阅读说明：本技术 用于堆叠卫星的结构承载装置 (Structural bearing device for stacked satellites ) 是由 张晓彤 杜冬 秦美泽 蔡一波 刘培 尹健 赵川 于 2021-09-10 设计创作，主要内容包括：本发明提供了航天卫星技术领域的一种用于堆叠卫星的结构承载装置,包括卫星单体和压紧块组件；卫星单体包括底板和多块隔板,多块隔板固定设置在所述底板上；压紧块组件包括多个压紧块件,压紧块件包括定位柱和固定部,多个压紧块采用不同数量的固定部周向设置在定位柱上的结构形式,且多个压紧块采用固定部对应定位柱不同端面设置的结构形式；不同结构的压紧块通过定位柱固定设置在底板与隔板上,多个卫星单体通过不同的压紧块相互配合进行固定。本发明能够实现卫星的高容积比,在整流罩有限空间内布局更多卫星,提高空间容积利用率,为有散热需求的星上仪器设备的温度控制提供了极大的便利。(The invention provides a structure bearing device for a stacked satellite in the technical field of space satellites, which comprises a satellite single body and a compression block assembly; the satellite single body comprises a bottom plate and a plurality of partition plates, and the partition plates are fixedly arranged on the bottom plate; the pressing block assembly comprises a plurality of pressing block pieces, each pressing block piece comprises a positioning column and a fixing part, the plurality of pressing blocks are in a structural form that the fixing parts with different numbers are circumferentially arranged on the positioning columns, and the plurality of pressing blocks are in a structural form that the fixing parts are arranged corresponding to different end faces of the positioning columns; the pressing blocks of different structures are fixedly arranged on the bottom plate and the partition plate through the positioning columns, and the satellite single bodies are mutually matched and fixed through different pressing blocks. The invention can realize high volume ratio of the satellite, arrange more satellites in the limited space of the fairing, improve the space volume utilization rate and provide great convenience for temperature control of on-satellite instruments and equipment with heat dissipation requirements.)

1. A structural load bearing device for stacked satellites, comprising a satellite monoblock (11) and a compact block assembly;

the satellite single body (11) comprises a bottom plate (1) and partition plates (2), wherein the partition plates (2) are provided with a plurality of blocks, the partition plates (2) are fixedly arranged on the bottom plate (1), and the partition plates (2) and the bottom plate (1) are arranged in a mutually vertical mode;

the pressing block assembly comprises a plurality of pressing block pieces, each pressing block piece comprises a positioning column (12) and fixing parts (13), the plurality of pressing blocks adopt structural forms that the fixing parts (13) with different numbers are circumferentially arranged on the positioning columns (12), and the plurality of pressing blocks adopt structural forms that the fixing parts (13) are arranged corresponding to different end faces of the positioning columns (12);

the pressing blocks with different structures are fixedly arranged on the bottom plate (1) and the partition plate (2) through positioning columns (12), and the satellite single bodies (11) are matched with each other through different pressing blocks to be fixed.

2. Structural support device for stacked satellites according to claim 1, characterized in that the floor (1) comprises a mounting surface providing a mounting for satellite equipment, on which surface a solar array (6) is fixedly arranged, the partitions (2) being arranged on the surface of the floor (1) not provided with the solar array (6).

3. The structural load carrying device for stacked satellites according to claim 2, wherein the bottom plate (1) is an aluminum alloy honeycomb sandwich plate, the length of the bottom plate (1) is 3200mm, the width of the bottom plate (1) is 1600mm, the thickness of the bottom plate (1) is 15mm, and the outer contour of the bottom plate (1) is in a convex structural form.

4. A structural load carrying device for stacked satellites according to claim 1 wherein the partitions (2) are in the form of honeycomb sandwich plate structures providing mounting interfaces for satellite equipment, the height of the partitions (2) being 273mm, the length of a plurality of partitions (2) being 126mm-1525mm, the thickness of the partitions (2) being 10 mm.

