Flat plate type satellite configuration

Abstract

The invention relates to the technical field of spaceflight, in particular to a flat plate type satellite configuration. The flat plate type satellite configuration comprises a first mounting plate, a second mounting plate opposite to the first mounting plate and a frame clamped between the first mounting plate and the second mounting plate, and the first mounting plate and the second mounting plate are arranged on the two opposite sides of the frame; the frame comprises a plurality of edge beams connected end to end and a plurality of middle beams detachably fixed to the inner sides of the edge beams, and the interior of the frame is divided into a plurality of containing spaces used for containing satellite single machines through the middle beams. According to the flat plate type satellite configuration, the frame is clamped between the first mounting plate and the second mounting plate, the bearing capacity can be improved, the manufacturing difficulty and cost are reduced through detachable connection of the middle beams and the edge beams, and protection can be provided for the satellite single machine through the containing space.

Description

Technical Field

[0001] The invention relates to the field of aerospace technology, in particular to a flat-plate satellite configuration. Background Art

[0002] The satellite's configuration design is the result of comprehensive consideration of factors such as its main payload characteristics, predetermined orbital requirements, and thermal control needs. Common configurations include rectangular blocks, cylinders, and polygonal prisms.

[0003] Compared with the above-mentioned configuration designs, the flat-panel satellite configuration, with its flat structure, has significant advantages in multi-satellite stacking, batch launch and rapid deployment, and can improve the payload efficiency of the launch vehicle and the speed of constellation deployment.

[0004] However, the main structure of the current flat-panel satellite generally adopts an integrated casting design, which requires a large casting mold, increasing the difficulty and cost of manufacturing. In addition, the main structure has poor adaptability to changes in the shape or interface of the satellite unit. If the satellite unit it carries changes, the main structure of the flat-panel satellite and its dedicated mold need to be redesigned and produced, increasing costs. In addition, the main structure of existing flat-panel satellites mostly adopts an open structure, which has poor overall structural strength and rigidity, poor bearing capacity, and the open structural design cannot provide effective protection for the satellite unit on the star, reducing the service life of the satellite unit. Summary of the invention

[0005] The purpose of the present invention is to provide a flat-panel satellite configuration that can improve the carrying capacity and adaptability, reduce the processing difficulty and cost, and provide protection for a single satellite.

[0006] To achieve the above-mentioned purpose, the present invention proposes a flat-panel satellite configuration, including a first mounting plate, a second mounting plate arranged opposite to the first mounting plate, and a frame clamped between the first mounting plate and the second mounting plate, the first mounting plate and the second mounting plate are arranged on two opposite sides of the frame; the frame includes a plurality of side beams connected end to end, and a plurality of middle beams detachably fixed to the inner sides of the side beams, the plurality of middle beams divide the interior of the frame into a plurality of accommodating spaces for accommodating single satellites.

[0007] Optionally, each side beam and middle beam includes a main body plate, a first connecting plate and a second connecting plate connected to opposite sides of the main body plate, and two third connecting plates respectively connected to opposite ends of the main body plate; the first connecting plate and the second connecting plate are respectively fixedly connected to the first mounting plate and the second mounting plate, the third connecting plates close to each other of every two adjacent side beams are fixedly connected, and the third connecting plate of each middle beam is fixedly connected to the main body plate of the side beam or the main body plate of the middle beam.

[0008] Optionally, the side beam includes a first side beam, a second side beam, and a third side beam detachably connected between the first side beam and the second side beam, and the third side beam is inclined relative to the first side beam.

[0009] Optionally, the third side beam further includes a fourth connecting plate, the third connecting plate of the third side beam is fixedly connected to the main body plate of the third side beam through the fourth connecting plate, and is tilted relative to the main body plate. A reinforcing rib is provided between the third connecting plate and the fourth connecting plate of the third side beam.

