Double star self-tandem main bearing structure

Abstract

The application relates to a double-star self-serial main bearing structure, which comprises a lower star main bearing structure, an upper star main bearing structure and an interstellar connecting structure for connecting the lower star main bearing structure and the upper star main bearing structure, the lower star main bearing structure comprises a support frame and a plurality of rod members arranged on the support frame, the rod members are arranged at corners of the lower star cabin body in the height direction, the upper star main bearing structure comprises a plurality of trusses and a first flange connected with the plurality of trusses, the trusses are arranged at the corners of the upper star cabin body in the height direction, the plurality of trusses are arranged to be gathered to form a gathering position, and the first flange is arranged at the gathering position. In the application, the double-star self-serial main bearing structure has a simple and direct force transmission path, conforms to the force flow continuity principle and the shortest force transmission path principle, and can reduce the sine vibration response of a traditional plate type large storage box support structure by about 2.5g.

Description

Technical Field

[0001] This invention relates to the field of aerospace technology, and to a dual-satellite self-connected main load-bearing structure, and more particularly to a dual-satellite self-connected main load-bearing structure adapted to small satellites with large storage tanks. Background Technology

[0002] In satellite launch missions in the aerospace field, traditional tandem satellite launch methods typically rely on the launch vehicle to connect the two satellites within the fairing via a support structure inside the satellite adapter. A typical tandem launch rocket's internal support structure is as follows: Figure 1 The rocket fairing is shown. However, this method has significant drawbacks: because the launch vehicle needs to provide an additional internal support structure, the launch mass cannot be maximized, resulting in high launch costs. Meanwhile, the 100L large propellant tanks configured for small satellites often use plate-type support structures, such as... Figure 2 As shown, the drum-skin effect is significant, and the mechanical response of large tanks is large. To solve this problem, it is often necessary to add reinforcing structures to improve stiffness, but the actual effect is minimal, further exacerbating the waste of structural weight.

[0003] In summary, the support structure design in traditional tandem satellite launches not only results in low launch mass utilization and high costs, but also makes it difficult to effectively solve the mechanical response problem of large tank plate support structures through conventional strengthening methods. Summary of the Invention

[0004] To address at least some of the aforementioned problems in the prior art, the present invention provides a dual-satellite self-connected main load-bearing structure, specifically a dual-satellite self-connected main load-bearing structure adapted to small satellites with large storage tanks.

[0005] This invention provides a self-connected main load-bearing structure for two satellites, comprising a lower satellite and an upper satellite mounted on the lower satellite. The lower satellite includes a lower satellite cabin, and the upper satellite includes an upper satellite cabin. The lower satellite cabin and the upper satellite cabin are flush. The self-connected main load-bearing structure for two satellites includes:

[0006] The lower satellite main load-bearing structure is the load-bearing structure of the lower satellite cabin. The lower satellite main load-bearing structure includes a support frame and a plurality of rods provided on the support frame. The rods are provided at the corners of the lower satellite cabin along the height direction.

[0007] The main load-bearing structure for the satellite launch vehicle is the load-bearing structure of the launch vehicle cabin. The main load-bearing structure includes multiple trusses and a first flange connected to the multiple trusses. The trusses are located at the corners of the launch vehicle cabin along its height direction. The multiple trusses are arranged in a convergent configuration to form a convergence point, and the first flange is located at the convergence point.

[0008] An inter-satellite connection structure is used to connect the lower satellite main load-bearing structure and the upper satellite main load-bearing structure. The inter-satellite connection structure is located between the lower satellite main load-bearing structure and the upper satellite main load-bearing structure to form a dual-satellite self-connected main load-bearing structure.

[0009] Furthermore, the lower satellite includes a first top plate, a first bottom plate, and a plurality of first side plates disposed between the first top plate and the first bottom plate, the first top plate, the first bottom plate, and the plurality of first side plates together forming the lower satellite cabin; the upper satellite includes a second top plate, a second bottom plate, and a plurality of second side plates disposed between the second top plate and the second bottom plate, the second top plate, the second bottom plate, and the plurality of second side plates together forming the upper satellite cabin; the inter-satellite connection structure is disposed between the first top plate and the second top plate to connect the lower satellite cabin and the upper satellite cabin.

[0010] Furthermore, the lower satellite module and the upper satellite module are cubic modules.

[0011] Furthermore, the support frame is disposed at the bottom of the first base plate. The support frame includes a ring body, a cross body disposed within the ring body, and an extension leg disposed outside the ring body. The cross body includes a first leg and a second leg that intersect each other. The first leg and the second leg intersect with the ring body to form an end intersection point. The extension leg extends outward along the end intersection point to the apex of the first base plate.

[0012] Furthermore, the first leg and the second leg intersect at the center of the annulus to form a central intersection point.

[0013] Furthermore, the support frame is integrally formed.

[0014] Furthermore, the annular body is threadedly connected to the cross body and the extended leg, and the extended leg is threadedly connected to the star-rocket docking joint.

[0015] Furthermore, the support frame is a carbon fiber frame. The support frame is made of M55J carbon fiber.

[0016] Furthermore, the annular body, the cross body, and the extended legs are screwed together as a whole by 16 M6 screws.

[0017] Furthermore, the lower satellite also includes a first storage tank and a storage tank support for supporting the first storage tank. The storage tank support is disposed on the first base plate, that is, the storage tank support and the support frame are respectively disposed on the top and bottom of the first base plate. The storage tank support is a column support, and the diameter of the column of the storage tank support is the same as the diameter of the annulus, so as to strengthen the supporting effect on the first storage tank.

