Double-star self-series-connection main force bearing structure

Abstract

The invention relates to a double-satellite self-series-connection main load-bearing structure which comprises a lower satellite main load-bearing structure, an upper satellite main load-bearing structure and an inter-satellite connecting structure used for connecting the lower satellite main load-bearing structure and the upper satellite main load-bearing structure. The lower satellite main force bearing structure comprises a supporting frame and a plurality of rod pieces arranged on the supporting frame, and the rod pieces are arranged at the corner angles of the lower satellite cabin in the height direction. The satellite main bearing structure comprises a plurality of trusses and a first flange connected with the trusses, the trusses are arranged at the corner angles of the satellite cabin body in the height direction, the trusses are gathered and arranged to form a gathering position, and the first flange is arranged at the gathering position. The force transmission path of the double-star self-series-connection main force bearing structure is simple and direct, the force flow continuity principle and the shortest force transmission path principle are met, and compared with a traditional plate type large storage box supporting structure, the sinusoidal vibration response can be reduced by about 2.5 g.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, in particular to a dual-satellite self-series main load-bearing structure, and in particular to a dual-satellite self-series main load-bearing structure suitable for configuring a large tank on a small satellite. Background Art

[0002] In the satellite launch mission in the aerospace field, the traditional satellite tandem launch method usually relies on the carrier rocket to connect the upper and lower satellites through the satellite adapter internal support structure in the fairing. The conventional tandem launch rocket internal support structure is as follows: Figure 1 However, this method has significant drawbacks: since the launch vehicle needs to provide additional internal support structures, the launch mass cannot be maximized, which in turn causes the launch cost to remain high. At the same time, the 100L large tanks configured for small satellites are mostly supported by plate structures. The traditional large tank plate support structure is as follows: Figure 2 As shown in the figure, the drum-skin effect is obvious and the large tank has a large mechanical response. To solve this problem, it is often necessary to add reinforcement structures to increase rigidity, but the actual effect is minimal, further exacerbating the waste of structural weight.

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

[0004] In order to solve at least part of the above problems in the prior art, the present invention provides a dual-satellite self-series main load-bearing structure, specifically a dual-satellite self-series main load-bearing structure that is suitable for configuring a large tank for a small satellite.

[0005] The present invention provides a dual-satellite self-connected main load-bearing structure, wherein the dual-satellite includes a lower satellite and an upper satellite disposed on the lower satellite, wherein the lower satellite includes a lower satellite cabin, and the upper satellite includes an upper satellite cabin, wherein the lower satellite cabin is flush with the upper satellite cabin, and the dual-satellite self-connected main load-bearing structure includes:

[0006] The lower satellite main load-bearing structure is the load-bearing structure of the lower satellite cabin body. 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 body along the height direction.

[0007] The upper satellite main load-bearing structure is the load-bearing structure of the upper satellite cabin, and the upper satellite main load-bearing structure includes a plurality of trusses and a first flange connected to the plurality of trusses. The trusses are arranged at the corners of the upper satellite cabin along the height direction. The plurality of trusses are gathered and arranged to form a gathering point, and the first flange is provided at the gathering point; and

[0008] The 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 arranged between the lower satellite main load-bearing structure and the upper satellite main load-bearing structure to form a double-satellite self-series 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 arranged between the first top plate and the first bottom plate, and the first top plate, the first bottom plate, and the plurality of first side plates together form the lower satellite cabin; the upper satellite includes a second top plate, a second bottom plate, and a plurality of second side plates arranged between the second top plate and the second bottom plate, and the upper satellite cabin is formed between the second top plate, the second bottom plate, and the plurality of second side plates; the inter-satellite connection structure is arranged 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 cabin body and the upper satellite cabin body are cubic cabin bodies.

[0011] Furthermore, the support frame is arranged at the bottom of the first base plate, and the support frame includes a circular body, a cross body arranged inside the circular body, and an extended leg arranged outside the circular body. The cross body includes a first leg and a second leg that cross each other. The first leg and the second leg intersect with the circular body to form an end intersection, and the extended leg extends outward along the end intersection to the vertex of the first base plate.

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

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

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

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

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

[0017] Furthermore, the lower star also includes a first tank and a tank bracket for supporting the first tank. The tank bracket is arranged on the first base plate, that is, the tank bracket and the support frame are respectively arranged on the top and bottom of the first base plate; the tank bracket is a column bracket, and the column diameter of the tank bracket is the same as the diameter of the annular body to strengthen the support for the first tank.

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

[0019] a satellite-rocket docking joint, which is used to connect the lower satellite and the rocket, and the satellite-rocket docking joint is provided at the end of the extension leg; and

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

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

[0022] The rod joint includes a rod joint body 1, a rod joint body 2 and a rod joint body 3 connected in sequence, the first top plate is threadedly connected to the rod joint body 2, the first bottom plate is threadedly connected to the satellite-rocket docking joint, and the first side plate is threadedly connected to the rod.