[0010] Optionally, the frame is provided with a plurality of reinforcing blocks, each of which is provided with a connection hole for cooperating with a fastener. A reinforcing rib is provided on the main plate of the frame, and opposite ends of the reinforcing rib are respectively connected to the first connecting plate and the second connecting plate through the reinforcing blocks.

[0011] Optionally, the middle beam includes staggered cross beams and longitudinal beams, the number of each of the cross beams and longitudinal beams is at least two, at least two cross beams are spaced apart along the width direction of the satellite configuration, and at least two longitudinal beams are spaced apart along the length direction of the satellite configuration.

[0012] Optionally, a plurality of weight-reducing holes are provided on the main body plate of the middle beam.

[0013] The flat-panel satellite configuration of the present invention further comprises a plurality of scraping pads, which are respectively arranged in the regions corresponding to the connecting holes between the frame and the first mounting plate and the second mounting plate.

[0014] The technical solution of the present invention has the following beneficial effects compared with the prior art: the flat-panel satellite configuration of the present invention is clamped between the first mounting plate and the second mounting plate through a frame, which can improve the load-bearing capacity, and is detachably connected to the side beams through the middle beam, thereby reducing the manufacturing difficulty and cost, and can provide protection for the satellite through the accommodating space. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for use in the embodiments will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present invention and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without paying creative work.

[0016] Figure 1 It is a structural schematic diagram of the flat-panel satellite configuration of the present invention.

[0017] Figure 2 It is an exploded view of the flat-panel satellite configuration of the present invention.

[0018] Figure 3 It is a partial cross-sectional schematic diagram of the first mounting plate in the present invention.

[0019] Figure 4 It is a schematic diagram of the assembly structure of the frame in the present invention.

[0020] Figure 5 It is a schematic diagram of the decomposed structure of the framework in the present invention.

[0021] Figure 6 It is a schematic diagram of the structure of a beam in an example of the present invention.

[0022] Figure 7 It is a cross-sectional schematic diagram of an intermediate beam in an example of the present invention.

[0023] Figure 8 It is a cross-sectional schematic diagram of an intermediate beam in another example of the present invention.

[0024] Fig. 9 Schematic diagram of the structure of the third side beam in an example of the present invention.

[0025] Fig.10 It is a schematic structural diagram of the third side beam in another example of the present invention.

[0026] Fig.11 It is a cross-sectional schematic diagram of the third side beam of the present invention.

[0027] Fig.12 It is a partial cross-sectional schematic diagram of a flat-panel satellite configuration in an example of the present invention.

[0028] Fig.13 It is a cross-sectional schematic diagram of an intermediate beam in an example of the present invention.

[0029] In the figure: 1-frame; 11-main body plate; 12-first connecting plate; 13-second connecting plate; 14-third connecting plate; 15-reinforcement block; 151-connection hole; 21-side beam; 211-first side beam; 212-second side beam; 213-third side beam; 213a-fourth connecting plate; 213b-reinforcement rib; 22-middle beam; 221-cross beam; 222-longitudinal beam; 223-second through hole; 224-weight-reducing hole; 23-strengthening rib; 3-Installation plate assembly; 31-first mounting plate; 311-first mounting surface; 312-second mounting surface; 313-first through hole; 32- second mounting plate; 4-scraping pad; 41-third through hole; 5- Fasteners. DETAILED DESCRIPTION

[0030] The specific embodiments of the present invention will be described in detail below in conjunction with the accompanying drawings. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all of the embodiments. Based on the description of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0031] The orientation or position relationship indicated by the terms "upper", "lower", "top", "bottom", "inside", "outside", etc. is based on the orientation or position relationship shown in the drawings, or is the orientation or position relationship in which the product of the invention is usually placed when used. It is only for the convenience of description and simplified description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation. Therefore, it should not be understood as a limitation on the present invention.

[0032] The terms "first", "second", etc. are merely used to distinguish elements of similar nature, and do not indicate or imply relative importance or a particular order.

