A large-carrying satellite cabin section connecting structure combined with plate shell beams

Abstract

This invention provides a plate-shell-beam composite large-load satellite module connection structure to meet the requirements for connecting large remote sensing satellite modules and supporting large payloads. It includes a cylindrical shell, a load-bearing frame, a variable cross-section end frame, a frame-to-cylinder shell connecting piece, a frame-to-cylinder shell connecting corner box, and a cylindrical shell root connector. The cylindrical shell is fixed to the variable cross-section end frame, and the load-bearing frame passes through the cylindrical shell and is fixed to the variable cross-section end frame. The cylindrical shell and the load-bearing frame are connected by the frame-to-cylinder shell connecting piece and the frame-to-cylinder shell connecting corner box. The cylindrical shell and the variable cross-section end frame are connected by the cylindrical shell root connector, and a cylindrical shell root heat insulation pad is provided at the cylindrical shell root. The cylindrical shell has a connection interface with the propulsion service module, the load-bearing frame provides an installation interface for large payload equipment and payload modules, and the variable cross-section end frame provides an installation interface for small equipment and supports.

Description

Technical Field

[0001] This invention relates to a plate-shell-beam composite large-load satellite module connection structure, which is applicable to the main structure of spacecraft that needs to install large payloads, and belongs to the field of spacecraft structure technology. Technical Background

[0002] The remote sensing satellite module connection structure is a transitional structure between the satellite platform and various large remote sensing payloads. Due to the diversification of remote sensing missions and the increasing accuracy of large remote sensing satellites, the satellite module connection structure is required to have good adaptability to different loads, large load capacity (not less than 2500 kg), and high stability (on-orbit thermal deformation not greater than 50 μm).

[0003] Large remote sensing satellites typically carry multiple large cameras, with the main camera payload usually located at the top of the satellite or the bottom of the payload bay. The interface with the launch vehicle commonly uses a strap-type satellite-rocket unlocking device. Under the constraints of these mission characteristics and configuration layouts, the main structure of large remote sensing satellites both domestically and internationally is primarily a multi-module structure of "cylindrical shell + box-plate" or "cylindrical shell + truss." The service module is a load-bearing cylinder + box-plate structure, while the payload bay is a box-plate or truss structure. In particular, when the payload bay floor plate serves as the structural foundation of the payload bay and the supporting structure for large payloads, to ensure a reliable connection between the payload bay and the service module and to meet the requirements of high rigidity, high strength, and light weight, many satellite payload bay floor plates, both domestically and internationally, often adopt a frame-plate structure (also known as a "planar frame structure"), such as the payload bay floor plates of the French SPOT satellite and the Chinese "Ziyuan-2" satellite.

[0004] As a connecting structure between two compartments, the frame-panel structure has high rigidity, strength, ease of operation, and adaptability to various mechanical interfaces, but it is limited by the characteristics of the frame-panel structure:

[0005] 1) The limited bending stiffness of the frame plate structure makes it difficult to meet the installation requirements of ultra-large loads. In order to adapt to large loads, two nearly orthogonal beams need to be added at the location of the large load to transfer the three-dimensional load. The beam configuration and layout design is relatively complex, and the complex force when the load installation surface is expanded results in poor expansion of the effective load installation surface.

[0006] 2) The frame-plate structure is relatively tall, generally over 1m, which makes the center of mass of the entire star relatively high, which is not conducive to bearing large loads.

[0007] 3) Frame-panel structure: Because the structural panels also serve to house instruments and equipment, which typically require heat dissipation, it's difficult to use only carbon fiber materials with low thermal expansion coefficients for the structural panels. Furthermore, the large area of ​​the cold space hinders precise temperature control, resulting in significant thermal deformation and poor dimensional stability of the structural panels. For frame-panel structures, the temperature variation of the aluminum honeycomb panels should be no less than ±20℃, and the height no less than 1m. Therefore, the thermal deformation of the outer panels of the frame-panel structure should be no less than 2.4 × 10⁻⁶. -5 ×20×1=48×10 -5 m = 480 μm. Summary of the Invention

[0008] In view of this, the present invention provides a plate-shell beam composite high-load-bearing satellite module connection structure. This structure overcomes the shortcomings of the existing "frame plate module connection structure" technology and provides a module connection structure with high load-bearing capacity, high rigidity, easily expandable load mounting surface, low height, and high dimensional stability, meeting the requirements of large remote sensing satellite module connection and large payload support structure.

