An integrated configuration of a remote sensing payload and a satellite

Abstract

The present invention relates to an integrated configuration of a remote sensing payload and a satellite, comprising a satellite body and a camera payload. The satellite body includes a top plate, a middle plate, and a bottom plate, which are arranged in parallel at intervals in sequence. The top plate and the middle plate are fixedly connected by an upper frame, and the middle plate and the bottom plate are fixedly connected by a lower frame. A first through hole is provided at the center of the top plate, a second through hole is provided at the center of the middle plate, and a third through hole is provided at the center of the bottom plate. An inner cylinder is provided at the central position of the axial direction of the satellite body. The inner cylinder is a hollow structure with both ends open. The upper end of the inner cylinder is fixed on the top plate of the satellite body and communicates with the first through hole, and the lower end of the inner cylinder is fixed on the middle plate of the satellite body and communicates with the second through hole. The lower end of the camera payload is fixedly supported on the bottom plate, and the camera payload is located inside the first through hole, the second through hole, the third through hole, and the inner cylinder.

Description

Technical Field

[0001] The present invention relates to the technical field of earth observation optical payloads, and particularly relates to an integrated configuration of a remote sensing payload and a satellite. Background Art

[0002] An earth observation optical payload needs to be installed on the side of the satellite facing the ground. Moreover, as the observation accuracy becomes higher and higher, the scale of the payload becomes larger, the weight becomes heavier, posing higher adaptability requirements for the existing small satellite configurations. An optical remote sensing small satellite generally needs to be equipped with a high-resolution camera, and the overall volume and weight of the satellite are relatively large. Currently, for common small satellite platforms, the remote sensing camera and the satellite platform are generally designed independently, and decoupled designs are carried out in terms of mechanical installation and thermal control. The advantage is that they are independent of each other and do not interfere with each other, while the disadvantage is that there is redundant design in the structure, and the overall weight and envelope size of the satellite platform are relatively large. Another approach is to design the satellite platform and the remote sensing camera completely integrally. The advantage of this method is that it can maximize the utilization rate of space and reduce the launch weight. Its disadvantages are that the design requirements are too high, the design difficulty is large, the cycle is long, and the risk is relatively high. Summary of the Invention

[0003] In order to solve one or several of the above technical problems, the present invention provides an integrated configuration of a remote sensing payload and a satellite.

[0004] The technical solution of the present invention for solving the above technical problems is as follows: An integrated configuration of a remote sensing payload and a satellite, including a satellite body and a camera payload. The satellite body includes a top plate, a middle plate, and a bottom plate. The top plate, the middle plate, and the bottom plate are arranged in parallel at intervals in sequence. The top plate and the middle plate are fixedly connected by an upper frame, and the middle plate and the bottom plate are fixedly connected by a lower frame. A first through hole is opened at the central position of the top plate, a second through hole is opened at the central position of the middle plate, and a third through hole is opened at the central position of the bottom plate.

[0005] An inner cylinder is provided at the central position of the axial direction of the satellite body. The inner cylinder is a hollow structure with both ends open. The upper end of the inner cylinder is fixed on the top plate of the satellite body and communicates with the first through hole, and the lower end of the inner cylinder is fixed on the middle plate of the satellite body and communicates with the second through hole. The lower end of the camera payload is fixedly supported on the bottom plate, and the camera payload is located inside the first through hole, the second through hole, the third through hole, and the inner cylinder.

[0006] The beneficial effects of the present invention are as follows: The integrated configuration applicable to remote sensing small satellites of the present invention can, on the one hand, avoid the disadvantages of a completely decoupled design, improve space utilization rate and reduce weight. On the other hand, it can also avoid the risk of too high difficulty in a completely integrated design, and is a relatively compromise configuration scheme. The present invention also realizes the deformation decoupling and integrated configuration of the satellite platform and the camera payload by sharing the secondary mirror barrel of the camera payload with the load-bearing barrel (i.e., the inner barrel) of the satellite platform, and no separate secondary mirror barrel is provided for the camera payload, and the load-bearing barrel on the satellite platform undertakes the function of the secondary mirror barrel, with a compact and reliable structure.

[0007] Based on the above technical solutions, the present invention can be further improved as follows.

[0008] Further, an outer barrel is also provided above the central position in the axial direction of the satellite body. The outer barrel is a hollow structure with both ends open, and the lower end of the outer barrel is fixed on the top plate of the satellite body and communicates with the first through hole.

