Platform and load integrated satellite structure suitable for multi-module splicing load

Abstract

The invention relates to a platform and load integrated satellite structure suitable for a multi-module splicing load, and relates to the technical field of spaceflight satellites. The system comprises a satellite structure and an effective load. The satellite structure comprises a butt joint ring, a platform bottom plate, a first platform long partition plate, a second platform long partition plate, a first platform short partition plate, a second platform short partition plate, a third platform short partition plate, a fourth platform short partition plate, a first platform small partition plate, a second platform small partition plate, four platform supporting beams, a load cabin large bottom plate, a load cabin small bottom plate, a first load mounting plate, a second load mounting plate and a third load mounting plate. The load cabin comprises a first load cabin small top plate, a second load cabin small top plate, four first load supporting beams, four second load supporting beams, a first side plate, a second side plate, a third side plate and a fourth side plate. And the effective load comprises five effective load modules I, five effective load modules II and three effective load modules III.

Description

Technical Field

[0001] The present invention relates to the technical field of aerospace satellites, and in particular to a platform and payload integrated satellite structure suitable for multi-module splicing payloads. Background Art

[0002] At present, the commonly used satellite structures in my country generally adopt a compartment design. The satellite structure and payload are designed separately. The payload has an independent main support structure, and then the payload is installed as a whole on the satellite structure, which greatly increases the weight and volume of the payload subsystem.

[0003] Therefore, in the prior art, the problem with space utilization on satellites is that the satellite structure and payload are designed separately, so that the satellite weight and volume cannot meet the requirements of launching multiple satellites with one rocket.

[0004] Based on the above problems, technical personnel in this field urgently need to develop a satellite structure that integrates platform and payload suitable for multi-module splicing payloads. Summary of the invention

[0005] In order to solve the technical problems existing in the above-mentioned prior art, the purpose of the present invention is to provide a satellite structure with an integrated platform and payload suitable for multi-module splicing payloads, which can overcome the problem in the prior art that the satellite structure and the payload are designed separately, resulting in the satellite weight and volume not being able to meet the requirements of launching multiple satellites with one rocket.

[0006] To achieve the above-mentioned purpose of the invention, the present invention provides a platform and payload integrated satellite structure suitable for multi-module splicing payloads, including a satellite structure and a payload;

[0007] The satellite structure includes a docking ring, a platform bottom plate, a platform long partition plate 1, a platform long partition plate 2, a platform short partition plate 1, a platform short partition plate 2, a platform short partition plate 3, a platform short partition plate 4, a platform small partition plate 1, a platform small partition plate 2, four platform support beams, a load cabin large bottom plate, a load cabin small bottom plate, a load installation plate 1, a load installation plate 2, a load installation plate 3, a load cabin small top plate 1, a load cabin small top plate 2, four load support beams 1, four load support beams 2, a side plate 1, a side plate 2, a side plate 3, and a side plate 4;

[0008] The payload includes five payload modules 1, five payload modules 2, and three payload modules 3. The payload module 1 is mounted on the payload mounting plate 1, the payload module 2 is mounted on the payload mounting plate 2, and the payload module 3 is mounted on the payload mounting plate 3.

[0009] Furthermore, the docking ring is connected to the platform long partition 1, the platform long partition 2, the platform short partition 1, the platform short partition 2, the platform short partition 3, and the platform short partition 4 through the platform bottom plate through a corner box, and is connected to the platform small partition 1 and the platform small partition 2 through screws;

[0010] The large bottom plate of the load compartment is connected to the platform long partition 1, the platform long partition 2, the platform short partition 1, the platform short partition 2, the platform small partition 1, and the platform small partition 2 through corner boxes, and the small bottom plate of the load compartment is connected to the platform short partition 3 and the platform short partition 4 through screws.

[0011] Furthermore, the load mounting plate 1 is aligned with the side plate 2 in the vertical direction, the load mounting plate 2 is aligned with the platform long partition 2 in the vertical direction, and the load mounting plate 3 is aligned with the platform long partition 1 in the vertical direction.

[0012] Furthermore, the four platform support beams adopt a right-angle cross-section, the lower ends of the platform support beams are installed at the four corners of the platform bottom plate, the upper ends are respectively connected to the large bottom plate of the load compartment and the small bottom plate of the load compartment, and the sides are respectively connected to the side panel one, the side panel two, the side panel three, and the side panel four.