5. The structural bearing device for the stacked satellite according to claim 1, wherein the compression block assembly comprises a first compression block (3), a second compression block (4) and a third compression block (5), the first compression block (3), the second compression block (4) and the third compression block (5) respectively adopt an integrated magnesium alloy thin-wall force bearing structure, and the heights of the first compression block (3), the second compression block (4) and the third compression block (5) are all 330 mm.

6. The structural bearing device for stacked satellites according to claim 5, wherein the upper end face of the positioning column (12) is provided with a coupling flange (9), the lower end face of the positioning column (12) is provided with a coupling groove (10), the upper end face of the fixing portion (13) is provided with a protruding block (7), the lower end face of the fixing portion (13) is provided with a shear-proof groove (8), the compression blocks with different structures are positioned corresponding to the coupling groove (10) through the coupling flange (9), and the compression blocks with different structures are fixed corresponding to the shear-proof groove (8) through the protruding block (7).

7. The structural bearing device for stacked satellites according to claim 6, wherein the first compression block (3) is correspondingly arranged in the X-axis direction of the bottom plate (1), the first compression block (3) comprises one positioning column (12) and three fixing portions (13), the height of the positioning column (12) is the same as that of the fixing portions (13), the fixing portions (13) comprise a first fixing body, a second fixing body and a third fixing body, the first fixing body and the second fixing body are arranged at 90 degrees from each other, and the second fixing body and the third fixing body are arranged at 90 degrees from each other.

8. The structural support device for stacked satellites according to claim 6, wherein the second compression block (4) is correspondingly arranged in the positive Y-axis direction of the bottom plate (1), the second compression block (4) comprises one positioning column (12) and two fixing portions (13), the height of the positioning column (12) is half of the height of the two fixing portions (13), the two fixing portions (13) are arranged perpendicular to each other, and the positioning column (12) is arranged at one end close to the upper end face of the fixing portions (13).

9. The structural support device for stacked satellites according to claim 6, wherein the third compression block (5) is correspondingly arranged in the negative Y-axis direction of the bottom plate (1), the third compression block (5) comprises one positioning column (12) and two fixing portions (13), the height of the positioning column (12) is half of the height of the two fixing portions (13), the two fixing portions (13) are arranged perpendicular to each other, and the positioning column (12) is arranged at one end close to the lower end face of the fixing portions (13).

10. Structural carrying device for stacked satellites according to claim 5, characterized in that the anti-shear grooves (8) are semi-cylindrical, the positioning posts (12) are in the form of hollow cylinders with an outer diameter of 150mm and a wall thickness of 6 mm; the fixing part (13) adopts a cuboid structure form, the width of the fixing part (13) is 50mm, the length of the fixing part (13) is 450mm, and the wall thickness of the fixing part (13) is 4 mm.

Technical Field

The invention relates to the technical field of space satellites, in particular to a structure bearing device for stacked satellites.

Background

Aiming at the defects that the ground network coverage is limited, the influence of natural environment is easy to influence and the like, the satellite communication can effectively solve the problem of internet service of users in remote areas, on the sea, in the air and the like. In recent years, countries such as the united states and canada have successively proposed global low-earth-orbit internet constellation plans, and the technical trend of internet satellite constellations has been raised. In order to enhance the competitiveness of China in the field and further consolidate and improve the future international influence, the low-orbit satellite constellation construction work of China is also continuously developed. Through investigation and analysis, if a traditional satellite cube configuration is used for designing a stacked satellite, the problems of too high overall height of a satellite group, low inherent frequency, severely limited emission quantity and the like exist, so that the optimal design of the satellite configuration and the layout form of the satellite group in a fairing are the key technologies for realizing the satellite constellation networking.

The prior art has searched and found that chinese patent publication No. CN107889482B discloses a stackable satellite and a stacking method thereof, including a satellite frame and at least one vertical pillar attached to the frame. The vertical strut has an upper end and a lower end. The upper end is coupled to the lower end of the vertical column of the satellite above and the lower end is coupled to the upper end of the vertical column of the satellite below. The vertical struts receive substantially all of the vertical load of the stackable satellite and any other satellites stacked above. However, the above patents have the following disadvantages: the whole size of the satellite is small, and the installation requirements of multiple loads and large loads are difficult to adapt.

