Large-bearing and multifunctional truss and flat plate combined type load adaptive structure

Abstract

The invention provides a large-bearing and multifunctional truss and flat plate combined type load adaptive structure. The large-bearing and multifunctional truss and flat plate combined type load adaptive structure comprises a top plate and a truss rod system. The bottom of the top plate is supported by a truss rod system; the + Z side of the load adaptation structure is provided with a plurality of mechanical interfaces connected with effective loads, a plurality of mechanical interfaces connected with the pointing adjusting mechanism and a plurality of mechanical interfaces connected with the deployable component. The-Z side of the load adaptation structure provides a plurality of mechanical interfaces connected with a satellite platform. The device has the characteristics of high rigidity, high precision, high dimensional stability and light weight, the problems of effective load, ultra-large-diameter expandable components, bearing of a pointing adjusting mechanism, high-precision installation, response control and the like are considered, the structure bearing efficiency is high, an effective load interface adopts a multipoint concentrated force transmission mode, and the structure is simple and convenient to operate. The load adaptation structure can adapt to installation of various effective loads and equipment on the basis of truss topology and top plate size adjustment.

Description

Technical Field

[0001] This invention belongs to the field of spacecraft structure technology and relates to a combined load adaptation structure. Background Technology

[0002] The load adapter structure is installed between the satellite platform and the payload to achieve force transmission between the two and ensure the installation rigidity and accuracy of the payload. According to published literature, satellite load adapter structures generally adopt metal frame structures, composite material plate shell structures, grid structures, truss structures, etc. The structural forms and functions are relatively simple. They can generally only adapt to a single payload load, and there are rarely combinations of different structural forms (such as the combination of truss and plate). They also do not have the ability to install and support other equipment (such as large deployable parts, pointing adjustment mechanisms, etc.). Their functions are simple and their load-bearing capacity is low (not higher than 2t). Summary of the Invention

[0003] The technical problem this invention aims to solve is: Addressing the high-precision installation requirements of ultra-large effective loads (over 3 tons), ultra-large diameter deployable components, and directional adjustment mechanisms, this invention proposes a novel load-bearing, multi-functional, truss-plate combination load-bearing structure. This structure features high rigidity, high precision, high dimensional stability, and lightweight design. It addresses issues related to effective load, ultra-large diameter deployable components, directional adjustment mechanism load bearing, high-precision installation, and response control. The structure boasts high load-bearing efficiency, and the effective load interface employs a multi-point centralized force transmission method. This load-bearing structure can adapt to the installation of various effective loads and equipment based on adjustments to the truss topology and top plate dimensions.

[0004] The technical solution adopted in this invention is: a high-load-bearing, multi-functional, truss-plate combined load-adaptive structure, including a top plate and a truss system; The top plate is a ring-shaped flat plate, and the bottom is supported by a truss system; The +Z side of the load adaptation structure provides several mechanical interfaces for connecting to the effective load, several mechanical interfaces for connecting to the pointing adjustment mechanism, and several mechanical interfaces for connecting to the deployable component. The -Z side of the load adaptor structure provides several mechanical interfaces for connection to the satellite platform.

[0005] Furthermore, the truss system includes: a main load joint, uprights, diagonal braces, a lower main joint, a first lower middle joint, a second lower middle joint, a directional adjustment mechanism support rod, an upper joint of the directional adjustment mechanism support rod, and crossbars; The truss system is a regular hexagonal frame on the OXY plane. The lower main joints are located at the vertices of the regular hexagonal frame, the second lower middle joints are located at the centers of a pair of parallel sides of the regular hexagonal frame, and the first lower middle joints are located at the centers of the remaining four sides of the regular hexagonal frame. The lower main joints, the first lower middle joints, and the second lower middle joints are connected by crossbars. Each payload main connector is located directly below the mechanical interface that connects to the payload, and is connected to the payload through the top plate; each payload main connector is connected to the lower main connector through the upright, and is connected to the first lower middle connector through the diagonal brace. Each of the first lower middle joints is connected to the pointing adjustment mechanism support rod and the pointing adjustment mechanism support rod upper joint, respectively. The pointing adjustment mechanism support rod upper joint is connected to the pointing adjustment mechanism through the top plate.

