Space truss assembly interface and use method

Abstract

The invention provides a space truss assembly connector and a using method, and relates to the technical field of aerospace. The space truss assembly connector comprises a supporting seat and variable structures, the variable structures are made of shape memory composite materials, the multiple variable structures are distributed in the circumferential direction of the supporting seat, the connecting end of each variable structure is connected with the supporting seat, and the connecting end of each variable structure is connected with the supporting seat. The deformation end of each variable structure extends away from the supporting base, and the multiple deformation ends are used for getting close to each other through external excitation to form a connector connected with a truss rod piece in an inserted mode. In the assembling process of the truss rod piece, only external excitation needs to be applied to the variable structure, and special connecting parts do not need to be additionally carried. According to the technology, a light-weight and low-cost assembly mode is provided for large-scale on-orbit facility construction, and dependence on a high-precision mechanical arm and out-of-cabin operation of astronauts is remarkably reduced.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to a space truss assembly interface and a use method thereof. Background Art

[0002] With the development of space technology and the increasing demand for space equipment, more and more components need to be assembled in space, among which trusses are an important component of such components.

[0003] Currently, on-orbit truss assembly systems rely heavily on collaborative work between space robotic arms and astronauts, facing challenges such as difficulty controlling rod drift in microgravity and insufficient multi-degree-of-freedom docking precision. To address this, mature ground-based technologies based on high-precision grasping by industrial robots, laser vision positioning, and modular unit scheduling are being gradually transferred to space applications. For example, onboard AI algorithms are used to plan truss topology paths, combined with force-position hybrid control to achieve flexible assembly of rods; and swarms of lightweight collaborative robots are used to achieve cross-scale configuration expansion, reducing reliance on extravehicular activities. However, the extreme operating conditions in space (-150 to 120°C alternating thermal cycling and high-energy particle irradiation) lead to a sharp decline in the reliability of traditional electromechanical systems. Furthermore, the strict weight restrictions imposed by rocket launch costs make space truss assembly difficult. Summary of the Invention

[0004] The problem solved by the present invention is: how to improve the spatial truss assembly operation.

[0005] To solve the above problems, on the one hand, the present invention provides a spatial truss assembly interface, including a support seat and a variable configuration structure, wherein the variable configuration structure is made of a shape memory composite material, and multiple variable configuration structures are distributed along the circumference of the support seat, and the connecting end of each of the variable configuration structures is connected to the support seat, and the deformation end of each of the variable configuration structures extends away from the support seat, and the multiple deformation ends are used to move closer to each other through external excitation to form an interface for plugging with the truss rod.

[0006] Optionally, the variable configuration structure is configured as an arc-shaped sheet, and two of the variable configuration structures are distributed along the circumference of the support seat.

[0007] Optionally, the arc-shaped piece is in an arc shape at the connection end, and when subjected to external stimulation, the arc-shaped piece is in the arc shape at the deformation end.

[0008] Optionally, a spring is further included, which is sleeved outside the connecting ends of the two arc-shaped sheets and pre-compressed. The ends of the spring facing away from the deformation end are respectively fixedly connected to the two connecting ends, and the ends of the spring facing the deformation end are also used to be sleeved outside the two deformation ends.

[0009] Optionally, a shape memory alloy ring is further included, which is sleeved outside the connecting end and connected to the end of the spring facing the deforming end, and is used to clamp the two deforming ends under external excitation.

[0010] Optionally, the phase transition temperature of the shape memory alloy ring is lower than the phase transition temperature of the deformation end.

[0011] Optionally, a threaded fastener is further included, and the connecting end is detachably connected to the supporting seat via the threaded fastener.

[0012] Optionally, the support seat includes at least one connecting column, and the variable configuration structure is distributed along the circumference of the connecting column.

