A spatial stretching arm based on smart composite material

Abstract

The application provides a space stretching arm based on intelligent composite material, and relates to the technical field of spacecrafts.The space stretching arm based on intelligent composite material comprises a base, a locking and releasing device, a terminal load and a stretching arm.The locking and releasing device comprises a locking buckle, a locking rope, a first locking plate, a pin head, a second locking plate and an intelligent composite material driving piece.The stretching arm is connected with the terminal load at one end and connected with the base at the other end.The first locking plate, the pin head and the second locking plate are sequentially arranged on the upper surface of the base.The two ends of the intelligent composite material driving piece are connected with the pin head and the second locking plate.The intelligent composite material driving piece drives the pin head to abut against the first locking plate.The locking rope wraps the retractable stretching arm.The intelligent composite material driving piece, the pin head and the locking buckle are used in cooperation, so that the stretching arm can be accurately unfolded when the spacecraft reaches the designated position, and the normal work of the spacecraft is not affected.

Description

Technical Field

[0001] This invention relates to the field of spacecraft technology, and more specifically, to a space extender arm based on smart composite materials. Background Technology

[0002] Space reach arms, as common deployable structures in space, have broad application prospects in areas such as large-scale space mesh antennas, deep space exploration, satellite attitude control, and solar sail masts. Before launch, the spacecraft structure is installed on the spacecraft with a relatively small volume and size. After reaching the designated position, it is deployed to the working state according to the design by receiving commands from the ground, extending the end-effectors such as detectors and magnetometers mounted on the space reach arm to the working position for space operations. Existing space reach arm structures are complex and prone to premature deployment under external forces before reaching the designated position, or failure to deploy upon reaching the designated position, which affects space operations. Summary of the Invention

[0003] The problem to be solved by the present invention is how to provide a space extension arm that is easy to deploy.

[0004] To address this, the present invention provides a space extension arm based on intelligent composite materials, comprising a base, a locking and releasing device, an end load, and an extension arm. The locking and releasing device includes a locking buckle, a locking rope, a first locking plate, a pin, a second locking plate, and an intelligent composite material drive plate. The base is used to connect to a spacecraft, and the extension arm is used to extend or retract along its length. One end of the extension arm is connected to the end load, and the other end is connected to the side of the base. The first locking plate and the second locking plate are both connected to the upper surface of the base and are arranged opposite to each other. The pin is disposed between the first locking plate and the second locking plate. Both ends of the intelligent composite material drive plate are connected to the pin and the second locking plate, respectively. The pin passes through the locking buckle and abuts against the first locking plate. One end of the locking rope is connected to the side of the base, and the other end is connected to the locking buckle. The locking rope is used to wrap the retracted extension arm.

[0005] Optionally, the locking release device further includes a locking pin, which is connected to one end of the second locking plate facing the first locking plate. A circular groove is formed on the side of the pin facing the second locking plate, and the locking pin is partially inserted into the circular groove and can slide telescopically relative to the circular groove.

[0006] Optionally, the locking release device further includes a first fixing plate, the locking pin and the second locking plate are integrally formed, the end of the second locking plate away from the locking pin is connected to the first fixing plate, and the first fixing plate is connected to the upper surface of the base.

[0007] Optionally, the locking release device further includes a locking bolt, and the base side has a threaded hole below the unfolding arm. One end of the locking rope is connected to the locking bolt, and the locking bolt is threadedly connected to the threaded hole and used to rotate along the thread.

[0008] Optionally, both the smart composite material drive plate and the deploying arm are made of fiber-reinforced smart polymer composite material.

[0009] Optionally, the unfolding arm is a lens-type thin-walled tubular structure, and the unfolding arm is provided with multiple heating strips connected in sequence along its length.

[0010] Optionally, the base is a hollow structure with a connection hole on the side, and the end of the unfolding arm away from the end load is inserted into the connection hole and connected to the base.

