CN111532452B - Force bearing structure of multi-star distributor - Google Patents
Force bearing structure of multi-star distributor Download PDFInfo
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- CN111532452B CN111532452B CN202010420938.4A CN202010420938A CN111532452B CN 111532452 B CN111532452 B CN 111532452B CN 202010420938 A CN202010420938 A CN 202010420938A CN 111532452 B CN111532452 B CN 111532452B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/002—Launch systems
Abstract
The embodiment of the invention provides a multi-satellite distributor bearing structure, which comprises: the bearing cylinder is provided with a grid structure, and the grid structure is a non-skin grid structure; a first inner reinforcing V-shaped frame is arranged at the first end of the bearing cylinder, and a second inner reinforcing V-shaped frame is arranged at the second end of the bearing cylinder; at least one first satellite supporting platform is arranged on the outer side arc surface of the first end of the bearing cylinder, and at least one second satellite supporting platform is arranged on the outer side arc surface of the second end of the bearing cylinder. The scheme of the invention can meet the use requirements of simultaneously carrying and releasing a plurality of satellites, and has the advantages of high rigidity, light weight, integrated structure manufacture, simple assembly, high reliability, good manufacturability and good product consistency.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a force bearing structure of a multi-star distributor.
Background
The multi-satellite distributor bearing cylinder is mainly used for one-rocket multi-satellite launching tasks, 2 or 4 satellites can be arranged on the multi-satellite distributor bearing cylinder generally according to the self annular direction, connection points are generally located at the upper end face and the lower end face of the multi-satellite distributor bearing cylinder, each satellite is generally connected with the multi-satellite distributor bearing cylinder through four connection points, and meanwhile the four points have the functions of separation and pop-up release. The weight efficiency of the multi-satellite distributor bearing cylinder is completely consistent with that of a satellite, and meanwhile, the bearing cylinder can meet the integral rigidity requirement after the multi-satellite is installed, so that the multi-satellite distributor bearing cylinder is required to be as light in weight as possible and high in integral rigidity requirement.
The traditional multi-star distributor bearing cylinder is generally designed into a ring frame and skin stringer structure, an integral honeycomb sandwich structure and the like, and has the defects that the multi-star distributor bearing cylinder is generally high in weight and complex in structural design and manufacture in order to ensure the rigidity of the integral structure.
Disclosure of Invention
The technical problem to be solved by the invention is to provide a multi-satellite distributor bearing structure which can meet the use requirement of carrying and releasing a plurality of satellites simultaneously.
In order to solve the technical problems, the technical scheme of the invention is as follows:
a multi-star distributor force-bearing structure, comprising: the bearing cylinder is provided with a grid structure, and the grid structure is a non-skin grid structure; a first inner reinforcing V-shaped frame is arranged at the first end of the bearing cylinder, and a second inner reinforcing V-shaped frame is arranged at the second end of the bearing cylinder;
at least one first satellite supporting platform is arranged on the outer side arc surface of the first end of the bearing cylinder, and at least one second satellite supporting platform is arranged on the outer side arc surface of the second end of the bearing cylinder.
Optionally, the grid structure is an inclined grid structure or an orthorhombic grid structure.
Optionally, the first end of the bearing cylinder is provided with a first section of skin structure along the axial direction;
the second end of the bearing cylinder is provided with a second section of skin structure along the axial direction;
when the grid structure is an inclined grid structure, an inclined grid structure without a skin is arranged between the first section of skin structure and the second section of skin structure of the bearing cylinder;
when the grid structure is an orthorhombic grid structure, an orthorhombic grid structure without a skin is arranged between the first section of skin structure and the second section of skin structure of the bearing cylinder.
Optionally, the inclined grid structure is a rhombic grid or triangular grid structure with equal edge distance;
the orthorhombic grid structure is a rectangular or square grid structure.
Optionally, the first inner reinforcing n-shaped frame is connected with the inner side of the first end of the bearing cylinder through a bolt;
the second inner reinforcing V-shaped frame is connected with the inner side of the second end of the bearing cylinder through a bolt.
Optionally, four first satellite supporting tables are arranged on the outer arc surface of the first end of the bearing cylinder;
the four first satellite supporting tables are respectively connected with the outer side arc surface of the first end of the bearing cylinder through bolts, and the four first satellite supporting tables are uniformly distributed on the outer side arc surface of the first end of the bearing cylinder.
Optionally, four second satellite support platforms are arranged on the outer arc surface of the second end of the bearing cylinder;
the four second satellite supporting tables are respectively connected with the outer side arc surface of the second end of the bearing cylinder through bolts, and the four second satellite supporting tables are uniformly distributed on the outer side arc surface of the second end of the bearing cylinder.
Optionally, the first end of the bearing cylinder is provided with a first L-shaped outward-turning frame connected with the adjacent cabin section;
the second end of the bearing cylinder is provided with a second L-shaped outward-turned frame connected with the adjacent cabin section.
Optionally, the bearing cylinder is an axial cylinder or a cone structure, and the first inner reinforcing n-shaped frame and the second inner reinforcing n-shaped frame are both axial cylinders or cone structures.