[0009] The technical solution adopted by this invention to solve its technical problem is as follows:

[0010] A plate-shell-beam composite large-load satellite module connection structure includes a cylindrical shell, a load-bearing frame, a variable cross-section end frame, a frame-to-cylinder shell connecting piece, a frame-to-cylinder shell connecting corner box, and a cylindrical shell root connector. The cylindrical shell is fixed to the variable cross-section end frame, and the load-bearing frame passes through the cylindrical shell and is fixed to the variable cross-section end frame. The cylindrical shell and the load-bearing frame are connected via the frame-to-cylinder shell connecting piece and the frame-to-cylinder shell connecting corner box. The cylindrical shell and the variable cross-section end frame are connected via the cylindrical shell root connector, and a cylindrical shell root heat insulation pad is provided at the cylindrical shell root. The cylindrical shell has a connection interface for the propulsion service module, the load-bearing frame provides an installation interface for large payload equipment and payload modules, and the variable cross-section end frame provides an installation interface for small equipment and supports.

[0011] Furthermore, the shell of the present invention includes a lower flange, a column section, and an upper flange, with a deep groove and a wide groove formed at the intersection of the column section, the upper flange, and the load-bearing frame.

[0012] Furthermore, the load-bearing frame of the present invention includes two main beams, two secondary beams, and two auxiliary beams; the two main beams are arranged in parallel, and the spacing between them can be adjusted according to different load interfaces; the two secondary beams and two auxiliary beams are arranged in parallel and perpendicular to the two main beams, and the spacing between them can be adjusted according to different load interfaces; the main beams adopt an "I" shaped cross section; the main beams and secondary beams adopt an isosceles trapezoidal design, and the sides of the main beams, secondary beams, and auxiliary beams are relatively low.

[0013] Furthermore, the four sets of installation points of the large load equipment described in this invention are located at the intersection of the main beam and the secondary beam, and the other four sets of installation points 2001 are located at the end of the main beam; the interface part of the load compartment is located on the secondary beam and the auxiliary beam.

[0014] Furthermore, the variable cross-section end frame of the present invention comprises an end face and a reinforcing flange, and the end face has mounting interfaces for large load equipment and screw connection clearance holes for the interfaces of load compartments.

[0015] The advantages of this invention compared to the prior art are as follows:

[0016] First, the plate-shell-beam composite large-load satellite module connection structure of this invention fully utilizes the load-bearing advantages of each structural component. The longitudinal load of large load equipment and load module structure is transferred to the shell through the load-bearing frame and diffused into a uniform load. The lateral load of large load equipment and load module structure is transferred downward in two forms: one is shear force, which is mainly transferred to the shell through the variable cross-section end frame; the other is that it is converted into local tensile and compressive forces through bending moment, which are then transferred to the shell through the load-bearing frame. By utilizing the load-bearing advantages of each structure of plate, shell, and beam, the complex concentrated large load and the load of square module are resolved into a uniform load of the shell end frame.

[0017] Secondly, this invention boasts high overall stiffness, strong load-bearing capacity, and easily expandable load mounting surfaces. Employing a combination of plate-shell-beam components, it leverages the load-bearing advantages of each structural member, resulting in a structure with high triaxial stiffness and strength. The normal stiffness depends on the design parameters of the load-bearing frame and the cylindrical shell structure, while the lateral stiffness depends on the design parameters of the variable cross-section end frame, the load-bearing frame, and the cylindrical shell structure. The normal stiffness of the structure can be significantly increased by raising the height of the load-bearing frame and the cylindrical shell structure. This efficiently achieves a square-to-round transition structural form.

