A lightweight satellite-rocket connection substrate

Abstract

The present invention discloses a lightweight satellite-rocket connection base plate, comprising two left and right longitudinal beams and a plurality of cross beams and diagonal bracing beams located between the two longitudinal beams. A satellite docking structure and a rocket docking structure are provided on the upper and lower sides of the middle portion of the base plate, respectively. The longitudinal beams, cross beams, and diagonal bracing beams are made of fiber materials. The longitudinal beam is integrally formed in a U-shaped configuration by an inner plate, an outer plate, and an upper flat plate and a lower flat plate located between the inner plate and the outer plate. The inner plate and the outer plate have L-shaped curling edges extending horizontally outward at the bottom to increase the strength and rigidity of the longitudinal beam. The ends of the outer plate are bent outward in a bow shape, forming two front and rear functional areas on the longitudinal beam, and a weight-reducing gap between the two functional areas on the outer side of the longitudinal beam. The advantages of the invention are that the main components are made of carbon fiber material, which reduces the total weight of the base plate; the U-shaped structure of the longitudinal beam and the curling design of the inner and outer plates can significantly enhance the structural strength and rigidity of the base plate, moderately reduce the amount of material used, and thus further achieve a weight-reduction effect.

Description

Technical Field

[0001] The present invention relates to a lightweight satellite-rocket connection substrate, belonging to the field of aerospace technology. Background Art

[0002] As an independent module connecting the satellite to the launch vehicle, the satellite-rocket connection substrate is a crucial component of satellite launch. It ensures the reliability of the connection between the satellite and the launch vehicle during ground and launch vehicle flight, and enables separation of the satellite from the launch vehicle when the satellite reaches its intended orbit. Existing satellite-rocket connection substrates with an aluminum alloy hollow structure have numerous components and joints, which seriously affects the reliability of the joints. Furthermore, to reduce weight, the aluminum alloy substrate is hollowed out, which increases the processing cost.

[0003] From the perspective of space launch costs (the cost per kilogram of payload is 5,000 to 10,000 US dollars), the industry hopes that the design of spacecraft components should reduce weight as much as possible. However, under the premise of current technical solutions, in order to ensure high strength and high stiffness (modal), the current aluminum alloy satellite-rocket connection substrate can no longer be optimized in terms of weight, and it is necessary to explore new materials and structural forms. Summary of the Invention

[0004] The technical problem to be solved by the present invention is: how to further reduce the weight of the satellite-rocket connection substrate while ensuring high strength and high rigidity.

[0005] In view of the above problems, the technical solution proposed by the present invention is:

[0006] A lightweight satellite-rocket connection base plate includes two left and right longitudinal beams and multiple cross beams and multiple diagonal bracing beams located between the two longitudinal beams. A satellite docking structure and a rocket docking structure are respectively provided on the upper and lower sides of the middle part of the base plate. The longitudinal beams, cross beams and diagonal bracing beams are made of fiber materials.

[0007] The longitudinal beam is integrally formed in a square shape by an inner plate, an outer plate, an upper flat plate and a lower flat plate located between the inner plate and the outer plate.

[0008] The inner and outer plates have L-shaped curling edges at the bottom that extend outward horizontally and are used to increase the strength and rigidity of the longitudinal beam.

[0009] The two ends of the outer plate are bent and protruded outward in a bow shape, so that the longitudinal beam forms two front and rear functional areas, and a weight-reducing gap is formed between the two functional areas on the outer side of the longitudinal beam.

[0010] The functional area includes a main docking area close to the middle of the longitudinal beam, an auxiliary docking area located at the end of the longitudinal beam, and a power supply cabin located in the main docking area and the auxiliary docking area.

[0011] The main docking area is provided with a satellite main interface for satellite fixation, and the satellite main interface is a tube hole of a metal sleeve. The outer periphery of the lower end of the metal sleeve is provided with an upward annular pressing platform. The upper plate and the lower plate are provided with fitting holes. The metal sleeve is inserted from the bottom to the top into the fitting holes on the upper plate and the lower plate, so that the pressing platform is pressed upward on the lower plate around the fitting hole. The outer periphery of the metal sleeve between the upper plate and the lower plate is provided with a reinforcing sleeve with upper and lower flanges, and the upper end face and the lower end face of the reinforcing sleeve are respectively against the upper plate and the lower plate; the two ends in the tube hole of the metal sleeve are provided with an upper internal thread and a lower internal thread respectively.