[0009] The beneficial effect of adopting the above further scheme is that the outer barrel can play a role in shielding light for the camera payload inside the inner barrel.

[0010] Further, the outer barrel is threadedly connected in the first through hole.

[0011] The beneficial effect of adopting the above further scheme is that it is convenient to install and fix the outer barrel.

[0012] Further, a satellite docking ring is also fixed below the central position of the bottom plate.

[0013] The beneficial effect of adopting the above further scheme is that the bottom plate of the satellite body is directly connected to the satellite docking ring, and the bottom plate is also directly connected to the camera payload. In this way, the satellite body is directly docked with the rocket through the satellite docking ring, and the vibration environment of the rocket on the satellite body is the vibration environment of the camera payload. The satellite body basically does not amplify the vibration. This embedded installation method of the camera payload effectively reduces the vibration input level of the camera payload.

[0014] Further, the camera payload includes a main load-bearing back plate. Below the periphery of the main load-bearing back plate, a plurality of support rods are provided. The support rods are fixedly supported on the bottom plate. Above the periphery of the main load-bearing back plate, a secondary mirror bracket for installing the secondary mirror is provided, and the secondary mirror bracket is located inside the inner barrel.

[0015] Further, the support rods include three groups of bipod support rods.

[0016] The beneficial effect of adopting the above further scheme is that the deformation decoupling between the camera payload and the satellite platform can be realized through the bipod support rods.

[0017] Further, the top plate, the middle plate and the bottom plate all adopt a regular hexagon structure. Six box plates are respectively arranged on the outer peripheral sides of the top plate, the middle plate and the bottom plate. Each box plate connects three corresponding sides of the top plate, the middle plate and the bottom plate; the box plates adopt aluminum honeycomb plates.

[0018] The beneficial effect of adopting the above further scheme is that the whole satellite body configuration is a regular hexagon configuration, which has high structural stability, high volume utilization rate and small overall moment of inertia.

[0019] Further, there are six upper frames. A vertically arranged upper frame is fixed at each corresponding corner of the top plate and the middle plate. The six upper frames are all arranged along the radial direction of the top plate and the middle plate.

[0020] The beneficial effect of adopting the above further scheme is that upper frames are arranged at each corner of the top plate and the middle plate, which can effectively and stably support the top plate and the middle plate.

[0021] Further, there are six lower frames. A vertically arranged lower frame is fixed at each corresponding corner of the middle plate and the bottom plate. The six lower frames are all arranged along the radial direction of the bottom plate and the middle plate.

[0022] The beneficial effect of adopting the above further scheme is that lower frames are arranged at each corner of the bottom plate and the middle plate, which can effectively and stably support the bottom plate and the middle plate.

[0023] Further, the upper frames and the lower frames all adopt square frames. A support beam is arranged at the middle diagonal of the square frame; the upper frames and the lower frames all adopt carbon fiber materials.

[0024] The beneficial effect of adopting the above further scheme is that the upper frames and the lower frames made of carbon fiber materials and with support beams arranged at the middle diagonals of the square frames are beneficial to the stable and reliable support structure of the upper and lower frames. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] Figure 1 It is a schematic internal structure diagram of the satellite body of the present invention;

[0026] Figure 2 It is a three-dimensional structure diagram of the camera payload of the present invention;

[0027] Figure 3 It is a three-dimensional internal structure diagram of the assembly of the satellite body and the camera payload of the present invention;

[0028] Figure 4 It is a schematic front view internal structure diagram of the assembly of the satellite body and the camera payload of the present invention;

[0029] Figure 5This is a schematic external three-dimensional structure diagram of the assembly of the satellite body and the camera payload of the present invention.

[0030] In the attached drawings, the list of components represented by each reference numeral is as follows:

[0031] 1. Satellite body; 11. Top plate; 12. Middle plate; 13. Bottom plate; 14. Upper frame; 15. Lower frame; 16. First through hole; 17. Third through hole; 18. Inner cylinder; 19. Outer cylinder; 190. Support beam;

[0032] 2. Camera payload; 21. Main load-bearing backplane; 22. Support rod; 23. Secondary mirror bracket; 24. Optical payload; 3. Solar panel; 4. Box plate; 5. Satellite docking ring. Specific embodiments

[0033] The principles and features of the present invention will be described below with reference to the attached drawings. The examples given are only used to explain the present invention and are not intended to limit the scope of the present invention.