[0011] Optionally, the base is provided with a connecting seat, and the upper surface of the connecting seat is provided with an arc-shaped groove. The shape of the arc-shaped groove corresponds to the shape of the end of the unfolding arm. The end of the unfolding arm that is inserted into the connecting hole is connected to the connecting seat with a screw.

[0012] Optionally, the end load is a cylindrical structure, and the unfolding arm is used to curl and retract around the circumferential surface of the end load.

[0013] Optionally, the upper surface of the base is provided with a first baffle and a second baffle on both sides along its length direction. The first baffle and the second baffle are located at the two ends outside the first locking plate and the second locking plate, respectively. The first baffle and the second baffle are provided with an arc-shaped groove at one end facing the unfolding arm. The end load is used to be mounted on the arc-shaped groove.

[0014] Compared with the prior art, the beneficial effects of the space extension arm based on intelligent composite materials of the present invention are:

[0015] This invention features a base that can be attached to a spacecraft, providing an installation position for the deployable arm. One end of the deployable arm is connected to the side of the base facing the negative Y-axis, and the other end is connected to the end load. On the upper surface of the base, facing the positive Z-axis, a first locking plate, a pin, and a second locking plate are sequentially arranged along the X-axis. The first and second locking plates are connected to the upper surface of the base, while the pin is not connected to the base. A smart composite material drive plate connects between the pin and the second locking plate. This drive plate has two states: deployed and retracted. It can move the pin along the X-axis, switching between contact with and away from the first locking plate. The deployable arm can extend or retract the end load. When the spacecraft has not reached the designated position, the deployable arm is in the retracted state. A locking rope is connected to the lower end of the deployable arm connection on the side of the base facing the negative Y-axis. The other end of the locking rope is connected to a locking buckle. The locking rope wraps around the deployable arm... The arm bends, allowing the locking buckle to insert between the first and second locking plates. At this point, the intelligent composite material drive plate is in the deployed state. The pin passes through the locking buckle and abuts against the first locking plate. The locking buckle engages with the locking rope connected to the pin to secure it, thus wrapping the locking rope around the retracted arm to prevent it from extending and keeping it in a retracted state. This prevents premature deployment of the arm, which could affect the normal operation of the spacecraft, reduces the size of the space-deployable arm, and facilitates its application on spacecraft. When the spacecraft reaches the designated position, the intelligent composite material drive plate switches to the retracted state, driving the pin to move in the positive X direction. The pin disengages from the first locking plate and also from the retracted buckle. The locking rope no longer restricts the arm, allowing it to deploy and deliver the end load to the working position, completing the deployment of the arm. The intelligent composite material drive plate, pin, and locking buckle work together in a simple structure, facilitating accurate deployment of the arm when the spacecraft reaches the designated position without affecting its normal operation. Attached Figure Description

[0016] Figure 1 This is one of the structural schematic diagrams of the space extension arm based on intelligent composite materials described in the embodiments of the present invention;

[0017] Figure 2 This is a second schematic diagram of the structure of the space extension arm based on intelligent composite materials described in an embodiment of the present invention;

[0018] Figure 3 This is a schematic diagram of the structure of the base described in an embodiment of the present invention;

[0019] Figure 4 This is a schematic diagram of the locking buckle structure according to an embodiment of the present invention;

[0020] Figure 5 This is a schematic diagram of the pin head structure according to an embodiment of the present invention;

[0021] Figure 6 This is one of the structural schematic diagrams of the intelligent composite material driving sheet described in the embodiments of the present invention;

[0022] Figure 7 This is a second schematic diagram of the structure of the intelligent composite material drive plate described in an embodiment of the present invention; Figure 8 This is a schematic diagram of the structure of the deployable arm according to an embodiment of the present invention.