[0033] The terms "comprises," "comprising," or any other variations thereof, are intended to cover a non-exclusive inclusion of elements other than those listed and may also include additional elements not expressly listed.

[0034] See also Figure 1 and Figure 2 The present invention provides a flat-plate satellite configuration. The satellite configuration of the present invention is in the shape of a flat plate as a whole, and the projection along the thickness direction thereof is preferably a polygon such as a quadrilateral, a hexagon or an octagon. Specifically, the flat-plate satellite configuration of the present invention includes a frame 1 and a mounting plate assembly 3, wherein the mounting plate assembly 3 is fixedly connected to the frame 1 by means of fastener connection or the like, and the satellite unit is fixed to the mounting plate assembly 3 by means of fastener connection or the like.

[0035] In some embodiments, the mounting plate assembly 3 includes a first mounting plate 31 and a second mounting plate 32, and the first mounting plate 31 and the second mounting plate 32 are respectively fixedly connected to the opposite sides of the frame 1. Specifically, the first mounting plate 31 and the second mounting plate 32 are respectively connected to the ceiling surface and the ground surface of the frame 1.

[0036] See also Figure 3, the first mounting plate 31 is provided with a first mounting surface 311 and a second mounting surface 312 on opposite sides, respectively, for fixing satellite units inside and outside the flat-panel satellite configuration of the present invention. For example, satellite units with field of view requirements such as antennas, sensors, solar wings, cameras, etc. are fixed to the second mounting surface 312. Among them, the first mounting surface 311 is provided on the side of the first mounting plate 31 close to the frame 1, and the second mounting surface 312 is provided on the side of the first mounting plate 31 away from the frame 1. The satellite units are preferably fixed to the first mounting surface 311 and the second mounting surface 312 respectively by fastener connection or the like.

[0037] The first mounting plate 31 is preferably an aluminum skin aluminum honeycomb core sandwich plate, which can improve strength while reducing weight, and is easy to process and install. It can be understood that the first mounting plate 31 can also be made of a carbon fiber plate or a metal plate of other materials.

[0038] The second mounting plate 32 has substantially the same structure as the first mounting plate 31 , and will not be described in detail herein.

[0039] See also Figure 4 and Figure 5 In some embodiments, the frame 1 includes a plurality of side beams 21 connected end to end and a plurality of middle beams 22 detachably fixed to the inner side of the side beams 21. The middle beams 22 divide the interior of the frame 1 into a plurality of accommodation spaces for accommodating satellite units. The accommodation spaces can provide protection for the satellite units inside the flat-panel satellite configuration and reduce the impact of the space environment on the satellite units. Preferably, the side beams 21 and the middle beams 22 are made of aluminum alloy, which can reduce the weight while ensuring the structural strength of the frame 1 and is easy to process.

[0040] The side beam 21 is preferably detachably connected to the middle beam 22 by fasteners, so as to facilitate the replacement of the side beam 21 or the middle beam 22, thereby adapting to different installation requirements, improving adaptability, facilitating maintenance, and reducing production difficulty and production cost compared to the integrated frame structure. It can be understood that the side beam 21 and the middle beam 22 can also be integrally formed, or fixedly connected by riveting, welding, etc.

[0041] In one example, the projection of the satellite configuration along its thickness direction is an octagon, and the side beam 21 includes a first side beam 211, a second side beam 212, and a third side beam 213 connected between the first side beam 211 and the second side beam 212. Specifically, the number of the first side beam 211 and the second side beam 212 is two, the number of the third side beam 213 is four, the two first side beams 211 are arranged oppositely and extend along the length direction of the satellite configuration, and the two second side beams 212 are arranged oppositely and extend along the width direction of the satellite configuration. The first side beam 211, the second side beam 212 and the third side beam 213 are connected end to end. Specifically, the opposite ends of the third side beam 213 are detachably connected to the ends of the first side beam 211 and the second side beam 212 close to each other, and the third side beam 213 is inclined relative to the first side beam 211. Optionally, the angle between the length direction of the third side beam 213 and the length direction of the first side beam 211 is 100°~170°. In one example, the angle between the length direction of the third side beam 213 and the first side beam 211 is 120° or 135°.