[0006] Furthermore, the truss system also includes: a first deployable component support rod and a first deployable component support rod upper connector; each lower main connector is connected through the first deployable component support rod and the first deployable component support rod upper connector, and the first deployable component support rod upper connector is connected to the deployable component through a top plate.

[0007] Furthermore, the truss system also includes: a second deployable component support rod, a second deployable component support rod upper connector, each first lower and middle connector being connected via the second deployable component support rod and the second deployable component support rod upper connector, and the second deployable component support rod upper connector being connected to the deployable component via a top plate.

[0008] Furthermore, the top plate adopts a carbon fiber composite material skin sandwich structure, including a carbon fiber composite material panel and an aluminum honeycomb core.

[0009] Furthermore, the aforementioned high-load-bearing, multi-functional truss-plate combined load-adaptive structure also includes an effective load adjustment pad and a deployable component adjustment pad. The effective load interface adjustment pad and the deployable component interface adjustment pad are respectively bonded to several mechanical interfaces on the top plate + Z surface that are connected to the effective load and several mechanical interfaces that are connected to the deployable components.

[0010] Furthermore, the uprights, diagonal braces, horizontal braces, directional adjustment mechanism support rods, first deployable component support rods, and second deployable component support rods are all made of carbon fiber wound molding and pressure cured.

[0011] Furthermore, the payload main connector, lower main connector, first lower middle connector, second lower middle connector, first deployable component support rod upper connector, second deployable component support rod upper connector, and pointing adjustment mechanism support rod upper connector are formed by metal machining or 3D printing.

[0012] The advantages of this invention compared to the prior art are: 1. The load-adaptive structure described in this invention ensures that, under the constraints of configuration size and structural weight, it can meet the load-bearing requirements of 3t-class effective load, pointing adjustment mechanism, ultra-large deployable component, cable, etc., and can expand or shrink the load-bearing capacity according to the requirements by changing the design parameters, which has the advantage of high adaptability. 2. The load adaptation structure described in this invention is a combination of a ring plate and a truss structure, which realizes the sinking installation of the effective load, thereby significantly reducing the height of the satellite's center of mass and the moment of inertia, providing a good dynamic environment for the satellite launch phase and facilitating the on-orbit control of the satellite. 3. The load adaptation structure top plate and truss system described in this invention are both made of carbon fiber composite material, which has high thermal stability and provides a high dimensional stability platform for the effective load to work in orbit. 4. The -Z side of the load adaptation structure described in this invention is hexagonal, providing a docking interface with the satellite platform. At the vertex position, six main force transmission points are provided, and at the midpoint of the hexagonal side length, six auxiliary force transmission points are provided, thereby reducing the concentrated load on the main force transmission points. 5. The six lower main joints of the load adaptation structure described in this invention are located directly below the six effective load main joints. Most of the main load can be directly transferred to the satellite platform through the uprights, which has the advantages of short force transmission path and high structural efficiency. 6. All uprights, diagonal braces, crossbars, directional adjustment mechanism support rods, first deployable component support rods, and second deployable component support rods of the load adapting structure described in this invention are made of high-modulus carbon fiber wound molding, which has high strength and stiffness and high manufacturing efficiency. The uprights and diagonal braces mainly bear the effective load force, the directional adjustment mechanism support rods mainly improve the installation stiffness and strength of the directional adjustment mechanism, the first deployable component support rods and the second deployable component support rods mainly improve the installation stiffness and strength of the deployable component, and the crossbars mainly improve the reference accuracy maintenance capability of the load adapting structure and the platform docking. The above-mentioned rods adopt different diameter and wall thickness parameters according to different forces, which realizes both the transmission of ultra-large effective load and the lightweight structure. 7. The load-adaptive structure top plate of the present invention adopts a carbon fiber composite material skin aluminum honeycomb sandwich structure, which connects 6 effective load main joints, 6 first deployable component support rod upper joints, and 4 second deployable component support rod upper joints into one unit, enhancing the rigidity and accuracy retention capability of the load-adaptive structure. The effective load interface adjustment pad and deployable component interface adjustment pad on its upper surface provide machining allowance, and the flatness of the interface can be ensured by overall machining. The load-adaptive structure top plate can also provide installation interfaces for cables, counterweights and other equipment. In addition, the load-adaptive structure top plate has lightening holes to further improve the lightweight level of the structure, and has the advantage of high structural load-bearing efficiency. 8. The load-adaptive structure top plate of the present invention has six effective load interfaces, each with an integral carbon fiber composite C-shaped reinforcing frame pre-embedded in the plate, which improves the local strength of the effective load interfaces. 9. The effective load main connector of the load adaptation structure described in this invention is a three-way metal connector that connects one upright and two diagonal bars into one unit to jointly bear the main load. A cable opening is designed on the outer side of the effective load main connector, and the flange face of the effective load main connector provides a mechanical interface for installation. Attached Figure Description