[0018] Furthermore, the lower satellite main load-bearing structure also includes:

[0019] A satellite-rocket docking joint, used to connect the lower satellite and the rocket, is located at the end of the extended outrigger; and

[0020] A rod joint, used to connect the inter-satellite connection structure and the lower satellite, wherein the rod joint and the satellite-rocket docking joint are respectively located at both ends of the rod; and / or

[0021] The inter-satellite connection structure is connected to the second top plate and the first top plate respectively, and the rod is engaged with the rod joint and the star-rocket docking joint; and / or

[0022] The rod joint includes a rod joint body one, a rod joint body two, and a rod joint body three connected in sequence. The first top plate is threadedly connected to the rod joint body two, the first bottom plate is threadedly connected to the star-arrow docking joint, and the first side plate is threadedly connected to the rod.

[0023] Furthermore, the material of the rod joint is forged aluminum 2A14T6. The number of star-rocket docking joints is four.

[0024] Furthermore, the star-rod docking joint is threadedly connected to the end of the extended leg; the rod joint and the star-rod docking joint are respectively located at the top and bottom ends of the rod. The rod joint is connected to the rod by four M6 screws; the star-rod docking joint is connected to the rod by an M8 screw.

[0025] Furthermore, the rod is a hollow cylindrical rod with an outer diameter of 30mm and an inner diameter of 24mm; the rod is made of aluminum alloy 2A14T6.

[0026] Furthermore, the rod is also threadedly connected to the rod joint and the star-arrow docking joint. The rod also includes a first connecting body at one end of the rod body and a second connecting body at the other end of the rod body. The first connecting body is threadedly connected to the star-arrow docking joint; the second connecting body is threadedly connected to the rod joint.

[0027] Furthermore, the first connector is connected to the star-rocket docking joint by four M10 screws to further strengthen the connection between the rod and the star-rocket docking joint; the second connector is connected to the rod by M6 screws to connect the rod to the rod joint.

[0028] Furthermore, a plurality of first corner plates are provided between the first top plate and the rod joint. The first corner plates are L-shaped and are located at the corners of the first top plate. The first top plate and the rod joint body are connected by threads through the first corner plates. During connection, one plate of the first corner plate is threadedly connected to the rod joint, and the other plate is threadedly connected to the first top plate.

[0029] Furthermore, the rod joint is connected to the first corner piece by an M4 screw, which facilitates the use of the first top plate to ensure the accuracy of the load-bearing structure during the final assembly process.

[0030] Furthermore, the rod joint is also provided with a weight-reducing groove. The weight-reducing groove reduces weight while ensuring strength.

[0031] Furthermore, the bottom of the satellite-rocket docking joint is provided with an explosive bolt mounting hole to connect the satellite-rocket docking joint to the rocket by bolts; the launch vehicle separation spring push rod contacts the bottom of the satellite-rocket docking joint so that the satellite and the rocket move away from each other after the satellite-rocket separation.

[0032] Further, the rod includes a rod body and bosses disposed on the rod body. The bosses are spaced apart along the axial direction of the rod body. Each boss includes a first boss. The first side plate is threadedly connected to the first boss. The first boss is a polygonal boss, and at least two sides of the first boss are perpendicular to each other or spatially perpendicular to each other, so that adjacent first side plates mounted on the same rod body are perpendicular to each other; and / or

[0033] The rod body is further provided with a first extension section and a second extension section at both ends, respectively. A first groove is formed at the top of the star-arrow connector, which conforms to the shape of the first extension section so that the first extension section can be inserted into the first groove. A second groove is formed at the bottom of the rod connector, which conforms to the shape of the second extension section so that the second extension section can be inserted into the second groove. The insertion of the first and second extension sections into the rod connector increases its shear resistance.

[0034] Furthermore, both the first and second grooves are designed with rounded corners to facilitate the insertion of the rods and reduce installation difficulty. The lengths of the first and second extension sections are 20mm.

[0035] Furthermore, the first side plate is threadedly connected to the rod body using M5 and M6 screws. Depending on the actual structural connection strength requirements, the interval between adjacent bosses is 70-100mm.

[0036] Furthermore, the boss is used to connect the rod and the first side plate (honeycomb plate), and the boss is provided with a first side plate mounting hole.

[0037] Furthermore, the first boss is a triangular boss, which includes a first boss, a second boss, and a third boss connected in sequence. The first boss and the third boss are spatially perpendicular to each other. The first boss and the third boss are provided with first side plate mounting holes. During installation, adjacent first side plates are respectively attached to the first boss and the third boss, and screws are used to pass through the first side plate mounting holes to form the lower satellite compartment enclosed by the first side plates.

[0038] Furthermore, the boss also includes a second boss, which is an arc-shaped boss, and the first boss and the second boss surround the outer wall of the rod body in a circumferential manner.

[0039] Furthermore, the aforementioned satellite launch is a full truss structure.

[0040] Further, the truss includes a truss body and connecting components for connecting the truss body. The truss body includes vertical members and upper and lower diagonal members located at both ends of the vertical members. The upper and lower diagonal members converge inward along the convergence direction to form a third intersection point. The intersection point of the upper diagonal member and the endpoint of the vertical member is the first intersection point, and the intersection point of the lower diagonal member and the endpoint of the vertical member is the second intersection point. The truss body also includes horizontal members, one end of which is located at the third intersection point, and the other end intersects the vertical member perpendicularly to form a fourth intersection point; and / or

[0041] The connecting assembly is a multi-pass hollow connecting assembly, comprising a connecting assembly body and a cavity disposed within the connecting assembly body. The cavity conforms to the truss body so that the vertical members, upper diagonal members, lower diagonal members, and horizontal members pass through the corresponding cavities of the connecting assembly body to form the truss; and / or

[0042] The second top plate and the second bottom plate are threaded to both ends of the vertical rod, and the second side plate is threaded to the vertical rod.