[0013] Compared to related technologies, the space truss assembly interface of the present invention connects the connection end of a variable configuration structure made of shape memory composite material to a support base. This allows the variable configuration structure to be supported by the support base, ensuring that the deformable end of the variable configuration structure extending away from the support base can be deformed by external stimulation, preventing the deformable end from causing the variable configuration structure to separate from the support base, thereby ensuring the stability of the variable configuration structure. Multiple deformable ends are then brought together by external stimulation to form an interface for plugging into the truss member. The end of the truss member can be directly inserted into this socket. During the assembly of the truss member, only external stimulation needs to be applied to the variable configuration structure, eliminating the need for additional dedicated connection components. This technology provides a lightweight, low-cost assembly method for large-scale on-orbit facility construction, significantly reducing the reliance on high-precision robotic arms and astronaut extravehicular operations.

[0014] On the other hand, the present invention also provides a method for using a space truss assembly interface, based on the above-mentioned space truss assembly interface, comprising: Applying pre-driving to the variable configuration structure connected to the support seat so that the distance between the variable configuration structure and the deformation end of the support seat is sufficient to accommodate the truss member; A first drive is applied to the variable configuration structure to move the deformed ends closer to each other to embrace the truss member.

[0015] Optionally, the method for using the spatial truss assembly interface further includes: A shape memory alloy ring is sleeved outside the deformation end by a spring, and a second drive is applied to the shape memory alloy ring so that the shape memory alloy ring clamps the deformation end.

[0016] Compared with the related art, the method for using the spatial truss assembly interface of the present invention applies a pre-drive to the variable-configuration structure connected to the support seat, so that the distance between the deformation end of the variable-configuration structure and the support seat is sufficient to accommodate the truss rod, thereby providing sufficient space for the subsequent placement of the truss rod to avoid interference. Then, by applying a first drive to the variable-configuration structure, the deformation ends are brought close to each other to embrace the truss rod. The deformation ends can be combined into a structure similar to a socket to facilitate the connection between the support seat and the truss rod, thereby improving the assembly efficiency of the truss rod. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a structural schematic diagram of the spatial truss assembly interface in an embodiment of the present invention when two deformable ends are separated; Figure 2 This is a structural schematic diagram of a spatial truss assembly interface in an embodiment of the present invention when two deformed ends are brought close together; Figure 3 This is a schematic diagram of the structure in which the spring is extended and the shape memory alloy ring is sleeved on the two deformation ends in an embodiment of the present invention; Figure 4 is a schematic diagram of a truss member assembly process in an embodiment of the present invention; Figure 5 Schematic diagram of various structural forms of the support base in the embodiment of the present invention; Figure 6 Schematic diagram of assembling truss members of support bases of different structural forms according to an embodiment of the present invention; Figure 7 Schematic diagram of a spatial truss assembly interface forming trusses of different structures in an embodiment of the present invention; Figure 8 This is a flow chart of a method for using a spatial truss assembly interface in an embodiment of the present invention.

[0018] Description of reference numerals: 1-support seat; 2-spring; 3-variable structure; 4-shape memory alloy ring; 5-threaded fastener. DETAILED DESCRIPTION

[0019] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, specific embodiments of the present invention are described in detail below with reference to the accompanying drawings.

[0020] In the accompanying drawings, the X-axis represents left-right positioning, with the positive direction of the X-axis representing the left side and the negative direction of the X-axis representing the right side. In the accompanying drawings, the Y-axis represents front-back positioning, with the positive direction of the Y-axis representing the front side and the negative direction of the Y-axis representing the rear side. In the accompanying drawings, the Z-axis represents up-down positioning, with the positive direction of the Z-axis representing the top side and the negative direction of the Z-axis representing the bottom side. It should also be noted that the aforementioned X-axis, Y-axis, and Z-axis are merely for the purpose of facilitating the description of the present invention and simplifying the description. They do not indicate or imply that the devices or components referred to must have a specific orientation, be constructed, or operate in a specific orientation, and therefore should not be construed as limiting the present invention.

[0021] It should be noted that the terms "first," "second," and the like in the description and claims of the present invention and the accompanying drawings are used to distinguish similar objects and are not necessarily used to describe a specific order or precedence. It should be understood that the terms used in this manner are interchangeable where appropriate, such that the embodiments of the present invention described herein can be practiced in an order other than that illustrated or described herein.