[0012] The main docking area is provided with a separation interface for separating the satellite from the substrate. The separation interface is a tube hole of a metal sleeve. The outer periphery of the upper end of the metal sleeve is provided with a downward annular pressing platform. The upper plate and the lower plate are provided with fitting holes. The metal sleeve is inserted from top to bottom into the fitting hole so that the pressing platform is pressed on the upper plate around the fitting hole. The outer periphery of the metal sleeve between the upper plate and the lower plate is provided with a fitting reinforcing sleeve. The upper end face and the lower end face of the reinforcing sleeve are respectively against the upper plate and the lower plate.

[0013] The main docking area is provided with a rocket main interface for fixing the rocket. The rocket main interface is a pipe hole of the metal sleeve three. The outer periphery of the metal sleeve three has a downward annular upper pressure platform three and a lower pressure platform four. The outer periphery of the lower end of the metal sleeve three has an external thread and is equipped with an anti-slip nut. The upper plate and the lower plate have a fitting hole. The metal sleeve three is inserted from top to bottom into the fitting holes of the upper plate and the lower plate, so that the pressure platform one and the pressure platform two are respectively pressed downward on the upper plate and the lower plate around the fitting hole. The anti-slip nut cooperates with the external thread of the lower end of the metal sleeve at the bottom of the lower plate to fasten the metal sleeve one.

[0014] The main docking area is provided with a main docking area module that can be temporarily installed, and the functional area is provided with a module installation position where the main docking area module can be installed.

[0015] The two ends of the crossbeam are directly connected to the longitudinal beams on the left and right sides, and the two ends of the diagonal bracing beam are connected to the two adjacent crossbeams in an N shape; the crossbeam and the diagonal bracing beam are square tubes, which have a tube hole with a rectangular cross-section; the tube holes at both ends of the crossbeam are filled with rectangular blocks, and the rectangular blocks are fixedly connected to the crossbeam and the longitudinal beam respectively by screws and / or glue; the tube holes at both ends of the diagonal bracing beam are filled with wedge blocks, and the wedge blocks have four positive surfaces that are in contact with the four walls of the tube hole of the diagonal bracing beam and one diagonal surface that is in contact with the crossbeam, and screws are drilled through the tube wall of the diagonal bracing beam into the positive surface 2 to fasten it to the wedge block, and screws are drilled through the crossbeam into the diagonal surface to fasten it to the wedge block. Beneficial effects

[0016] 1. The main components are made of carbon fiber, which reduces the total weight of the substrate by 20-30%;

[0017] 2. The U-shaped structure of the longitudinal beam and the curling design of the inner and outer panels can significantly enhance the structural strength and rigidity of the base plate, moderately reduce the total amount of carbon fiber material, and thus further achieve the effect of weight reduction;

[0018] 3. All stress-bearing joints use metal sleeves such as metal sleeve 1, metal sleeve 2 and metal sleeve 3, which can fully meet the requirements of joint strength and wear resistance;

[0019] 4. The main interface area is modularized, so that the baseboard can adapt to the docking of various types of satellites. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 This is a three-dimensional schematic diagram of the connection substrate described in Example 1;

[0021] Figure 2 This is a three-dimensional schematic diagram of the longitudinal beam functional area described in Example 1;

[0022] Figure 3 is a schematic cross-sectional view of the longitudinal beam described in Example 1;

[0023] Figure 4 Schematic cross-section of the satellite main interface according to Example 1;

[0024] Figure 5 Schematic cross-sectional view of the satellite separation interface described in Example 1;

[0025] Figure 6 Schematic cross-sectional view of the rocket main interface described in Example 1;

[0026] Figure 7 This is a schematic diagram of the assembly structure of the longitudinal beam, transverse beam, and diagonal bracing beam described in Example 1;

[0027] Figure 8 This is a top view of the functional area of ​​​​the second embodiment, showing the module installation position set in the main docking area;

[0028] Figure 9 This is a three-dimensional schematic diagram of the main docking area module described in Example 2.