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

[0024] Furthermore, the satellite-rocket joint is threadedly connected to the end of the extension leg; the rod joint and the satellite-rocket joint are respectively provided at the top and bottom ends of the rod. The rod joint is connected to the rod via four M6 screws; the satellite-rocket joint is connected to the rod via M8 screws.

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

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

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

[0028] Furthermore, a plurality of first angle pieces are provided between the first top plate and the rod joint, wherein the first angle piece is an L-shaped angle piece, and the first angle piece is provided at the corner of the first top plate. The first top plate and the rod joint body 2 are threadedly connected through the first angle piece. When connected: one plate of the first angle piece 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 angle piece by an M4 screw, so as to ensure the accuracy of the load-bearing structure through the first top plate during the final assembly process.

[0030] Furthermore, a weight-reducing groove is provided on the rod joint to reduce weight while ensuring strength.

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

[0032] Further, the rod includes a rod body and bosses provided on the rod body, the bosses are arranged at intervals along the axial direction of the rod body, the bosses include 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 perpendicular to each other in space, so that adjacent first side sides installed 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 each end. A first slot is defined at the top of the satellite-rocket joint, shaped to fit the first extension section so that the first extension section can be inserted into the first slot. A second slot is defined at the bottom of the rod joint, shaped to fit the second extension section so that the second extension section can be inserted into the second slot. The first and second extension sections inserted into the rod joint enhance its shear resistance.

[0034] Furthermore, the first and second slots are both designed with rounded corners to facilitate the insertion of the rod and reduce the difficulty of installation. The length of the first extension section and the second extension section is 20 mm.

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

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

[0037] Furthermore, the first boss is a triangular boss, and the triangular boss includes boss one, boss two and boss three connected in sequence, and the boss one and boss three are perpendicular to each other in space. The boss one and boss three are provided with first side panel mounting holes. During installation: adjacent first side panels are respectively attached to the boss one and boss three, and screws are used to penetrate the first side panel mounting holes to form a lower satellite cabin body surrounded by each first side panel.

[0038] Furthermore, the boss further includes a second boss, the second boss is an arc-shaped boss, and the first boss and the second boss are circumferentially surrounded along the outer wall of the rod body.

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

[0040] Furthermore, the truss includes a truss body and a connecting assembly for connecting the truss body, the truss body includes a vertical rod and an upper oblique rod and a lower oblique rod provided at both ends of the vertical rod, the upper oblique rod and the lower oblique rod are retracted inwardly along the direction of the retraction point to form a third intersection, the intersection of the upper oblique rod and the end point of the vertical rod is a first intersection, and the intersection of the lower oblique rod and the end point of the vertical rod is a second intersection, the truss body also includes a cross rod, one end of the cross rod is provided at the third intersection, and the other end intersects with the vertical rod at right angles to form a fourth intersection; and / or

[0041] The connecting assembly is a multi-pass hollow connecting assembly, comprising a connecting assembly body and a cavity provided in the connecting assembly body, wherein the cavity is shaped to conform to the truss body so that the vertical rods, upper oblique rods, lower oblique rods and cross rods are passed through the cavities of the corresponding connecting assembly bodies to form the truss; and / or

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

[0043] Furthermore, the truss body is a hollow truss body to reduce the weight of the load-bearing structure, the vertical rod includes a vertical rod body, the cross-section of the vertical rod body is a polygon, and at least two sides of the polygon are perpendicular to each other or perpendicular to each other in space, so that adjacent second sides installed on the same vertical rod body are perpendicular to each other; and / or

[0044] The connecting component includes connecting member 1, connecting member 2, connecting member 3 and connecting member 4, and the connecting member 1, connecting member 2, connecting member 3 and connecting member 4 are respectively arranged at the first intersection, the second intersection, the third intersection and the fourth intersection. The connecting member 1 includes a connecting member 1 body and a first connecting piece arranged on the connecting member 1 body. The connecting member 2 includes a connecting member 2 body and a second connecting piece arranged on the connecting member 2 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 connection assembly is a carbon fiber connection assembly, and the truss is formed by the connection assembly using gluing and / or riveting.

[0046] Furthermore, the first connector also includes a plurality of cavities provided in the body of the first connector, the second connector also includes a plurality of cavities provided in the body of the second connector, the third connector includes a third connector body and a plurality of cavities provided in the body of the third connector, and the fourth connector includes a fourth connector body and a plurality of cavities provided in the body of the fourth connector; the wall thickness of the first connector body, the second connector body, the third connector body and the fourth connector body is 2 mm, the first connecting piece and the second connecting piece are places where stress is concentrated, and the wall thickness of the first connecting piece and the second connecting piece is 6 mm.

[0047] Furthermore, the cross-sections of the horizontal bars, upper oblique bars, and lower oblique bars are square, while the cross-sections of the vertical bars are hexagonal. The vertical bars include a first bent plate and a second bent plate encircling and connected to the first bent plate. The first bent plate includes a first plate, a second plate, and a third plate connected in sequence. The first and third plates are spatially perpendicular to each other, so that adjacent second sides installed on the same vertical bar are perpendicular to each other. To ensure a secure mounting interface between the truss vertical bars and the second side plates, the vertical bars are designed as hexahedrons.