[0018] Third, this invention utilizes the load-bearing advantages of the plate, shell, and beam structures to dissipate complex, concentrated, large loads and square compartment loads into uniform loads on the shell end frames. The design of the plate-shell-beam composite compartment connection structure allows for adjustments to the spacing between the two main beams, two secondary beams, and two auxiliary beams of the load-bearing frame, based on the large loads and the layout and interface forms of the compartment structures. Besides the load-bearing frame, which can accommodate large load equipment and compartment structures, the shell structure can also serve as an installation interface for large load equipment, compartment structures, storage tanks, and other structures. The entire structure is highly expandable and can readily adapt to various load interfaces and mission requirements.

[0019] Fourth, the present invention has a low height. Under the same effective load conditions, the traditional frame plate structure is generally more than 1m high, while the satellite module connection structure of the present invention has a height of no more than 450mm.

[0020] Fifth, compared to frame-panel structures, this invention lacks the function of installing high-heat-dissipation electronic equipment, allowing the use of composite materials with low thermal expansion coefficients, and its structural form is also adaptable to composite material molding. Furthermore, the side height of this invention is lower, resulting in a smaller area of ​​the side space exposed to cold air, facilitating precise overall temperature control. Therefore, this invention exhibits higher dimensional stability. The temperature control accuracy of this invention is ±5℃, the maximum lateral dimension is 4m, and the maximum thermal deformation is 1×10⁻⁶. -6 ×5×4=2×10 -5 m = 20μm, which is only 1 / 24 of the thermal deformation of traditional frame plate structures. Attached Figure Description

[0021] Figure 1 A bottom view showing the plate-shell-beam composite compartment connection structure;

[0022] Figure 2 A top view showing the plate-shell-beam composite compartment connection structure;

[0023] Figure 3 This is a schematic diagram of the cylindrical shell structure;

[0024] Figure 4 This is a schematic diagram of a load-bearing frame structure;

[0025] Figure 5 This is a schematic diagram of a variable cross-section end frame. Detailed Implementation

[0026] The following detailed explanation is provided in conjunction with the accompanying drawings and specific examples.

[0027] like Figure 1-2 As shown, a plate-shell beam composite large-load satellite module connection structure includes a cylindrical shell 1, a load-bearing frame 2, a variable cross-section end frame 3, a frame-to-cylinder shell connecting piece 4, a frame-to-cylinder shell connecting corner box 5, and a cylindrical shell root connector. The cylindrical shell 1 is fixed to the variable cross-section end frame 3, and the load-bearing frame 2 passes through the cylindrical shell 1 and is fixed to the variable cross-section end frame 3. The cylindrical shell 1 and the load-bearing frame 2 are connected via the frame-to-cylinder shell connecting piece 4 and the frame-to-cylinder shell connecting corner box 5. The cylindrical shell 1 and the variable cross-section end frame 3 are connected via the cylindrical shell root connector, and a cylindrical shell root heat insulation pad is provided at the root of the cylindrical shell 1. The cylindrical shell 1 has a connection interface 1011 for the propulsion service module, the load-bearing frame provides an installation interface 2001 for large payload equipment and an interface 2002 for the payload module, and the variable cross-section end frame 3 provides an installation interface for small equipment and supports.

[0028] In practical implementation, the assembly of the plate-shell beam composite large-load satellite module connection structure uses the lower end face of the cylindrical shell 1 as the assembly reference. The cylindrical shell 1 and the load-bearing frame 2 are glued together through the frame-to-cylinder connecting piece 4 and the frame-to-cylinder connecting corner box 5, and then screwed together with connecting fasteners. The cylindrical shell 1, the load-bearing frame 2, and the variable cross-section end frame 3 are glued together, and a cylindrical shell root connector is set between the cylindrical shell 1 and the variable cross-section end frame 3 for connection. The longitudinal load of the large load equipment and load module structure is transferred to the cylindrical shell 1 through the load-bearing frame 2 and diffused into a uniform load. The lateral load of the large load equipment and load module structure is transferred downward in two forms: one is shear force, which is mainly transferred to the cylindrical shell 1 through the variable cross-section end frame 3; the other is that the bending moment is converted into local tensile and compressive forces, which are then transferred to the cylindrical shell 1 through the load-bearing frame 2. By adopting the combination of plate-shell beam components, the load-bearing advantages of each structural component are utilized, and the structure has high triaxial stiffness and strength.