[0013] Furthermore, the upper parts of the load mounting plate 1, the load mounting plate 2 and the load mounting plate 3 are designed to be arc-shaped.

[0014] Furthermore, the lower parts of the load mounting plate 1, the load mounting plate 2 and the load mounting plate 3 are connected to the large bottom plate of the load compartment through a corner box.

[0015] Furthermore, the lower parts of the load mounting plate 1, the load mounting plate 2, and the load mounting plate 3 are positioned and mounted to the large bottom plate of the load compartment by setting positioning pins.

[0016] Furthermore, the load supporting beam 1 and the load supporting beam 2 have circular cross-sections.

[0017] Furthermore, the platform small partition 1, the platform small partition 2 and the platform long partition 1, the platform long partition 2 and the large load-bearing bottom plate are connected by corner boxes.

[0018] Furthermore, the docking ring, the platform bottom plate, the platform long partition 1, the platform long partition 2, the platform cabin short partition 1, the platform cabin short partition 2, the platform cabin short partition 3, the platform cabin short partition 4, and the four platform support beams are in a state that cannot be disassembled separately after the structural parts are installed.

[0019] Compared with the prior art, the present invention has the following beneficial effects:

[0020] The present invention proposes a satellite structure with integrated platform and payload suitable for multi-module splicing payloads. By proposing an integrated design concept of the platform structure and the payload structure, that is, the main supporting structure of the payload is also the main supporting structure of the satellite, and the platform and payload share the main supporting structure, not only can the overall weight of the satellite be greatly reduced, but also the on-board space can be effectively utilized, the envelope size of the satellite can be reduced, and it becomes possible for a new generation of ocean satellites to achieve the launch of three satellites with one rocket. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0022] Figure 1 A schematic diagram schematically shows a structure of a platform and payload integrated satellite structure suitable for multi-module splicing payloads in one embodiment of the present invention;

[0023] Figure 2 A schematic diagram showing an exploded view of a satellite structure integrating a platform and a payload suitable for a multi-module spliced ​​payload in one embodiment of the present invention;

[0024] Figure 3 A diagram schematically showing the position of the main load-bearing joint in one embodiment of the present invention;

[0025] Figure 4 The figure schematically shows the complete assembly diagram of the satellite structure in one embodiment of the present invention. DETAILED DESCRIPTION

[0026] In order to make the purpose, technical solution and advantages of the embodiments of the present invention clearer, the technical solution in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments 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.

[0027] See also Figures 1 to 4 As shown; this embodiment discloses a platform and payload integrated satellite structure suitable for multi-module splicing payloads, including a satellite structure 1 and a payload 2;

[0028] The satellite structure 1 includes a docking ring 101, a platform bottom plate 102, a platform long bulkhead 103, a platform long bulkhead 2 104, a platform short bulkhead 105, a platform short bulkhead 2 106, a platform short bulkhead 3 107, a platform short bulkhead 4 108, a platform small bulkhead 109, a platform small bulkhead 2 110, four platform support beams 111, a payload cabin large bottom plate 112, a payload cabin small bottom plate 116, a payload mounting plate 1 113, a payload mounting plate 2 114, a payload mounting plate 3 115, a payload cabin small top plate 1 117, a payload cabin small top plate 2 118, four load support beams 1 119, four load support beams 2 120, a side plate 1 121, a side plate 2 122, a side plate 3 123, and a side plate 4 124;

[0029] Payload 2 includes five payload modules 1 201, five payload modules 202, and three payload modules 3 203. Payload module 1 201 is mounted on payload mounting plate 1 113, payload module 2 202 is mounted on payload mounting plate 2 114, and payload module 3 203 is mounted on payload mounting plate 3 115.

[0030] Further, the docking ring 101 is connected to the platform long partition 1 103, the platform long partition 2 104, the platform short partition 1 105, the platform short partition 2 106, the platform short partition 3 107, and the platform short partition 4 108 through the platform bottom plate 102 through a corner box, which is the main load-bearing joint position, and is directly connected to the platform small partition 1 and the platform small partition 2 through screws;

[0031] The large bottom plate 112 of the load compartment is connected to the platform long partition 103, the platform long partition 2 104, the platform short partition 1 105, the platform short partition 2 106, the platform small partition 1 109, and the platform small partition 2 110 through corner boxes, and the small bottom plate 116 of the load compartment is connected to the platform short partition 3 107, and the platform short partition 4 108 through screws.