[0042] The middle beam 22 includes a cross beam 221 and a longitudinal beam 222, which are staggered and detachably connected to each other. Preferably, the cross beam 221 and the longitudinal beam 222 are perpendicular to each other, and the cross beam 221 is substantially parallel to the first side beam 211, so as to improve the rigidity and the space utilization of the accommodation space. Optionally, the cross beam 221 can also be tilted relative to the first side beam 211. In one example, the number of the cross beams 221 and the longitudinal beams 222 is at least two, at least two cross beams 221 are spaced apart along the width direction of the satellite configuration, and at least two longitudinal beams 222 are spaced apart along the length direction of the satellite configuration, so as to improve the structural strength and rigidity of the satellite configuration.

[0043] In one example, a weight-reducing hole 224 is provided on the middle beam 22, and the weight and cost can be reduced through the weight-reducing hole 224. In addition, the weight-reducing hole 224 is also used for cables to pass through. In one example, the middle beam 22 is provided with a plurality of weight-reducing holes 224 along its length direction, and the weight-reducing holes 224 are preferably waist-shaped holes, so as to allow the cables to have a certain range of movement in the weight-reducing holes 224, which is convenient for installation.

[0044] See also Figure 6 and Figure 7In some embodiments, the cross section of each side beam 21 and the middle beam 22 is in the shape of an "I". The cross section in this embodiment refers to the cross section of the side beam 21 or the middle beam 22 along the height direction of the frame 1 (i.e., the thickness direction of the satellite configuration), which can improve the bending resistance of the frame 1, prevent deformation, increase rigidity and stability, and facilitate installation. In addition, compared with rectangular or circular cross sections, the "I"-shaped cross section can reduce weight and reduce costs while ensuring the same mechanical properties. It can be understood that the cross section of each side beam 21 and the middle beam 22 of the present invention can also be in a "U" shape or other shapes.

[0045] Please combine Figure 6 Specifically, each side beam 21 and middle beam 22 includes a main body plate 11, a first connecting plate 12 and a second connecting plate 13. The first connecting plate 12 and the second connecting plate 13 are integrally connected to opposite sides of the main body plate 11 along its height direction, and are respectively fixedly connected to the first mounting plate 31 and the second mounting plate 32. The first connecting plate 12 and the second connecting plate 13 can provide a mounting surface that meets the mounting accuracy requirements for the mounting plate assembly 3. Preferably, the first connecting plate 12 and the second connecting plate 13 are parallel to each other and are both perpendicular to the main body plate 11.

[0046] Each side beam 21 and the middle beam 22 further includes a third connecting plate 14, and the third connecting plates 14 close to each other of every two adjacent side beams 21 are fixedly connected. Specifically, the number of the third connecting plates 14 is two, and the two third connecting plates 14 are respectively integrally connected to the opposite ends of each side beam 21 along the length direction thereof, and the first connecting plate 12, the second connecting plate 13 and the two third connecting plates 14 enclose a rectangular frame, and the main body plate 11 is integrally connected to the inner side of the rectangular frame.

[0047] See also Figure 8 and Fig. 9 In one example, each side beam 21 and the middle beam 22 is provided with a fastener 5 (see Fig.12 ) passes through a plurality of connection holes 151. Optionally, the inner surface of the connection hole 151 is provided with an internal thread for threaded connection with the fastener 5.

[0048] Specifically, the first connecting plate 12 and the second connecting plate 13 are respectively provided with a plurality of connecting holes 151 along the length direction of each side beam 21. Fig.12 As shown, in this example, the first mounting plate 31 and the second mounting plate 32 respectively define a plurality of first through holes 313 that cooperate with the connecting holes 151, and the fasteners 5 sequentially pass through the first through holes 313 and the connecting holes 151 from the outside of the flat-panel satellite configuration, respectively fixing the first mounting plate 31 and the second mounting plate 32 to the opposite sides of each side beam 21 along its height direction.