The search of the prior art shows that the Chinese patent publication No. CN106043741B discloses a satellite configuration design method suitable for one-rocket multi-satellite launching. Aiming at the illumination characteristic of the solar angle of the low-inclination orbit which changes in a large range, the invention improves the outer surface corresponding to the lower bottom of the trapezoidal section of the satellite into an arch formed by three plates as the mounting surface for fixing the solar cell array, and carries out an iterative optimization method on the included angle of the three cell plates. However, the above patents have the following disadvantages: the application of the central bearing structure and the configuration of the bottom arch lead to serious waste of the carrying and launching space, and lead to low effective utilization rate of carrying circumferential envelope.

The prior art searches and discovers that the ' one-arrow-more-star ' configuration optimization design method for launching the low earth orbit satellite ' has publication numbers as follows: 11-5574/V. The document designs a satellite configuration considering multi-satellite-single-satellite coupling, and realizes series-parallel hybrid arrangement of satellites by a satellite group mainly through a multi-satellite distributor. However, the above patents have the following disadvantages: the multi-satellite distributor reduces the utilization efficiency of carrying space, can only contain one arrow and eight satellites at most, and is difficult to adapt to the application requirement of rapid deployment of a satellite group.

The bearing structure for the stacked satellites has the advantages that the convex outer contour and the flattened configuration are designed to be matched with the metal pressing block bearing structure, the use of the bearing structure in the center of a satellite group is avoided, the height of the integral mass center of the satellite group can be effectively reduced, the circumferential utilization rate of a carrying fairing and the utilization rate of carrying and launching capacity are improved, the requirements of one-rocket multi-satellite launching and rapid networking of a satellite constellation are better met, and the application process of networking of the low-orbit satellite constellation in China is further accelerated and promoted.

Disclosure of Invention

In view of the deficiencies in the prior art, it is an object of the present invention to provide a structural carrier for stacked satellites.

The invention provides a structure bearing device for stacked satellites, which comprises a satellite single body and a compression block assembly;

the satellite single body comprises a bottom plate and a plurality of partition plates, the partition plates are fixedly arranged on the bottom plate, and the partition plates and the bottom plate are perpendicular to each other;

the pressing block assembly comprises a plurality of pressing block pieces, each pressing block piece comprises a positioning column and fixing parts, the plurality of pressing blocks are in a structural form that the fixing parts with different numbers are circumferentially arranged on the positioning columns, and the plurality of pressing blocks are in a structural form that the fixing parts are arranged corresponding to different end faces of the positioning columns;

the pressing blocks of different structures are fixedly arranged on the bottom plate and the partition plate through positioning columns, and the satellite single bodies are mutually matched and fixed through different pressing blocks.

In some embodiments, the bottom plate comprises a mounting surface for providing mounting for satellite equipment, the mounting surface is fixedly provided with a solar array, and the partition plate is arranged on the surface of the bottom plate which is not provided with the solar array.

In some embodiments, the bottom plate is an aluminum alloy honeycomb sandwich plate, the length of the bottom plate is 3200mm, the width of the bottom plate is 1600mm, the thickness of the bottom plate is 15mm, and the outer contour of the bottom plate is in a convex structural form.

In some embodiments, the partition is in the form of a honeycomb sandwich plate structure providing a mounting interface for satellite equipment, the height of the partition is 273mm, the length of a plurality of partitions is 126mm to 1525mm, and the thickness of the partition is 10 mm.

In some embodiments, the pressing block assembly comprises a first pressing block, a second pressing block and a third pressing block, the first pressing block, the second pressing block and the third pressing block respectively adopt an integrated magnesium alloy thin-wall force bearing structure, and the heights of the first pressing block, the second pressing block and the third pressing block are all 330 mm.

