A modular space architecture that can be assembled in orbit and its assembly components

Abstract

This invention provides a modular space architecture that can be assembled in orbit and its assembly components. It employs a 3D printing-like assembly method. After the basic structural members of the space architecture are transported to space, the assembly components modularly assemble them to form a working structural foundation. The basic components include three types: main poles, support poles, and joint components. The main poles are connected end-to-end to form a beam-column structure. Three beam-columns are arranged side-by-side at equal intervals to form a triangular cross-section. The joint components are fitted onto the main poles, with each joint component connecting to two support poles. Furthermore, the two support poles connected to the joint components on the main poles of each beam-column are respectively fixedly connected to the joint components on the main poles of the other two beam-columns.

Description

Technical Field

[0001] This invention belongs to the technical field of space frame equipment such as space satellite supports and space station architecture, and specifically relates to a modular space architecture that can be built in orbit and its building components. Background Technology

[0002] With the development of technology, both the needs in communication and the needs in space technology research and development require the launch of a large number of low-Earth orbit satellites for networking, and the construction of space research and development bases with an ever-expanding scale. Both require the launch of a large number of framework systems into space, including satellite telescopic and foldable antennas or modular expansion space station support frameworks.

[0003] Although foldable antennas can be launched into space in a retracted state and then automatically extend into a working state, the supporting frame structure obviously cannot be assembled before launch into space. Its excessive size would make it extremely easy to be damaged during launch, or it would be impossible to transport it at all. Summary of the Invention

[0004] Based on the above-mentioned technological status, the purpose of this invention is to provide a modular space architecture that can be assembled in orbit and its assembly components. It adopts a 3D printing-like assembly mode. After the basic components of the space architecture are transported to space, they are modularly assembled by the assembly components to form the foundation of the architecture in a working state.

[0005] The technical solution adopted in this invention is as follows: a modular space architecture that can be built in orbit, including three basic components: a main pole, support poles, and joint components. The main pole is connected end to end to form a beam column. The three beam columns are arranged side by side at equal intervals to form a triangular cross-section. The joint components are sleeved on the main pole. Each joint component is connected to two support poles, and the two support poles connected to the joint components on the main pole of each beam column are respectively fixedly connected to the joint components on the main poles of the other two beam columns.

[0006] The main rod includes a main body and a plug and a docking part located at both ends of the main body. The outer diameter of the plug is the same as the inner diameter of the docking part. The plug of each main rod is inserted into the docking part of another main rod. The outer periphery of the main body is evenly distributed with annular grooves at equal intervals. The outer periphery of the plug is also evenly distributed with annular grooves. The inner periphery of the docking part is evenly distributed with annular grooves. The outer diameter of the area between the annular grooves of the plug is slightly smaller than the inner diameter of the area between the annular grooves of the docking part. The docking part has a grouting port that penetrates the wall of the docking part.

[0007] The support rod includes a rod body and connectors located at both ends of the rod body, and the outer peripheral wall of the connectors is evenly distributed with annular grooves.

[0008] The joint component includes a collar portion and two joint heads inclinedly fixed to the collar portion. The two joint heads are inclined in the same direction in the axial direction, and the included angle between the two joint heads projects to 60° on the horizontal plane. The inner diameter of the collar portion is the same as the outer diameter of the main body portion of the main rod, so as to fix the joint component onto the main body portion of the main rod. The joint head is hollow, and the minimum inner diameter of the joint head is the same as the maximum outer diameter of the connector of the support rod. Both ends of each support rod are fixedly inserted into the joint head of the joint component. A wide groove is provided on the inner circumferential surface of the collar portion of the joint component, and the width of the wide groove covers at least two annular grooves on the main body portion. The inner circumferential surface of the joint head is evenly distributed with annular grooves, and the outer diameter of the area between the annular grooves of the connector is slightly smaller than the inner diameter of the area between the annular grooves of the joint head. The collar portion is provided with a grouting port penetrating its wall thickness, and the joint head is provided with a grouting port penetrating its wall thickness.

[0009] The grouting ports on the docking section, the collar section, and the joint head are all used to inject liquid adhesive material. The irregular shape formed after the liquid adhesive material cures secures the connection between the three base components. The liquid adhesive material is preferably liquid polyamide, but other curable adhesive materials can also be used.

[0010] The main rod can be a hollow rod or a solid rod. When a solid rod is used, the mating part is hollow to form a slot for the plug part to be inserted.