[0022] With the surge in demand for missions like space station expansion and the networking of large space telescopes, automated on-orbit truss assembly technology has become a key area of ​​focus for overcoming bottlenecks in extraterrestrial infrastructure construction. Current on-orbit assembly systems rely heavily on collaborative space robotic arms and astronauts, facing challenges such as difficulty controlling member drift in microgravity and insufficient multi-degree-of-freedom docking accuracy. To address this, mature ground-based technologies based on high-precision grasping by industrial robots, laser vision positioning, and modular unit scheduling are being gradually transferred to space applications. For example, onboard AI algorithms are used to plan truss topology paths, combined with force-position hybrid control to achieve flexible member assembly. Swarms of lightweight collaborative robots are also being used to achieve cross-scale configuration expansion, reducing reliance on extravehicular activities. However, the extreme operating conditions in space (-150 to 120°C thermal cycling and high-energy particle irradiation) lead to a sharp decline in the reliability of traditional electromechanical systems. Furthermore, the strict launch costs of rockets severely limit the quality and complexity of equipment, necessitating the urgent need for disruptive lightweight, adaptive assembly technologies.

[0023] In response to the above challenges, an embodiment of the present invention proposes a space truss assembly interface based on smart materials for on-orbit construction: this interface is based on shape memory composite materials optimized for the space environment, and uses off-orbit solar radiation or low-power electrothermal excitation to trigger active deformation. It can adaptively correct the position offset of the rods under microgravity, achieve normal assembly in extreme environments, and has good resistance to radiation aging. In addition, the assembly interface supports on-orbit mission iteration (such as switching from solar panel supports to payload platform frames) without the need for additional transportation of dedicated connection components. This technology provides a lightweight, low-cost assembly method for large-scale on-orbit facility construction, significantly reducing dependence on high-precision robotic arms and astronaut extravehicular operations.

[0024] Combine Figures 1 to 3As shown, an embodiment of the present invention provides a spatial truss assembly interface, including a support seat 1 and a variable configuration structure 3, the variable configuration structure 3 is made of a shape memory composite material, and multiple variable configuration structures 3 are distributed along the circumference of the support seat 1, and the connecting end of each variable configuration structure 3 is connected to the support seat 1, and the deformation end of each variable configuration structure 3 extends away from the support seat 1, and the multiple deformation ends are used to move closer to each other through external excitation to form an interface for plugging with the truss rod.

[0025] Specifically, shape memory composite materials can exhibit different shapes and strengths according to different phase transition temperatures. Figure 1 As shown, the two variable configuration structures 3 are distributed along the circumference of the support base 1, the connection end of each variable configuration structure 3 (the lower end of the variable configuration structure 3) is fixed on the support base 1, and the deformation end of each variable configuration structure 3 (the upper end of the variable configuration structure 3) extends upward away from the support base 1. When the truss members do not need to be connected (on the ground), external excitation is applied to each variable configuration structure 3. Under the action of the external excitation, the two deformation ends of the two variable configuration structures 3 move away from each other, that is, the two variable configuration structures 3 are in an expanded state. At this time, cooling the two variable configuration structures 3 can keep the two deformation ends of the two variable configuration structures 3 away from each other. When the truss members need to be connected (on track), external excitation is applied to each variable configuration structure 3 again. Under the action of the external excitation, the two deformation ends of the two variable configuration structures 3 move closer to each other, that is, the two variable configuration structures 3 are in a collapsed state, and the area surrounded by the two deformation ends forms a socket. The two variable configuration structures 3 are cooled to increase the stiffness of the two variable configuration structures 3. Then, the truss member is inserted into the socket, that is, the truss member can be inserted between the two deformation ends, completing the assembly of the truss member.