[0032] Furthermore, the load mounting plate 1 13 is aligned with the side plate 2 122 in the vertical direction, the load mounting plate 2 114 is aligned with the platform long partition 2 104 in the vertical direction, and the load mounting plate 3 115 is aligned with the platform long partition 1 103 in the vertical direction.

[0033] Furthermore, the four platform support beams 111 adopt a right-angled cross-section, the lower end of the platform support beam 111 is installed at the four corners of the platform bottom plate 102, the upper end is respectively connected to the large bottom plate 112 of the load compartment and the small bottom plate 116 of the load compartment, and the side faces are respectively connected to the side panel 1 121, the side panel 2 122, the side panel 3 123, and the side panel 4 124.

[0034] Furthermore, the upper parts of the load mounting plate 1 113 , the load mounting plate 2 114 , and the load mounting plate 3 115 are designed to be in an arc shape, and the arc state can be adjusted according to the distribution of the load.

[0035] Furthermore, the lower parts of the load mounting plate 1 13 , the load mounting plate 2 114 , and the load mounting plate 3 115 are connected to the large bottom plate 112 of the load compartment through corner boxes, ensuring that they are in a detachable state during the installation and adjustment of the effective load 2 .

[0036] Furthermore, positioning pins are arranged between the lower parts of the load mounting plate 1 13 , the load mounting plate 2 114 , and the load mounting plate 3 115 and the large bottom plate 112 of the load compartment to ensure the reset accuracy of each load mounting plate.

[0037] Furthermore, the load support beam 1 119 and the load support beam 2 120 have circular cross-sections, and the lengths of the load support beam 1 119 and the load support beam 2 120 are designed to be adjustable, and the final length is determined based on the final installation result of the load mounting plate.

[0038] Furthermore, corner boxes are used to connect the platform small partition 109, platform small partition 2 110 and the platform long partition 103, platform long partition 2 104 and large load-bearing bottom plate 112. The platform small partition 109 and platform small partition 2 110 are designed to be detachable and can be detached between the platform long partition 103, platform long partition 2 104 and large load-bearing bottom plate 112.

[0039] Furthermore, the docking ring 101, the platform bottom plate 102, the platform long partition 1 103, the platform long partition 2 104, the platform cabin short partition 1 105, the platform cabin short partition 2 106, the platform cabin short partition 3 107, the platform cabin short partition 4 108, and the four platform support beams 111 are in a state that cannot be disassembled separately after the structural parts are installed.

[0040] The following is further described based on specific embodiments:

[0041] In the current embodiment, if Figure 1 , Figure 2 As shown, the satellite structure includes a docking ring 101, a platform bottom plate 102, a platform long partition 103, a platform long partition 2 104, a platform short partition 1 105, a platform short partition 2 106, a platform short partition 3 107, a platform short partition 4 108, a platform small partition 1 109, a platform small partition 2 110, four platform support beams 111, a payload cabin large bottom plate 112, a payload cabin small bottom plate 116, a payload mounting plate 1 113, a payload mounting plate 2 114, a payload mounting plate 3 115, a payload cabin small top plate 1 117, a payload cabin small top plate 2 118, four load support beams 1 119, four load support beams 2 120, a side plate 1 121, a side plate 2 122, a side plate 3 123, and a side plate 4 124.

[0042] like Figure 3As shown, the docking ring 101 adopts a 1194-type docking ring. The distance between the satellite platform long partition 103 and the platform long partition 2 104 is 540 mm. The distance between the satellite platform short partition 105 and the platform short partition 2 106 and the distance between the platform short partition 3 107 and the platform short partition 4 108 are all 700 mm. The distance between the satellite platform small partition 109 and the platform small partition 2 110 is 1162 mm. Ten spacers are set between the above partitions of the platform cabin and the docking ring 101. The main load-bearing joints 3, including the eight positions between the docking ring 101 and the two end positions on the platform long partition 103, the two end positions on the platform long partition 2 104, the platform short partition 1 105, the platform short partition 2 106, the platform short partition 3 107, and the platform short partition 4 108, are realized by pasting metal reinforcements on the outside of the partitions. In addition, the main load-bearing joints 3 between the docking ring 101 and the platform short partition 4 108 and the platform small partition 1 109 are realized by pre-embedded metal reinforcements in the partitions.