[0034] As Figures 1 to 5 shown, an integrated configuration of a remote sensing payload and a satellite in this embodiment includes a satellite body 1 and a camera payload 2. The satellite body 1 includes a top plate 11, a middle plate 12, and a bottom plate 13. The top plate 11, the middle plate 12, and the bottom plate 13 are arranged in parallel at intervals in sequence. The top plate 11 and the middle plate 12 are fixedly connected by an upper frame 14, and the middle plate 12 and the bottom plate 13 are fixedly connected by a lower frame 15. A first through hole 16 is provided at the center position of the top plate 11, a second through hole is provided at the center position of the middle plate 12, and a third through hole 17 is provided at the center position of the bottom plate 13;

[0035] An inner cylinder 18 is provided at the central position of the axial direction of the satellite body 1. The inner cylinder 18 is a hollow structure with both ends open. The upper end of the inner cylinder 18 is fixed on the top plate 11 of the satellite body 1 and communicates with the first through hole 16, and the lower end of the inner cylinder 18 is fixed on the middle plate 12 of the satellite body 1 and communicates with the second through hole. The lower end of the camera payload 2 is fixedly supported on the bottom plate 13, and the camera payload 2 is located inside the first through hole 16, the second through hole, the third through hole 17, and the inner cylinder 18.

[0036] Specifically, the upper end and the lower end of the inner cylinder 18 can be fixedly connected to the lower side surface of the top plate 11 and the upper side surface of the middle plate 12 respectively, or the diameter of the inner cylinder 18 can be fixed on the hole walls of the first through hole 16 and the second through hole.

[0037] As Figure 1 、 Figures 3 to 5As shown in the figure, above the central position of the satellite body 1 in the axial direction of the present embodiment, an outer cylinder 19 is further provided. The outer cylinder 19 is a hollow structure with both ends open. The lower end of the outer cylinder 19 is fixed on the top plate 11 of the satellite body 1 and communicates with the first through hole 16. The outer cylinder can play a role in shielding light for the camera payload inside the inner cylinder.

[0038] Among them, the inner diameter of the first through hole 16 of the present embodiment can be the same as the inner diameters of the outer cylinder and the inner cylinder. The inner diameter of the second through hole can also be the same as the inner diameter of the inner cylinder, as long as the camera payload can pass through the second through hole. The inner diameter of the third through hole can be smaller than the inner diameter of the second through hole, which is convenient for reserving a certain space for installing the bottom of the camera payload.

[0039] A preferred solution of the present embodiment is that the outer cylinder 19 is threadedly connected in the first through hole 16, which is convenient for the installation and fixation of the outer cylinder.

[0040] As Figure 4 shown, below the central position of the bottom plate 13 of the present embodiment, a satellite docking ring 5 is further fixed. The bottom plate of the satellite body is directly connected to the satellite docking ring, and the bottom plate is also directly connected to the camera payload. In this way, the satellite body is directly docked with the rocket through the satellite docking ring. The vibration environment of the rocket for the satellite body is the vibration environment of the camera payload. The satellite body basically does not amplify vibration. This embedded installation method of the camera payload effectively reduces the vibration input level of the camera payload.

[0041] As Figure 2 and Figure 4 shown, the camera payload 2 of the present embodiment includes a main load-bearing backplane 21. Below the periphery of the main load-bearing backplane 21, a plurality of support rods 22 are provided. The support rods 22 are fixedly supported on the bottom plate 13. Above the periphery of the main load-bearing backplane 21, a secondary mirror support 23 for installing a secondary mirror is provided. The secondary mirror support 23 is located inside the inner cylinder 18.

[0042] As Figures 2 to 4 shown, the support rod 22 of the present embodiment includes three groups of bipod support rods. Through the bipod support rods, deformation decoupling between the camera payload and the satellite platform can be achieved.

[0043] As Figure 3 and Figure 4 shown, at the bottom of the main load-bearing backplane 21, an optical payload 24 is further fixed. The optical payload 24 is located between the middle plate 12 and the bottom plate 13. The size of the third through hole 17 on the bottom plate 13 should be appropriate so as not to interfere with the optical payload 24. The main load-bearing backplane 21 is located below the middle plate 12, and a certain interval can be reserved between the main load-bearing backplane 21 and the middle plate 12 to avoid interference.

[0044] AsFigure 1 , Figure 3 and Figure 5 As shown in Figure 1 , Figure 3 , and Figure 5 , the top plate 11, middle plate 12, and bottom plate 13 of this embodiment all adopt a regular hexagon structure. Six box plates 4 are respectively arranged on the outer peripheral sides of the top plate 11, middle plate 12, and bottom plate 13. Each box plate 4 connects the three corresponding sides of the top plate 11, middle plate 12, and bottom plate 13; the box plate 4 adopts an aluminum honeycomb panel. The entire satellite body configuration is a regular hexagon configuration, which has high structural stability, high volume utilization rate, and small overall moment of inertia.