[0026] Therefore, in this embodiment, the connection end of the variable configuration structure 3, made of a shape-memory composite material, is connected to the support base 1. This allows the variable configuration structure 3, supported by the support base 1, to deform at the deformable end extending away from the support base 1. This prevents the deformable end from causing the variable configuration structure 3 to separate from the support base 1, thereby ensuring the stability of the variable configuration structure 3. The multiple deformable ends are then brought together by external stimulation to form an interface for plugging into the truss member. The end of the truss member can be directly inserted into this socket. During the assembly of the truss member, only external stimulation needs to be applied to the variable configuration structure 3, eliminating the need for additional dedicated connection components. This technology provides a lightweight, low-cost assembly method for large-scale on-orbit facility construction, significantly reducing the reliance on high-precision robotic arms and astronaut extravehicular operations.

[0027] Based on the above embodiment, when the truss member needs to be dismantled, the two deformable ends move away from each other under the action of external excitation, so that the truss member can be pulled out from between the two deformable ends, thereby facilitating the disassembly of the truss member.

[0028] Optionally, combined Figure 1 、 Figure 2 As shown, the variable configuration structure 3 is configured as an arc-shaped sheet, and two variable configuration structures 3 are distributed along the circumference of the support seat 1 .

[0029] Specifically, the shape of the axial cross section of the truss member is circular, and the variable configuration structure 3 can be set as an arc piece, and two variable configuration structures 3 are distributed along the circumference of the support seat 1, that is, the number of the arc pieces is two, such as Figure 1 As shown, when the truss rods do not need to be assembled, the connecting end (lower end) of the arc piece is connected to the support seat 1, and the deformed ends (upper ends) of the arc piece move away from each other under external stimulation, forming a petal-like opening. Figure 2 As shown, when the truss member needs to be assembled, the two deformed ends of the two arc pieces approach each other under external excitation, and the two deformed ends are combined into a straight cylindrical structure. After cooling and shaping, the end of the truss member can be inserted into the straight cylindrical structure to complete the assembly of the truss member.

[0030] In this way, by configuring the variable configuration structure 3 as two arc pieces distributed along the circumference of the support seat 1 , the use cost of the variable configuration structure 3 can be reduced and the deformation efficiency of the variable configuration structure 3 can be improved.

[0031] Optionally, the arc-shaped piece is in an arc shape at the connection end, and when subjected to external stimulation, the arc-shaped piece is in an arc shape at the deformation end.

[0032] Specifically, the connecting end of the arc-shaped piece is in an arc shape so that the connecting end is adapted to the shape of the connecting column on the support seat 1 and, at the same time, is adapted to the shape of the truss member. When the arc-shaped piece receives external stimulation, the deformed end of the arc-shaped piece is in an arc shape, so that the arc-shaped piece can fully contact the outer surface of the truss member. When the arc-shaped piece does not receive external stimulation, the deformed end of the arc-shaped piece is roughly flat or slightly curved, and there is enough space between the two deformed ends of the two arc-shaped pieces to place the truss member. In this way, it can be ensured that when the arc-shaped piece is subjected to external stimulation, it can form an arc surface that bends along the circumference of the truss member, so that the arc-shaped piece can fully contact the truss member and ensure the stability of the connection between the arc-shaped piece and the truss member.

[0033] In some embodiments, three or four variable configuration structures 3 can also be set. The setting of three variable configuration structures 3 is used for exemplary explanation. When three variable configuration structures 3 are set, the three variable configuration structures 3 are distributed along the circumference of the support seat 1, and the three connecting ends of the three variable configuration structures 3 are arc-shaped, and the three deformation ends of the three variable configuration structures 3 can be flat or slightly bent away from each other. There is enough space between the three deformation ends for placing truss rods. When subjected to external excitation, the three deformation ends approach each other, and each deformation end is arc-shaped under external excitation, so that the three variable configuration structures 3 are combined into a cylindrical socket structure in the circumferential direction, so that the end of the truss rod can be inserted into the socket structure, thereby realizing the spatial assembly of the truss rods.