[0011] The present invention also claims protection for a construction component for assembling the aforementioned modular space architecture that can be assembled in orbit, comprising a longitudinal moving truss, a base, a circumferential moving truss, and a robotic arm. The base is slidably mounted on the longitudinal moving truss and is driven to reciprocate along the axial direction of the longitudinal moving truss. The circumferential moving truss is a ring structure, which is fixedly mounted on the base and is driven by the base to reciprocate. The robotic arm is a three-degree-of-freedom robotic arm, which is slidably mounted on the circumferential moving truss and is driven to move circumferentially along the circumferential moving truss.

[0012] The robotic arm includes at least a grouting robotic arm and a clamping robotic arm. The clamping robotic arm is used to clamp and fix the various basic components of the space structure, and the grouting robotic arm is used to bond the relative positions of the various basic components.

[0013] Furthermore, the longitudinal moving truss is a cuboid frame with a certain axial length, and the base is a square frame. The four corners of the square frame are slidably fitted onto the four columns of the cuboid frame. When the square frame slides along the axial direction of the cuboid frame, it drives the circumferential moving truss fixed inside the square frame to move.

[0014] The advantages of this invention are as follows: the space architecture is assembled from three basic components, which are convenient for standardized production and easy to transport in a dispersed state to space orbit; irregular gaps are formed between the basic components through annular grooves, and liquid solidifiable material is injected into these gaps. The hydraulic pressure of the liquid material causes the irregular gaps to tend towards maximizing volume, thereby automatically adjusting the relative positions between the basic components. This prevents the cumulative error of the entire space architecture from continuously increasing due to errors in the insertion dimensions, ensuring the stability and robustness of the space architecture structure. The assembly method, similar to 3D printing, using building components, makes the construction and assembly process faster, saves time, and can be automated. Attached Figure Description

[0015] Figure 1 This is a schematic diagram illustrating the construction process of the space architecture and its construction components of the present invention;

[0016] Figure 2 This is a schematic diagram of the overall structure of the space architecture of this invention;

[0017] Figure 3 This is a schematic diagram of the disassembled structure of the space architecture of the present invention;

[0018] Figure 4 This is a schematic diagram of the main pole structure of the space architecture of this invention;

[0019] Figure 5 This is a schematic cross-sectional view of the main pole of the space architecture of this invention;

[0020] Figure 6 yes Figure 5 Enlarged structural diagrams at points A and B in the middle;

[0021] Figure 7 This is a schematic diagram of the overlapping state of the two main poles of the space architecture of this invention;

[0022] Figure 8 This is a schematic diagram of the support rod structure of the space architecture of the present invention;

[0023] Figure 9 This is a schematic diagram of the joint component structure of the space architecture of the present invention;

[0024] Figure 10 This is a schematic diagram of the structure of the components used in this invention;

[0025] In the image: 1. Space architecture; 2. Building components;

[0026] 1-1 Main rod; 1-2 Support rod; 1-3 Joint component; 1-1-1 Plug part; 1-1-2 Main body part; 1-1-3 Butt joint part; 1-1-4 Grouting port; 1-2-1 Rod body; 1-2-2 Connector; 1-3-1 Collar part; 1-3-2 Joint head; 1-3-3 Collar part grouting port; 1-3-4 Joint head grouting port;

[0027] 2-1. Longitudinal moving truss; 2-2. Base; 2-3. Circumferential moving truss; 2-4. Grouting robotic arm; 2-5. Clamping robotic arm. Detailed Implementation

[0028] The present invention will be further described in detail below with reference to the accompanying drawings and embodiments.

[0029] The following specific embodiments illustrate the implementation method of the present invention. Those skilled in the art can easily understand other advantages and effects of the present invention from the content disclosed in this specification.

[0030] Referring to the accompanying drawings, the structures, proportions, sizes, etc., depicted in the drawings are merely for illustrative purposes to aid those skilled in the art in understanding and reading the content disclosed herein. They are not intended to limit the conditions under which the invention can be implemented and therefore have no substantial technical significance. Any modifications to the structure, changes in proportions, or adjustments to the size, without affecting the effects and objectives achieved by the invention, should still fall within the scope of the technical content disclosed herein. Furthermore, the positional limitations used in this specification are merely for clarity of description and are not intended to limit the scope of the invention. Changes or adjustments to their relative relationships, without substantially altering the technical content, should also be considered within the scope of the invention's implementation.