[0043] Furthermore, the truss body is a hollow truss body, reducing the weight of the load-bearing structure. The vertical member includes a vertical member body, the cross-section of which is polygonal, and at least two sides of the polygon are perpendicular to each other or spatially perpendicular, so that adjacent second sides installed on the same vertical member body are perpendicular to each other; and / or

[0044] The connecting assembly includes connector one, connector two, connector three, and connector four. Connector one, connector two, connector three, and connector four are respectively located at the first intersection point, the second intersection point, the third intersection point, and the fourth intersection point. Connector one includes a connector one body and a first connecting piece disposed on the connector one body. Connector two includes a connector two body and a second connecting piece disposed on the connector two body. The second top plate and the second bottom plate are respectively threadedly connected to the second connecting piece and the first connecting piece.

[0045] Furthermore, the connecting assembly is a carbon fiber connecting assembly, and the truss is formed by adhesive bonding and / or riveting through the connecting assembly.

[0046] Furthermore, the first connector also includes multiple cavities within the body of the first connector, the second connector also includes multiple cavities within the body of the second connector, the third connector includes the body of the third connector and multiple cavities within the body of the third connector, and the fourth connector includes the body of the fourth connector and multiple cavities within the body of the fourth connector; the wall thickness of the bodies of the first connector, the second connector, the third connector, and the fourth connector is 2mm, and the first connecting piece and the second connecting piece are stress concentration points, with a wall thickness of 6mm at the first connecting piece and the second connecting piece.

[0047] Furthermore, the cross-sections of the horizontal bars, upper diagonal bars, and lower diagonal bars are square, while the cross-section of the vertical bars is hexagonal. Each vertical bar includes a first bent plate and a second bent plate connected to it. The first bent plate comprises three plates connected in sequence: plate one, plate two, and plate three. Plate one and plate three are spatially perpendicular to each other, ensuring that adjacent second side panels installed on the same vertical bar are perpendicular to each other. To ensure the installation interface between the truss vertical bar and the second side panel, the vertical bar is designed as a hexahedron.

[0048] Furthermore, the truss is a carbon fiber truss. M55J carbon fiber is selected to ensure sufficient stiffness; the cross-sections of the horizontal bars, upper diagonal bars, and lower diagonal bars are square with a size of 40mm; the wall thickness of the truss is 2mm.

[0049] Furthermore, a second side plate mounting hole is provided on plate one and plate three.

[0050] Furthermore, the inter-satellite connection structure is threadedly connected to the second top plate; the inter-satellite connection structure is also threadedly connected to the first top plate.

[0051] Furthermore, connector one and connector three are located at both ends of the vertical rod and are threadedly connected to the second top plate and the second bottom plate, respectively.

[0052] Furthermore, the vertical rod is also provided with an embedded part, which is arranged along the axial direction of the vertical rod and conforms to the shape of the vertical rod. The embedded part includes an embedded part body and a second side plate mounting hole two opened on the embedded part body. The second side plate mounting hole two provides a threaded interface. The second side plate mounting hole one corresponds to the second side plate mounting hole two. The second side plate is threadedly connected to the vertical rod through the embedded part.

[0053] Furthermore, the outer wall of the vertical rod body is also provided with a gasket to ensure the shape and position accuracy of the mounting surface, facilitate assembly, and ensure the installation accuracy of the entire star. The gasket is provided on plate one and plate three, and the gasket has a second side plate mounting hole three, which corresponds to the second side plate mounting holes one and two. When installing the second side plate, the gasket is positioned between the second side plate and the vertical rod body. During installation: the screw passes through the second side plate mounting hole three, the second side plate mounting hole one, and the second side plate mounting hole two in sequence.

[0054] Furthermore, the truss is threadedly connected to the first flange, and a plurality of second corner plates are provided between the first flange and the truss. The second corner plates are L-shaped and are located on both sides of the truss, at the bottom of the first flange. When the truss is connected to the first flange: one plate of the second corner plate is threadedly connected to the truss, and the other plate is threadedly connected to the first flange; and / or

[0055] The upper satellite also includes a second storage tank, one end of which is threaded to the second base plate and the other end is threaded to the first flange. The second corner plate is used to increase the connection area between the truss and the second storage tank, and the second corner plate is screwed to both sides of the truss.

[0056] Furthermore, the second storage tank is a cylindrical storage tank, the first flange is an annular flange, and the second storage tank is also provided with a second flange that matches the first flange, the second flange being threadedly connected to the first flange. That is, the first flange connects the truss to the second flange, thereby connecting the second storage tank to the truss.

[0057] Furthermore, to ensure sufficient rigidity and reduce the amplification factor of the sinusoidal vibration response, the first flange is made of carbon fiber M55J material with a wall thickness of 15mm. The first flange provides an installation interface for the second storage tank.

[0058] Furthermore, the inter-satellite connection structure includes an adapter ring and a base located at the bottom of the adapter ring. The adapter ring is connected to the second top plate, and the base is connected to the rod joint.

[0059] Furthermore, the adapter ring has a second through hole, and the thickness of the adapter ring at the connection of the second through hole is 8mm; the base has a first through hole, and the thickness of the base at the connection of the first through hole is 8mm. The adapter ring is connected to the first top plate by screws; the base is connected to the rod joint by M8 screws.

[0060] Furthermore, there are four second through holes with a diameter of 8.2 mm, and four first through holes with a diameter of 8.5 mm.

[0061] Furthermore, the inter-satellite connection structure also includes bolts and release nuts. Bolts are used to connect the adapter ring and the base. The base-release nut-bolt-adaptor ring bears the bending moment load caused by axial tension, compression and shear force. The adapter ring-base conical surface contact bears the shear load. The entire inter-satellite connection structure uses bolts to transmit the connection force, which has a simple force transmission path and uniform force distribution.