[0034] Optionally, combined Figures 1 to 4 As shown, the spatial truss assembly interface also includes a spring 2, which is sleeved outside the connecting ends of the two arc-shaped sheets and pre-compressed. The ends of the spring 2 facing away from the deformation end are fixedly connected to the two connecting ends respectively, and the ends of the spring 2 facing the deformation end are also used to be sleeved outside the two deformation ends.

[0035] Specifically, the end of the spring 2 away from the deformation end is referred to as the lower end of the spring 2, and the end of the spring 2 toward the deformation end is referred to as the upper end of the spring 2. The spring 2 is sleeved on the two connecting ends of the two arc pieces, and the lower end of the spring 2 is fixedly connected to the two connecting ends. The spring 2 is pre-compressed. Initially, as shown in FIG. Figure 1 As shown, the two deformed ends of the two arc pieces are away from each other, and the two deformed ends can hinder the free extension of the spring 2. When the two deformed ends of the two arc pieces are close to each other, as shown in FIG. Figure 2 As shown, the two deformed ends cannot hinder the free extension of the spring 2, as shown in FIG. Figure 3 As shown, after the spring 2 is freely extended, the upper end of the spring 2 is sleeved on the two deformed ends, and the upper end of the spring 2 can wrap the two deformed ends at the same time to prevent the two deformed ends from moving away from each other. Figure 4 As shown in a in FIG, initially, the two deformation ends are away from each other, and the spring 2 remains in a pre-compressed state under the obstruction of the two deformation ends, as shown in FIG. Figure 4 As shown in b in FIG, after the two deformed ends approach each other to wrap the truss member, the upper end of the spring 2 can stretch freely, as shown in FIG. Figure 4 As shown in Figure c, when the upper end of spring 2 extends, the upper end of paralysis 2 wraps around the two deformed ends, preventing the two deformed ends from moving away from each other, thereby improving the stability of the two deformed ends wrapping around the truss member. The rebound of spring 2 can be ignored.

[0036] Optionally, combined Figures 1 to 4 As shown, the spatial truss assembly interface also includes a shape memory alloy ring 4, which is sleeved outside the connection end and connected to the end of the spring 2 facing the deformation end. The shape memory alloy ring 4 is used to clamp the two deformation ends under external excitation.

[0037] Specifically, the shape memory alloy ring 4 is sleeved on the two connecting ends and welded to the upper end of the spring 2. The shape memory alloy ring 4 moves with the upper end of the spring 2. Initially, as shown in FIG. Figure 1 As shown, under the obstruction of the two deformation ends, the spring 2 remains in a pre-compression state, the shape memory alloy ring 4 is stationary, and after the two deformation ends approach each other, as shown in FIG. Figure 2 As shown, the upper end of the spring 2 drives the shape memory alloy ring 4 to move upward, as shown in FIG. Figure 3 As shown, the shape memory alloy ring 4 is sleeved on the two deformation ends. Figure 4 As shown in a in FIG, the shape memory alloy ring 4 remains stationary. Figure 4 As shown in b, the upper end of the spring 2 drives the shape memory alloy ring 4 to move upward, as shown in FIG. Figure 4 As shown in Figure c, the shape-memory alloy ring 4 is placed over the two deformable ends. After being placed over the two deformable ends, the ring shrinks in diameter under external stimulation, clamping the two arcuate segments. At this point, the ring acts as a clamp, securing the ends of the truss members to be connected. This allows the ring to further enhance the stability of the truss members wrapped around the two deformable ends under external stimulation.

[0038] Optionally, the phase transition temperature of the shape memory alloy ring 4 is lower than the phase transition temperature of the deformation end.

[0039] Specifically, the deforming end deforms before the shape memory alloy ring 4. By utilizing the fact that the phase transition temperature of the shape memory alloy ring 4 is lower than that of the deforming end, the temperature of the deformed shape memory alloy ring 4 can be prevented from affecting the structure of the deforming end. This reduces the effect of the temperature of the deformed shape memory alloy ring 4 on the structural stability of the deforming end.

