Space on-orbit composite material component assembling and connecting structure

Abstract

The invention relates to the technical field of space on-orbit composite material assembly, in particular to a space on-orbit composite material component assembly connecting structure which comprises a truss rod, one end of the truss rod is fixedly connected with a connector, and one end of the connector is detachably connected with a female connector. A clamping ring is fixedly connected to the side wall of the connector in the circumferential direction, and the top of the clamping ring is of an inclined face structure. A plurality of sleeves are fixedly connected to the female connector, horizontal grooves are formed in the middles of the inner side walls of the sleeves, first springs are fixedly connected into the grooves, connecting blocks are fixedly connected to the other ends of the first springs, first wedge-shaped blocks are fixedly connected to the side walls of the connecting blocks, second wedge-shaped blocks are fixedly connected to the bottoms of the first wedge-shaped blocks, and bottom plates are arranged on the inner bottom walls of the sleeves. Multiple second springs are fixedly connected to the bottoms of the bottom plates, and control assemblies are arranged at the bottoms of the sleeves. Through the wedge-shaped inclined plane matching between the connector and the female connector, the external impact force is converted into the reinforcing force of the self structure, and the stability of the truss structure connection is improved.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of space on-orbit composite material assembly, in particular to a space on-orbit composite material component assembly connection structure. BACKGROUND

[0002] Space on-orbit assembly refers to an engineering technical process in which multiple modules, components or structures launched in advance are connected, integrated and tested in a microgravity environment in space through extravehicular activity of astronauts or space robot operation, and finally a larger, more complex or more powerful space system is constructed; the entire assembly process involves precise orbital rendezvous and docking technology, complex robot remote operation, and special processing for composite material structures, such as on-orbit drilling and fastening operations for connection.

[0003] For example, the International Space Station is completed by launching modules in batches and assembling in orbit, sending functional cabin sections, truss structures, solar panels and other components into space, and astronauts completing module assembly through extravehicular activity and mechanical arm assistance, wherein the truss structure is a lattice bearing structure composed of slender rods connected by nodes through bolt connection, the rods mainly bear axial tension or pressure, and the load is transmitted through geometric stability; the truss structure can be used to support solar panels, radiators and other equipment, and realize modular expansion of the International Space Station.

[0004] In actual use, on-orbit assembly of the truss structure requires drilling holes at the corresponding rod ends to facilitate node connection by bolts. Drilling holes can cause composite material fiber breakage and stress concentration at the drilling site, reducing connection strength, and because there are high-speed moving dust, micro-meteoroids, meteoroids and space debris in space, these high-speed moving objects in space have a lot of kinetic energy, and the truss structure is highly likely to be hit by high-speed moving objects in space. When a collision occurs, the connection nodes of the truss and the bolt connection site vibrate due to the impact, causing "fretting wear" on the thread engagement surface between the bolt and the nut, loosening the connection, causing resonance and even serious deformation, resulting in thread disengagement, and further leading to unstable connection of the truss structure or even disconnection.

[0005] Therefore, the present application provides a space on-orbit composite material component assembly connection structure to solve the above problems. SUMMARY

[0006] To solve the above problems, the present application provides a space on-orbit composite material component assembly connection structure, which converts external impact force into self-structure reinforcing force through the wedge-shaped inclined surface cooperation between the connecting head and the female connector, improving the stability of the truss structure connection.

[0007] In order to achieve the above purpose, the technical scheme of the present application is as follows:

[0008] A space in-orbit composite material component assembly connecting structure, comprising a truss rod, one end of the truss rod is fixedly connected with a connecting head, one end of the connecting head is detachably connected with a female connector; the bottom of the connecting head is provided as a tapered structure, the side wall of the connecting head is fixedly connected with a snap ring along the circumference thereof, the top of the snap ring is provided as an inclined surface structure, and the top of the snap ring is lower on one side of the connecting head than on the other side; a plurality of sleeves are fixedly connected on the female connector, the inner side wall of each sleeve is provided with a horizontally arranged groove in the middle, a first spring is fixedly connected in each groove, the other end of each first spring is fixedly connected with a connecting block, the side wall of each connecting block is fixedly connected with a first wedge-shaped block, the bottom of each first wedge-shaped block is fixedly connected with a second wedge-shaped block, the first wedge-shaped block and the second wedge-shaped block are higher on one side of the connecting head than on the other side, a bottom plate is arranged on the inner bottom wall of the sleeve, a plurality of second springs are fixedly connected on the bottom plate, the other end of each second spring is fixedly connected with the inner bottom wall of the corresponding sleeve, and the bottom of each sleeve is provided with a control assembly for controlling the locking and unlocking of the corresponding connecting head.