In some embodiments, a coupling flange is arranged on the upper end face of the positioning column, a coupling groove is arranged on the lower end face of the positioning column, a protruding block is arranged on the upper end face of the fixing portion, an anti-shearing groove is arranged on the lower end face of the fixing portion, the pressing blocks of different structures are correspondingly positioned with the coupling groove through the coupling flange, and the pressing blocks of different structures are correspondingly fixed with the anti-shearing groove through the protruding block.

In some embodiments, the first pressing block is correspondingly disposed in the X-axis direction of the bottom plate, the first pressing block includes one positioning column and three fixing portions, the height of the one positioning column is the same as the height of the three fixing portions, the three fixing portions include a first fixing body, a second fixing body and a third fixing body, the first fixing body and the second fixing body are disposed at 90 ° intervals, and the second fixing body and the third fixing body are disposed at 90 ° intervals.

In some embodiments, the second pressing block is correspondingly disposed in the positive Y-axis direction of the bottom plate, the second pressing block includes one positioning column and two fixing portions, the height of the positioning column is half of the height of the two fixing portions, the two fixing portions are disposed perpendicular to each other, and the positioning column is disposed at an end close to the upper end face of the fixing portion.

In some embodiments, the third pressing block is correspondingly disposed in the negative Y-axis direction of the bottom plate, the third pressing block includes one positioning column and two fixing portions, the height of the positioning column is half of the height of the two fixing portions, the two fixing portions are disposed perpendicular to each other, and the positioning column is disposed at an end close to the lower end face of the fixing portion.

In some embodiments, the anti-shearing groove is semi-cylindrical, the positioning column is in a hollow cylindrical structure, the outer diameter of the cylinder is 150mm, and the wall thickness of the cylinder is 6 mm; the fixed part adopts cuboid structural style, the width of fixed part is 50mm, the length of fixed part is 450mm, the wall thickness of fixed part is 4 mm.

Compared with the prior art, the invention has the following beneficial effects:

1. according to the invention, by arranging the bottom plate and the partition plate, a flat stacking configuration is adopted, and a flat single machine is used in a matching manner, so that the high volume ratio of the satellite can be realized, more satellites are distributed in the limited space of the fairing, and the space volume utilization rate is improved;

2. the invention improves the utilization rate of the circumferential section of the carrying fairing by arranging the bottom plate in the convex shape structure, reduces the overall height of the satellite group, provides an installation surface for a large-area solar array, only designs the bottom plate and the partition plate, does not design an independent top plate, reduces the structural weight, and provides great convenience for the temperature control of on-board instruments and equipment with heat dissipation requirements;

3. according to the invention, the pressing block assembly is arranged, the coupling flange and the coupling groove are designed on the positioning column of the cylindrical structure part, the protruding block and the anti-shearing groove are designed on the fixing part extending out of the cuboid part, so that the emission section stacked satellites are firmly and reliably connected, an independent central force bearing structure is not needed, the integral mass center height of a satellite group can be effectively reduced, the circumferential utilization rate of a carrying fairing and the effective utilization rate of carrying emission weight are improved, more satellites and larger loads can be distributed under the same carrying constraint condition, and the requirement of rapid deployment of a satellite networking can be better met;

4. the invention reserves enough space for the arrangement of onboard instruments and equipment by adopting the bottom plate with the length of 3200mm, the width of 1600mm and the thickness of 15mm, provides a reliable installation environment, is convenient to operate and install, adopts the aluminum alloy honeycomb sandwich plate structure as the bottom plate and the partition plate, has high production and processing speed and mature process, can better match the requirement of batch production, further shortens the manufacturing period and reduces the cost.

Drawings

Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:

FIG. 1 is a first structural schematic view of a structural support device for stacked satellites according to the present invention;

FIG. 2 is a second structural schematic view of the structural support device for stacked satellites according to the present invention;

FIG. 3 is an assembled elevation view of a structural carrier for stacked satellites according to the present invention;

FIG. 4 is an assembled view of the structural support device for stacked satellites of the present invention;

FIG. 5 is a schematic structural view of a first compact of the present invention;

FIG. 6 is a schematic structural view of a second compact of the present invention;

fig. 7 is a schematic structural diagram of a third compact block of the present invention.