[0040] Optionally, combined Figure 1 As shown, the spatial truss assembly interface further includes a threaded fastener 5 , and the connecting end is detachably connected to the support base 1 via the threaded fastener 5 .

[0041] Specifically, the two connecting ends of the two arc pieces are fixed to the support base 1 by screws respectively, so that the arc pieces can be easily replaced. At the same time, the stability of the connection between the connecting ends and the support base 1 can be improved by the threaded connection.

[0042] Optionally, combined Figures 5 to 7 As shown, the support seat 1 includes at least one connecting column, and two variable configuration structures 3 are distributed along the circumference of the connecting column.

[0043] Specifically, Figure 5 This is a schematic diagram of at least two structures of the support base 1 in this embodiment, such as Figure 5As shown in a, the support base 1 is provided with six connecting columns in the circumferential direction, or as shown in Figure 5 As shown in b, twelve connecting columns are arranged around the support base 1. Figure 6 As shown, Figure 6 a in Figure 5 a in the figure corresponds to, that is, the variable configuration structure 3 on the six connecting columns is assembled with six truss members, Figure 6 b in Figure 5 b in the figure corresponds to that the variable configuration structures 3 on the twelve connecting columns are assembled with twelve truss members, as shown in FIG. Figure 7 As shown, Figure 7 a in Figure 6 The a in the figure corresponds to the assembly of the hexahedral truss. Figure 7 b in Figure 5 Corresponding to b in , the assembly of the triangular pyramid is completed by selecting an appropriate number of connecting columns.

[0044] In this way, the support seat 1 includes at least one connecting column, and the two variable configuration structures 3 are distributed along the circumference of the connecting column, so that the structural form of the support seat 1 can be freely expanded according to the number of connecting columns to improve the flexibility of use of each support seat 1.

[0045] Combine Figure 8 As shown, another embodiment of the present invention further provides a method for using a space truss assembly interface, based on the above space truss assembly interface, comprising: Step 1: Apply pre-drive to the variable configuration structure 3 connected to the support base 1 so that the distance between the variable configuration structure 3 and the deformation end of the support base 1 is sufficient to accommodate the truss rod.

[0046] It should be noted that if the spacing between the deformation ends is sufficient to accommodate the truss members, then the pre-drive applied to the variable configuration structure 3 at this time can be understood as not applying additional excitation to it, or only applying appropriate excitation to adjust its shape.

[0047] Step 2: Apply a first drive to the variable conformation structure 3 to move the deformed ends closer to each other to embrace the truss member.

[0048] Specifically, if Figure 1As shown, two variable configuration structures 3 made of shape memory composite material are distributed along the circumference of the support base 1, the connection end of each variable configuration structure 3 (the lower end of the variable configuration structure 3) is fixed on the support base 1, and the deformation end of each variable configuration structure 3 (the upper end of the variable configuration structure 3) extends upward away from the support base 1. When the truss members do not need to be connected (on the ground), external excitation is applied to each variable configuration structure 3. Under the action of the external excitation, the two deformation ends of the two variable configuration structures 3 move away from each other, that is, the two variable configuration structures 3 are in an expanded state. At this time, cooling the two variable configuration structures 3 can keep the two deformation ends of the two variable configuration structures 3 away from each other; when the truss members need to be connected (on track), external excitation is applied to each variable configuration structure 3 again. Under the action of the external excitation, the two deformation ends of the two variable configuration structures 3 move closer to each other, that is, the two variable configuration structures 3 are in a collapsed state, and the area surrounded by the two deformation ends serves as a connection for the truss members. After the two deformation ends are in contact with the truss members, the two variable configuration structures 3 can be cooled to increase the stiffness of the two variable configuration structures 3, and the truss member can be inserted between the two deformation ends to complete the assembly of the truss members.

[0049] In this way, by applying a pre-drive to the variable-configuration structure 3 connected to the support seat 1, the distance between the deformation end of the variable-configuration structure 3 and the support seat 1 is sufficient to accommodate the truss rod, so as to provide sufficient space for the subsequent placement of the truss rod to avoid interference. Then, by applying a first drive to the variable-configuration structure 3, the deformation ends are brought closer to each other to embrace the truss rod. The deformation ends can be combined into a structure similar to a socket to facilitate the connection between the support seat 1 and the truss rod, thereby improving the assembly efficiency of the truss rod.

