folded solar panel bodies are opened by driving the deformation hinge to change from the first shape to the second shape.

In a possible design, the deformation hinge is provided with the heating film, and the heating film is used to provide heat for the deformation hinge to drive its deformation.

In a possible design, the deformation hinge is a curved surface structure, two clamps are arranged at both ends of the deformation hinge, and the two clamps are respectively fixed on the two solar panel bodies.

In a possible design, the preparation material of the deformable hinge is a shape-memory polymer composite material, and the shape-memory polymer composite material includes a polymer matrix and a reinforcement.

In a possible design, the reinforcing body includes at least one of carbon fiber, glass fiber, Kevlar fiber and aramid fiber.

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

In order to prevent the locking and releasing mechanism from occupying the space of the aerospace device, grooves are provided on the mutually adhering surfaces of the aerospace device in a locked state, and the locking and releasing mechanism is arranged in the groove. A piston is set in the groove, and the piston is fixed in the groove by a spring. When applying force to the spring, the piston is located in the middle of the groove, and the surface of the piston facing the outside of the groove is provided with a shape-memory polymer reversible glue, and the piston is pulled to make the spring in the In the stretched state, the two pistons are bonded together by the shape memory polymer reversible glue on the two pistons. After the two pistons are bonded, the locking function of the aerospace device is realized. In addition, the piston is fixed on the aerospace device through the spring. In this way, when the pistons of different aerospace devices are bonded together, the displacement of the aerospace device can be allowed to a certain extent in the locked state, and then it can adapt to the space flight. Complex sports environment. If a rigid locking mechanism is used to fasten, during the spaceflight process, the aerospace device will bear a large sudden force, and there is a risk of damage and fracture. When the aerospace device is released, the piston will be quickly stored in the groove under the tension of the spring, which will not affect the overall shape of the aerospace device, and at the same time, the piston will not fall off to form space junk.

It should be noted that, compared with the locking and releasing mechanism made of pyrotechnics, the product provided by this application can be repeatedly tested on the ground to test its locking and releasing effect, and there is basically no impact or a small impact when released, which is suitable for aerospace. Devices are more secure.

Description of drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following will briefly introduce the drawings that need to be used in the description of the embodiments or the prior art. Obviously, the accompanying drawings in the following description are For some embodiments of the present invention, those skilled in the art can also obtain other drawings based on these drawings without creative work.

Fig. 1 is a schematic structural view of a locking release mechanism based on reversible glue provided in an embodiment of the present invention in a locked state;

Fig. 2 is a schematic structural view of a locking release mechanism based on reversible glue provided in an embodiment of the present invention in a released state;

Fig. 3 is a schematic structural view of a lockable and releasable solar panel provided by an embodiment of the present invention;

Fig. 4 is a schematic structural view of another lockable and releasable solar panel provided by an embodiment of the present invention;

Fig. 5 is a schematic structural diagram of a deformable hinge provided by an embodiment of the present invention.

In the picture:

1-piston; 2-spring; 3-shape memory polymer reversible glue; 4-pulley; 5-solar panel body; 6-deformation hinge; 7-fixture.

Detailed ways

In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments It is a part of the embodiments of the present invention, but not all of them. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative work belong to the protection of the present invention. scope.

In the description of the embodiments of the present invention, unless otherwise specified and limited, the terms "first" and "second" are only used for the purpose of description, and cannot be understood as indicating or implying relative importance; unless otherwise specified Or to explain, the term "plurality" refers to two or more; the terms "connection", "fixation" and so on should be understood in a broad sense, for example, "connection" can be a fixed connection or a detachable connection, or Connected integrally, or electrically; either directly or indirectly through an intermediary. Those of ordinary skill in the art can understand the specific meanings of the above terms in the present invention according to specific situations.

In the description of this specification, it should be understood that the orientation words such as "up" and "down" described in the embodiments of the present invention are described from the angles shown in the drawings, and should not be interpreted as a description of the embodiments of the present invention. limited. Furthermore, in this context, it also needs to be understood that when it is mentioned that an element is connected "on" or "under" another element, it can not only be directly connected "on" or "under" another element, but can also To be indirectly connected "on" or "under" another element through an intervening element.

As shown in Figures 1 to 5, the embodiment of the present invention provides a locking and releasing mechanism based on shape memory reversible glue, which is used for locking and releasing aerospace devices. The aerospace device is provided with a groove, and the locking and releasing mechanism is arranged in the groove , the lock release mechanism includes a spring 2, a piston 1 and a shape memory polymer reversible glue 3, the piston 1 is set in the groove by the spring 2, and the shape memory polymer reversible glue 3 is arranged on the surface of the piston 1 away from the spring 2;

When locking is required, the multiple pistons 1 respectively located on different aerospace devices are pasted by the shape memory polymer reversible glue 3, thereby realizing the locking function, and the spring 2 is in a stretched state at this time;

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 viscosity, 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 the heating film is energized to provide heat for the shape memory polymer reversible glue 3 .