[0048] Furthermore, the truss is a carbon fiber truss. The carbon fiber is selected from M55J to ensure sufficient rigidity. The cross-sections of the crossbars, upper and lower diagonal bars are square and 40 mm in size. The wall thickness of the truss is 2 mm.

[0049] Furthermore, a second side panel mounting hole 1 is provided on the panel 1 and the panel 3.

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

[0051] Furthermore, the connecting member 1 and the connecting member 3 are provided at both ends of the vertical rod and are threadedly connected to the second top plate and the second bottom plate respectively.

[0052] Furthermore, an embedded part is provided in the vertical rod. The embedded part is arranged along the axial direction of the vertical rod and conforms to the vertical rod. The embedded part includes an embedded part body and a second side plate mounting hole 2 opened on the embedded part body. The second side plate mounting hole 2 provides a threaded interface. The second side plate mounting hole 1 corresponds to the second side plate mounting hole 2. The second side plate and the vertical rod are threadedly connected via the embedded part.

[0053] Furthermore, a gasket is provided on the outer wall of the vertical rod body to ensure the shape and position accuracy of the mounting surface, facilitating final assembly and ensuring the installation accuracy of the entire satellite. The gasket is provided on Panels 1 and 3 and defines Second Side Panel Mounting Hole 3. Second Side Panel Mounting Hole 3 corresponds to Second Side Panel Mounting Hole 1 and Second Side Panel Mounting Hole 2. When the second side panel is installed, the gasket is positioned between the second side panel and the vertical rod body. During installation, screws are sequentially inserted through Second Side Panel Mounting Hole 3, Second Side Panel Mounting Hole 1, and Second Side Panel Mounting Hole 2.

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

[0055] The upper star also includes a second tank, one end of which is threadedly connected to the second base plate, and the other end is threadedly connected to the first flange. The second angle piece is used to increase the connection area between the truss and the second tank, and the second angle piece is screwed to both sides of the truss.

[0056] Furthermore, the second tank is a cylindrical tank, the first flange is a circular flange, and the second tank is further provided with a second flange that matches the first flange, and the second flange is threadedly connected to the first flange. That is, the first flange connects the truss to the second flange, thereby connecting the second 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 15 mm. The first flange provides a mounting interface with the second tank.

[0058] Furthermore, the inter-satellite connection structure includes an adapter ring and a base provided 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 8 mm. The base has a first through hole, and the thickness of the base at the connection of the first through hole is 8 mm. The adapter ring is connected to the first top plate via screws, and the base is connected to the rod joint via M8 screws.

[0060] Furthermore, the number of the second through holes is four, and the diameter is 8.2 mm; the number of the first through holes is four, and the diameter is 8.5 mm.

[0061] Furthermore, the intersatellite connection structure also includes bolts and separation nuts. The bolts are used to connect the adapter ring and the base. The base-separation nut-bolt-adapter ring bears the bending moment load caused by axial tension and compression and shear force, and the adapter ring-base conical surface contact bears the shear load. The entire intersatellite connection structure uses bolts to transmit the connection force, the force transmission path is simple, and the force is uniform.

[0062] Furthermore, the lower satellite also includes a lower satellite component, and the lower satellite component is arranged in the lower satellite cabin; the upper satellite also includes an upper satellite component, and the upper satellite component is arranged in 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-series main load-bearing structure in the present invention is simple and direct, which complies with the principle of force flow continuity and the principle of the 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 designability, 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, it can reduce the weight by about 20kg, greatly saving the weight of the launch structure; 3) The dual-satellite self-series main load-bearing structure in the present invention can be widely used in micro-satellites below 500kg in the future, which has a promoting significance for low-cost launch and lightweight satellites carrying large tank fuel to carry out deep space exploration. BRIEF DESCRIPTION OF THE DRAWINGS

[0064] To further illustrate the above and other advantages and features of various embodiments of the present invention, a more detailed description of various embodiments of the present invention will be presented with reference to the accompanying drawings. It will be understood that these drawings depict only typical embodiments of the present invention and are not to be considered as limiting the scope thereof. In the drawings, for clarity, identical or corresponding parts will be represented by the same or similar reference numerals.