[0062] Furthermore, the lower satellite also includes a lower satellite assembly, which is disposed within the lower satellite cabin; the upper satellite also includes an upper satellite assembly, which is disposed within the upper satellite cabin.

[0063] The present invention has at least the following beneficial effects: 1) The force transmission path of the dual-satellite self-connected main load-bearing structure in the present invention is simple and direct, conforming to the principle of force flow continuity and the principle of shortest force transmission path. Compared with the traditional plate-type large tank support structure, the sinusoidal vibration response can be reduced by about 2.5g; 2) The truss structure in the present invention has strong design flexibility, and can use less lightweight structural materials to obtain higher structural stiffness and strength, and improve structural efficiency. Compared with the traditional plate-type large tank support structure, the weight can be reduced by about 20kg, which greatly saves the weight of the launch structure; 3) The dual-satellite self-connected main load-bearing structure in the present invention can be widely used in microsatellites weighing less than 500kg in the future, which is of great significance for low-cost launch and lightweight satellites carrying large tank fuel for deep space exploration. Attached Figure Description

[0064] To further illustrate the above and other advantages and features of the various embodiments of the present invention, a more specific description of the embodiments of the invention will be presented with reference to the accompanying drawings. It is to be understood that these drawings depict only typical embodiments of the invention and are therefore not intended to limit its scope. In the drawings, identical or corresponding parts will be indicated by identical or similar reference numerals for clarity.

[0065] Figure 1 The internal support structure of a conventional tandem-launched rocket is shown.

[0066] Figure 2 This illustrates a traditional large storage tank plate support structure;

[0067] Figure 3 This diagram illustrates the application of the self-connected main load-bearing structure of binary stars in this invention to binary stars.

[0068] Figure 4 A schematic diagram of the dual-star self-connected main load-bearing structure in this invention is shown;

[0069] Figure 5 This invention illustrates a schematic diagram of the structure of the support frame and the star-rocket docking joint.

[0070] Figure 6A schematic diagram of the star-rocket docking joint in this invention is shown;

[0071] Figure 7 A schematic diagram of the rod joint structure in this invention is shown;

[0072] Figure 8 A schematic diagram of the rod joint structure in this invention is shown;

[0073] Figure 9 A schematic diagram of the rod structure in this invention is shown;

[0074] Figure 10 It shows Figure 9 A magnified view of a portion of point A in the middle;

[0075] Figure 11 A schematic diagram of the upper satellite main load-bearing structure in this invention is shown;

[0076] Figure 12 A schematic diagram of the truss structure in this invention is shown;

[0077] Figure 13 This invention illustrates the following: Figure 12 A magnified view of a portion of point B in the middle;

[0078] Figure 14 A schematic diagram of the structure of connector one in this invention is shown;

[0079] Figure 15 A schematic diagram of the structure of connector two in this invention is shown;

[0080] Figure 16 A schematic diagram of the structure of connector three in this invention is shown;

[0081] Figure 17 A schematic diagram of the structure of connector four in this invention is shown;

[0082] Figure 18 A schematic diagram of the installation structure of the first flange and the truss in this invention is shown;

[0083] Figure 19 A front view of the inter-satellite connection structure in this invention is shown;

[0084] Figure 20 A top view of the inter-satellite connection structure in this invention is shown;

[0085] Figure 21 A bottom view of the inter-satellite connection structure in this invention is shown;

[0086] Figure label:

[0087] 1-Support frame, 101-Ring, 102-Intersecting body, 103-Extension leg, 2-Rib, 201-Rib body, 202-First boss, 2021-Boss 1, 2022-Boss 2, 2023-Boss 3, 2024-First side plate mounting hole, 203-Second boss, 204-First extension section, 205-Second extension section, 206-First connector, 207-Second connector, 3-Rib Joint, 301-Ribbon Joint Body 1, 302-Ribbon Joint Body 2, 303-Ribbon Joint Body 3, 304-Second Groove, 305-Weight Reduction Groove, 4-Star-Rocket Docking Joint, 401-First Groove, 402-Explosion Bolt Mounting Hole, 5-Inter-Star Connection Structure, 501-Adapter Ring, 5011-Second Through Hole, 502-Base, 5021-First Through Hole, 6-Truss, 601-Vertical Rod, 6011-Plate Part 1, 6012 - Plate Part 2, 6013 - Plate Part 3, 6014 - Second Side Plate Mounting Hole 1, 602 - Upper Diagonal Rod, 603 - Lower Diagonal Rod, 604 - Cross Rod, 605 - Connecting Assembly, 6051 - Connector Part 1, 6051-1 - Connector Part 1 Body, 6051-2 - First Connecting Piece, 6052 - Connector Part 2, 6052-1 - Connector Part 2 Body, 6052-2 - Second Connecting Piece, 6053 - Connector Part 3, 6053-1-Connector 3 Body, 6054-Connector 4, 6054-1-Connector 4 Body, 7-Embedded Part, 701-Embedded Part Body, 8-Gasket, 9-First Corner Plate, 10-Second Corner Plate, 11-First Storage Tank, 12-Second Storage Tank, 13-First Top Plate, 14-First Bottom Plate, 15-Second Top Plate, 16-Second Bottom Plate, 17-First Flange, 18-Second Flange, 19-Storage Tank Support. Detailed Implementation

[0088] It should be noted that the components in the accompanying drawings may be shown exaggerated for illustrative purposes and may not be to scale.

[0089] In this invention, the various embodiments are merely intended to illustrate the solutions of the invention and should not be construed as limiting.

[0090] In this invention, unless otherwise specified, the quantifiers “a” and “one” do not exclude scenarios involving multiple elements.