In order to prevent the locking and releasing mechanism from occupying the space of the aerospace device, grooves are provided on the mutually adhering surfaces of the aerospace device in a locked state, and the locking and releasing mechanism is arranged in the groove. A piston 1 is set in the groove, and the piston 1 is fixed in the groove by a spring 2. When applying force to the spring 2, the piston 1 is located in the middle of the groove, and the surface of the piston 1 facing the outside of the groove is provided with a shape memory polymer reversible glue 3. Pull the piston 1 to make the spring 2 in a stretched state, and then bond the two pistons 1 through the shape memory polymer reversible glue 3 on the two pistons 1. After the two pistons 1 are bonded, the lock of the aerospace device is realized. tight function. In addition, the piston 1 is fixed on the aerospace device through the spring 2. With this arrangement, when the piston 1 of different aerospace devices is bonded together, the displacement of the aerospace device can be allowed to a certain extent in the locked state, and then it can adapt to aerospace Complex motion environment in flight. If a rigid locking mechanism is used to fasten, during the spaceflight process, the aerospace device will bear a large sudden force, and there is a risk of damage and fracture. When the aerospace device is released, the piston 1 will be quickly accommodated in the groove under the tension of the spring 2, which will not affect the overall shape of the aerospace device, and at the same time, the piston 1 will not fall off to form space junk.

It should be noted that, compared with the locking and releasing mechanism made of pyrotechnics, the product provided by this application can be repeatedly tested on the ground to test its locking and releasing effect, and there is basically no impact or a small impact when released, which is suitable for aerospace. Devices are more secure.

In some embodiments of the present invention, pulleys 4 are provided on both sides of the piston 1 , and the pulleys 4 are used to reduce resistance so that the spring 2 pulls the piston 1 apart.

In this embodiment, the pulley 4 includes pins and rollers. On the one hand, the pulley 4 can reduce the sliding resistance of the piston 1, so that the spring 2 can pull the piston 1 apart. On the other hand, prevent the piston 1 from sliding and damaging the groove.

In some embodiments of the present invention, the piston 1 is one of circular, square and rectangular.

In some embodiments of the present invention, the preparation material of the shape memory polymer reversible glue 3 is a thermosetting shape memory polymer. When the temperature is lower than the glass transition temperature, the shape memory polymer reversible glue 3 is in a rigid state, and the shape memory polymer The pullout force of the reversible adhesive 3 on the substrate is 10-200N/cm2. When the temperature is lower than the glass transition temperature, the shape memory reversible adhesive is in a flexible state, the dry viscosity is reduced, and the peel strength is not greater than 0.1MPa. In the locked state, Spring 2 provides a peeling force greater than 0.1MPa.

In some embodiments of the present invention, the preparation material of the shape-memory reversible adhesive includes at least one of shape-memory epoxy resin and shape-memory polyurethane.

In some embodiments of the present invention, the aerospace device includes a solar panel body 5, and two solar panel bodies 5 are connected by a deformation hinge 6. The preparation material of the deformation hinge 6 is a shape memory material, and the deformation hinge 6 includes a first shape and a second shape. The first shape is U-shaped, and the second shape is linear. The two folded solar panel bodies 5 are opened by driving the deformation hinge 6 to change from the first shape to the second shape.

In this embodiment, the aerospace device can be a solar panel body 5 , and the controllable locking and releasing of the solar panel body 5 can be realized through the cooperation of the locking release mechanism and the deformed hinge 6 . Specifically, a deformable hinge 6 made of shape memory material is used to connect two solar panels 5 . The first shape and the second shape of the deformable hinge 6 are U-shaped and straight-line respectively. When the deformed hinge 6 is in the first shape, the two solar panel bodies 5 are folded together, and the deformed hinge 6 is driven to deform, and the deformed hinge 6 becomes a linear second shape. During the deformation process, the deformed hinge 6 drives the two solar panels to release Open. The deformation hinge 6 has simple structure, gentle and slow deformation process, small impact, light weight and low cost. During the process of deforming the hinge 6 into the second shape, the shape memory polymer reversible glue 3 is heated to make it lose its dry viscosity, and the solar panel body 5 is opened in cooperation with the deformed hinge 6 .

The specific steps are:

Before the satellite is launched, the spring 2 in the groove is pre-strained to generate tensile stress, and the strong dry viscosity of the shape memory polymer reversible glue 3 and the stress balance of the spring 2 are used for locking. The deformed hinge 6 is linear in its initial state, and its stiffness decreases under heating, so that its shape is bent 180° to form a U shape, and then the temperature is lowered to maintain the U-shaped bending state to keep the solar panel in a folded state.

After the satellite is put into orbit, the satellite platform receives the command to deploy the solar panels, the heating film of the shape memory polymer reversible glue 3 receives the heating command and starts to heat, the shape memory polymer reversible glue 3 produces a phase change and the dry viscosity decreases, and the pretension of the spring 2 will be The shape memory polymer reversible adhesive 3 is pulled apart to release the solar panel body 5 .