[0023] Explanation of reference numerals in the attached figures:

[0024] 1-Base; 11-Connecting hole; 12-Connecting seat; 13-Threaded hole; 14-First baffle; 15-Second baffle; 16-Locking bolt; 21-Locking buckle; 22-Locking rope; 23-First locking plate; 24-Pin head; 25-Second locking plate; 26-Intelligent composite material drive plate; 27-Locking pin; 28-First fixing plate; 3-Expanding arm; 31-Heating strip; 4-End load; 5-Mounting seat. Detailed Implementation

[0025] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, specific embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

[0026] It should be noted that in the description of this invention, the orientations or positional relationships indicated by terms such as "upper," "lower," "left," "right," "top," "bottom," "front," "back," "inner," and "outer" are based on the orientations or positional relationships shown in the accompanying drawings and are only for the convenience of describing this invention. They are not intended to indicate or imply that the device referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as limiting the scope of protection of this invention.

[0027] The terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature.

[0028] Furthermore, although specific embodiments have been described herein, it should be understood that these embodiments are merely examples of the principles and applications of the invention. Therefore, it should be understood that many modifications can be made to the exemplary embodiments, and other arrangements can be designed without departing from the spirit and scope of the invention as defined by the appended claims. It should be understood that different dependent claims and features herein can be combined in ways not used as described in the original claims. It is also understood that features described in conjunction with individual embodiments can be used in other embodiments.

[0029] To solve the above problems, such as Figure 1 , Figure 2 and Figures 4 to 7 As shown, this invention provides a space extension arm based on intelligent composite materials, including a base 1, a locking and releasing device, an end load 4, and an extension arm 3. The locking and releasing device includes a locking buckle 21, a locking rope 22, a first locking plate 23, a pin 24, a second locking plate 25, and an intelligent composite material drive plate 26. The base 1 is used to connect to a spacecraft, and the extension arm 3 is used to extend or retract along its length. One end of the extension arm 3 is connected to the end load 4, and the other end is connected to the side of the base 1. The first locking plate 23 and the end load 4 are connected to the end load 4. The second locking plates 25 are all connected to the upper surface of the base 1 and are arranged opposite to each other. The pin head 24 is arranged between the first locking plate 23 and the second locking plate 25. The two ends of the intelligent composite material drive plate 26 are respectively connected to the pin head 24 and the second locking plate 25. The pin head 24 is used to pass through the locking buckle 21 and abut against the first locking plate 23. One end of the locking rope 22 is connected to the side of the base 1, and the other end is connected to the locking buckle 21. The locking rope 22 is used to wrap the retracted unfolding arm 3.

[0030] In this embodiment, a base 1 is provided, which can be connected to the spacecraft to provide an installation position for the deployable arm 3. One end of the deployable arm 3 is connected to the side of the base 1 facing the negative Y-axis, and the other end is connected to the end load 4. On the upper surface of the base 1, i.e., the surface facing the positive Z-axis, a first locking plate 23, a pin 24, and a second locking plate 25 are sequentially provided along the X-axis. The first locking plate 23 and the second locking plate 25 are connected to the upper surface of the base 1. The pin 24 is not connected to the base 1. A smart composite material drive plate 26 is connected between the pin 24 and the second locking plate 25. Figure 5 and Figure 6 As shown, the intelligent composite material drive plate 26 has two states: unfolded and retracted. The intelligent composite material drive plate 26 can drive the pin head 24 to move along the X-axis, so that the pin head 24 switches between two states: abutting against the first locking plate 23 and moving away from the first locking plate 23. (Refer to...) Figure 1 and Figure 2As shown, the deployable arm 3 can extend or retract the end load 4. When the spacecraft has not reached the designated position, the deployable arm 3 is in a retracted state. A locking rope 22 is connected to the lower end of the connection point of the deployable arm 3 on the side of the base 1 facing the negative Y-axis. The other end of the locking rope 22 is connected to a locking buckle 21. The locking rope 22 bends around the deployable arm 3, so that the locking buckle 21 is inserted between the first locking plate 23 and the second locking plate 25. At this time, the intelligent composite material drive plate 26 is in an extended state. The pin 24 passes through the locking buckle 21 and abuts against the first locking plate 23. The locking buckle 21 cooperates with and fixes the end of the locking rope 22 connected to the pin 24, thereby wrapping the deployable arm 3 in the retracted state and preventing the deployable arm 3 from extending. This design ensures that the deployable arm 3 remains in a retracted state, preventing premature deployment that could disrupt the spacecraft's normal operation. It also reduces the size of the deployable arm 3, making it easier to use on spacecraft. When the spacecraft reaches its designated position, the intelligent composite material drive plate 26 switches to a retracted state, driving the pin head 24 to move in the positive X direction. The pin head 24 disengages from the first locking plate 23 and also from the locking buckle 21. The locking rope 22 no longer restricts the deployable arm 3, allowing it to deploy and deliver the end load 4 to its working position, thus completing the deployment of the deployable arm 3. The intelligent composite material drive plate 26, pin head 24, and locking buckle 21 work together, resulting in a simple structure that allows for accurate deployment of the deployable arm 3 when the spacecraft reaches its designated position without affecting the spacecraft's normal operation.