[0065] Figure 1 The inner support structure of a conventional tandem launch rocket is shown;

[0066] Figure 2 The conventional large tank plate support structure is shown;

[0067] Figure 3 It shows a schematic structural diagram of the dual-satellite self-series main load-bearing structure applied to the dual-satellite in the present invention;

[0068] Figure 4 It shows a schematic diagram of the main bearing structure of the double star self-series connection in the present invention;

[0069] Figure 5 It shows a structural schematic diagram of the support frame and the satellite-rocket docking joint in the present invention;

[0070] Figure 6The structure diagram of the satellite-rocket docking joint in the present invention is shown;

[0071] Figure 7 It shows a schematic structural diagram of the rod joint in the present invention;

[0072] Figure 8 It shows a schematic structural diagram of the rod joint in the present invention;

[0073] Figure 9 shows a schematic structural diagram of the rod member in the present invention;

[0074] Figure 10 Shown Figure 9 A partial enlarged schematic diagram of point A in the middle;

[0075] Figure 11 It shows the schematic diagram of the main bearing structure of the satellite in the present invention;

[0076] Figure 12 shows a schematic structural diagram of the truss in the present invention;

[0077] Figure 13 The present invention shows Figure 12 A partial enlarged schematic diagram of point B in the middle;

[0078] Figure 14 It shows a structural schematic diagram of the connecting member 1 in the present invention;

[0079] Figure 15 It shows a schematic structural diagram of the connecting member 2 in the present invention;

[0080] Figure 16 It shows a schematic structural diagram of the connecting member 3 in the present invention;

[0081] Figure 17 Schematic diagram of the structure of the connecting member 4 in the present invention is shown;

[0082] Figure 18 It shows a schematic diagram of the installation structure of the first flange and the truss in the present invention;

[0083] Figure 19 Shows a front view of the intersatellite connection structure of the present invention;

[0084] Figure 20 A top view of the intersatellite connection structure of the present invention is shown;

[0085] Figure 21 A bottom view of the intersatellite connection structure of the present invention is shown;

[0086] Reference numerals:

[0087] 1-Support frame, 101-Annular body, 102-Cross body, 103-Extended leg, 2-Rod, 201-Rod body, 202-First boss, 2021-Boss 1, 2022-Boss 2, 2023-Boss 3, 2024-First side panel mounting hole, 203-Second boss, 204-First extension section, 205-Second extension section, 206-First connector, 207-Second connector, 3-Rod Joint, 301-Rod Joint Body 1, 302-Rod Joint Body 2, 303-Rod Joint Body 3, 304-Second Trough, 305-Weight Reduction Trough, 4-Satellite-Rocket Butt Joint, 401-First Trough, 402-Explosive Bolt Mounting Hole, 5-Intersatellite 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 2, 6013- Plate 3, 6014- Second side panel mounting hole 1, 602- Upper oblique rod, 603- Lower oblique rod, 604- Crossbar, 605- Connecting assembly, 6051- Connecting piece 1, 6051-1- Connecting piece 1 body, 6051-2- First connecting piece, 6052- Connecting piece 2, 6052-1- Connecting piece 2 body, 6052-2- Second connecting piece, 6053- Connecting piece Part three, 6053-1-Connector three body, 6054-Connector four, 6054-1-Connector four body, 7-Embedded parts, 701-Embedded parts body, 8-Gasket, 9-First angle piece, 10-Second angle piece, 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-Tank bracket. DETAILED DESCRIPTION

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

[0089] In the present invention, each embodiment is only intended to illustrate the aspects of the present invention and should not be construed as limiting.

[0090] In the present invention, unless otherwise specified, the quantifiers "a" and "an" do not exclude the presence of multiple elements.

[0091] It should also be pointed out that in the embodiments of the present invention, for the sake of clarity and simplicity, only a portion of the parts or components may be shown, but a person skilled in the art will understand that under the teachings of the present invention, the required parts or components may be added according to the needs of the specific scenario.

[0092] It should also be pointed out that within the scope of the present invention, the terms "same", "equal", "equal to" and the like do not mean that the two values ​​are absolutely equal, but allow a certain reasonable error, that is, the terms also cover "substantially the same", "substantially equal", and "substantially equal to".

[0093] It should also be noted that in the description of the present invention, the terms "center," "longitudinal," "lateral," "upper," "lower," "front," "back," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," and "outer" and the like, indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely to facilitate description and simplify the present invention. They do not explicitly or implicitly state that the devices or components referred to must have a specific orientation, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limitations on the present 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] In addition, the embodiments of the present invention describe the process steps in a specific order, but this is only for the convenience of distinguishing the steps, and does not limit the order of the steps. In different embodiments of the present invention, the order of the steps can be adjusted according to the adjustment of the process.

[0095] The following embodiment provides a dual-star self-series main bearing structure. Figure 3 The figure shows a structural schematic diagram of a double-satellite self-series main load-bearing structure applied to a double-satellite. The double-satellite includes a lower satellite and an upper satellite arranged 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 is flush with the upper satellite cabin. Specifically, the lower satellite includes a first top plate 13, a first bottom plate 14, a plurality of first side plates arranged between the first top plate 13 and the first bottom plate 14, a first tank 11, and a tank bracket 19 for supporting the first tank 11. The tank bracket 19 is arranged on the first bottom plate 14. The first top plate 13, the first bottom plate 14 and the plurality of first side plates together form the lower satellite cabin; the upper satellite includes a second top plate 15, a second bottom plate 16, a plurality of second side plates arranged between the second top plate 15 and the second bottom plate 16, and a second tank 12. One end of the second tank 12 is threadedly connected to the second bottom plate 16, and the other end is threadedly connected to the first flange 17. The upper satellite cabin is formed between the second top plate 15, the second bottom plate 16 and the plurality of second side plates.