[0013] Figure 1 For load-adaptive structural diagrams; Figure 2 This is a schematic diagram of the load-adaptive structure assembly. Detailed Implementation

[0014] The present invention will be described in conjunction with the accompanying drawings.

[0015] The load-adaptive structure proposed in this invention uses 6 mechanical connection interfaces with the effective load, and the main force transmission path uses 6 carbon fiber reinforced composite vertical poles and 12 carbon fiber reinforced composite diagonal poles, which solves the requirements of large load-bearing capacity, high rigidity and high precision for 3t effective loads, and can adapt to the requirements of effective load for structural dimensional stability. The load-adaptive structure and satellite platform employ 12 mechanical connection interfaces, of which 6 correspond to the connection positions of the 6 uprights and are the main force transmission points; the remaining 6 correspond to the connection positions of the diagonal braces and are auxiliary force transmission points, reducing the load on the main force transmission points. The load-adaptive structure uses 10 deployable component support rods, which improves the installation rigidity of large-diameter deployable components; it also uses 4 pointing adjustment mechanism support rods, which improves the installation rigidity of the pointing adjustment mechanism. The load-adaptive structure top plate is a carbon fiber composite sandwich structure, providing 6 connection interfaces with the effective load, 10 connection interfaces with the deployable parts, and 4 connection interfaces with the pointing adjustment mechanism. It has strong versatility and adaptability, and solves the problems of centralized and unified installation, accuracy assurance and dimensional stability of various equipment. The top plate of the load-adapting structure connects the six upper joints of the effective load, the upper joints of the ten upper joints of the deployable component support rods, and the upper joints of the four upper joints of the directional adjustment mechanism support rods, thereby improving the overall rigidity of the load-adapting structure. The six lower main joints and six lower middle joints of the load-adapting structure are connected by 12 crossbars, which improves the ability of the entire load-adapting structure to maintain the reference accuracy. The load-bearing structure employs six tee connectors at the top to connect one upright and two diagonal braces, providing openings for the load-bearing cables; six four-way connectors at the bottom to connect two horizontal bars, one upright, and one extendable component support rod; four six-way connectors at the bottom center to connect two horizontal bars, two diagonal braces, one extendable component support rod, and one directional adjustment mechanism support rod; two four-way connectors at the bottom center to connect two horizontal bars, two diagonal braces, one extendable component support rod, and one directional adjustment mechanism support rod; four one-way connectors to connect the directional adjustment mechanism support rod to the top plate; and ten one-way connectors to connect the extendable component support rod to the top plate.