[0029] like Figure 3 As shown, the shell 1 includes a lower flange 101, a column section 102, and an upper flange 103. The upper flange 101 provides a connection interface 1011 with the propulsion service module. The assembly of the module connection structure requires the load-bearing frame 2 to pass through the shell 1. To meet the assembly connection requirements, deep grooves 1021 and wide grooves 1031 are formed at the intersections of the column section 102, the upper flange 103, and the load-bearing frame. The main function of the shell is to assemble the main components of the module connection structure into a whole, connect it to the propulsion service module, and withstand longitudinal, lateral, and torsional loads.

[0030] like Figure 4 As shown, the load-bearing frame includes two main beams 201, two secondary beams 202, and two auxiliary beams 203. The two main beams 201 are arranged in parallel, and the spacing between them can be adjusted according to different load interfaces. The two secondary beams 202 and two auxiliary beams 203 are arranged in parallel and perpendicular to the two main beams 201, and the spacing between them can be adjusted according to different load interfaces. The concentrated stress points of the load-bearing frame are the installation interface 2001 of large load equipment and the interface 2002 of the load compartment. According to the needs of interfaces 2001 and 2002, the overall configuration adopts a "well" shape. The main beam adopts an "I"-shaped cross-section; the main beam and secondary beams adopt an isosceles trapezoidal design, with low sides and auxiliary beam height; four sets of mounting points 2001 for large load-bearing equipment are located at the intersection of the main beam 201 and secondary beam 202, providing good local connection rigidity; the other four sets of mounting points 2001 are located at the ends of the main beam; the interface 2002 of the load compartment is partially located on the secondary beam 202 and auxiliary beam 203. To meet assembly and connection requirements, slots 2003 are opened at the intersections of the load-bearing frame main beam 202, secondary beam 202 and the shell.

[0031] like Figure 5As shown, the variable cross-section end frame 3 comprises an end face 301 and a reinforcing flange 302. The end face 301 has mounting interfaces 2001 for large load-bearing equipment and screw connection clearance holes 3001 for the interface 2002 of the load compartment. Because the compartment connection structure is very large and its radial stiffness is relatively weak, the variable cross-section end frame can effectively improve the radial and torsional stiffness of the compartment connection structure and transmit the effective load and the lateral load of the load compartment.

[0032] This invention designs a plate-shell-beam composite high-load-bearing satellite module connection structure, which has the following characteristics:

[0033] First, the structural design adopts a plate-shell beam form combining a cylindrical shell, variable cross-section end frames, and load-bearing frames. Longitudinal loads are transferred to the cylindrical shell through the load-bearing frames and diffused into uniform loads; lateral loads are transferred downwards in two forms: one is shear force, which is mainly transferred to the cylindrical shell through the variable cross-section end frames; the other is transformed into local tensile and compressive forces through bending moments, which are then transferred to the cylindrical shell through the load-bearing frames.

[0034] Secondly, a square-to-round transition structure is provided, which utilizes the load-bearing advantages of the plate, shell, and beam structures to dissipate complex, concentrated, large loads and square compartment loads into uniform loads on the cylindrical shell end frames. This leverages the strong and uniform load-bearing capacity of the bending beams in the load-bearing frame, the shear plates in the variable cross-section end frames, and the overall cylindrical shell structure.