[0043] The satellite's docking ring 101 is made of forged aluminum, the platform bottom plate 102, platform long bulkhead 1 103, platform long bulkhead 2 104, platform short bulkhead 1 105, platform short bulkhead 2 106, platform short bulkhead 3 107, platform short bulkhead 4 108, platform small bulkhead 1 109, platform small bulkhead 2 110, four platform support beams 111, payload cabin small bottom plate 116, side panel 1 121, side panel 2 122, side panel 3 123, side panel 4 124 all adopt an aluminum skin plus aluminum honeycomb sandwich structure, the payload cabin large bottom plate 112, load mounting plate 1 113, load mounting plate 2 114, load mounting plate 3 115 adopt a carbon fiber skin plus aluminum honeycomb sandwich structure, the four platform support beams 111, four load support beams 1 119, four load support beams 2 120 are formed of carbon fiber.

[0044] The satellite assembly sequence is as follows: 1. Connect the platform base plate 102 and the flange of the docking ring 101; 2. Connect the platform base plate 102 with the platform long partition 1 103 and the platform long partition 2 104; 3. Connect the platform base plate 102 with the platform short partition 1 105, the platform short partition 2 106, the platform short partition 3 107, and the platform short partition 4 108; 4. Connect the platform long partition 1 103 with the platform short partition 1 105 and the platform short partition 2 106 ; 5. Connect the platform long partition 2 104 with the platform short partition 3 107 and the platform short partition 4 108; 6. Connect the platform bottom plate 102 with the platform small partition 1 109 and the platform small partition 2 110; 7. Connect the platform small partition 1 109 and the platform small partition 2 110 between the platform long partition 1 103 and the platform long partition 2 104; 8. Connect the load cabin large bottom plate 112 with the platform long partition 1 103 and the platform long partition 2 104 , platform short partition 1 105, platform short partition 2 106, platform small partition 1 109, platform small partition 2 110; 9. Connect the load cabin small bottom plate 116 with the platform short partition 3 107, platform short partition 4 108; 10. Install four platform support beams 111; 11. Connect the load cabin large bottom plate 112 with the load mounting plate 1 113; 12. Connect the load cabin large bottom plate 112 with the load mounting plate 2 114; 13. Connect The load cabin large bottom plate 112 and the load installation plate 3 115; 14. Connect the load cabin small top plate 1 117, the load cabin small top plate 2 118 and the load installation plate 1 113, the load installation plate 2 114, and the load installation plate 3 115; 15. Install four load support beams 1 119 and four load support beams 2 120 respectively; 16. Install the side plate 1 121 and the side plate 3 123; 17. Install the side plate 2 122 and the side plate 4 124. The state after the structure is assembled is as follows Figure 4 Show.

[0045] like Figure 1 As shown, the integrated design diagram of the satellite structure 1 and the payload 2, the payload cabin large base plate 112, the payload mounting plate 1 113, the payload mounting plate 2 114, and the payload mounting plate 3 115 in the satellite structure 1 are both the main load-bearing structure of the satellite and the main supporting structure of the payload.

[0046] A satellite structure with integrated platform and payload suitable for multi-module spliced ​​payloads breaks the traditional design idea of ​​satellite platform and payload compartments. Through the integrated structural design of satellite platform and payload, the satellite platform and the payload body share the same main load-bearing structure, which can meet the requirements of satellite weight and envelope for the new generation of ocean observation satellites to achieve three-satellite launch with one rocket.

[0047] It should be noted that the above is a preferred embodiment of the present invention. It should be pointed out that although the preferred embodiment of the present invention has been described, once the basic creative concept of the present invention is known, a number of improvements and modifications can be made by a person skilled in the art without departing from the principles of the present invention, and these improvements and modifications should also be regarded as the protection scope of the present invention. Therefore, the attached claims are intended to be interpreted as including the preferred embodiment and all changes and modifications that fall within the scope of the embodiments of the present invention.