[0091] It should also be noted that, in the embodiments of the present invention, only a portion of the parts or components may be shown for clarity and simplicity. However, those skilled in the art will understand that, under the teachings of the present invention, the required parts or components can be added as needed for specific scenarios.

[0092] It should also be noted that within the scope of this invention, the terms "same", "equal", and "equal to" do not mean that the two values ​​are absolutely equal, but allow for a certain reasonable error. In other words, the terms also cover "substantially the same", "substantially equal", and "substantially equal to".

[0093] It should also be noted that in the description of this invention, the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing the invention and for simplifying the description, and do not explicitly or implicitly suggest that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on the invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0094] Furthermore, the embodiments of the present invention describe the process steps in a specific order. However, this is only for the convenience of distinguishing each step, and is not a limitation on the order of each step. In different embodiments of the present invention, the order of each step can be adjusted according to the process.

[0095] The following embodiment provides a dual-star self-connected main load-bearing structure. Figure 3 A schematic diagram of a self-connected main load-bearing structure for a dual-satellite system is shown. The dual-satellite system includes a lower satellite and an upper satellite mounted on the lower satellite. The lower satellite includes a lower satellite cabin, and the upper satellite includes an upper satellite cabin. The lower satellite cabins are flush with the upper satellite cabins. Specifically, the lower satellite includes a first top plate 13, a first bottom plate 14, multiple first side plates located between the first top plate 13 and the first bottom plate 14, a first storage tank 11, and a storage tank support 19 for supporting the first storage tank 11. The storage tank support 19 is located on the first bottom plate 14. The first top plate 13, the first bottom plate 14, and the multiple first side plates together form the lower satellite cabin. The upper satellite includes a second top plate 15, a second bottom plate 16, multiple second side plates located between the second top plate 15 and the second bottom plate 16, and a second storage tank 12. One end of the second storage tank 12 is threaded to the second bottom plate 16, and the other end is threaded to a first flange 17. The second top plate 15, the second bottom plate 16, and the multiple second side plates together form the upper satellite cabin.

[0096] Figure 4 A schematic diagram of the self-connected main load-bearing structure of the binary system is shown. It can be seen that the self-connected main load-bearing structure of the binary system includes:

[0097] The lower satellite's main load-bearing structure, which serves as the load-bearing structure for the lower satellite's cabin, includes a support frame 1 and multiple rods 2 mounted on the support frame 1. The rods 2 are located at the corners of the lower satellite's cabin along its height direction. Each rod 2 is a hollow cylindrical rod with an outer diameter of 30mm and an inner diameter of 24mm. The material of the rods 2 is aluminum alloy 2A14T6. The storage tank bracket 19 and the support frame 1 are respectively located at the top and bottom of the first base plate 14. The support frame 1 is located at the bottom of the first base plate 14. Figure 5 The diagram shows the structure of the support frame 1 and the star-rocket docking joint 4. The support frame 1 includes a circular ring 101, a cross body 102 located inside the circular ring 101, and an extension leg 103 located outside the circular ring 101. The circular ring 101, the cross body 102, and the extension leg 103 are screwed together into a whole by 16 M6 screws. The cross body 102 includes a first leg and a second leg that intersect each other. The first leg and the second leg intersect at the center of the circular ring 101 to form a central intersection point. The second leg intersects with the annular body 101 to form an end intersection point, and the extension leg 103 extends outward along the end intersection point to the apex of the first base plate 14; the support frame 1 is a carbon fiber frame, and the carbon fiber used is M55J; the storage tank support 19 is a column support, and the column diameter of the storage tank support 19 is the same as the diameter of the annular body 101 to strengthen the support for the first storage tank 11; the main load-bearing structure of the lower satellite also includes a satellite-rocket docking joint 4 and a rod joint 3. The satellite-rocket docking joint 4 is used to connect the lower satellite and the rocket. Figure 6 A schematic diagram of the structure of the star-rocket docking joint 4 is shown. There are four star-rocket docking joints 4, which are threaded to the ends of the extension legs 103 respectively. The bottom of the star-rocket docking joint 4 is provided with an explosive bolt mounting hole 402 to connect the star-rocket docking joint 4 to the rocket by bolts. Figure 7 and Figure 8A schematic diagram of the structure of the rod joint 3 is shown. The rod joint 3 is used to connect the inter-satellite connection structure 5 and the lower satellite. The rod joint 3 and the star-rocket docking joint 4 are respectively located at the top and bottom ends of the rod 2. The rod joint 3 is connected to the rod 2 by four M6 screws; the star-rocket docking joint 4 is connected to the rod 2 by M8 screws. The material of the rod joint 3 is forged aluminum 2A14T6. The rod joint 3 includes a first rod joint body 301, a second rod joint body 302, and a third rod joint body 303 connected in sequence. The rod joint 3 also has a weight reduction groove 305. 305 reduces weight while ensuring strength; the first top plate 13 is threaded to the rod joint body 302, the first bottom plate 14 is threaded to the star-arrow docking joint 4, and the rod 2 is threadedly connected to the rod joint 3 and the star-arrow docking joint 4 after snapping together. The snapping includes: the rod body 201 is provided with a first extension section 204 and a second extension section 205 at both ends, the length of the first extension section 204 and the second extension section 205 is 20mm, and the star-arrow docking joint 4 is provided with a first groove 401 at the top, the first groove 401 being adapted to the first extension section 204. The first extension 204 is shaped to fit into the first groove 401; the bottom of the rod joint 3 has a second groove 304, which is conformable to the shape of the second extension 205 so that the second extension 205 can be inserted into the second groove 304. Both the first groove 401 and the second groove 304 are rounded to facilitate the insertion of the rod 2 and reduce the installation difficulty. The insertion of the first extension 204 and the second extension 205 into the rod joint 3 increases its shear resistance; the first side plate is threaded to the rod 2, and the rod 2 also includes a part provided on the rod body 201. The first connecting body 206 at one end and the second connecting body 207 at the other end of the rod body 201 are provided. The first connecting body 206 is connected to the star-arrow docking joint 4 by four M10 screws to further strengthen the connection between the rod 2 and the star-arrow docking joint 4. The second connecting body 207 is connected to the rod joint 3 by M6 screws to connect the rod 2 and the rod joint 3. The first side plate is connected to the rod body 201 by M5 screws and M6 screws. According to the actual structural connection strength requirements, the interval between adjacent bosses is 70-100mm. Figure 9 and Figure 10A schematic diagram of the structure of rod 2 is shown. Rod 2 includes a rod body 201 and bosses provided on the rod body 201. The bosses are used to connect rod 2 and the first side plate (honeycomb plate). The bosses are spaced apart along the axial direction of the rod body 201. The bosses include a first boss 202 and a second boss 203. The first side plate is threaded to the first boss 202. The first boss 202 is a triangular boss, which includes a first boss 2021, a second boss 2022, and a third boss 2023 connected in sequence. The first boss 2021 and the third boss 2023 are spatially perpendicular to each other. The first boss 2021 and the third boss 2023 are provided with first side plate mounting holes 2024. During installation, adjacent first side plates are respectively attached to the first boss 202. 1 and boss 2023, screws are used to pass through the mounting holes 2024 of the first side plate to form the lower star cabin body surrounded by the first side plates; the second boss 203 is an arc-shaped boss, and the first boss 202 and the second boss 203 surround the outer wall of the rod body 201 circumferentially; a plurality of first corner pieces 9 are also provided between the first top plate 13 and the rod joint 3. The first corner pieces 9 are L-shaped corner pieces. The first corner pieces 9 are located at the corners of the first top plate 13. The first top plate 13 and the rod joint body 202 are connected by threads through the first corner pieces 9. When connected: one plate of the first corner piece 9 is threaded to the rod joint 3 through M4 screws, and the other plate is threaded to the first top plate 13, so as to ensure the accuracy of the load-bearing structure through the first top plate 13 during the final assembly process;