[0050] Optionally, the method for using the spatial truss assembly interface further includes: sleeve the shape memory alloy ring 4 outside the deformation end through the spring 2, and apply a second drive to the shape memory alloy ring 4 to tighten the deformation end.

[0051] Specifically, if Figure 3 As shown, after the spring 2 is stretched, the shape memory alloy ring 4 can be driven to be sleeved on the two deformed ends, and then the shape memory alloy ring 4 is driven for the second time to shrink the diameter of the shape memory alloy ring 4 to tighten the two deformed ends. In this way, the two deformed ends can be prevented from separating from each other, so as to ensure the stability of the truss member surrounded by the two deformed ends.

[0052] Although the present invention is disclosed as above, the protection scope of the present invention is not limited thereto. Those skilled in the art may make various changes and modifications without departing from the spirit and scope of the present invention, and these changes and modifications will fall within the protection scope of the present invention.

Claims

1. A spatial truss assembly interface, characterized in that: The invention comprises a support seat (1) and a variable configuration structure (3), wherein the variable configuration structure (3) is made of a shape memory composite material, and a plurality of the variable configuration structures (3) are distributed along the circumference of the support seat (1), and a connection end of each of the variable configuration structures (3) is connected to the support seat (1), and a deformation end of each of the variable configuration structures (3) extends away from the support seat (1), and the plurality of deformation ends are used to move closer to each other through external excitation to form an interface for plugging with a truss rod.

2. The spatial truss assembly interface according to claim 1, characterized in that: The variable configuration structure (3) is configured as an arc-shaped sheet, and two of the variable configuration structures (3) are distributed along the circumference of the support seat (1).

3. The spatial truss assembly interface according to claim 2, characterized in that: The arc-shaped piece is in an arc shape at the connection end, and when subjected to external stimulation, the arc-shaped piece is in the arc shape at the deformation end.

4. The spatial truss assembly interface according to claim 2, characterized in that: It also includes a spring (2), which is sleeved outside the connecting ends of the two arc-shaped sheets and is pre-compressed. The ends of the spring (2) facing away from the deformation end are fixedly connected to the two connecting ends respectively, and the ends of the spring (2) facing the deformation end are also used to be sleeved outside the two deformation ends.

5. The spatial truss assembly interface according to claim 3, characterized in that: It also includes a shape memory alloy ring (4), which is sleeved outside the connection end and connected to the end of the spring (2) facing the deformation end, and is used to clamp the two deformation ends under external excitation.

6. The spatial truss assembly interface according to claim 5, characterized in that: The phase transition temperature of the shape memory alloy ring (4) is lower than the phase transition temperature of the deformation end.

7. The spatial truss assembly interface according to claim 1, characterized in that: It also includes a threaded fastener (5), and the connecting end is detachably connected to the support seat (1) via the threaded fastener (5).

8. The spatial truss assembly interface according to claim 1, characterized in that: The support seat (1) comprises at least one connecting column, and the variable configuration structure (3) is distributed along the circumference of the connecting column.

9. A method for using a space truss assembly interface, based on the space truss assembly interface according to any one of claims 1 to 8, characterized in that: include: Applying a pre-drive to the variable configuration structure (3) connected to the support seat (1) so that the distance between the variable configuration structure (3) and the deformation end of the support seat (1) is sufficient to accommodate the truss rod; A first drive is applied to the variable configuration structure (3) so that the deformed ends approach each other to embrace the truss member.

10. The method for using the spatial truss assembly interface according to claim 9, characterized in that: Also includes: A shape memory alloy ring (4) is sleeved outside the deformation end by a spring (2), and a second drive is applied to the shape memory alloy ring (4) so ​​that the shape memory alloy ring (4) tightens the deformation end.

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