[0049] Furthermore, the main plate 11 is also provided with a connection hole 151, and the third connection plate 14 of the middle beam 22 is provided with a second through hole 223 (see Figure 6 ), optionally, the fastener 5 passes through the second through hole 223 and the connecting hole 151 in sequence to fix the middle beam 22 to the side beam 21.

[0050] Optionally, each side beam 21 and middle beam 22 is provided with a plurality of reinforcing blocks 15, and the plurality of reinforcing blocks 15 are respectively arranged around the connecting holes 151 on the main plate 11 of each side beam 21 and middle beam 22 to improve the structural strength of the connecting area, thereby improving the connection reliability.

[0051] See also Fig. 9 and Fig.10 The third side beam 213 is further provided with a fourth connecting plate 213a, which is integrally connected between the main body plate 11 and the third connecting plate 14 of the third side beam 213, and is used to change the angle of the third connecting plate 14 relative to the main body plate 11. Since the third side beam 213 is tilted relative to the first side beam 211, compared with the third connecting plate 14 tilted at the end of the main body plate 11, the third connecting plate 14 is substantially perpendicular to the fourth connecting plate 213a, and is connected to the main body plate 11 through the fourth connecting plate 213a, which can improve the structural strength of the connection area. Optionally, a reinforcing rib 213b is provided between the third connecting plate 14 and the fourth connecting plate 213a to further improve the structural strength. The number of the reinforcing ribs 213b can be one or more. In one example, at least two reinforcing ribs 213b are arranged at intervals along the height direction of the third side beam 213.

[0052] See also Fig.10 and Fig.11 Optionally, a reinforcing rib 23 is provided on the main plate 11 of the frame 1, and the opposite ends of the reinforcing rib 23 are respectively connected to the first connecting plate 12 and the second connecting plate 13 through the reinforcing block 15, so that the structural strength of the connecting area is further improved by the reinforcing rib 23.

[0053] In one example, the reinforcing rib 23 is arranged on the side of the third side beam 213 away from the accommodating space, and a reinforcing block 15 is integrally connected between the reinforcing rib 23 and the first connecting plate 12 and the second connecting plate 13. In this example, the connecting hole 151 opened on the reinforcing block 15 is used to cooperate with the fastener 5 to fix the satellite unit to the outside of the frame 1.

[0054] See also Fig.12 and Fig.13In some embodiments, the satellite configuration of the present invention further includes a scraping pad 4, which is sandwiched between the mounting plate assembly 3 and the frame 1 in the area corresponding to the connection hole 151, and the scraping pad 4 is provided with a third through hole 41 for the fastener 5 to pass through. Specifically, the mounting plate assembly 3 and the frame 1 are provided with scraping pads 4 on their surfaces close to each other, and the mounting plate assembly 3 is abutted against the frame 1 through the scraping pads 4. By milling the scraping pads 4, the flatness and flatness of the mounting surface can be ensured, the processing procedures can be simplified, and the production efficiency can be improved. In addition, the scraping pads 4 can be used to appropriately adjust the assembly gap, reduce the difficulty of installation, and improve the connection reliability.

[0055] The flat-panel satellite configuration of the present invention sandwiches the frame 1 between the mounting plate assemblies 3, and the frame 1 uses an "I"-shaped cross-section, which can improve the overall stiffness and strength, prevent the satellite configuration from bending and deformation, and is beneficial to enhancing the ability of the flat-panel satellite configuration to resist deformation, thereby improving the structural precision control, and improving the load-bearing capacity, ensuring structural reliability; the frame 1 is detachably connected by a plurality of side beams 21 and a plurality of middle beams 22, which can reduce the manufacturing difficulty and production cost, improve adaptability, and facilitate installation and maintenance; through the accommodating space, protection can be provided for the satellite unit inside the satellite configuration; in addition, the first mounting plate 31 and the second mounting plate 32 are both made of honeycomb core sandwich panels, which ensure strength while helping to reduce weight and improve the thermal conductivity of the satellite configuration.