[0096] Figure 4 The schematic diagram of the main bearing structure of the double star self-series connection is shown. It can be seen that the main bearing structure of the double star self-series connection includes:

[0097] The main load-bearing structure of the lower satellite is the load-bearing structure of the lower satellite cabin. The main load-bearing structure of the lower satellite includes a support frame 1 and a plurality of rods 2 arranged on the support frame 1. The rods 2 are arranged at the corners of the lower satellite cabin along the height direction. The rods 2 are hollow cylindrical rods with an outer diameter of 30 mm and an inner diameter of 24 mm. The material of the rods 2 is aluminum alloy 2A14T6. The tank bracket 19 and the support frame 1 are respectively arranged at the top and bottom of the first bottom plate 14; the support frame 1 is arranged at the bottom of the first bottom plate 14. Figure 5 The schematic diagram of the structure of the support frame 1 and the satellite-rocket docking joint 4 is shown. The support frame 1 includes a ring body 101, a cross body 102 arranged inside the ring body 101, and an extension leg 103 arranged outside the ring body 101. The ring body 101, the cross body 102 and the extension leg 103 are screwed 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 ring body 101 to form a central intersection. The first leg The second leg intersects with the annulus 101 to form an end intersection, and the extended leg 103 extends outward along the end intersection to the vertex of the first base plate 14; the support frame 1 is a carbon fiber frame, and the carbon fiber is selected from carbon fiber M55J. The tank bracket 19 is a column bracket, and the column diameter of the tank bracket 19 is the same as the diameter of the annulus 101 to strengthen the support effect on the first 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 The figure shows the structure of the satellite-rocket docking joint 4. There are four satellite-rocket docking joints 4, which are respectively threadedly connected to the ends of the extension legs 103. The bottom of the satellite-rocket docking joint 4 is provided with an explosive bolt mounting hole 402 for connecting the satellite-rocket docking joint 4 to the rocket via bolts. Figure 7 and Figure 8The schematic diagram of the structure of the rod joint 3 is shown. The rod joint 3 is used to connect the intersatellite connection structure 5 and the lower satellite. The rod joint 3 and the satellite-rocket docking joint 4 are respectively arranged at the top and bottom ends of the rod 2. The rod joint 3 is connected to the rod 2 through four M6 screws; the satellite-rocket docking joint 4 is connected to the rod 2 through M8 screws. The material of the rod joint 3 is forged aluminum 2A14T6. The rod joint 3 includes a rod joint body 1 301, a rod joint body 2 302 and a rod joint body 3 303 connected in sequence. The rod joint 3 is also provided with a weight reduction groove 305. 305 to ensure strength while reducing weight; the first top plate 13 is threadedly connected to the rod joint body 2 302, the first bottom plate 14 is threadedly connected to the star-rocket butt joint 4, the rod 2 and the rod joint 3 and the star-rocket butt joint 4 are clamped and threaded, and the clamping includes: the rod body 201 is also 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 top of the star-rocket butt joint 4 is provided with a first groove 401, the first groove 401 is adapted to the first extension section 204 shaped so that the first extension section 204 is inserted into the first groove body 401; a second groove body 304 is provided at the bottom of the rod joint 3, and the second groove body 304 is adapted to the second extension section 205 so that the second extension section 205 is inserted into the second groove body 304. The first groove body 401 and the second groove body 304 are both rounded to facilitate the insertion of the rod 2, so as to reduce the difficulty of installation. The first extension section 204 and the second extension section 205 are inserted into the rod joint 3 to increase its shear resistance; the first side plate is threadedly connected to the rod 2, and the rod 2 also includes a rod body 201 provided with a The first connector 206 at one end and the second connector 207 at the other end of the rod body 201 are threadedly connected to the satellite-rocket butt joint 4 by four M10 screws to further strengthen the connection between the rod 2 and the satellite-rocket butt joint 4; the second connector 207 is threadedly connected to the rod joint 3 by M6 screws to connect the rod 2 and the rod joint 3. The first side plate and the rod body 201 are threadedly connected by M5 screws and M6 screws. Depending on the actual structural connection strength requirements, the spacing between adjacent bosses is 70-100mm; Figure 9 and Figure 10The schematic diagram of the structure of the rod 2 is shown. The rod 2 includes a rod body 201 and a boss provided on the rod body 201. The boss is used to connect the rod 2 and the first side plate (honeycomb plate). The boss is arranged at intervals along the axial direction of the rod body 201. The boss includes a first boss 202 and a second boss 203. The first side plate is threadedly connected to the first boss 202. The first boss 202 is a triangular boss. The triangular boss includes a boss 1 2021, a boss 2022 and a boss 3 2023 connected in sequence. The boss 1 2021 and the boss 3 2023 are perpendicular to each other in space. The boss 1 2021 and the boss 3 2023 are provided with a first side plate mounting hole 2024. When installed: the adjacent first side plates are respectively fitted with the boss 1 202 1 and boss three 2023, use screws to penetrate the first side panel mounting holes 2024 to form a lower satellite cabin body surrounded by each first side panel; the second boss 203 is an arc-shaped boss, and the first boss 202 and the second boss 203 are circumferentially surrounded along the outer wall of the rod body 201; a plurality of first angle pieces 9 are further provided between the first top plate 13 and the rod joint 3, and the first angle piece 9 is an L-shaped angle piece. The first angle piece 9 is provided at the corner of the first top plate 13, and the first top plate 13 is threadedly connected to the rod joint body 2 302 through the first angle piece 9. When connected: one plate of the first angle piece 9 is threadedly connected to the rod joint 3 through the M4 screw, and the other plate is threadedly connected to the first top plate 13, so as to facilitate the first top plate 13 to ensure the load-bearing structure accuracy during the final assembly process;