[0016] like Figure 1 , Figure 2 As shown, the satellite payload adaptation structure includes a payload adaptation structure top plate 1 and a truss system. The +Z side provides 6 mechanical interfaces for the payload, 4 mechanical interfaces for the pointing adjustment mechanism, and 10 mechanical interfaces for the deployable components. The -Z side provides 12 mechanical interfaces for connection to the satellite platform, of which the main force transmission joints are located at the vertices of the hexagon, and the auxiliary force transmission joints are located between the vertices.

[0017] Satellite payload adapter structure top plate 1, payload interface adjustment pad 2, deployable component interface adjustment pad 3, such as Figure 1 As shown. The load-adaptive structure top plate 1 has an annular flat plate configuration, avoiding interference with the effective load sinking equipment; the top plate 1 adopts a carbon fiber composite skin sandwich structure, which improves the installation rigidity of various equipment and is provided with several weight-reducing holes to reduce the structural weight; the upper surface of the load-adaptive structure top plate 1 provides 6 effective load interfaces near the inner circumference, and each effective load is reinforced with a pre-embedded carbon fiber composite annular frame; the upper surface provides 10 deployable component interfaces near the outer circumference; the effective load adjustment pad 2 and the deployable component adjustment pad 3 provide machining allowance, and the flatness of all mechanical interfaces is guaranteed through an overall machining process.

[0018] The truss system is a regular hexagonal frame on the OXY plane. The lower main joints 7 are located at the vertices of the regular hexagonal frame, the second lower middle joints 9 are located at the centers of a pair of parallel sides of the regular hexagonal frame, and the first lower middle joints 8 are located at the centers of the remaining four sides of the regular hexagonal frame. The lower main joints 7, the first lower middle joints 8, and the second lower middle joints 9 are connected by crossbars 16. The six main load connectors 4 of the load adapter structure are located directly below the load interface and are connected to the load through the top plate 1 of the load adapter structure. The main load is transmitted to the lower main connector 7, the first lower middle connector 8, and the second lower middle connector 9 through six uprights 5 (along the Z-axis direction) and twelve diagonal bars 6, respectively.

[0019] Four pointing adjustment mechanism support rods 10 are located between the first lower middle joint 8 and the pointing adjustment mechanism support rod upper joint 11. The pointing adjustment mechanism support rod upper joint 11 is connected to the pointing adjustment mechanism through the load adapting structure top plate 1 to improve the installation rigidity of the pointing adjustment mechanism. Six first deployable component support rods 12 are located between the lower main joint 7 and the upper joint 13 of the first deployable component support rods. The upper joint 13 of the first deployable component support rods is connected to the deployable component through the load-adaptive structure top plate 1. This is used to improve the installation rigidity of the deployable component. Four second deployable component support rods 14 are located between the first lower middle joint 8 and the second deployable component support rod upper joint 15. The second deployable component support rod upper joint 15 is connected to the deployable component through the load-adaptive structure top plate 1 to improve the installation rigidity of the deployable component. Twelve horizontal bars connect six lower main joints (7), four first lower middle joints (8), and two second lower middle joints (9) into one unit to enhance the rigidity and accuracy retention of the load-bearing structure.