[0045] In this embodiment, by setting box plates which adopt a laminated structure, the various subsystems and equipment of the satellite platform are basically installed inside the box body, and the layout is optimized considering factors such as thermal control, mechanics, irradiation, and electromagnetic environment. The skin of the box plate can adopt an aluminum alloy thin plate with a thickness of 0.3 mm, the honeycomb core is an aluminum core, the thickness of the bottom plate and the top plate is 30 mm, the thickness of the middle plate is 20 mm, and the thickness of the box plate is 20 mm. All the installation hole embedded parts are selected as aerospace standard embedded parts, which reduces the structural weight and the design and processing costs. The bottom plate and the middle plate are respectively connected to the inner cylinder, which are key parts for transmitting force loads. In order to ensure the connection reliability, non-standard integral embedded parts are designed for both.

[0046] As Figure 1 , Figure 3 and Figure 4 As shown in Figure 1 , Figure 3 , and Figure 4 , there are six upper frames 14 in this embodiment. A vertically arranged upper frame 14 is fixed at each corresponding corner of the top plate 11 and the middle plate 12. The six upper frames 14 are all arranged along the radial direction of the top plate 11 and the middle plate 12. Setting upper frames at each corner of the top plate and the middle plate can provide effective and stable structural support for the top plate and the middle plate. Among them, in order to make the connection with the inner cylinder 18 more stable and reliable, the upper frame 14 can be abutted against the outer side wall of the inner cylinder 18 and connected and fixed to the inner cylinder through a connecting piece.

[0047] As Figure 1 , Figure 3 and Figure 4 As shown in Figure 1 , Figure 3 , and Figure 4 , there are six lower frames 15 in this embodiment. A vertically arranged lower frame 15 is fixed at each corresponding corner of the middle plate 12 and the bottom plate 13. The six lower frames 15 are all arranged along the radial direction of the bottom plate 13 and the middle plate 12. Setting lower frames at each corner of the bottom plate and the middle plate can provide effective and stable structural support for the bottom plate and the middle plate.

[0048] Further preferably, as Figure 1 , Figure 3 and Figure 4As shown, the upper frame 14 and the lower frame 15 in this embodiment both adopt square frames, and a support beam 190 is provided at the diagonal of the middle of the square frame; both the upper frame 14 and the lower frame 15 adopt carbon fiber materials, preferably M55J with excellent comprehensive performance, which can achieve the lightest weight on the premise of ensuring good structural stiffness and strength. In order to ensure the connection strength, titanium alloy standard embedded parts can be pre-embedded at all connection holes of the upper frame and the lower frame. Using the upper and lower frames made of carbon fiber materials and setting a support beam at the diagonal of the middle of the square frame is beneficial to the stable and reliable support structure of the upper and lower frames.

[0049] As Figures 3 to 5 shown, at one end of the satellite body 1 in this embodiment close to the satellite docking ring 5, a plurality of solar panel wings 3 are also hinged. The solar panel wings 3 in this embodiment can be hinged to the satellite body 1 by using the existing common connection methods, and the connection relationship between the solar panel wings 3 and the satellite body 1 is not shown in the figure.

[0050] The integrated configuration applicable to remote sensing small satellites in this embodiment can, on the one hand, avoid the disadvantages of completely decoupled design, improve space utilization rate and reduce weight, and on the other hand, avoid the risk of too high difficulty in completely integrated design. It is a relatively compromise configuration scheme. The present invention also realizes the deformation decoupling and integrated configuration of the satellite platform and the camera payload by sharing the secondary mirror barrel of the camera payload with the load-bearing barrel (that is, the inner barrel) of the satellite platform, and no separate secondary mirror barrel is set for the camera payload, and the load-bearing barrel on the satellite platform undertakes the function of the secondary mirror barrel, with a compact and reliable structure. The integrated configuration applicable to remote sensing small satellites in this embodiment has a compact satellite configuration, light weight, high space utilization rate, small moment of inertia, and excellent economy and functionality.

[0051] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by the terms "center", "longitudinal", "transverse", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", "axial", "radial", "circumferential", etc. is based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be construed as a limitation to the present invention.