[0031] Figure 1 This is a schematic diagram illustrating the assembly process of the space architecture and its assembly components of the present invention. The assembly process of the space architecture adopts a mode similar to that of a 3D printer. The working part is the assembly component 2, which is an integral frame structure on which multiple robotic arms are mounted. The robotic arms are responsible for assembling the rods of the space architecture 1, such as... Figure 1 As shown, the robotic arm rotates circumferentially and moves axially on assembly component 2, gradually assembling the space architecture 1 into a complete structure. When the assembly range reaches the limit of assembly component 2, as... Figure 1 Once the robotic arm moves to the top of the outer frame, it moves the entire assembly component 2 along the assembly direction of the space architecture 1, allowing the robotic arm to continue assembling the space architecture 1 from the bottom of the outer frame of the assembly component 2.

[0032] To achieve the technical objectives of transporting components and 3D-printed assembly in space, this invention provides a self-designed space architecture 1, see [link / reference]. Figure 1 and Figure 2 These are, respectively, an overall structural diagram of the space architecture of the present invention and a disassembled structural diagram of the space architecture of the present invention. The assembled state of the space architecture 1 includes three beams and columns arranged in a triangle with equal spacing between them. Adjacent beams and columns are connected and fixed by support rods 1-2. Each beam and column is composed of multiple main rods 1-1 connected end to end. The space architecture 1 extends as it is built, that is, the length of the beams and columns is continuously extended by the continuous connection and assembly of the main rods 1-1. During the assembly process, the main rods 1-1 are connected and fixed to each other by the support rods 1-2 in real time.

[0033] See Figure 3 The space structure 1 includes three basic components: main rod 1-1, support rod 1-2, and joint component 1-3. The main rods 1-1 are connected end to end to extend the length of the beams and columns. The joint component 1-3 is fixedly sleeved on the main rod 1-1. The two ends of the support rod 1-2 are respectively fixed on two joint components 1-3 sleeved on different main rods 1-1, thereby fixing the relative position between the beams and columns.

[0034] Figure 4 This is a schematic diagram of the main structure of the space architecture of the present invention. As shown in the figure, the main structure 1-1 includes a main body 1-1-2 and a plug part 1-1-1 and a docking part 1-1-3 located at the beginning and end of the main body 1-1-2, respectively. The outer periphery of the main body 1-1-2 is evenly distributed with grooves along the circumference. The outer diameter of the plug part 1-1-1 is slightly smaller than the outer diameter of the main body 1-1-2, and the outer periphery of the plug part 1-1-1 is also evenly distributed with grooves along the circumference. The main body 1-1-2 can be a solid or hollow rod, but the connecting part 1-1-3 at the tail of the main body 1-1-2 is hollow inside, and grooves are evenly distributed around the circumference on the inner circumferential wall of the connecting part 1-1-3. The inner diameter of the connecting part 1-1-3 is adapted to the outer diameter of the plug part 1-1-1, so that the plug part 1-1-1 of one main rod 1-1 can be inserted into the connecting part 1-1-3 of another main rod 1-1, realizing the connection of the head and tail of the main rods 1-1. The connecting part 1-1-3 is also provided with a grouting port 1-1-4 communicating with the internal space of the connecting part 1-1-3. When the main rods are connected, liquid concrete or nylon material, etc., are injected through the grouting port 1-1-4. In this embodiment, liquid polyamide is specifically used. It solidifies in the gap between the plug part 1-1-1 and the connecting part 1-1-3 to achieve the fixation and bonding of the two.

[0035] Figure 5 This is a schematic cross-sectional view of the main strut of the space architecture of this invention. For specific details, please refer to [link / reference]. Figure 6 They are respectively Figure 5Enlarged structural diagrams at points A and B are shown. Point A is a partially enlarged cross-sectional view of the connecting part 1-1-3, showing multiple annular grooves evenly distributed on the inner circumferential wall of the connecting part 1-1-3. The grouting port 1-1-4 penetrates the wall of the connecting part 1-1-3 and communicates with its interior. Point B is a partially enlarged cross-sectional view of the plug part 1-1-1, whose outer diameter is slightly smaller than the outer diameter of the main rod 1-1, but matches the inner diameter of the connecting part 1-1-3. Multiple annular grooves are also evenly distributed on the outer circumferential surface of the plug part 1-1-1. See [reference needed] for details. Figure 7 This is a schematic diagram of the two main rods of the space architecture of the present invention in an overlapping state. The outer diameter of the two ends of the area with evenly distributed annular grooves of the plug part 1-1-1 is the same as the inner diameter of the two ends of the area with evenly distributed annular grooves of the docking part. However, in the area with evenly distributed annular grooves of both parts, the outer diameter of the part between the annular grooves of the plug part 1-1-1 is further reduced, and the inner diameter of the part between the annular grooves of the docking part 1-1-3 is further reduced. After the plug part 1-1-1 is inserted into the docking part 1-1-4, an irregular gap is formed between the two. Adhesive material is injected into this gap through the grouting port 1-1-4. After the adhesive material cures, a mating fastener is formed between the plug part 1-1-1 and the docking part 1-1-3, which firmly locks the two together. One of the advantages of the technical solution of the present invention is that when liquid adhesive material is injected into the gap through the grouting port 1-1-4, the liquid pressure itself will cause the gap to increase in volume, thereby enabling the plug part 1-1-1 and the docking part 1-1-3 to be inserted into the optimal position during the insertion and mating, so that the gap between them has the largest volume. The indirect effect is that the insertion length of each main rod 1-1 produced in a standardized manner is the same when docking. Thus, the three beams and columns can be kept at the same elongation speed as they are built, so that the cumulative length difference between the three beams and columns due to dimensional deviations will not destroy the structural stability of the space structure 1.