[0056] The above description is only a specific implementation mode of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily conceived by a technician familiar with the technical field within the technical scope disclosed by the present invention should be covered within the protection scope of the present invention.

Claims

1. A flat-panel satellite configuration, characterized in that: The invention comprises a first mounting plate (31), a second mounting plate (32) arranged opposite to the first mounting plate (31), and a frame (1) sandwiched between the first mounting plate (31) and the second mounting plate (32), wherein the first mounting plate (31) and the second mounting plate (32) are arranged on two opposite sides of the frame (1); the frame (1) comprises a plurality of side beams (21) connected end to end, and a plurality of middle beams (22) detachably fixed to the inner sides of the side beams (21), wherein the plurality of middle beams (22) divide the interior of the frame (1) into a plurality of accommodating spaces for accommodating satellite units.

2. The flat-panel satellite configuration according to claim 1, characterized in that: Each of the side beams (21) and the middle beam (22) comprises a main body plate (11), a first connecting plate (12) and a second connecting plate (13) connected to opposite sides of the main body plate (11), and two third connecting plates (14) respectively connected to opposite ends of the main body plate (11); the first connecting plate (12) and the second connecting plate (13) are respectively fixedly connected to the first mounting plate (31) and the second mounting plate (32), the third connecting plates (14) close to each other of every two adjacent side beams (21) are fixedly connected, and the third connecting plate (14) of each middle beam (22) is fixedly connected to the main body plate (11) of the side beam (21) or the main body plate (11) of the middle beam (22).

3. The flat-panel satellite configuration according to claim 2, characterized in that: The side beam (21) comprises a first side beam (211), a second side beam (212), and a third side beam (213) detachably connected between the first side beam (211) and the second side beam (212), wherein the third side beam (213) is arranged obliquely relative to the first side beam (211).

4. The flat-panel satellite configuration according to claim 3, characterized in that: The third side beam (213) further comprises a fourth connecting plate (213a), and the third connecting plate (14) of the third side beam (213) is fixedly connected to the main body plate (11) of the third side beam (213) via the fourth connecting plate (213a), and is arranged to be inclined relative to the main body plate (11).

5. The flat-panel satellite configuration according to claim 4, characterized in that: A reinforcing rib (213b) is provided between the third connecting plate (14) and the fourth connecting plate (213a) of the third side beam (213).

6. The flat-panel satellite configuration according to claim 1, characterized in that: The frame (1) is provided with a plurality of reinforcement blocks (15), and each reinforcement block (15) is provided with a connection hole (151) for cooperating with a fastener (5).

7. The flat-panel satellite configuration according to claim 2, characterized in that: A reinforcing rib (23) is provided on the main body plate (11) of the frame (1), and opposite ends of the reinforcing rib (23) are respectively connected to the first connecting plate (12) and the second connecting plate (13) via the reinforcing block (15).

8. The flat-panel satellite configuration according to claim 2, characterized in that: The intermediate beam (22) comprises cross beams (221) and longitudinal beams (222) arranged in a staggered manner, the number of the cross beams (221) and the number of the longitudinal beams (222) are at least two, at least two of the cross beams (221) are arranged at intervals along the width direction of the satellite configuration, and at least two of the longitudinal beams (222) are arranged at intervals along the length direction of the satellite configuration.

9. The flat-panel satellite configuration according to claim 3, characterized in that: A plurality of weight-reducing holes (224) are provided on the main body plate (11) of the middle beam (22).

10. The flat-panel satellite configuration according to claim 6, characterized in that: It also comprises a plurality of scraping pads (4), wherein the plurality of scraping pads (4) are respectively clamped between the frame (1) and the first mounting plate (31) and the second mounting plate (32) in an area corresponding to the connection hole (151).

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