[0035] Third, the load-bearing frame features two parallel main beams 201, the spacing of which can be adjusted according to different load interfaces. Two secondary beams 202 and two auxiliary beams 203 are also parallel and perpendicular to the two main beams 201, with their spacing also adjustable according to different load interfaces. Besides the load-bearing frame, which can accommodate large load-bearing equipment and compartment structures, the shell structure can also serve as an installation interface for large load-bearing equipment, compartment structures, storage tanks, and other structures. The structure has strong scalability and can adapt to various load interfaces and mission requirements.

[0036] Fourth, the assembly requirements for the load-bearing frame to pass through the shell are met during the assembly of the compartment connection structure by opening deep grooves in the column sections and wide grooves in the upturned edges; the connection between the shell and the frame is efficiently achieved through frame-shell connecting plates and frame-shell connecting corner boxes. The shell, plate, and frame structural components are relatively simple in form and can be achieved through structural assembly, making them highly manufacturable.

[0037] Fifth, when the dimensions of the compartment connection structure are very large and the radial stiffness is weak, the radial stiffness and torsional stiffness of the compartment connection structure can be effectively improved by adding variable cross-section end frames, and the effective load and the lateral load of the load compartment can be transferred.

[0038] Sixth, a composite material plate-shell beam-cabin segment connection structure with a "grid-shaped" main load-bearing frame structure is adopted, with structural dimensions of 3280mm×2800mm×450mm. Under the direct load of a 2500kg large camera, the requirements are met through spacecraft whole-vehicle mechanical analysis, thermal stability analysis, and dimensional stability analysis.

[0039] The above description is merely a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in the present invention should be included within the scope of protection of the present invention. Therefore, the scope of protection of the present invention should be determined by the scope of the claims.

Claims

1. A plate-shell beam composite high-load-bearing satellite module connection structure, characterized in that, The system includes a cylindrical shell, a load-bearing frame, a variable cross-section end frame, a frame-to-cylinder shell connecting piece, a frame-to-cylinder shell connecting corner box, and a cylinder shell root connector. The cylindrical shell is fixed to the variable cross-section end frame, and the load-bearing frame passes through the cylindrical shell and is fixed to the variable cross-section end frame. The cylindrical shell and the load-bearing frame are connected via the frame-to-cylinder shell connecting piece and the frame-to-cylinder shell connecting corner box. The cylindrical shell and the variable cross-section end frame are connected via the cylinder shell root connector, and a cylinder shell root heat insulation pad is provided at the cylinder shell root. The cylindrical shell has a connection interface for connecting to the propulsion service module. The load-bearing frame provides installation interfaces for large load-bearing equipment and load compartments, while the variable cross-section end frame provides installation interfaces for small equipment and supports. The load-bearing frame includes two main beams, two secondary beams, and two auxiliary beams. The two main beams are arranged in parallel, and the spacing between them can be adjusted according to different load interfaces. The two secondary beams and two auxiliary beams are arranged in parallel and perpendicular to the two main beams, and the spacing between them can be adjusted according to different load interfaces. The main beams adopt an "I"-shaped cross-section. The main beams and secondary beams adopt an isosceles trapezoidal design, and the sides of the main beams, secondary beams, and auxiliary beams are relatively low.

2. The plate-shell beam composite high-load-bearing satellite module connection structure according to claim 1, characterized in that, The shell includes a lower flange, a column section, and an upper flange. Deep and wide grooves are formed at the intersections of the column section, the upper flange, and the load-bearing frame.

3. The plate-shell beam composite high-load-bearing satellite module connection structure according to claim 2, characterized in that, The four sets of installation points for the large load-bearing equipment are located at the intersection of the main beam and the secondary beam, and the other four sets of installation points 2001 are located at the ends of the main beam; the interface of the load compartment is located on the secondary beam and the auxiliary beam.

4. The plate-shell beam composite high-load-bearing satellite module connection structure according to any one of claims 1-3, characterized in that, The variable cross-section end frame consists of an end face and a reinforcing flange. The end face has mounting interfaces for large load equipment and screw connection clearance holes for the interfaces of the load compartment.

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