[0029] Figure: 1. Longitudinal beam; 101. Inner plate; 102. Outer plate; 103. Upper plate; 104. Lower plate; 105. Hemming; 11. Functional area; 111. Main docking area; 112. Auxiliary docking area; 113. Power supply compartment; 114. Weight reduction notch; 2. Crossbeam; 3. Diagonal bracing beam; 4. Satellite main interface; 41. Metal casing 1; 411. Upper internal thread; 412. Lower internal thread; 413 , press platform one; 42, reinforced sleeve one; 5, separation interface; 51, metal sleeve two; 511, press platform two; 52, reinforced sleeve two; 6, rocket main interface; 61, metal sleeve three; 611, press platform three; 612, press platform four; 62, anti-slip nut; 7, main docking area module; 71, module installation position; 8, rectangular block; 9, wedge block; 91, front veneer; 92, oblique veneer; 10, screw. DETAILED DESCRIPTION

[0030] The present invention will be further described below with reference to the embodiments and accompanying drawings: Example 1

[0031] like Figure 1 As shown, a lightweight satellite-rocket connection baseplate comprises two left and right longitudinal beams 1, multiple crossbeams 2, and multiple diagonal bracing beams 3 positioned between the two longitudinal beams 1. Satellite docking structures and rocket docking structures are located on the upper and lower sides of the central portion of the baseplate, respectively. The baseplate's improvements include: the longitudinal beams 1, crossbeams 2, and diagonal bracing beams 3 are made of fiber material, reducing the baseplate's weight. Fiber material offers high structural strength and controllable stiffness through process adjustments. Its specific gravity is lower than that of metal, enabling the baseplate to be lightweight while maintaining structural strength and stiffness.

[0032] The fiber material referred to here is preferably carbon fiber.

[0033] like Figure 1 As shown in Figure 3, the longitudinal beam 1 is formed integrally in a U-shaped configuration, comprising an inner panel 101, an outer panel 102, and an upper flat panel 103 and a lower flat panel 104 positioned between the inner and outer panels 101 and 102. Compared to the H-shaped design of conventional technologies, this significantly enhances structural strength, ensuring the required base strength while reducing structural components and material thickness for lightweighting. Furthermore, the U-shaped structure facilitates carbon fiber molding and fabrication.

[0034] The inner and outer panels 101 and 102 have L-shaped, horizontally extending, curled edges 105 at their bottoms to increase the strength and rigidity of the longitudinal beam 1. This horizontal curling design not only enhances the horizontal strength and rigidity of the longitudinal beam 1, but also strengthens the strength and rigidity of the entire base panel in all directions, thereby reducing the material used in other areas and achieving lightweighting.

[0035] Experiments show that the U-shaped structure can increase the original H-shaped first-order mode (stiffness) by 40%, and the L-shaped curling structure can increase the original H-shaped first-order mode by 15%. The combination of the two can increase the original first-order mode by 55%.

[0036] like Figure 1 As shown, both ends of the outer plate 102 are bent outward in a bow shape, so that the longitudinal beam 1 forms two front and rear functional areas 11, and a weight-reducing gap 114 is formed between the two functional areas 11 on the outer side of the longitudinal beam 1, which can reduce the weight by about 5%.

[0037] like Figure 2 As shown, the functional area 11 includes a main docking area 111 near the middle of the longitudinal beam 1, an auxiliary docking area 112 located at the end of the longitudinal beam 1, and a power supply compartment 113 located between the main docking area 111 and the auxiliary docking area 112. The auxiliary docking area 112 is used to secure the satellite's wings, and the power supply compartment 113 is used to house batteries, which are used to provide power for satellite-rocket separation.

[0038] like Figure 4 As shown, the main docking area 111 is provided with a satellite main interface 4 for satellite fixation. The satellite main interface 4 is a tube hole of a metal sleeve 41. The outer periphery of the lower end of the metal sleeve 41 is provided with an upward annular pressing platform 413. The upper plate 103 and the lower plate 104 are provided with fitting holes. The metal sleeve 41 is inserted from the bottom to the top into the fitting holes on the upper plate 103 and the lower plate 104, so that the pressing platform 413 presses upward on the lower plate 104 around the fitting holes. The satellite is installed on the upper plate 103 of the substrate, thus ensuring that it is not pulled out upward; the outer periphery of the metal sleeve 41 between the upper plate 103 and the lower plate 104 is provided with a reinforcing sleeve 42 with upper and lower flanges, the upper end face and the lower end face of the reinforcing sleeve 42 respectively press against the upper plate 103 and the lower plate 104, so that the metal sleeve 41 and the longitudinal beam 1 are more integrated; the two ends in the tube hole of the metal sleeve 41 are provided with an upper internal thread 411 and a lower internal thread 412 respectively.