[0009] The technical principle of the above scheme is as follows: during assembly, the connecting head is inserted into the corresponding sleeve on the female connector, the tapered bottom of the connecting head first contacts the bottom plate and compresses the second spring, the snap ring is synchronously lowered along with the connecting head, the bottom of the snap ring extrudes the inclined surface of the first wedge-shaped block, the first wedge-shaped block is pushed to compress the first spring and move into the groove, and the second wedge-shaped block is synchronously driven to move into the groove; the snap ring continues to move downward, the side wall of the snap ring contacts the side wall of the second wedge-shaped block, and the side wall of the second wedge-shaped block is continuously extruded, when the top of the snap ring and the bottom of the groove are located at the same horizontal plane, the second wedge-shaped block is blocked and disappears, the second wedge-shaped block is pushed out and reset by the rebound force of the first spring, the inclined surface of the first wedge-shaped block is tightly fitted with the inclined surface of the snap ring, and radial clamping force is formed; then the height of the bottom plate is fixed by the control assembly, and the connecting head is axially locked, external impact force, such as axial or radial vibration, makes the connecting head have a tendency to move upward or tilt, the inclined surface of the snap ring further extrudes the first wedge-shaped block, the reaction force of the first spring increases after being compressed, the normal force between the wedge-shaped blocks is converted into greater radial clamping force, and the impact force is converted into internal stress of the structure.

[0010] The above scheme has the following beneficial effects:

[0011] 1. The impact force is converted into radial clamping force through the wedge-shaped inclined surface, the greater the external disturbance, the more secure the connection, and the problem that the traditional bolt connection is easily loosened under vibration is solved.

[0012] 2. No punching is required, fiber breakage and stress concentration are avoided, force is transmitted through surface contact, and the integrity of the composite material component is protected.

[0013] 3. The connecting head and the female connector can be quickly disassembled and assembled through the control assembly, and in-orbit maintenance is facilitated.

[0014] Further, the control assembly each includes a symmetrically arranged threaded rod, the threaded rod is rotationally connected with the corresponding sleeve side wall, the threaded rod is provided with a conical structure at one end close to the center of the sleeve, the conical end of the threaded rod extends to the bottom of the corresponding bottom plate, and the connecting block is fixedly connected with a pull rod away from the first wedge block.

[0015] Beneficial effects: when locked, rotating the threaded rod makes the conical end lift the bottom plate, compresses the second spring, and the bottom plate pushes the connector to move upwards, the snap ring is more closely attached to the first wedge block, and the radial clamping force is increased; when unlocked, the threaded rod is reversely rotated, the conical end is separated from the bottom plate, the second spring is reset, the bottom plate moves downwards, the pressure between the connector and the wedge block is released, and the connector can be pulled out after the pull rod is pulled outwards; the height of the bottom plate is controlled by rotating the threaded rod to push the bottom plate up and down, and the locking of the connector is controlled.

[0016] Further, the threaded rod is fixedly connected with a handle at one end away from the center of the sleeve.

[0017] Beneficial effects: the handle increases the contact area of operation, avoids slipping in a weightless environment, and improves assembly efficiency.

[0018] Further, the second wedge block is embedded with a shape memory alloy plate.

[0019] Beneficial effects: automatically compensates for the assembly gap at low temperature, reduces the connection loosening caused by thermal expansion and cold contraction, and improves the stability at extreme temperature.

[0020] Further, the phase transition temperature of the shape memory alloy plate is -100℃ to -60℃.

[0021] Beneficial effects: ensures that the alloy plate is only activated in a low-temperature space environment, avoids accidental triggering during ground normal-temperature assembly, and balances ground debugging and on-orbit performance.

[0022] Further, the top of the sleeve is fixedly connected with a guide cylinder.