[0098] The main load-bearing structure of the satellite is the load-bearing structure of the satellite cabin. Figure 11 The figure shows a schematic diagram of the main load-bearing structure of the upper satellite, which 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 the sinusoidal vibration response, the first flange 17 is made of carbon fiber M55J material with a wall thickness of 15 mm. The first flange 17 provides an installation interface with the second tank 12. The truss 6 is threadedly connected to the first flange 17 to connect the truss 6 and the first tank 11. The second tank 12 is a cylindrical tank. The first flange 17 is a circular flange. The second 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 truss 6 is a carbon fiber truss 6. The carbon fiber is made of carbon fiber M55J to ensure that it has sufficient rigidity. The truss 6 is provided at the corners of the upper satellite cabin along the height direction. Multiple trusses 6 are gathered and arranged to form a gathering place. The first flange 17 is provided at the gathering place. Figure 12 and Figure 13The structural diagram of the truss 6 is shown. The truss 6 includes a truss body 6 and a connecting assembly 605 for connecting the truss body 6. The truss body 6 is a hollow truss body 6 to reduce the weight of the load-bearing structure. The truss body 6 includes a vertical rod 601 and an upper oblique rod 602 and a lower oblique rod 603 provided at both ends of the vertical rod 601. The upper oblique rod 602 and the lower oblique rod 603 are retracted inward along the direction of the gathering to form a third intersection. The intersection of the upper oblique rod 602 and the end point of the vertical rod 601 is the first intersection, and the intersection of the lower oblique rod 603 and the end point of the vertical rod 601 is the second intersection. The truss 6 body also includes a cross bar 604. One end of the cross bar 604 is provided at the third intersection. At the intersection, the other end intersects vertically with the vertical rod 601 to form a fourth intersection; the connecting component 605 is a carbon fiber connecting component 605, and the truss 6 is formed by the connecting component 605 using adhesive bonding and / or riveting. The connecting component 605 is a multi-pass hollow connecting component 605, and the connecting component 605 includes a connecting component 605 body and a cavity provided in the connecting component 605 body. The cavity is conformable to the truss 6 body so that the vertical rod 601, the upper oblique rod 602, the lower oblique rod 603 and the cross rod 604 are passed through the cavity of the corresponding connecting component 605 body to form the truss 6; specifically, the connecting component 605 includes a connecting piece 6051 ( Figure 14 ), Connector 2 6052 ( Figure 15 ), connector three 6053 ( Figure 16 ) and connector four ( Figure 17), the first connector 6051, the second connector 6052, the third connector 6053 and the fourth connector are respectively arranged at the first intersection, the second intersection, the third intersection and the fourth intersection, the first connector 6051 includes a first connector body 6051-1, a first connecting piece 6051-2 provided on the first connector body 6051-1 and a plurality of cavities provided in the first connector body 6051-1, the second connector 6052 includes a second connector body 6052-1, a second connecting piece 6052-2 provided on the second connector body 6052-1 and a plurality of cavities provided in the second connector body 6052-1, the third connector 6053 includes a connector The third connector body 6053-1 and multiple cavities provided in the third connector body 6053-1, the fourth connector includes a fourth connector body 6054-1 and multiple cavities provided in the fourth connector body 6054-1, the first connector 6051 and the third connector 6053 are provided at both ends of the vertical rod 601, and the second top plate 15 and the second bottom plate 16 are respectively threadedly connected to the second connecting piece 6052-2 and the first connecting piece 6051-2; the wall thickness of the first connector body 6051-1, the second connector body 6052-1, the third connector body 6053-1 and the fourth connector body 6054-1 is 2 mm, and the first connecting piece 6051-2 The stress concentration places are at the first connecting piece 6051-2 and 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 oblique bar 602 and the lower oblique bar 603 are square and 40mm in size. In order 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 connected to the first bent plate. The first bent plate includes a plate 1 6011, a plate 2 6012 and a plate 3 6013 connected in sequence. The plate A second side panel mounting hole 1 6014 is provided on the first plate 6011 and the third plate 6013. The first plate 6011 and the third plate 6013 are spatially perpendicular to each other so that adjacent second side edges installed on the same vertical rod 601 are perpendicular to each other. An embedded part 7 is also provided in the vertical rod 601. The second side panel and the vertical rod 601 are threadedly connected via the embedded part 7. The embedded part 7 is arranged axially along the vertical rod 601 and conforms to the vertical rod 601. The embedded part 7 includes an embedded part body 701 and a second side panel mounting hole 2 provided on the embedded part body 701. The second side panel mounting hole 2 provides a threaded interface. The second side panel mounting hole 1 6014 corresponds to the second side panel mounting hole 2.The outer wall of the vertical rod 601 is also equipped with a gasket 8 to ensure the shape and position accuracy of the mounting surface, facilitating final assembly and ensuring the installation accuracy of the entire satellite. Gasket 8 is installed on plate 1 6011 and plate 3 6013. Gasket 8 is provided with second side panel mounting hole 3, which corresponds to second side panel mounting hole 1 6014 and second side panel mounting hole 2. When installing the second side panel, gasket 8 is located between the second side panel and the vertical rod 601. During installation, screws are sequentially inserted through second side panel mounting hole 3, second side panel mounting hole 1 6014, and second side panel mounting hole 2. Figure 18 A schematic diagram of the installation structure of the first flange 17 and the truss 6 is shown. A plurality of second angle pieces 10 are provided between the first flange 17 and the truss 6. The second angle pieces 10 are L-shaped angle pieces and are used to increase the connection area between the truss 6 and the second storage tank 12. The second angle pieces 10 are screwed to both sides of the truss 6 and are 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 angle piece 10 is screwed to the truss 6, and the other plate is screwed to the first flange 17.