[0031] Specifically, the base 1 can be bolted to the mounting base 5, which is connected to the spacecraft. The mounting base 5 provides a mounting position for the space deployment arm 3. The mounting base 5 can be connected to the side of the base 1 facing the positive Y-axis direction, as shown in the reference. Figure 4 As shown, the locking buckle 21 has a through hole for the pin head 24 to pass through, and a hole for easy connection with the locking rope 22; the two ends of the intelligent composite material drive plate 26 can be connected to the pin head 24 and the second locking plate 25 by screws.

[0032] Optionally, such as Figure 1 As shown, the locking and releasing device further includes a locking pin 27, which is connected to one end of the second locking plate 25 facing the first locking plate 23. A circular groove is provided on the side of the pin head 24 facing the second locking plate 25. The locking pin 27 is partially inserted into the circular groove and can slide telescopically relative to the circular groove.

[0033] In this embodiment, a locking pin 27 is provided between the pin head 24 and the second locking plate 25. The locking pin 27 is connected to the second locking plate 25. The side surface of the pin head 24 facing the locking pin 27 has a circular groove with a size matching that of the locking pin 27. The locking pin 27 can be inserted into the circular groove. When the intelligent composite material drive plate 26 is in the unfolded state, the end of the locking pin 27 can be inserted into the circular groove, but it does not abut against the bottom of the groove. When the intelligent composite material drive plate 26 retracts, the pin head 24 can move along the locking pin 27 in the positive X-axis direction through the circular groove. At this time, the locking buckle 21 disengages from the pin head 24. The circular groove and the locking pin 27 cooperate to provide guidance for the movement of the pin head 24 and prevent the pin head 24 from deviating.

[0034] Optionally, such as Figure 1 As shown, the locking and releasing device further includes a first fixing plate 28, the locking pin 27 and the second locking plate 25 are integrally formed, the end of the second locking plate 25 away from the locking pin 27 is connected to the first fixing plate 28, and the first fixing plate 28 is connected to the upper surface of the base 1.

[0035] In this embodiment, by setting the locking pin 27 and the second locking plate 25 as an integral structure, and setting the first fixing plate 28, which can be L-shaped, the second locking plate 25 can be connected to the end of the first fixing plate 28 that is parallel to the second locking plate 25 by screws, and the other end of the first fixing plate 28 can be connected to the upper surface of the base 1 by screws, thereby improving the overall structural connection stability.

[0036] Specifically, the structure of the first locking plate 23 is the same as that of the first fixing plate 28.

[0037] Optionally, such as Figure 3 As shown, the locking and releasing device also includes a locking bolt 16. A threaded hole 13 is provided on the side of the base 1 and below the unfolding arm 3. One end of the locking rope 22 is connected to the locking bolt 16. The locking bolt 16 is threadedly connected to the threaded hole 13 and is used to rotate along the thread.