[0052] In addition, the terms "first" and "second" are for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, features defined with "first" and "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0053] In the present invention, unless otherwise clearly defined and limited, terms such as "mounted", "connected", "connected to", "fixed" and the like shall be construed in a broad sense. For example, it may be a fixed connection, a detachable connection, or integrated; it may be a mechanical connection or an electrical connection; it may be directly connected or indirectly connected through an intermediate medium, and it may be the communication inside two elements or the interaction relationship between two elements, unless otherwise clearly limited. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0054] In the present invention, unless otherwise clearly defined and limited, the first feature being "on" or "under" the second feature may be that the first and second features are in direct contact, or the first and second features are in indirect contact through an intermediate medium. Moreover, the first feature being "above", "over" and "on top of" the second feature may be that the first feature is directly above or obliquely above the second feature, or merely indicates that the first feature has a higher horizontal height than the second feature. The first feature being "under", "beneath" and "underneath" the second feature may be that the first feature is directly below or obliquely below the second feature, or merely indicates that the first feature has a lower horizontal height than the second feature.

[0055] In the description of this specification, the description with reference to terms such as "an embodiment", "some embodiments", "example", "specific example", or "some examples" means that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials, or characteristics described may be combined in any one or more embodiments or examples in a suitable manner. In addition, without contradiction, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of different embodiments or examples.

[0056] Although the embodiments of the present invention have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those of ordinary skill in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present invention.

Claims

1. An integrated configuration of a remote sensing payload and a satellite, characterized in that, It includes a satellite body and a camera payload. The satellite body includes a top plate, a middle plate, and a bottom plate. The top plate, the middle plate, and the bottom plate are arranged in parallel at intervals in sequence. The top plate and the middle plate are fixedly connected by an upper frame, and the middle plate and the bottom plate are fixedly connected by a lower frame. A first through hole is provided at the central position of the top plate, a second through hole is provided at the central position of the middle plate, and a third through hole is provided at the central position of the bottom plate. An inner cylinder is provided at the central position along the axis of the satellite body. The inner cylinder is a hollow structure with both ends open. The upper end of the inner cylinder is fixed on the top plate of the satellite body and communicates with the first through hole, and the lower end of the inner cylinder is fixed on the middle plate of the satellite body and communicates with the second through hole. The lower end of the camera payload is fixedly supported on the bottom plate, and the camera payload is located inside the first through hole, the second through hole, the third through hole, and the inner cylinder. A satellite docking ring is also fixed below the central position of the bottom plate. The camera payload includes a main load-bearing backplane. Below the periphery of the main load-bearing backplane, there are multiple support rods. The support rods are fixedly supported on the bottom plate. Above the periphery of the main load-bearing backplane, there is a secondary mirror support for installing a secondary mirror. The secondary mirror support is located inside the inner cylinder. The support rods include three groups of bipod support rods.

2. The integrated configuration of a remote sensing payload and a satellite according to claim 1, wherein, An outer cylinder is also provided above the central position along the axis of the satellite body. The outer cylinder is a hollow structure with both ends open. The lower end of the outer cylinder is fixed on the top plate of the satellite body and communicates with the first through hole.

3. The integrated configuration of a remote sensing payload and a satellite according to claim 2, characterized in that, The outer cylinder is threadedly connected inside the first through hole.

4. The integrated configuration of a remote sensing payload and a satellite according to claim 1, wherein, The top plate, the middle plate, and the bottom plate all adopt a regular hexagon structure. Six box plates are respectively provided on the outer peripheral sides of the top plate, the middle plate, and the bottom plate. Each box plate connects three corresponding sides of the top plate, the middle plate, and the bottom plate. The box plates adopt aluminum honeycomb plates.

5. The integrated configuration of a remote sensing payload and a satellite according to claim 4, characterized in that, There are six upper frames. At each corresponding corner of the top plate and the middle plate, a vertically arranged upper frame is fixed. The six upper frames all extend along the radial direction of the top plate and the middle plate.

6. The integrated configuration of a remote sensing payload and a satellite according to claim 4, characterized in that, There are six lower frames. At each corresponding corner of the middle plate and the bottom plate, a vertically arranged lower frame is fixed. The six lower frames all extend along the radial direction of the bottom plate and the middle plate.

7. The integrated configuration of a remote sensing payload and a satellite according to claim 1, characterized in that, Both the upper frame and the lower frame adopt a square frame. A support beam is provided at the diagonal of the middle part of the square frame. Both the upper frame and the lower frame adopt a carbon fiber material.

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