[0098] The main load-bearing structure for the satellite launch is the load-bearing structure of the satellite cabin. Figure 11 A schematic diagram of the main load-bearing structure of the upper satellite is shown. The main load-bearing structure of the upper satellite includes multiple trusses 6 and a first flange 17 connected to the multiple trusses 6. In order to ensure sufficient rigidity and reduce the amplification factor of sinusoidal vibration response, the first flange 17 is made of carbon fiber M55J material with a wall thickness of 15mm. The first flange 17 provides an installation interface with the second storage tank 12. The trusses 6 are threadedly connected to the first flange 17 to connect the trusses 6 and the first storage tank 11. The second storage tank 12 is a cylindrical storage tank. The first flange 17 is a circular flange. The second storage tank 12 is also provided with a second flange 18 that matches the first flange 17. The second flange 18 is threadedly connected to the first flange 17. The trusses 6 are carbon fiber trusses 6. The carbon fiber is selected as M55J to ensure that it has sufficient rigidity. The trusses 6 are located at the corners along the height direction of the upper satellite body. Multiple trusses 6 are arranged to converge to form a convergence point. The first flange 17 is located at the convergence point. Figure 12 and Figure 13A schematic diagram of the truss 6 is shown. The truss 6 includes a truss 6 body and a connecting assembly 605 for connecting the truss 6 body. The truss 6 body is a hollow truss 6 body to reduce the weight of the load-bearing structure. The truss 6 body includes a vertical member 601 and an upper diagonal member 602 and a lower diagonal member 603 located at both ends of the vertical member 601. The upper diagonal member 602 and the lower diagonal member 603 converge inward to form a third intersection point. The intersection point of the upper diagonal member 602 and the end point of the vertical member 601 is the first intersection point, and the intersection point of the lower diagonal member 603 and the end point of the vertical member 601 is the second intersection point. The truss 6 body also includes a horizontal member 604, one end of which is located at the third intersection point. At the intersection, the other end intersects perpendicularly with the vertical member 601 to form a fourth intersection; the connecting component 605 is a carbon fiber connecting component 605, and the truss 6 is formed by adhesive bonding and / or riveting through the connecting component 605. The connecting component 605 is a multi-pass hollow connecting component 605, which includes a connecting component 605 body and a cavity provided in the connecting component 605 body. The cavity conforms to the truss 6 body so that the vertical member 601, the upper diagonal member 602, the lower diagonal member 603, and the horizontal member 604 pass through the corresponding cavity of the connecting component 605 body to form the truss 6; specifically, the connecting component 605 includes a connector 6051 ( Figure 14 ), Connector 2 6052 ( Figure 15 ), connector 3 6053 ( Figure 16 ) and connector four ( Figure 17Connector 1 6051, connector 2 6052, connector 3 6053, and connector 4 are respectively located at the first intersection point, the second intersection point, the third intersection point, and the fourth intersection point. Connector 1 6051 includes a connector 1 body 6051-1, a first connecting piece 6051-2 disposed on the connector 1 body 6051-1, and multiple cavities disposed within the connector 1 body 6051-1. Connector 2 6052 includes a connector 2 body 6052-1, a second connecting piece 6052-2 disposed on the connector 2 body 6052-1, and multiple cavities disposed within the connector 2 body 6052-1. Connector 3 6053 includes a connecting piece 6051-1, a second connecting piece 6052-2 disposed on the connector 2 body 6052-1, and multiple cavities disposed within the connector 2 body 6052-1. The connector includes a body 6053-1 and multiple cavities within the body 6053-1. The fourth connector includes a body 6054-1 and multiple cavities within it. Connectors 6051 and 6053 are located at both ends of the vertical rod 601. The second top plate 15 and the second bottom plate 16 are threadedly connected to the second connecting piece 6052-2 and the first connecting piece 6051-2, respectively. The wall thickness of the first connecting piece body 6051-1, the second connecting piece body 6052-1, the third connecting piece body 6053-1, and the fourth connecting piece body 6054-1 is 2mm. The first connecting piece 6051-2... The stress concentration points are located at the second connecting piece 6052-2. The wall thickness of the first connecting piece 6051-2 and the second connecting piece 6052-2 is 6mm. The wall thickness of the truss 6 is 2mm. The cross-sections of the horizontal bar 604, the upper diagonal bar 602, and the lower diagonal bar 603 are square, with a size of 40mm. To ensure the installation interface between the vertical bar 601 of the truss 6 and the second side plate, the vertical bar 601 is designed as a hexahedron, that is, the cross-section of the vertical bar 601 is hexagonal. The vertical bar 601 includes a first bent plate and a second bent plate that surrounds and connects with the first bent plate. The first bent plate includes plate 6011, plate 6012, and plate 6013 connected in sequence. A second side plate mounting hole 6014 is provided on plate 6011 and plate 6013. Plate 6011 and plate 6013 are spatially perpendicular to each other so that adjacent second side plates installed on the same vertical rod 601 are perpendicular to each other. A pre-embedded part 7 is also provided in the vertical rod 601. The second side plate is threadedly connected to the vertical rod 601 through the pre-embedded part 7. The pre-embedded part 7 is arranged along the axial direction of the vertical rod 601 and conforms to the shape of the vertical rod 601. The pre-embedded part 7 includes a pre-embedded part body 701 and a second side plate mounting hole 2 opened on the pre-embedded part body 701. The second side plate mounting hole 2 provides a threaded interface. The second side plate mounting hole 6014 corresponds to the second side plate mounting hole 2.The outer wall of the vertical rod 601 body is also provided with a gasket 8 to ensure the shape and position accuracy of the mounting surface, facilitate assembly, and ensure the installation accuracy of the entire star. The gasket 8 is provided on plate 1 6011 and plate 3 6013. The gasket 8 has a second side plate mounting hole 3, which corresponds to the second side plate mounting hole 1 6014 and the second side plate mounting hole 2. When installing the second side plate, the gasket 8 is placed between the second side plate and the vertical rod 601 body. During installation: the screw passes through the second side plate mounting hole 3, the second side plate mounting hole 1 6014, and the second side plate mounting hole 2 in sequence. Figure 18 A schematic diagram of the installation structure of the first flange 17 and the truss 6 is shown. Multiple second corner plates 10 are also provided between the first flange 17 and the truss 6. The second corner plates 10 are L-shaped and are used to increase the connection area between the truss 6 and the second storage tank 12. The second corner plates 10 are screwed to both sides of the truss 6 and placed at the bottom of the first flange 17. When the truss 6 is connected to the first flange 17: one plate of the second corner plate 10 is threaded to the truss 6, and the other plate is threaded to the first flange 17; and