[0038] In this embodiment, a locking bolt 16 is provided, and a threaded hole 13 is opened on the side of the base 1 facing the negative Y-axis direction below the unfolding arm 3. The locking bolt 16 can be threaded into the threaded hole 13 and rotated along the thread to change the relative position of the locking bolt 16 in the Y-axis direction. The end of the locking rope 22 away from the locking buckle 21 is connected to the locking bolt 16. The movement of the locking bolt 16 can adjust the length of the locking rope 22 extending out of the base 1 to use and wrap unfolding arms 3 of different sizes.

[0039] Optionally, both the smart composite material drive plate 26 and the unfolding arm 3 are made of fiber-reinforced smart polymer composite material.

[0040] In this embodiment, both the smart composite material drive plate 26 and the unfolding arm 3 are made of fiber-reinforced smart polymer composite material, with the reinforcing phase being glass fiber, carbon fiber, aramid fiber, etc. The smart polymer includes shape memory resins such as epoxy, cyanate ester, polyimide, and bismaleimide. The fiber-reinforced smart polymer composite material can be shaped into a temporary shape under external excitation. When subjected to the same excitation again, it can return to its initial shape. Specific excitation methods include thermal excitation, magnetic excitation, and electrical excitation, to adapt to different working environments and selected according to specific usage. When thermal excitation is used, the glass transition temperature of the fiber-reinforced smart polymer composite material is between 100°C and 300°C. Heating plates can be installed on the smart composite material drive plate 26 and the unfolding arm 3. When magnetic excitation is used, ferromagnetic materials, such as iron oxide particles, can be filled into the composite material system. When electrical excitation is used, single-walled or multi-walled carbon nanotubes, graphene, carbon black, carbon nanopaper, carbon nanofibers, or hybrid particles can be doped into the composite material system. If a combined drive method is used, the particles doped into the composite material system should be a combination of two or more of the above. This arrangement facilitates changes to the smart composite material drive plate 26. The state of the 6th and 3rd deployable arms, and the low density of the fiber-reinforced smart polymer composite material, compared with traditional metal structures and motor-driven structures, the prepared deployable arm 3 does not require complex motor drive, is lightweight, and has high specific stiffness and specific strength, solving the problem of insufficient launch vehicle carrying capacity. When the deployable arm 3 is deployed, it relies on shape memory characteristics to unfold, without sudden release of elastic energy, which can avoid the spacecraft being subjected to high impact instantaneously, improving the overall structural stability. After deployment, the smart composite material is stiffened, and the deployable arm 3 structure exhibits high stiffness, which can be used as a load-bearing structure to meet the on-orbit operation requirements of the spacecraft without the need for other extra supports, and the structure is simple.

[0041] Specifically, the intelligent composite material drive piece 26 and the unfolding arm 3 can be made by 4D printing technology. 4D printing technology has the advantages of simple preparation method, no need for complex molds, fast molding, and customization as needed. They can also be prepared by traditional composite material molding process, which is not specifically limited here.

[0042] Optionally, such as Figure 8 As shown, the unfolding arm 3 is a lens-type thin-walled tubular structure, and the unfolding arm 3 is provided with multiple heating strips 31 connected in sequence along its length direction.

[0043] In this embodiment, the unfolding arm 3 is set as a thin-walled tubular structure. The tubular structure is easy to shrink. According to the different lengths of the unfolding arm 3, multiple heating strips 31 are set in the length direction of the unfolding arm 3. When the unfolding arm 3 unfolds, it can unfold in segments to achieve orderly and stable unfolding. The structure is simple and the unfolding impact is small. It avoids large impact and uncontrollable unfolding path during the unfolding process of the unfolding arm 3. The unfolding arm 3 is a lens-type structure. It can unfold into a straight state by receiving sunlight when the temperature reaches the glass transition temperature without external power supply heating.