[0023] Beneficial effects: when the connector is inserted, the guide cylinder corrects the radial deviation through the conical inner wall, ensures that the snap ring is accurately aligned with the center of the sleeve, and reduces the assembly resistance; reduces the requirement for positioning accuracy of on-orbit operation, shortens the assembly time, and is especially suitable for scenes with large mechanical arm operation errors.

[0024] Further, the elastic ring is fixedly connected at the entrance of the sleeve.

[0025] Beneficial effects: when the connector contacts the elastic ring, the elastic deformation absorbs the initial kinetic energy, reduces the impact damage to the sleeve and the connector, and at the same time, the friction force assists in preliminary positioning; avoids micro-cracks in composite components during assembly collision, prolongs the service life, and at the same time, prevents impurities from entering the sleeve to cause structure jamming.

[0026] Further, the bottom plate top is fixedly connected with a buffer layer.

[0027] Beneficial effect: the bottom plate top is fixedly connected with a buffer layer, absorbing the impact force when the connecting head contacts the bottom plate; when the connecting head is inserted into the bottom, the buffer layer disperses the impact force through plastic deformation, avoiding stress concentration caused by rigid contact; protecting the second spring and the bottom plate structure, especially reducing the risk of component damage in emergency docking or accidental collision.

[0028] Further, the angle between the bevel of the snap ring and the bevel of the second wedge block is 30-45°.

[0029] Beneficial effect: the angle of the bevel of the snap ring, the first wedge block, and the second wedge block is set to 30°-45°, based on the friction self-locking condition, the bevel angle is designed to be smaller than the friction angle; within this angle range, the normal force between the wedge blocks is decomposed into radial clamping force and axial component force, the axial component force is smaller than the pre-tightening force of the second spring, ensuring the stability of self-locking; at the same time, avoiding excessive assembly resistance caused by too small angle.

[0030] Further, the bevel of the snap ring, the first wedge block, and the second wedge block are all provided with a polytetrafluoroethylene wear-resistant coating.

[0031] Beneficial effect: reducing the friction coefficient of the contact surface, reducing wear, when long-term vibration or multiple disassembly and assembly, the coating avoids direct contact between metal / composite materials, reducing friction heat and surface scratches, maintaining the fitting accuracy of the bevel, and improving the reusability of the connection structure. BRIEF DESCRIPTION OF DRAWINGS

[0032] Figure 1 It is the overall axonometric view of the space in-orbit composite material component assembly connection structure embodiment of the application;

[0033] Figure 2 It is the sleeve forward sectional view of the space in-orbit composite material component assembly connection structure embodiment of the application;

[0034] Figure 3 It is the appendix of the space in-orbit composite material component assembly connection structure embodiment of the application Figure 2 Detail view at -A;

[0035] Figure 4 It is the connecting head locking forward sectional view of the space in-orbit composite material component assembly connection structure embodiment of the application;

[0036] Figure 5 It is the appendix of the space in-orbit composite material component assembly connection structure embodiment of the application Figure 4 Detail view at -B;

[0037] Figure 6 It is the connecting head internal structure schematic view of the space in-orbit composite material component assembly connection structure embodiment of the application.

[0038] List of reference numerals in the attached diagram:

[0039] The components are as follows: 1. Truss rod; 2. Connector; 3. Female connector; 4. Snap ring; 5. Sleeve; 6. Groove; 7. First spring; 8. Connecting block; 9. First wedge block; 10. Second wedge block; 11. Base plate; 12. Second spring; 13. Threaded rod; 14. Handle; 15. Guide cylinder; 16. Elastic ring; 17. Tie rod. Detailed Implementation

[0040] The present invention will be further illustrated below with reference to the accompanying drawings and specific embodiments. It should be understood that the following specific embodiments are for illustrative purposes only and are not intended to limit the scope of the invention. It should be noted that the terms "front," "rear," "left," "right," "up," and "down" used in the following description refer to directions in the accompanying drawings, and the terms "inner" and "outer" refer to directions toward or away from the geometric center of a specific component, respectively.