[0099] Inter-satellite connection structure 5 is used to connect the main load-bearing structure of the lower satellite and the main load-bearing structure of the upper satellite. The inter-satellite connection structure 5 is located between the main load-bearing structure of the lower satellite and the main load-bearing structure of the upper satellite to form a dual-satellite self-connected main load-bearing structure. Specifically, the inter-satellite connection structure 5 is located between the first top plate 13 and the second top plate 15 to connect the lower satellite cabin and the upper satellite cabin. Figure 19 The front view of inter-satellite connection structure 5 is shown. Figure 20 A top view of inter-satellite connection structure 5 is shown. Figure 21 A bottom view of the inter-satellite connection structure 5 is shown. The inter-satellite connection structure 5 includes a transition ring 501, a base 502 located at the bottom of the transition ring 501, and bolts for connecting the transition ring 501 and the base 502. The transition ring 501 is connected to the second top plate 15, and the base 502 is connected to the rod joint 3. The transition ring 501 has four second through holes 5011 with a diameter of 8.2 mm, and the thickness of the transition ring 501 at the connection of the second through holes 5011 is 8 mm. The base 502 has four first through holes 5021 with a diameter of 8.5 mm, and the thickness of the base 502 at the connection of the first through holes 5021 is 8 mm. The adapter ring 501 is connected to the first top plate 13 by screws; the base 502 is connected to the rod joint 3 by M8 screws; the inter-satellite connection structure 5 also includes a separation nut, the base 502-separation nut-bolt-adaptor ring 501 bears the bending moment load caused by axial tension and compression and shear force, the adapter ring 501-base 502 conical surface contact bears the shear load, the entire inter-satellite connection structure 5 uses bolts to transmit the connection force, the force transmission path is simple and the force is uniform.

[0100] While some embodiments of the present invention have been described in this application, those skilled in the art will understand that these embodiments are merely illustrative. Numerous variations, alternatives, and improvements will arise in those skilled in the art under the teachings of this invention without departing from its scope. The appended claims are intended to define the scope of the invention and thereby cover methods and structures within the scope of the claims themselves and their equivalents.