[0020] The main load connector 4 is a three-way metal connector that connects one upright 5 and two diagonal braces 6 into one unit to jointly bear the main load. A cable opening is designed on the outer side of the main load connector 4, and the upper flange of the main load connector 4 provides a mechanical interface for installation. The lower main connector 7 is a four-way metal connector that connects one upright 5, two horizontal bars 16, and one first deployable component support rod 12 into one unit, transferring the load of the above-mentioned rods to the satellite platform. The lower flange of the lower main connector 7 provides a mechanical interface for docking with the satellite platform. The first lower central connector 8 is a six-way metal connector that connects two diagonal rods 6, two horizontal rods 16, one directional adjustment mechanism support rod 10, and one second deployable component support rod 14 into one unit, transferring the load of the above rods to the satellite platform. The lower flange of the first lower central connector 8 provides a mechanical interface for docking with the satellite platform. The second lower central joint 9 is a four-way metal joint that connects two diagonal bars 6 and two horizontal bars 16 into one unit, transferring the load of the aforementioned bars to the satellite platform. The lower flange of the second lower central joint 9 provides a mechanical interface for docking with the satellite platform. The novel load-bearing, multifunctional, truss-plate combined structure is as follows: 1) The uprights 5, diagonal braces 6, horizontal bars 16, directional adjustment mechanism support rods 10, first deployable component support rods 12, and second deployable component support rods 14 are all made of high-modulus carbon fiber through winding molding and pressure curing. 2) The adhesive surfaces of the above-mentioned composite material rods are machined to ensure the mating dimensions of the adhesive surfaces; 3) The payload main connector 4, lower main connector 7, first lower middle connector 8, second lower middle connector 9, first deployable component support rod upper connector 13, second deployable component support rod upper connector 15, and pointing adjustment mechanism support rod upper connector 11 are made of metal by machining or 3D printing. 4) The load-adaptive structure top plate 1 is a composite sandwich structure plate, which is composed of carbon fiber composite panel and aluminum honeycomb core through pressure curing. It provides installation interfaces for the effective load, three-super actuator and deployable parts through embedded parts. Carbon fiber composite C-shaped reinforcing frames are embedded in the plate at 6 effective load connection points. Effective load interface adjustment pad 2 and deployable part interface adjustment pad 3 are respectively bonded to the effective load and deployable part interfaces on the surface of top plate 1+Z. 5) Using adhesive bonding fixtures, the composite material rods and metal joints are assembled and bonded, and then cured at room temperature in one step to complete the assembly and forming of the truss system. 6) Glue the -Z surface of the load-adapting structure top plate 1 to the +Z surface of the truss member joint; 7) Based on the overall satellite reference, the payload interface adjustment pad 2 and the deployable component interface adjustment pad 3 were combined and machined to complete the final mechanical interface machining of the load adaptation structure, ensuring the flatness of all mechanical interfaces.

[0021] Structural strength analysis under launch conditions was performed using Patran / Nastran finite element software. The uprights, diagonal braces, horizontal braces, pointing adjustment mechanism support rods, and deployable component support rods of the load adaptation structure were simulated using beam elements, the top plate of the load adaptation structure was simulated using shell elements, and various joints were simulated using solid elements. The Nastran analysis results included the stress, strain, and safety margin of each component. Through structural weight optimization, the final design parameters were determined while meeting the safety margin specifications, including parameters such as the layup, wall thickness, diameter, adhesive length, and joint wall thickness of the composite material rods.

[0022] To verify the effectiveness, a load-adaptive structure qualification component was manufactured and subjected to qualification-level mechanical environment testing along with the entire satellite. The test results show that the structural scheme described in this invention is correct, the parameters are reasonably selected, and it can meet the load-bearing requirements of a 3t-class effective load, pointing adjustment mechanism, and ultra-large deployable components. The stiffness and accuracy of the load-adaptive structure both meet the usage requirements.

[0023] In practical applications, the topology and structural parameters of the load-adaptive structure, top plate, and truss rods can be adjusted according to different requirements of effective load and installation equipment. This invention does not impose specific limitations on these aspects.

[0024] It should be noted that the contents not described in detail in this specification are achievable by those skilled in the art through the descriptions in this specification and the prior art, and will not be elaborated here.

[0025] The above description is merely a preferred embodiment of the present invention and is not intended to limit the scope of protection of the present invention. Those skilled in the art can make various modifications and substitutions to the present invention without creative effort, and all such modifications and substitutions should be covered within the scope of protection of the present invention.

[0026] The parts of this invention not described in detail are well-known to those skilled in the art.