[0044] Specifically, the cross-section of the unfolding arm 3 can also be C-shaped, circular, elliptical, rounded rhombus, hexagonal honeycomb, concave hexagonal honeycomb, etc., without specific limitations. When the unfolding arm 3 needs to be rolled up, the heating strip 31 near the end load 4 is first energized and heated. When the temperature of the unfolding arm 3 is higher than the glass transition temperature of the smart composite material, an external force is applied to the end load 4 to roll it up. After the heating strip 31 near the end load 4 is rolled up in place, the heating is stopped. When the temperature drops below the glass transition temperature of the smart composite material, the external force is removed, and the first section of rolling is completed. Then, the above steps are repeated to roll up multiple heating strips 31 in the direction from the end load 4 to the base 1 to complete the rolling operation of the unfolding arm 3. When the unfolding arm 3 needs to be unfolded, the locking buckle 21 is disengaged from the pin head 24, and the heating strip 31 near the base 1 is energized and heated. The unfolding arm 3 completes the first section of unfolding under excitation. Then, multiple heating strips 31 in the direction from the base 1 to the end load 4 are energized and heated to complete the unfolding operation of the unfolding arm 3.

[0045] Optionally, such as Figure 3 As shown, the base 1 is a hollow structure with a connection hole 11 on the side. The end of the unfolding arm 3 away from the end load 4 is inserted into the connection hole 11 and connected to the base 1.

[0046] In this embodiment, by setting the base 1 as a hollow structure and opening a connecting hole 11 on the side of the base 1 facing the negative Y-axis, the shape of the connecting hole 11 can correspond to the shape of the end of the unfolding arm 3, so that the unfolding arm 3 can pass through the connecting hole 11 and be inserted into the interior of the base 1 and connected to the interior of the base 1, thereby improving the stability of the connection between the unfolding arm 3 and the base 1.

[0047] Optionally, such as Figure 3 As shown, the base 1 is provided with a connecting seat 12. The upper surface of the connecting seat 12 is provided with an arc-shaped groove. The shape of the arc-shaped groove corresponds to the shape of the end of the unfolding arm 3. The end of the unfolding arm 3 that is inserted into the connecting hole 11 is screwed to the connecting seat 12.

[0048] In this embodiment, a connecting seat 12 is provided inside the base 1. The lower surface of the connecting seat 12 is screwed to the lower surface of the base 1. The shape of the upper surface of the connecting seat 12 matches the shape of the lower surface of the end of the unfolding arm 3. After the unfolding arm 3 passes through the connecting hole 11, it can be screwed to the connecting seat 12, thereby improving the stability of the connection between the unfolding arm 3 and the base 1.

[0049] Optionally, such as Figure 1 As shown, the end load 4 is a cylindrical structure, and the unfolding arm 3 is used to curl and retract around the periphery of the end load 4.

[0050] In this embodiment, by setting the end load 4 as a cylindrical structure, the end of the unfolding arm 3 away from the base 1 is connected to the circumferential surface of the cylindrical structure, and when the unfolding arm 3 retracts, it can retract around the circumferential surface of the cylindrical structure to reduce the size of the unfolding arm 3. The cylindrical structure also provides a guiding effect for the retraction of the unfolding arm 3.

[0051] Optionally, such as Figure 1 and Figure 3 As shown, the upper surface of the base 1 is provided with a first baffle 14 and a second baffle 15 on both sides along its length direction. The first baffle 14 and the second baffle 15 are located at the two ends outside the first locking plate 23 and the second locking plate 25, respectively. The first baffle 14 and the second baffle 15 are provided with an arc-shaped groove at one end facing the unfolding arm 3. The end load 4 is used to be mounted on the arc-shaped groove.

[0052] In this embodiment, a first baffle 14 and a second baffle 15 are respectively provided on both sides of the upper surface of the base 1 along the X-axis direction. A first locking plate 23 and a second locking plate 25 are provided between the first baffle 14 and the second baffle 15. Both the first baffle 14 and the second baffle 15 have arc-shaped grooves on the side facing the unfolding arm 3. The size of the arc-shaped grooves matches the size of the end load 4. When the unfolding arm 3 is retracted, the end load 4 and the retracted unfolding arm 3 can be mounted on the arc-shaped grooves of the first baffle 14 and the second baffle 15. The first baffle 14 and the second baffle 15 limit and fix the unfolding arm 3 and the end load 4.