[0041] Example 1:

[0042] As attached Figure 2 As shown: A space-based on-orbit composite material component assembly and connection structure includes truss rods 1. Traditional truss rod 1 connections involve drilling holes at the ends of the truss rods 1 to facilitate bolt connections. However, drilling these holes can cause fiber breakage and stress concentration in the composite material, reducing connection strength. To improve the connection strength of the truss rods 1, as shown in the attached diagram... Figure 1 Appendix Figure 2 Appendix Figure 3 and attached Figure 6 As shown, one end of the truss rod 1 is integrally formed with a connector 2, and one end of the connector 2 is detachably connected to a female connector 3; the bottom of the connector 2 is set as a conical structure, and a retaining ring 4 is welded to the side wall of the connector 2 along its circumference; the top of the retaining ring 4 is set as a sloping structure, and the side of the top sloping surface of the retaining ring 4 closer to the connector 2 is lower than the other side.

[0043] The female joint 3 is fixedly connected with a plurality of sleeves 5 arranged uniformly, the top of each sleeve 5 is welded with a guide cylinder 15, and the inlet of each sleeve 5 is fixedly connected with an elastic ring 16 through adhesive, so that impurities are prevented from entering the connection node, the inner side wall of each sleeve 5 is provided with a horizontal groove 6 arranged symmetrically in the middle, the groove 6 is welded with a first spring 7, the other end of the first spring 7 is welded with a connecting block 8, the side wall of the connecting block 8 is welded with a first wedge block 9, the bottom of the first wedge block 9 is welded with a second wedge block 10, the first wedge block 9 and the second wedge block 10 are higher on the side away from the connecting head 2 than on the other side, the inclined surface of the clamping ring 4, the first wedge block 9 and the second wedge block 10 is provided with a polytetrafluoroethylene wear-resistant coating, and the angle between the inclined surface of the clamping ring 4 and the inclined surface of the second wedge block 10 is 30-45°, based on the friction self-locking condition, the design of the inclined surface with an angle smaller than the friction angle, within the angle range, the normal force between the wedge blocks is decomposed into a radial clamping force and an axial component force, the axial component force is smaller than the pre-tightening force of the second spring 12, so as to ensure the stability of self-locking; the inner bottom wall of the sleeve 5 is provided with a bottom plate 11, the bottom of the bottom plate 11 is welded with a plurality of second springs 12, the other end of the second spring 12 is welded with the inner bottom wall of the corresponding sleeve 5, after the connecting head 2 is inserted into the sleeve 5, the top of the clamping ring 4 can be at the same horizontal height as the bottom wall of the groove 6 by extruding the bottom plate 11 and the second spring 12, so as to ensure that the second wedge block 10 can be popped out, and the connecting head 2 is axially preliminarily pre-tightened by the rebound force of the second spring 12 after the second wedge block 10 is popped out;

[0044] After the connecting head 2 is preliminarily pre-tightened, in order to avoid impact in use, high-speed movement of dust in space and the like causing the connecting head 2 to move up and down and thus generating a retraction space of the second wedge block 10, the bottom of the sleeve 5 is provided with a control assembly for controlling locking and unlocking of the corresponding connecting head 2, as shown in Figure 2 and Figure 4 The control assembly includes symmetrically arranged threaded rods 13, the threaded rods 13 are rotationally connected with the side wall of the corresponding sleeve 5, the threaded rod 13 close to the center of the sleeve 5 is provided with a conical structure, the conical end of the threaded rod 13 extends to the bottom of the corresponding bottom plate 11, the threaded rod 13 away from the center of the sleeve 5 is welded with a handle 14, the side of the connecting block 8 away from the first wedge block 9 is welded with a pull rod 17, the other end of the pull rod 17 extends to the outside of the sleeve 5 by penetrating through the wall of the corresponding sleeve 5; the lifting height of the bottom plate 11 is controlled by the threaded rod 13 to control the unlocking state of the connecting head 2; the top of the bottom plate 11 is glued with a buffer layer, which can absorb the impact force when the connecting head 2 contacts the bottom plate 11.

[0045] The specific implementation process is as follows: When assembling the truss structure, first align the connector 2 at one end of the truss rod 1 with the guide cylinder 15 at the top of the sleeve 5 on the female connector 3. The conical inner wall of the guide cylinder 15 can correct the radial deviation when the connector 2 is inserted, ensuring that the retaining ring 4 is accurately aligned with the center of the sleeve 5, reducing the requirements for positioning accuracy during on-orbit operation, which is especially suitable for scenarios with large operating errors of the robotic arm. At the same time, the elastic ring 16 at the entrance of the sleeve 5 undergoes elastic deformation when the connector 2 contacts, reducing the impact damage to the sleeve 5 and the connector 2, avoiding micro-cracks in the composite material components during assembly collisions, and extending the service life.