Claims

1. A high-load-bearing, multi-functional, truss-plate combined load-adaptive structure, characterized in that, Includes the top plate (1) and the truss system; The top plate (1) is an annular flat plate, and the bottom is supported by a truss system; The +Z side of the load adaptation structure provides several mechanical interfaces for connecting to the effective load, several mechanical interfaces for connecting to the pointing adjustment mechanism, and several mechanical interfaces for connecting to the deployable component. The -Z side of the load adaptor structure provides several mechanical interfaces for connection to the satellite platform.

2. The high-load-bearing, multi-functional, truss-plate combined load-adaptive structure according to claim 1, characterized in that, The truss system includes: a load-bearing main joint (4), a vertical pole (5), a diagonal pole (6), a lower main joint (7), a first lower middle joint (8), a second lower middle joint (9), a pointing adjustment mechanism support rod (10), a pointing adjustment mechanism support rod upper joint (11), and a crossbar (16). The truss system is a regular hexagonal frame on the OXY plane. The lower main joints (7) are located at the vertices of the regular hexagonal frame, the second lower middle joints (9) are located at the center of a pair of parallel sides of the regular hexagonal frame, and the first lower middle joints (8) are located at the center of the other four sides of the regular hexagonal frame. The lower main joints (7), the first lower middle joints (8), and the second lower middle joints (9) are connected by crossbars (16). Each main load connector (4) is located directly below each mechanical interface connected to the load and is connected to the load through the top plate (1); each main load connector (4) is connected to the lower main connector (7) through the upright (5) and to the first lower middle connector (8) through the diagonal bar (6); Each of the first lower middle joints (8) is connected to the pointing adjustment mechanism support rod (10) and the pointing adjustment mechanism support rod upper joint (11) respectively. The pointing adjustment mechanism support rod upper joint (11) is connected to the pointing adjustment mechanism through the top plate (1).

3. The high-load-bearing, multi-functional, truss-plate combined load-adaptive structure according to claim 2, characterized in that, The truss system also includes: a first deployable component support rod (12) and a first deployable component support rod upper connector (13); each lower main connector (7) is connected through the first deployable component support rod (12) and the first deployable component support rod upper connector (13), and the first deployable component support rod upper connector (13) is connected to the deployable component through the top plate (1).

4. The high-load-bearing, multi-functional, truss-plate combined load-adaptive structure according to claim 3, characterized in that, The truss system further includes: a second deployable component support rod (14) and a second deployable component support rod upper connector (15). Each first lower middle connector (8) is connected through the second deployable component support rod (14) and the second deployable component support rod upper connector (15). The second deployable component support rod upper connector (15) is connected to the deployable component through the top plate (1).

5. The high-load-bearing, multi-functional, truss-plate combined load-adaptive structure according to claim 4, characterized in that, The top plate (1) adopts a carbon fiber composite material skin sandwich structure, including a carbon fiber composite material panel and an aluminum honeycomb core.

6. The high-load-bearing, multi-functional, truss-plate combined load-adaptive structure according to claim 5, characterized in that, It also includes a payload adjustment pad (2) and a deployable component adjustment pad (3). The payload interface adjustment pad (2) and the deployable component interface adjustment pad (3) are respectively bonded to several mechanical interfaces connected to the payload and several mechanical interfaces connected to the deployable components on the Z surface of the top plate (1).

7. The high-load-bearing, multi-functional, truss-plate combined load-adaptive structure according to claim 6, characterized in that, The upright (5), diagonal bar (6), horizontal bar (16), directional adjustment mechanism support rod (10), first deployable component support rod (12) and second deployable component support rod (14) are all made of carbon fiber winding and pressure cured.

8. The high-load-bearing, multi-functional, truss-plate combined load-adaptive structure according to claim 7, characterized in that, The payload main connector (4), lower main connector (7), first lower middle connector (8), second lower middle connector (9), first deployable component support rod upper connector (13), second deployable component support rod upper connector (15) and pointing adjustment mechanism support rod upper connector (11) are formed by metal machining or 3D printing.

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