The heating film of the deformable hinge 6 receives a heating command and the temperature rises, so that it gradually returns from the U-shaped folded state to the linear state to drive the solar panel to expand.

It should be noted that when the shape memory polymer reversible adhesive 3 is lower than the glass transition temperature, it has high dry viscosity. After the shape memory polymer reversible adhesive 3 is heated, the dry viscosity of the shape memory polymer reversible adhesive 3 decreases when the temperature is higher than the glass transition temperature.

It can be understood that the groove is arranged at the corner away from the end of the deformable hinge 6 , so that the piston 1 can generate a larger moment after being adhered by the shape memory polymer reversible glue 3 .

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.

In some embodiments of the present invention, the deformation hinge 6 is provided with a heating film for providing heat to the deformation hinge 6 to drive its deformation.

In some embodiments of the present invention, the deformed hinge 6 is a curved surface structure, and two clamps 7 are provided at both ends of the deformed hinge 6 , and the two clamps 7 are respectively fixed on the two solar panel bodies 5 .

In this embodiment, the deformed hinge 6 with curved surface structure is more convenient to be deformed into a straight line or a U shape.

In some embodiments of the present invention, the preparation material of the deformable hinge 6 is a shape-memory polymer composite material, and the shape-memory polymer composite material includes a polymer matrix and a reinforcement.

In some embodiments of the present invention, the reinforcement includes at least one of carbon fiber, glass fiber, Kevlar fiber and aramid fiber.

Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that: it can still be Modifications are made to the technical solutions described in the foregoing embodiments, or equivalent replacements are made to some of the technical features; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the various embodiments of the present invention.

Claims (10)

1. The locking release mechanism based on the shape memory reversible glue is characterized by being used for locking and releasing a spaceflight device, wherein the spaceflight device is provided with a groove, the locking release mechanism is arranged in the groove and comprises a spring (2), a piston (1) and a shape memory polymer reversible glue (3), the piston (1) is arranged in the groove through the spring (2), and the shape memory polymer reversible glue (3) is arranged on the surface, away from the spring (2), of the piston (1);

when locking is needed, a plurality of pistons (1) respectively positioned on different aerospace devices are attached through the shape memory polymer reversible adhesive (3), so that a locking function is realized, and the springs (2) are in a stretching state;

when the release is needed, heating the shape memory polymer reversible glue (3) to enable the shape memory polymer reversible glue (3) to lose dry viscosity, and releasing pistons on different aerospace devices under the stretching action of a spring so as to realize the release function;

a heating film is arranged in the groove, and the heating film is electrified to provide heat for the shape memory polymer reversible glue (3).

2. The lock release mechanism according to claim 1, characterized in that pulleys (4) are provided on both sides of the piston (1), the pulleys (4) being used to reduce the resistance in order for the spring (2) to pull the piston (1) apart.

3. The lock release mechanism of claim 1 wherein the piston is one of circular, square, rectangular.

4. The lock release mechanism according to claim 1, wherein the shape memory polymer reversible glue (3) is made of a thermosetting shape memory polymer, and when the temperature is lower than the glass transition temperature, the shape memory polymer reversible glue (3) is in a rigid state, and the pulling force of the shape memory polymer reversible glue (3) to the substrate is 10-200N/cm ² When the temperature is lower than the glass transition temperature, the shape memory reversible glue is in a flexible state, the dry viscosity is reduced, the peeling strength is not more than 0.1MPa, and in a locking state, the spring (2) provides peeling force of more than 0.1 MPa.

5. The lock release mechanism of claim 1 wherein the shape memory reversible glue is made of a material comprising at least one of a shape memory epoxy and a shape memory polyurethane.

6. The locking and releasing mechanism according to claim 1, wherein the aerospace device comprises solar panels (5), two solar panels (5) are connected through a deformation hinge (6), the preparation material of the deformation hinge (6) is a shape memory material, the deformation hinge (6) comprises a first shape and a second shape, the first shape is U-shaped, the second shape is linear, and the folded two solar panels (5) are opened by driving the deformation hinge (6) from the first shape to the second shape.

7. The lock release mechanism according to claim 6, characterized in that the deformation hinge (6) is provided with the heating film for providing heat to the deformation hinge (6) to drive its deformation.

8. The locking and releasing mechanism according to claim 6, wherein the deformation hinge (6) has a curved surface structure, two clamps (7) are provided at both ends of the deformation hinge (6), and the two clamps (7) are respectively fixed on the two solar panel bodies (5).

9. The lock release mechanism according to claim 6, characterized in that the deformation hinge (6) is made of a shape memory polymer composite comprising a polymer matrix and reinforcement.

10. The lock release mechanism of claim 9 wherein the reinforcement comprises at least one of carbon fiber, glass fiber, kevlar fiber, and aramid fiber.