[0039] like Figure 5 As shown, the main docking area 111 is provided with a separation interface 5 for separating the satellite from the substrate. The separation interface 5 is a tube hole of the metal sleeve 51, and a pre-compression spring for separation is placed in the tube hole. The outer periphery of the upper end of the metal sleeve 51 is provided with a downward annular pressure platform 511. The upper plate 103 and the lower plate 104 are provided with fitting holes. The metal sleeve 51 is inserted into the fitting holes from top to bottom, so that the pressure platform 511 is pressed on the upper plate 103 around the fitting holes; the outer periphery of the metal sleeve 51 between the upper plate 103 and the lower plate 104 is provided with a fitting reinforcing sleeve 52, and the upper end face and the lower end face of the reinforcing sleeve 52 respectively press against the upper plate 103 and the lower plate 104, which also makes the metal sleeve 51 and the longitudinal beam 1 more integrated.

[0040] like Figure 6 As shown, the main docking area 111 is provided with a rocket main interface 6 for fixing the rocket. The rocket main interface 6 is a tube hole of the metal sleeve three 61. The outer periphery of the metal sleeve three 61 has a downward annular upper pressure platform three 611 and a lower pressure platform four 612. The outer periphery of the lower end of the metal sleeve three 61 has an external thread and is equipped with an anti-slip nut 62. The upper plate 103 and the lower plate 104 have a fitting hole. The metal sleeve three 61 is inserted from top to bottom into the fitting holes of the upper plate 103 and the lower plate 104, so that the pressure platform one 413 and the pressure platform two 511 are pressed downward on the upper plate 103 and the lower plate 104 around the fitting hole respectively, and the anti-slip nut 62 cooperates with the external thread of the lower end of the metal sleeve one 41 at the bottom of the lower plate 104 to fasten the metal sleeve one 41.

[0041] like Figure 7 As shown, the ends of the crossbeam 2 are directly connected to the left and right longitudinal beams 1, while the ends of the diagonal bracing beam 3 are connected to two adjacent crossbeams 2 in an N-shaped pattern. The crossbeam 2 and diagonal bracing beam 3 are square tubes with rectangular cross-sections. The crossbeam 2 and diagonal bracing beam 3 are filled with rectangular blocks 8, which are fixed to the crossbeam 2 and longitudinal beam 1 respectively via screws 10 and / or glue. The diagonal bracing beam 3 is filled with wedge-shaped blocks 9. The wedge blocks 9 have four positive surfaces 91 that abut the four walls of the diagonal bracing beam 3 holes and one diagonal surface 92 that abuts the crossbeam 2. Screws 10 are drilled through the walls of the diagonal bracing beam 3 into the positive surfaces 2 to secure them to the wedge blocks 9, and screws 10 are drilled through the crossbeam 2 into the diagonal surfaces 92 to secure them to the wedge blocks 9. This ensures that the crossbeam 2 and diagonal bracing beam 3 are hollow, weight-reducing square tubes while also ensuring a reliable, solid connection at both ends.

[0042] This embodiment achieves an overall weight reduction of 20-30% through structural optimization and the selection of carbon fiber materials. Example 2

[0043] like Figure 8 、 9 As shown, the difference from the first embodiment is that the main docking area 111 is configured as a main docking area module 7 that can be temporarily installed. The functional area 11 is provided with a module installation position 71 for installing the main docking area module 7. When in use, the appropriate main docking area module 7 is installed in the module installation position 71. In this way, when docking different rockets and satellites, only different main docking area modules 7 need to be used, that is, different docking holes need to be set on the main docking area module 7, without having to adjust the entire base plate as in the prior art.

[0044] The directions “up”, “down”, “left” and “right” mentioned in this article are relative to the view direction, not the directions in actual application.

[0045] The above embodiments are only used to more clearly describe the present invention and cannot be regarded as limiting the scope of protection covered by the present invention. Any modifications in equivalent forms should be regarded as falling within the scope of protection covered by the present invention.