Claims

1. A satellite structure integrating platform and payload suitable for multi-module splicing payload, characterized by: It includes a satellite structure (1) and a payload (2); The satellite structure (1) comprises a docking ring (101), a platform bottom plate (102), a platform long partition plate 1 (103), a platform long partition plate 2 (104), a platform short partition plate 1 (105), a platform short partition plate 2 (106), a platform short partition plate 3 (107), a platform short partition plate 4 (108), a platform small partition plate 1 (109), a platform small partition plate 2 (110), four platform support beams (111), a load cabin large bottom plate (112), a load cabin small bottom plate (116), a load installation plate 1 (113), a load installation plate 2 (114), a load installation plate 3 (115), a load cabin small top plate 1 (117), a load cabin small top plate 2 (118), four load support beams 1 (119), four load support beams 2 (120), a side plate 1 (121), a side plate 2 (122), a side plate 3 (123), and a side plate 4 (124); The payload (2) includes five payload modules 1 (201), five payload modules 2 (202), and three payload modules 3 (203). The payload module 1 (201) is mounted on the payload mounting plate 1 (113), the payload module 2 (202) is mounted on the payload mounting plate 2 (114), and the payload module 3 (203) is mounted on the payload mounting plate 3 (115).

2. The platform and payload integrated satellite structure suitable for multi-module splicing payloads according to claim 1, characterized in that: The docking ring (101) is connected to the platform long partition 1 (103), the platform long partition 2 (104), the platform short partition 1 (105), the platform short partition 2 (106), the platform short partition 3 (107), and the platform short partition 4 (108) through the platform bottom plate (102) through a corner box, and is connected to the platform small partition 1 (109) and the platform small partition 2 (110) through screws; The large bottom plate (112) of the load compartment is connected to the long partition plate 1 (103) of the platform, the long partition plate 2 (104) of the platform, the short partition plate 1 (105) of the platform, the short partition plate 2 (106) of the platform, the small partition plate 1 (109) of the platform, and the small partition plate 2 (110) of the platform through a corner box, and the small bottom plate (116) of the load compartment is connected to the short partition plate 3 (107) of the platform, and the short partition plate 4 (108) of the platform through screws.

3. The platform and payload integrated satellite structure suitable for multi-module splicing payload according to claim 1, characterized in that: The load mounting plate 1 (113) is aligned with the side plate 2 (122) in the vertical direction, the load mounting plate 2 (114) is aligned with the platform long partition 2 (104) in the vertical direction, and the load mounting plate 3 (115) is aligned with the platform long partition 1 (103) in the vertical direction.

4. The platform and payload integrated satellite structure suitable for multi-module splicing payload according to claim 1, characterized in that: The four platform support beams (111) have a right-angled cross section. The lower ends of the platform support beams (111) are installed at the four corners of the platform bottom plate (102), the upper ends are respectively connected to the large bottom plate (112) of the load compartment and the small bottom plate (116) of the load compartment, and the sides are respectively connected to the side plate one (121), the side plate two (122), the side plate three (123), and the side plate four (124).

5. The platform and payload integrated satellite structure suitable for multi-module splicing payloads according to claim 1, characterized in that: The upper parts of the load mounting plate 1 (113), the load mounting plate 2 (114) and the load mounting plate 3 (115) are designed to be arc-shaped.

6. The platform and payload integrated satellite structure suitable for multi-module splicing payloads according to claim 1, characterized in that: The lower parts of the load mounting plate 1 (113), the load mounting plate 2 (114) and the load mounting plate 3 (115) are connected to the large bottom plate (112) of the load compartment through a corner box.

7. The platform and payload integrated satellite structure suitable for multi-module splicing payloads according to claim 1, characterized in that: Positioning pins are arranged between the lower parts of the load mounting plate 1 (113), the load mounting plate 2 (114), and the load mounting plate 3 (115) and the large bottom plate (112) of the load compartment for positioning and mounting.

8. The platform and payload integrated satellite structure suitable for multi-module splicing payloads according to claim 1, characterized in that: The load supporting beam 1 (119) and the load supporting beam 2 (120) have circular cross sections.

9. The platform and payload integrated satellite structure suitable for multi-module splicing payloads according to claim 1, characterized in that: The platform small partition 1 (109), the platform small partition 2 (110), the platform long partition 1 (103), the platform long partition 2 (104), and the load-bearing large bottom plate (112) are connected by using corner boxes.

10. The platform and payload integrated satellite structure suitable for multi-module splicing payloads according to claim 1, characterized in that: The docking ring (101), the platform bottom plate (102), the platform long partition one (103), the platform long partition two (104), the platform cabin short partition one (105), the platform cabin short partition two (106), the platform cabin short partition three (107), the platform cabin short partition four (108), and the four platform support beams (111) are in a state where they cannot be disassembled separately after the structural parts are installed.

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