Claims

1. A dual-satellite self-connected main load-bearing structure, comprising a lower satellite and an upper satellite disposed on the lower satellite, wherein the lower satellite comprises a lower satellite body, a first top plate, a first bottom plate, and a plurality of first side plates disposed between the first top plate and the first bottom plate, the first top plate, the first bottom plate, and the plurality of first side plates together forming the lower satellite body; the upper satellite comprises an upper satellite body, a second top plate, a second bottom plate, and a plurality of second side plates disposed between the second top plate and the second bottom plate, the second top plate, the second bottom plate, and the plurality of second side plates forming the upper satellite body; the lower satellite body is flush with the upper satellite body, characterized in that, The binary self-connected main load-bearing structure includes: The lower satellite main load-bearing structure is the load-bearing structure of the lower satellite cabin. The lower satellite main load-bearing structure includes a support frame, multiple rods provided on the support frame, and rod joints provided at the ends of the rods. The rods are provided at the corners of the lower satellite cabin along the height direction. The main load-bearing structure for the satellite launch vehicle is the load-bearing structure of the launch vehicle cabin. The main load-bearing structure includes multiple trusses and a first flange connected to the multiple trusses. The trusses are located at the corners of the launch vehicle cabin along its height direction. The multiple trusses are arranged in a convergent configuration to form a convergence point, and the first flange is located at the convergence point. An inter-satellite connection structure is used to connect the lower satellite main load-bearing structure and the upper satellite main load-bearing structure. The inter-satellite connection structure is located between the lower satellite main load-bearing structure and the upper satellite main load-bearing structure to form a dual-satellite self-connected main load-bearing structure. The inter-satellite connection structure is located between the first and second top plates to connect the lower and upper satellite modules. The inter-satellite connection structure includes a transition ring and a base at the bottom of the transition ring. The transition ring is connected to the second top plate, and the base is connected to the rod joint. The truss includes a truss body and connecting components for connecting the truss body. The truss body includes vertical members and upper and lower diagonal members at both ends of the vertical members. The upper and lower diagonal members converge inwards along the convergence direction to form a third intersection point. The intersection of the upper diagonal brace and the endpoint of the vertical brace is the first intersection point, and the intersection of the lower diagonal brace and the endpoint of the vertical brace is the second intersection point. The truss body also includes a horizontal bar, one end of which is located at the third intersection point, and the other end intersects the vertical brace perpendicularly to form a fourth intersection point. The truss body is a hollow truss body, and the vertical brace includes a vertical bar body. The cross-section of the vertical bar body is a polygon, and the polygon has at least two sides that are perpendicular to each other or spatially perpendicular to each other, so that adjacent second sides installed on the same vertical bar body are perpendicular to each other.

2. The binary self-connected main load-bearing structure according to claim 1, characterized in that, The support frame is located at the bottom of the first base plate. The support frame includes a ring, a cross body located inside the ring, and an extension leg located outside the ring. The cross body includes a first leg and a second leg that intersect each other. The first leg and the second leg intersect with the ring to form an end intersection point. The extension leg extends outward along the end intersection point to the apex of the first base plate.

3. The binary self-connected main load-bearing structure according to claim 2, characterized in that, The lower satellite main load-bearing structure also includes: A satellite-rocket docking joint, used to connect the lower satellite and the rocket, is located at the end of the extended outrigger; the rod joint and the satellite-rocket docking joint are respectively located at both ends of the rod; and / or The inter-satellite connection structure is connected to the second top plate and the first top plate respectively, and the rod is engaged with the rod joint and the star-rocket docking joint; and / or The rod joint includes a rod joint body one, a rod joint body two, and a rod joint body three connected in sequence. The first top plate is threadedly connected to the rod joint body two, the first bottom plate is threadedly connected to the star-arrow docking joint, and the first side plate is threadedly connected to the rod.

4. The binary self-connected main load-bearing structure according to claim 3, characterized in that, The rod includes a rod body and bosses disposed on the rod body. The bosses are spaced apart along the axial direction of the rod body. Each boss includes a first boss. The first side plate is threadedly connected to the first boss. The first boss is a polygonal boss, and at least two sides of the first boss are perpendicular to each other or spatially perpendicular to each other, so that adjacent first side plates installed on the same rod body are perpendicular to each other; and / or The rod body is provided with a first extension section and a second extension section at both ends, and a first groove is provided at the top of the star-arrow docking joint. The first groove is conformed to the first extension section so that the first extension section can be inserted into the first groove. A second groove is provided at the bottom of the rod joint. The second groove is conformed to the second extension section so that the second extension section can be inserted into the second groove.

5. The binary self-connected main load-bearing structure according to claim 2, characterized in that, The connecting assembly is a multi-pass hollow connecting assembly, comprising a connecting assembly body and a cavity disposed within the connecting assembly body. The cavity conforms to the truss body so that the vertical members, upper diagonal members, lower diagonal members, and horizontal members pass through the corresponding cavities of the connecting assembly body to form the truss; and / or The second top plate and the second bottom plate are threaded to both ends of the vertical rod, and the second side plate is threaded to the vertical rod.

6. The binary self-connected main load-bearing structure according to claim 1, characterized in that, The connecting assembly includes connector one, connector two, connector three, and connector four. Connector one, connector two, connector three, and connector four are respectively located at the first intersection point, the second intersection point, the third intersection point, and the fourth intersection point. Connector one includes a connector one body and a first connecting piece disposed on the connector one body. Connector two includes a connector two body and a second connecting piece disposed on the connector two body. The second top plate and the second bottom plate are respectively threadedly connected to the second connecting piece and the first connecting piece.

7. The binary self-connected main load-bearing structure according to claim 1, characterized in that, The vertical rod is also provided with a pre-embedded part, which is arranged along the axial direction of the vertical rod and conforms to the shape of the vertical rod. The second side plate is threadedly connected to the vertical rod through the pre-embedded part.

8. The binary self-connected main load-bearing structure according to claim 1, characterized in that, The truss is threadedly connected to the first flange. A plurality of second corner plates, L-shaped, are also provided between the first flange and the truss. These second corner plates are located on both sides of the truss. When the truss is connected to the first flange: one plate of each second corner plate is threadedly connected to the truss, and the other plate is threadedly connected to the first flange; and / or The satellite also includes a second storage tank, one end of which is threadedly connected to the second base plate, and the other end is threadedly connected to the first flange.

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