[0036] Figure 8 This is a schematic diagram of the support rod structure of the space architecture of the present invention. The support rod 1-2 includes a rod body 1-2-1 and connectors 1-2-2 located at both ends of the rod body 1-2-1. The structure of the connectors 1-2-2 is similar to that of a plug, and its outer peripheral wall is also provided with multiple evenly distributed annular grooves.

[0037] See Figure 9This is a schematic diagram of the joint component structure of the space architecture of the present invention. The joint component 1-3 includes a collar portion 1-3-1 and two joint heads 1-3-2 fixed on the collar portion 1-3-1. The two joint heads 1-3-2 are fixed at an angle or integrally formed on the collar portion 1-3-1. Preferably, the angle is such that the projection of the two joint heads 1-3-2 on the horizontal plane is 60°. The inner diameter of the collar portion 1-3-1 is the same as the outer diameter of the main body portion 1-1-2 of the main rod 1-1. A wide groove is formed on its inner circumferential surface. The width of the groove is preferably sufficient to cover the grooves on at least two main body portions 1-1-2. When the collar portion 1-3-1 is fitted onto the main body portion 1-1-2 of the main rod 1-1, liquid polyamide is injected into the collar portion 1-3-1 through the grouting port 1-3-3 provided on the collar portion 1-3-1. After solidification, the collar portion 1-3-1 is fixed on the main body portion 1-1-2. The inner circumferential surfaces of the two joint heads 1-3-2 are also provided with multiple evenly distributed annular grooves, and each joint head 1-3-2 is provided with a joint head grouting port 1-3-4. During assembly, the connector 1-2-2 of the support rod 1-2 is inserted into the joint head 1-3-2. The way they fit together is the same as the way the plug part 1-1-1 and the mating part 1-1-3 fit together. Liquid polyamide is injected into the gap between the connector 1-2-2 and the joint head 1-3-2 through the joint head grouting port 1-3-4 to fix the two together. For the sequential connection method, see [link to connection details]. Figure 2 and Figure 3 The two support rods 1-2 connected to the joint component 1-3 on the main rod 1-1 of each beam column are respectively fixedly connected to the joint components 1-3 on the main rods of the other two beam columns, thus forming a structure as shown in the figure. Figure 2 The three beams shown form a space structure with a triangular cross-section.

[0038] The assembly component 2 of this invention can adopt an existing three-degree-of-freedom robotic arm structure. Figure 10 This is a schematic diagram of the structure of the components used in this invention. The purpose is to clearly illustrate its structure. Figure 10 Only a small section of the external frame of component 2, namely the longitudinal moving truss 2-1, is retained in the middle. See [link / reference]. Figure 1The longitudinal moving truss 2-1 is a cuboid frame with a certain length. A base 2-2 is slidably installed on the longitudinal moving truss 2-1. The base 2-2 is driven by an electric component (motor, wheel, or motor, chain, etc.) to reciprocate along the longitudinal moving truss 2-1. An annular moving truss 2-3 is fixedly installed inside the base 2-2. A grouting robotic arm 2-4 and a clamping robotic arm 2-5 are slidably installed on the annular moving truss 2-3. Both robotic arms are three-degree-of-freedom robotic arms, and both can be driven by an electric component to move circumferentially along the annular moving truss 2-3. The grouting robotic arm 2-4 is used to inject liquid adhesive material into each grouting port. The clamping robotic arm 2-5 is used to clamp each component of the space structure 1 to assemble each component into place in sequence.