[0053] While the present invention has been disclosed above, its scope of protection is not limited thereto. Those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention, and all such changes and modifications will fall within the scope of protection of the present invention.

Claims

1. A spatial extendable arm based on intelligent composite materials, characterized in that, The system includes a base (1), a locking and releasing device, an end load (4), and a deployable arm (3). The locking and releasing device includes a locking buckle (21), a locking rope (22), a first locking plate (23), a pin (24), a second locking plate (25), and a smart composite material drive plate (26). The base (1) is used to connect to a spacecraft. The deployable arm (3) is used to extend or retract along its length. One end of the deployable arm (3) is connected to the end load (4), and the other end is connected to the side of the base (1). The first locking plate (23) and the second locking plate (25) are both connected to the end load (4). The base (1) is arranged on the upper surface and opposite to each other. The pin (24) is arranged between the first locking plate (23) and the second locking plate (25). The two ends of the intelligent composite material drive plate (26) are respectively connected to the pin (24) and the second locking plate (25). The pin (24) is used to pass through the locking buckle (21) and abut against the first locking plate (23). One end of the locking rope (22) is connected to the side of the base (1), and the other end is connected to the locking buckle (21). The locking rope (22) is used to wrap the retracted unfolding arm (3). The locking and releasing device further includes a locking pin (27), which is connected to one end of the second locking plate (25) facing the first locking plate (23). A circular groove is provided on the side of the pin head (24) facing the second locking plate (25). The locking pin (27) is partially inserted into the circular groove and can slide telescopically relative to the circular groove. Both the intelligent composite material drive plate (26) and the unfolding arm (3) are made of fiber-reinforced intelligent polymer composite material; The unfolding arm (3) is a lens-type thin-walled tubular structure, and the unfolding arm (3) is provided with multiple heating strips (31) connected in sequence along its length.

2. The spatial extension arm based on intelligent composite materials according to claim 1, characterized in that, The locking and releasing device further includes a first fixing plate (28), the locking pin (27) and the second locking plate (25) are integrally formed, the end of the second locking plate (25) away from the locking pin (27) is connected to the first fixing plate (28), and the first fixing plate (28) is connected to the upper surface of the base (1).

3. The space extension arm based on intelligent composite materials according to claim 1, characterized in that, The locking release device also includes a locking bolt (16). The base (1) has a threaded hole (13) on its side below the unfolding arm (3). One end of the locking rope (22) is connected to the locking bolt (16). The locking bolt (16) is threadedly connected to the threaded hole (13) and is used to rotate along the thread.

4. The space extension arm based on intelligent composite materials according to claim 1, characterized in that, The base (1) is a hollow structure with a connection hole (11) on the side. The end of the unfolding arm (3) away from the end load (4) is inserted into the connection hole (11) and connected to the base (1).

5. The space extension arm based on intelligent composite materials according to claim 4, characterized in that, The base (1) is provided with a connecting seat (12), and the upper surface of the connecting seat (12) is provided with an arc-shaped groove. The shape of the arc-shaped groove corresponds to the shape of the end of the unfolding arm (3). The end of the unfolding arm (3) inserted into the connecting hole (11) is screwed to the connecting seat (12).

6. The space extension arm based on intelligent composite materials according to claim 1, characterized in that, The end load (4) is a cylindrical structure, and the unfolding arm (3) is used to curl and retract around the circumferential surface of the end load (4).

7. The space extension arm based on intelligent composite materials according to claim 6, characterized in that, The base (1) has a first baffle (14) and a second baffle (15) on its upper surface along its length. The first baffle (14) and the second baffle (15) are located at the two ends outside the first locking plate (23) and the second locking plate (25), respectively. The first baffle (14) and the second baffle (15) have arc-shaped grooves at one end facing the unfolding arm (3). The end load (4) is used to be mounted on the arc-shaped grooves.

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