Reference numerals:

Detailed Description

The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.

Establishing a layout coordinate system (O-XYZ) of the satellite, which is defined as follows:

origin of coordinates O: the middle point of the lower bottom edge of the bottom plate of the satellite monomer;

OZ axis: the bottom plate is vertical to the single satellite and points to the direction of the partition plate;

OX axis: pointing to the middle point of the upper bottom edge of the satellite monomer along the origin of coordinates;

y-axis: in right-hand relationship with axis X, Z.

Fig. 1 is a schematic structural diagram of a structural bearing device for stacked satellites, and fig. 2 is a schematic structural diagram of a structural bearing device for stacked satellites, including a satellite single body 11 and a compact block assembly. Satellite monomer 11 includes bottom plate 1 and baffle 2, and baffle 2 is equipped with the polylith, and polylith baffle 2 is fixed to be set up on bottom plate 1, and baffle 2 and 1 mutually perpendicular setting of bottom plate. The compact heap subassembly includes a plurality of compact heap spare that compress tightly, and the compact heap spare includes reference column 12 and fixed part 13, and a plurality of compact heap adopt the fixed part 13 circumference of different quantity to set up the structural style on reference column 12, and a plurality of compact heap adopt the structural style that fixed part 13 corresponds the different terminal surfaces of reference column 12 and sets up.

Fig. 3 is an assembly front view of a structure bearing device for stacking satellites, fig. 4 is an assembly schematic view of the structure bearing device for stacking satellites, compression blocks with different structures correspond to each other through positioning columns 12, the compression blocks with different structures are fixedly arranged on a bottom plate 1 and a partition plate 2 through fixing portions 13, and a plurality of satellite single bodies 11 are mutually matched and fixed through different compression blocks.

The bottom plate 1 comprises a mounting surface for providing mounting for satellite equipment, a solar array 6 is fixedly arranged on the mounting surface, and the partition plate 2 is arranged on the surface of the bottom plate 1 which is not provided with the solar array 6. In this embodiment, bottom plate 1 adopts aluminum alloy honeycomb sandwich panel, and bottom plate 1's length is 3200mm, and bottom plate 1's width is 1600mm, and bottom plate 1's thickness is 15mm, and bottom plate 1's outline adopts the type of a chinese character ' tu structural style of calligraphy. The partition board 2 adopts a honeycomb sandwich plate structure form for providing an installation interface for satellite equipment, the height of the partition board 2 is 273mm, the length of the partition boards 2 is 126mm-1525mm, and the thickness of the partition boards 2 is 10 mm. The size can be correspondingly modified according to the carrying envelope size, and holes and embedded parts are arranged on the solar panel according to the overall single machine layout requirement to provide installation interfaces for large-area thin-film solar wings and other single machines.

The pressing block assembly comprises a first pressing block 3, a second pressing block 4 and a third pressing block 5, the first pressing block 3, the second pressing block 4 and the third pressing block 5 are respectively of an integrated magnesium alloy thin-wall force bearing structure, and the heights of the first pressing block 3, the second pressing block 4 and the third pressing block 5 are 330mm respectively.

The up end of reference column 12 is equipped with coupling flange 9, and the lower terminal surface of reference column 12 is equipped with coupling recess 10, and the up end of fixed part 13 is equipped with protruding piece 7, and the lower terminal surface of fixed part 13 is equipped with anti-shear groove 8, and compact heap of isostructure is fixed a position through coupling flange 9 and coupling recess 10 correspondence, and compact heap of isostructure is fixed through protruding piece 7 and anti-shear groove 8 are corresponding. The anti-shearing groove 8 is in a semi-cylindrical shape, the positioning column 12 is in a hollow cylindrical structure, the outer diameter of the cylinder is 150mm, and the wall thickness of the cylinder is 6 mm; the fixing part 13 is in a rectangular parallelepiped structure, the width of the fixing part 13 is 50mm, the length of the fixing part 13 is 450mm, and the wall thickness of the fixing part 13 is 4 mm.