[0039] In the description of this invention, it should be understood that the use of terms such as "first," "second," and "third" to define components is merely for the purpose of distinguishing the aforementioned components. Unless otherwise stated, these terms have no special meaning and therefore should not be construed as limiting the scope of protection of this invention.

[0040] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention and not to limit them; although the present invention has been described in detail with reference to preferred embodiments, those skilled in the art should understand that modifications can still be made to the specific implementation of the present invention or equivalent substitutions can be made to some technical features without departing from the spirit of the technical solutions of the present invention, and all such modifications and substitutions should be covered within the scope of the technical solutions claimed in the present invention.

Claims

1. A modular space architecture assembly component capable of being built in orbit, characterized in that: The system includes a modular space architecture that can be assembled in orbit. The modular space architecture includes three basic components: a main pole, support poles, and joint components. The main poles are connected end to end to form a beam column. The three beam columns are arranged side by side at equal intervals to form a triangular cross-section. The joint components are fitted onto the main poles. Each joint component is connected to two support poles. The two support poles connected to the joint components on the main poles of each beam column are respectively fixedly connected to the joint components on the main poles of the other two beam columns. The main rod includes a main body and a plug and a docking part located at both ends of the main body. The outer diameter of the plug is the same as the inner diameter of the docking part. The plug of each main rod is connected to the docking part of another main rod for assembly. The support rod includes a rod body and connectors located at both ends of the rod body; The joint component includes a collar portion and two joint heads that are inclined and fixed on the collar portion. The two joint heads are inclined in the same direction in the axial direction and the included angle between the two joint heads is 60° when projected onto the horizontal plane. The inner diameter of the collar portion is the same as the outer diameter of the main body portion of the main rod, so as to fix the joint component on the main body portion of the main rod. The joint head is hollow, and the smallest part of the inner diameter of the joint head is the same as the largest part of the outer diameter of the connector of the support rod. Both ends of each support rod are fixedly inserted into the joint head of the joint component. The outer periphery of the main body is evenly distributed with annular grooves at equal intervals, the outer periphery of the plug is also evenly distributed with annular grooves, the inner periphery of the mating part is evenly distributed with annular grooves, the outer diameter of the area between the annular grooves of the plug is slightly smaller than the inner diameter of the area between the annular grooves of the mating part; the mating part is provided with a grouting port that penetrates the wall of the mating part. The outer peripheral wall of the connector is evenly distributed with annular grooves; The inner circumferential surface of the collar portion of the joint component is provided with a wide groove, the width of which at least covers the two annular grooves on the main body portion; the inner circumferential surface of the joint head is evenly distributed with annular grooves, and the outer diameter of the area between the annular grooves of the connector is slightly smaller than the inner diameter of the area between the annular grooves of the joint head; the collar portion is provided with a collar portion grouting port that penetrates its wall thickness, and the joint head is provided with a joint head grouting port that penetrates its wall thickness. The assembly also includes a longitudinal moving truss, a base, a circumferential moving truss, and a robotic arm. The base is slidably mounted on the longitudinal moving truss and is driven to reciprocate along the axial direction of the longitudinal moving truss. The circumferential moving truss is a ring structure, which is fixedly mounted on the base and is driven by the base to reciprocate. The robotic arm is a three-degree-of-freedom robotic arm, which is slidably mounted on the circumferential moving truss and is driven to move circumferentially along the circumferential moving truss. The robotic arm includes a grouting robotic arm and a clamping robotic arm.

2. The assembly components for the modular space architecture that can be assembled in orbit according to claim 1, characterized in that: The grouting ports on the docking part, the grouting ports on the collar part, and the grouting ports on the joint head are all used to inject liquid adhesive material. The connection position between the three basic components is locked by relying on the irregular shape formed after the liquid adhesive material is cured.

3. The assembly components for the modular space architecture that can be assembled in orbit according to claim 2, characterized in that: The liquid adhesive material is liquid polyamide.

4. The assembly components for the modular space architecture that can be assembled in orbit according to claim 1, characterized in that: The main rod is a hollow rod.

5. The assembly components for the modular space architecture that can be assembled in orbit according to claim 1, further characterized in that: The clamping robotic arm is used to clamp and fix the various basic components of the space structure, and the grouting robotic arm is used to bond the relative positions of the various basic components.

6. The assembly components for the modular space architecture that can be assembled in orbit according to claim 1 or 5, further characterized in that: The longitudinally moving truss is a cuboid frame, and the base is a square frame. The four corners of the square frame are slidably fitted onto the four columns of the cuboid frame.

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