[0099] The intersatellite connection structure 5 is used to connect the lower satellite main load-bearing structure and the upper satellite main load-bearing structure. The intersatellite connection structure 5 is provided between the lower satellite main load-bearing structure and the upper satellite main load-bearing structure to form a dual-satellite self-series main load-bearing structure. Specifically, the intersatellite connection structure 5 is provided between the first top plate 13 and the second top plate 15 to connect the lower satellite cabin body and the upper satellite cabin body; Figure 19 shows a front view of the intersatellite connection structure 5, Figure 20 shows a top view of the intersatellite connection structure 5, Figure 21 A bottom view of the intersatellite connection structure 5 is shown, which includes an adapter ring 501, a base 502 provided at the bottom of the adapter ring 501, and bolts for connecting the adapter ring 501 and the base 502. The adapter ring 501 is connected to the second top plate 15, and the base 502 is connected to the rod joint 3; four second through holes 5011 with a diameter of 8.2 mm are opened on the adapter ring 501, and the thickness of the adapter ring 501 at the connection of the second through holes 5011 is 8 mm; four first through holes 5021 with a diameter of 8.5 mm are opened on the base 502, 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-adapter ring 501 to withstand the bending moment load caused by axial tension and compression and shear force, and the adapter ring 501-base 502 conical surface contact withstands 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 evenly distributed.

[0100] Although certain embodiments of the present invention have been described in this application, those skilled in the art will appreciate that these embodiments are provided by way of example only. Numerous variations, alternatives, and modifications will be contemplated by those skilled in the art in light of the teachings of this disclosure without departing from the scope of the present invention. The appended claims are intended to define the scope of the present invention and are intended to encompass methods and structures within the scope of these claims and their equivalents.

Claims

1. A dual-satellite self-series main bearing structure, wherein the dual-satellite comprises a lower satellite and an upper satellite disposed on the lower satellite, wherein the lower satellite comprises a lower satellite cabin, and the upper satellite comprises an upper satellite cabin, wherein the lower satellite cabin is flush with the upper satellite cabin, and wherein: The dual-star self-series main bearing structure includes: The lower satellite main load-bearing structure is the load-bearing structure of the lower satellite cabin body. 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 body along the height direction. The upper satellite main load-bearing structure is the load-bearing structure of the upper satellite cabin, and the upper satellite main load-bearing structure includes a plurality of trusses and a first flange connected to the plurality of trusses. The trusses are arranged at the corners of the upper satellite cabin along the height direction. The plurality of trusses are gathered and arranged to form a gathering point, and the first flange is provided at the gathering point; and The 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 arranged between the lower satellite main load-bearing structure and the upper satellite main load-bearing structure to form a double-satellite self-series main load-bearing structure.

2. The double star self-series main bearing structure according to claim 1 is characterized in that: The lower satellite includes a first top plate, a first bottom plate, and a plurality of first side plates arranged between the first top plate and the first bottom plate, and the first top plate, the first bottom plate, and the plurality of first side plates together form the lower satellite cabin; the upper satellite includes a second top plate, a second bottom plate, and a plurality of second side plates arranged between the second top plate and the second bottom plate, and the second top plate, the second bottom plate, and the plurality of second side plates together form the upper satellite cabin; The inter-satellite connection structure is provided between the first top plate and the second top plate to connect the lower satellite cabin body and the upper satellite cabin body.