[0046] As connector 2 continues to be inserted, base plate 11 moves downward under the pressure of connector 2, compressing the second spring 12 at the bottom of base plate 11. Meanwhile, retaining ring 4 moves downward in sync with connector 2. The bottom of retaining ring 4 first presses against the inclined surface of first wedge block 9, pushing first wedge block 9 into the corresponding groove 6, compressing the first spring 7 in groove 6 to store energy. Connecting block 8 and second wedge block 10 move downward in sync with first wedge block 9 into the corresponding groove 6. Retaining ring 4 continues to move downward, and the side wall of retaining ring 4 contacts the side wall of second wedge block 10 and continuously applies compressive force.

[0047] As connector 2 is continuously inserted, the second spring 12 is further compressed. When the retaining ring 4 descends to the point where its top is level with the bottom of the groove 6, the squeezing force of the retaining ring 4 on the second wedge block 10 disappears. The first spring 7 releases its rebound force, pushing the connecting block 8, the first wedge block 9, and the second wedge block 10 to pop out and reset towards the center of the sleeve 5, as shown in the attached figure. Figure 4 and attached Figure 5 As shown, the inclined surface of the second wedge block 10 is in close contact with the inclined surface of the retaining ring 4. Since the angle between the inclined surface of the retaining ring 4 and the inclined surface of the second wedge block 10 is designed to be 30-45°, based on the friction self-locking condition (the inclined surface angle is less than the friction angle), the normal force between the wedge blocks within this angle range can be decomposed into radial clamping force and axial component force. The axial component force is less than the preload force of the second spring 12, ensuring self-locking stability. At this time, the rebound force of the first spring 7 is converted into the radial clamping force between the second wedge block 10 and the retaining ring 4, achieving preliminary radial fixation of the connector 2.

[0048] Next, by rotating the bottom handle 14 of the sleeve 5, the handle 14 drives the threaded rod 13 to rotate, and its conical end gradually pushes up the base plate 11. The base plate 11 pushes the connector 2 upward, making the snap ring 4 and the second wedge block 10 fit more tightly, increasing the radial clamping force, and achieving axial locking of the connector 2. At this time, the connector 2 is firmly fixed in both the radial and axial directions.

[0049] When used in space, if subjected to external impact force, the connector 2 has a tendency to tilt upward or oblique, and the inclined surface of the clamping ring 4 will further press the second wedge block 10. The first spring 7 is compressed and the reaction force increases. The normal force is converted into a larger radial clamping force through the inclined surface, and the impact force is converted into internal stress of the structure. The larger the external disturbance, the greater the radial clamping force, the more secure the connection, solving the problem of traditional bolt connection loosening under vibration. Moreover, the entire connection process does not require drilling holes on the truss rod 1, avoiding the fiber breakage and stress concentration caused by drilling holes. The force is transmitted through the surface contact between the connector 2 and the female connector 3, protecting the integrity of the composite material component.

[0050] When unlocking is needed, the threaded rod 13 is rotated in the opposite direction, the conical end of the threaded rod 13 gradually separates from the bottom plate 11, the second spring 12 releases the elastic force, driving the bottom plate 11 to move downward, the pressure of the bottom plate 11 on the connector 2 is released, and the pressure between the clamping ring 4 and the second wedge block 10 is synchronously released. At this time, the pull rod 17 is pulled outward, the pull rod 17 drives the connecting block 8, the first wedge block 9 and the second wedge block 10 to move into the groove 6, so that the first wedge block 9 and the second wedge block 10 are out of contact with the clamping ring 4. The connector 2 can be pulled out of the sleeve 5, realizing the disassembly of the connector 2 and the female connector 3, and facilitating in-orbit maintenance.

[0051] According to the space in-orbit composite material component assembly connection structure of embodiment 1 and the traditional truss structure of international space station, the specific experiment is as follows:

[0052] Purpose of the experiment: compare the performance differences of the structure of embodiment 1 and the traditional bolt connection structure in the simulated space environment, focus on evaluating the connection stability, impact resistance, disassembly convenience and influence on the integrity of the composite material of the two connection structures, in order to verify the advantages of the structure of embodiment 1 in solving the problems of traditional bolt connection such as easy loosening and stress concentration caused by drilling holes.