As shown in fig. 5, which is a schematic structural diagram of the first pressing block 3, the first pressing block 3 is correspondingly disposed in the X-axis direction of the bottom plate 1, the first pressing block 3 includes a positioning column 12 and three fixing portions 13, the height of the positioning column 12 is the same as that of the three fixing portions 13, the three fixing portions 13 include a first fixing body, a second fixing body and a third fixing body, the first fixing body and the second fixing body are disposed at an interval of 90 degrees, and the third fixing body and the second fixing body are disposed at an interval of 90 degrees.

As shown in fig. 6, which is a schematic structural diagram of the second pressing block 4, the second pressing block 4 is correspondingly disposed in the positive Y-axis direction of the bottom plate 1, the second pressing block 4 includes a positioning column 12 and two fixing portions 13, the height of the positioning column 12 is half of the height of the two fixing portions 13, the two fixing portions 13 are disposed perpendicular to each other, and the positioning column 12 is disposed at one end close to the upper end face of the fixing portion 13.

As shown in fig. 7, which is a schematic structural diagram of the third pressing block 5, the third pressing block 5 is correspondingly disposed in the negative Y-axis direction of the bottom plate 1, the third pressing block 5 includes a positioning column 12 and two fixing portions 13, the height of the positioning column 12 is half of the height of the two fixing portions 13, the two fixing portions 13 are disposed perpendicular to each other, and the positioning column 12 is disposed at one end close to the lower end face of the fixing portion 13.

Baffle 2 and first compact heap 3, second compact heap 4, third compact heap 5 pass through built-in fitting, screw and are connected with bottom plate 1, and baffle 2 and first compact heap 3, second compact heap 4, third compact heap 5 pass through fasteners such as angle piece, screw, nut, gasket and are connected with adjacent baffle 2.

When the satellite single bodies 11 are stacked and assembled, the first pressing block 3 is fixedly arranged on the X-axis direction of the bottom plate 1, and the second pressing block 4 and the third pressing block 5 are respectively fixedly arranged on two vertex angles of the Y-axis direction of the convex bottom plate 1. The coupling flange 9 on the upper end face of the positioning column 12 of the first pressing block 3 of the middle satellite single body 11 is connected to the coupling groove 10 on the lower end face of the positioning column 12 of the first pressing block 3 of the upper satellite single body 11, and the coupling groove 10 on the lower end face of the positioning column 12 of the first pressing block 3 of the middle satellite single body 11 is connected to the coupling flange 9 on the upper end face of the positioning column 12 of the first pressing block 3 of the lower satellite single body 11.

The coupling flange 9 of the upper end face of the positioning column 12 of the second compression block 4 of the middle satellite single body 11 is connected to the coupling groove 10 of the lower end face of the positioning column 12 of the third compression block 5 of the upper layer satellite, and the coupling groove 10 of the lower end face of the positioning column 12 of the second compression block 4 of the middle satellite single body 11 is connected to the coupling flange 9 of the upper end face of the positioning column 12 of the third compression block 5 of the same layer satellite. The coupling flange 9 of the upper end face of the positioning column 12 of the third pressing block 5 of the middle satellite single body 11 is connected to the coupling groove 10 of the lower end face of the positioning column 12 of the second pressing block 4 of the same-layer satellite, and the coupling groove 10 of the lower end face of the positioning column 12 of the third pressing block 5 of the middle satellite single body 11 is connected to the coupling flange 9 of the upper end face of the positioning column 12 of the second pressing block 4 of the lower-layer satellite. And the protruding block 7 of each compression block piece is overlapped with the anti-shearing groove 8 of the upper satellite compression block piece, so that the transverse anti-shearing capacity between the upper compression block and the lower compression block and the reliability of design are improved.

In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.

The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.