Claims

1. A lightweight satellite-rocket connection base plate, comprising two left and right longitudinal beams (1), a plurality of transverse beams (2) and a plurality of diagonal bracing beams (3) located between the two longitudinal beams (1), wherein a satellite docking structure and a rocket docking structure are provided on the upper side and the lower side of the middle portion of the base plate, respectively, and characterized in that: The longitudinal beam (1), the transverse beam (2) and the diagonal bracing beam (3) are made of carbon fiber material; the longitudinal beam (1) is formed in a U-shaped integral body by an inner plate (101), an outer plate (102) and an upper plate (103) and a lower plate (104) located between the inner plate (101) and the outer plate (102); the two ends of the outer plate (102) are bent outward in a bow shape, so that the longitudinal beam (1) forms two front and rear functional areas (11), and a weight-reducing gap (114) is formed between the two functional areas (11) on the outer side of the longitudinal beam (1); the functional area (11) includes a main docking area near the middle of the longitudinal beam (1) (111), an auxiliary docking area (112) located at the end of the longitudinal beam (1), and a power supply cabin (113) located in the main docking area (111) and the auxiliary docking area (112); the main docking area (111) is provided with a satellite main interface (4) for satellite fixation, the satellite main interface (4) is a pipe hole of a metal sleeve (41), the lower end periphery of the metal sleeve (41) has an upward annular pressing platform (413), the upper plate (103) and the lower plate (104) have a set hole, the metal sleeve (41) is inserted from the bottom to the top into the upper plate (103) and the lower plate (104) on the outer periphery. The sleeve hole is fitted so that the pressing platform 1 (413) is pressed upward on the lower plate (104) on the periphery of the sleeve hole; a reinforcing sleeve 1 (42) with upper and lower flanges is fitted on the periphery of the metal sleeve 1 (41) between the upper plate (103) and the lower plate (104), and the upper end surface and the lower end surface of the reinforcing sleeve 1 (42) respectively abut against the upper plate (103) and the lower plate (104); the two ends of the tube hole of the metal sleeve 1 (41) respectively have an upper internal thread (411) and a lower internal thread (412); the main docking area (111) is provided with a separation interface (5) for separating the satellite from the substrate, and the separation interface (5) is The metal sleeve (51) has a tube hole, the outer periphery of the upper end of the metal sleeve (51) has a downward annular pressing platform (511), the upper plate (103) and the lower plate (104) have a sleeve hole, the metal sleeve (51) is inserted from top to bottom into the sleeve hole, so that the pressing platform (511) is pressed on the upper plate (103) around the sleeve hole; the outer periphery of the metal sleeve (51) between the upper plate (103) and the lower plate (104) has a sleeved reinforcing sleeve (52), the upper end surface and the lower end surface of the reinforcing sleeve (52) respectively abut against the upper plate (103) and the lower plate (104);The main docking area (111) is provided with a rocket main interface (6) for fixing the rocket. The rocket main interface (6) is a tube hole of the metal sleeve three (61). The outer periphery of the metal sleeve three (61) has a downward annular upper pressing platform three (611) and a lower pressing platform four (612). The outer periphery of the lower end of the metal sleeve three (61) has an external thread and is equipped with an anti-slip nut (62). The upper plate (103) and the lower plate (104) have a set hole. The metal sleeve three (61) is inserted from top to bottom into the set hole of the upper plate (103) and the lower plate (104), so that the pressing platform three (611) is pressed downward on the upper plate (103) around the set hole, and the pressing platform four (612) is pressed downward on the lower plate (104) around the set hole. The anti-slip nut (62) cooperates with the external thread of the lower end of the metal sleeve three (61) at the bottom of the lower plate (104) to fasten the metal sleeve three (61). ; 2. The lightweight satellite-rocket connection substrate according to claim 1, characterized in that: The inner plate (101) and the outer plate (102) have L-shaped curling edges (105) extending outward horizontally at the bottom for increasing the strength and rigidity of the longitudinal beam (1).

3. The lightweight satellite-rocket connection substrate according to claim 1, characterized in that: The main docking area (111) is provided with a main docking area module (7) that can be temporarily installed, and the functional area (11) is provided with a module installation position (71) capable of installing the main docking area module (7).

4. The lightweight satellite-rocket connection substrate according to any one of claims 1 to 3, characterized in that: The two ends of the crossbeam (2) are directly connected to the longitudinal beams (1) on the left and right sides, and the two ends of the diagonal bracing beam (3) are connected to the two adjacent crossbeams (2) in an N-shape; the crossbeam (2) and the diagonal bracing beam (3) are square tubes, each having a tube hole with a rectangular cross section; the tube holes at both ends of the crossbeam (2) are filled with rectangular blocks (8), and the rectangular blocks (8) are fixedly connected to the crossbeam (2) and the longitudinal beam (1) respectively by screws (10) and / or glue; The tube holes at both ends of the diagonal bracing beam (3) are filled with wedge-shaped blocks (9). The wedge-shaped blocks (9) have four positive veneers (91) affixed to the four walls of the tube hole of the diagonal bracing beam (3) and one oblique veneer (92) affixed to the crossbeam (2). The screws (10) penetrate the tube wall of the diagonal bracing beam (3) and drill into the positive veneer (91) to fasten with the wedge-shaped blocks (9). The screws (10) penetrate the crossbeam (2) and drill into the oblique veneer (92) to fasten with the wedge-shaped blocks (9).

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