[0053] Experimental steps:

[0054] 1. Sample preparation: prepare a group of truss rod samples using the connection structure of embodiment 1 and a group of truss rod samples using traditional bolt connection. All samples are made of the same carbon fiber composite material, with consistent size and geometric shape.

[0055] 2. Environmental simulation: place the samples in a vacuum chamber to simulate the microgravity environment in space, and use a temperature control system to cycle the temperature between -100°C and 100°C to simulate the extreme temperature fluctuations in space.

[0056] 3. Connection strength test: apply axial tensile and compressive forces to the two connection structures, use a universal testing machine to load gradually until failure, and record the maximum bearing capacity.

[0057] 4. Impact resistance test: Apply radial and axial impacts to the connection node using a pneumatic impact device, simulating space debris or fragment impacts, with an impact energy of 10 J. Measure the displacement and loosening of the connection structure after impact.

[0058] 5. Vibration test: Fix the connection structure on an electric vibration table and apply random vibration with a frequency range of 5-2000 Hz for 1 hour, simulating the vibration environment during launch or orbital operation. Measure the fretting wear and loosening tendency of the connection point.

[0059] 6. Disassembly test: Record the time required for two connection structures to go from the locked state to complete disassembly, and observe the wear of the components during disassembly.

[0060] 7. Composite material integrity check: Use a scanning electron microscope (SEM) to inspect the composite material surface near the connection point, observing fiber breakage, cracks, or stress concentration phenomena.

[0061] Experimental data:

[0062] Test item Example 1 connection structure Conventional bolt connection structure Maximum tensile load (kN) 120 100 Maximum compressive load (kN) 115 95 Looseness after impact (mm) 0.02 0.15 Connection looseness rate after vibration (%) 0.5 15.0 Disassembly time (min) 6 16 Damage degree of composite material No visible damage Fiber fracture is obvious Change in gap after temperature cycle (mm) 0.01 (shape memory alloy compensation) 0.10 (thermal expansion and contraction)

[0063] Experimental conclusion:

[0064] The experimental results show that the space in-orbit composite material component assembly connection structure of Example 1 is superior to the traditional bolt connection structure in various performance indicators. The structure of Example 1 converts external impact force into radial clamping force through the wedge-shaped inclined surface, significantly improving the connection stability and showing extremely low loosening in impact and vibration tests. At the same time, the structure does not need to be punched, avoiding composite material fiber breakage and stress concentration, protecting the component integrity. In addition, the structure of Example 1 is faster to disassemble, facilitating in-orbit maintenance. The introduction of shape memory alloy plates effectively compensates for the gap caused by temperature changes, enhancing the reliability in extreme environments. Therefore, the connection structure of Example 1 is more suitable for space in-orbit assembly tasks and has high engineering application value.

[0065] Obviously, the above examples are only examples for clarity and do not limit the embodiments. Based on the above description, other different forms of changes or variations can be made by those of ordinary skill in the art. Here, it is not necessary and impossible to exhaust all embodiments. The obvious changes or variations derived therefrom are still within the protection scope of the present invention.

[0066] The composite fiber breakage and stress concentration are avoided, and the component integrity is protected. In addition, the structure of the embodiment 1 is disassembled more quickly, and the on-orbit maintenance is facilitated. The introduction of the shape memory alloy plate effectively compensates the gap caused by temperature change, and enhances the reliability in extreme environment. Therefore, the connecting structure of the embodiment 1 is more suitable for the space on-orbit assembly task, and has higher engineering application value.