3. The double star self-series main bearing structure according to claim 2 is characterized in that: The support frame is arranged at the bottom of the first base plate, and the support frame includes a circular body, a cross body arranged inside the circular body, and an extended leg arranged outside the circular body. The cross body includes a first leg and a second leg that cross each other. The first leg and the second leg intersect with the circular body to form an end intersection, and the extended leg extends outward along the end intersection to the vertex of the first base plate.

4. The double star self-series main bearing structure according to claim 2, characterized in that: The lower satellite main bearing structure also includes: a satellite-rocket docking joint, which is used to connect the lower satellite and the rocket, and the satellite-rocket docking joint is provided at the end of the extension leg; and A rod joint, which is used to connect the inter-satellite connection structure and the lower satellite, the rod joint and the satellite-rocket docking joint are respectively provided at both ends of the rod; and / or The intersatellite connection structure is connected to the second top plate and the first top plate respectively, and the rod is clamped with the rod joint and the satellite-rocket docking joint; and / or The rod joint includes a rod joint body 1, a rod joint body 2 and a rod joint body 3 connected in sequence, the first top plate is threadedly connected to the rod joint body 2, the first bottom plate is threadedly connected to the satellite-rocket docking joint, and the first side plate is threadedly connected to the rod.

5. The double star self-series main bearing structure according to claim 2, characterized in that: The rod comprises a rod body and bosses provided on the rod body, the bosses are spaced apart along the axial direction of the rod body, the bosses comprise 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 perpendicular to each other in space, so that adjacent first sides installed on the same rod body are perpendicular to each other; and / or The two ends of the rod body are respectively provided with a first extension section and a second extension section. The top of the satellite-rocket docking joint is provided with a first groove body, and the first groove body is adapted to the first extension section so that the first extension section can be inserted into the first groove body; the bottom of the rod joint is provided with a second groove body, and the second groove body is adapted to the second extension section so that the second extension section can be inserted into the second groove body.

6. The double star self-series main bearing structure according to claim 2, characterized in that: The truss includes a truss body and a connecting assembly for connecting the truss body, the truss body includes a vertical rod and an upper oblique rod and a lower oblique rod provided at both ends of the vertical rod, the upper oblique rod and the lower oblique rod are retracted inwardly along the direction of the retraction point to form a third intersection, the intersection of the upper oblique rod and the end point of the vertical rod is a first intersection, and the intersection of the lower oblique rod and the end point of the vertical rod is a second intersection, the truss body also includes a cross rod, one end of the cross rod is provided at the third intersection, and the other end intersects with the vertical rod at right angles to form a fourth intersection; and / or The connecting assembly is a multi-pass hollow connecting assembly, comprising a connecting assembly body and a cavity provided in the connecting assembly body, wherein the cavity is shaped to conform to the truss body so that the vertical rods, upper oblique rods, lower oblique rods and cross rods are passed through the cavities of the corresponding connecting assembly bodies to form the truss; and / or The second top plate and the second bottom plate are threadedly connected to both ends of the vertical rod, and the second side plate is threadedly connected to the vertical rod.

7. The double star self-series main bearing structure according to claim 6, characterized in that: The truss body is a hollow truss body, the vertical rod includes a vertical rod body, the cross-section of the vertical rod body is a polygon, and at least two sides of the polygon are perpendicular to each other or perpendicular to each other in space, so that adjacent second sides installed on the same vertical rod body are perpendicular to each other; and / or The connecting component includes connecting member 1, connecting member 2, connecting member 3 and connecting member 4, and the connecting member 1, connecting member 2, connecting member 3 and connecting member 4 are respectively arranged at the first intersection, the second intersection, the third intersection and the fourth intersection. The connecting member 1 includes a connecting member 1 body and a first connecting piece arranged on the connecting member 1 body. The connecting member 2 includes a connecting member 2 body and a second connecting piece arranged on the connecting member 2 body. The second top plate and the second bottom plate are respectively threadedly connected to the second connecting piece and the first connecting piece.

8. The double star self-series main bearing structure according to claim 6, characterized in that: An embedded part is further provided in the vertical rod. The embedded part 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 embedded part.

9. The double star self-series main bearing structure according to claim 6, characterized in that: The truss is threadedly connected to the first flange, and a plurality of second angle pieces are provided between the first flange and the truss, wherein the second angle pieces are L-shaped angle pieces and are provided on both sides of the truss. When the truss is connected to the first flange: one plate of the second angle piece is threadedly connected to the truss, and the other plate is threadedly connected to the first flange; and / or The upper star further includes a second storage tank, one end of which is threadedly connected to the second bottom plate, and the other end of which is threadedly connected to the first flange.

10. The double star self-series main bearing structure according to claim 6, characterized in that: The inter-satellite connection structure includes an adapter ring and a base provided 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.

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