[0067] Embodiment 2

[0068] As shown in the accompanying drawings, Figure 1 The difference from the embodiment 1 is that, due to the absence of heat transfer and heat dissipation in space as in the ground air, the side directly irradiated by sunlight can produce a high temperature of more than 100 DEG C. While the shady side, the temperature can be as low as -100 DEG C to -200 DEG C, leading to more significant thermal expansion and cold contraction of the component. In order to prevent the problem that the connection is loose or falls off due to the cold contraction of the component at too low temperature, the second wedge-shaped block 10 is embedded with a shape memory alloy plate on the inclined surface. The phase transition temperature of the shape memory alloy plate is -100 DEG C to -60 DEG C. The assembly gap is automatically compensated by the shape memory alloy plate at low temperature, the connection looseness caused by thermal expansion and cold contraction is reduced, the stability under extreme temperature is improved, and the alloy plate is activated only in the low-temperature environment in space through the phase transition temperature control of the shape memory alloy plate, so that the mis-triggering during the ground normal temperature assembly is avoided, and the ground debugging and on-orbit performance are considered.

[0069] The technical means disclosed in the scheme of the application is not only limited to the technical means disclosed in the above-mentioned embodiments, but also includes the technical scheme composed of any combination of the above technical features.

Claims

1. A space in-orbit composite material component assembly connecting structure comprising a truss rod (1), characterized in that: The truss rod (1) one end is fixedly connected with the connector (2), and the connector (2) one end is detachably connected with the female connector (3); the bottom of the connector (2) is provided as a tapered structure, the side wall of the connector (2) is fixedly connected with the snap ring (4) along the circumference thereof, the top of the snap ring (4) is provided as an inclined surface structure, and the top of the snap ring (4) inclined surface near one side of the connector (2) is lower than the other side; a plurality of sleeve (5) are fixedly connected on the female connector (3) and are uniformly arranged, the inner side wall of the sleeve (5) is provided with a horizontal groove (6) symmetrically arranged in the middle, the first spring (7) is fixedly connected in the groove (6), the other end of the first spring (7) is fixedly connected with the connecting block (8), the side wall of the connecting block (8) is fixedly connected with the first wedge block (9), the bottom of the first wedge block (9) is fixedly connected with the second wedge block (10), the first wedge block (9) and the second wedge block (10) are higher on the side away from the connector (2) than on the other side, the inner bottom wall of the sleeve (5) is provided with the bottom plate (11), the bottom plate (11) is fixedly connected with a plurality of second springs (12) at the bottom, the other end of the second spring (12) is fixedly connected with the inner bottom wall of the corresponding sleeve (5), and the bottom of the sleeve (5) is provided with a control assembly for controlling locking and unlocking of the corresponding connector (2).

2. The space in-orbit composite material component assembly connecting structure according to claim 1, characterized in that: The control assembly comprises symmetrically arranged threaded rods (13), the threaded rods (13) are rotatably connected with the side wall of the corresponding sleeve (5), the threaded rod (13) is provided as a conical structure at one end near the center of the sleeve (5), the conical end of the threaded rod (13) extends to the bottom of the corresponding bottom plate (11), the side away from the first wedge block (9) of the connecting block (8) is fixedly connected with the pull rod (17), and the other end of the pull rod (17) extends to the outside of the sleeve (5) through the wall of the corresponding sleeve (5).

3. The space in-orbit composite material component assembly connecting structure according to claim 2, characterized in that: The threaded rod (13) is fixedly connected with the handle (14) at one end away from the center of the sleeve (5).

4. The space in-orbit composite material component assembly connecting structure according to claim 1, characterized in that: The second wedge block (10) is embedded with a shape memory alloy plate.

5. The space in-orbit composite material component assembly connecting structure according to claim 4, characterized in that: The phase transition temperature of the shape memory alloy plate is -100℃ to -60℃.

6. The space in-orbit composite material component assembly connecting structure according to claim 1, characterized in that: The top of the sleeve (5) is fixedly connected with the guide cylinder (15).

7. The space in-orbit composite material component assembly connecting structure according to claim 6, characterized in that: The elastic ring (16) is fixedly connected at the inlet of the sleeve (5).

8. The space in-orbit composite material component assembly connecting structure according to claim 7, characterized in that: The top of the bottom plate (11) is fixedly connected with the buffer layer.

9. The space in-orbit composite material component assembly connecting structure according to claim 1, characterized in that: The angle between the inclined surface of the snap ring (4) and the inclined surface of the second wedge block (10) is 30-45°.

10. The space in-orbit composite material component assembly connecting structure according to claim 9, characterized in that: The inclined surfaces of the snap ring (4), the first wedge block (9) and the second wedge block (10) are provided with a polytetrafluoroethylene wear-resistant coating.

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