Optionally, one side of the first inner reinforcing n-shaped frame and one side of the second inner reinforcing n-shaped frame are provided with a first flanging structure, and the other side of the first inner reinforcing n-shaped frame and the second inner reinforcing n-shaped frame are provided with a second flanging structure.
Optionally, the first satellite support table and the second satellite support table are both box-type thin-walled structures, a third flanging structure is arranged on a first arc-shaped edge of the first satellite support table, the second satellite support table and the bearing cylinder, which are matched with each other, and a fourth flanging structure is arranged on a second arc-shaped edge;
at least one first satellite support platform is fixedly connected with a first flanging structure of the first internal reinforcing inverted-V-shaped frame through a third flanging structure and is fixedly connected with a second flanging structure of the first internal reinforcing inverted-V-shaped frame through a fourth flanging structure;
at least one second satellite supporting platform is fixedly connected with a first flanging structure of the second internal reinforcing inverted-V-shaped frame through the third flanging structure and is fixedly connected with a second flanging structure of the second internal reinforcing inverted-V-shaped frame through a fourth flanging structure.
Optionally, the mounting surfaces of the first satellite support platform and the second satellite support platform have at least one mounting hole.
The scheme of the invention at least comprises the following beneficial effects:
in the above scheme of the invention, the multi-star distributor bearing structure comprises: a force bearing cylinder with a grid structure; the grid structure is a non-skin grid structure; a first inner reinforcing V-shaped frame is arranged at the first end of the bearing cylinder, and a second inner reinforcing V-shaped frame is arranged at the second end of the bearing cylinder; at least one first satellite supporting platform is arranged on the outer side arc surface of the first end of the bearing cylinder, and at least one second satellite supporting platform is arranged on the outer side arc surface of the second end of the bearing cylinder. The multi-star distributor bearing structure integrally manufactured by utilizing the carbon fiber composite material main body ensures the use rigidity requirement of the whole system, and simultaneously reduces the weight by more than 20 percent compared with the traditional structure. And the structure is manufactured and assembled simply, the reliability is high, the manufacturability is good, the product uniformity is good.
Drawings
FIG. 1 is a first view of the overall construction of the multi-star distributor force-bearing structure of the slanted grid structure of the present invention;
FIG. 2 is a second view of the overall construction of the multi-star distributor force-bearing structure of the slanted grid structure of the present invention;
FIG. 3 is a cross-sectional view of the overall structure of the multi-star distributor force bearing structure of the slanted grid structure of the present invention;
FIG. 4 is a structural diagram of a bearing cylinder of a multi-star distributor bearing structure of the inclined grid structure;
FIG. 5 is a cut-away view of the bearing cylinder of the multi-star distributor bearing structure of the slanted grid structure of the present invention;
fig. 6 is a first view of the overall structure of the multi-star distributor force-bearing structure of the orthonormal grid structure of the present invention;
fig. 7 is a second view of the overall structure of the multi-star distributor force-bearing structure of the orthonormal grid structure of the present invention;
FIG. 8 is a cross-sectional view of the overall structure of the multi-star distributor force-bearing structure of the orthonormal grid structure of the present invention;
FIG. 9 is a structural diagram of a bearing cylinder of the multi-star distributor bearing structure of the orthorhombic grid structure;
FIG. 10 is a cut-away view of the bearing cylinder of the multi-star distributor bearing structure of the orthonormal grid structure of the present invention;
FIG. 11 is a block diagram of an internal reinforcing frame of the multi-star distributor force-bearing structure of the present invention;
fig. 12 is a structural view of a satellite support table of the multi-star distributor bearing structure of the invention.
Description of reference numerals:
1-bearing cylinder; 11- -first end; 12- -a second end;
21- -first inner reinforcing frame; 22- -second inner reinforcing frame;
31- -a first satellite support table; 32- -a second satellite support table;
41- -first section skin structure; 42- -second section skin structure; 43- -inclined grid construction; 44- -orthonormal grid configuration;
211 — a first cuff structure; 212- -second flange structure;
311- -third flange structure; 312- -fourth flange structure;
313 — a mounting surface; 314-mounting holes.
Detailed Description
Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.
As shown in fig. 1 to 12, an embodiment of the present invention provides a multi-star distributor force-bearing structure, including: a bearing cylinder 1 with a grid structure; the grid structure is a non-skin grid structure; a first inner reinforcing V-shaped frame 21 is arranged at the first end 11 of the bearing cylinder 1, and a second inner reinforcing V-shaped frame 22 is arranged at the second end 12 of the bearing cylinder 1;
at least one first satellite support platform 31 is arranged on the outer side arc surface of the first end 11 of the bearing cylinder 1, and at least one second satellite support platform 32 is arranged on the outer side arc surface of the second end 12 of the bearing cylinder 1.
In this embodiment, the overall structure of the force-bearing structure of the multi-satellite distributor is a cylindrical section structure, and may also be a conical section structure, and includes a force-bearing cylinder 1, a first internal reinforcing n-shaped frame 21, a second internal reinforcing n-shaped frame 22, a plurality of satellite supporting tables, and the like. The bearing cylinder 1 is a base body of the whole structure, the whole structure adopts a grid structure form, and the grid structure has a high rigidity characteristic, so that the high rigidity requirement of the whole structure can be guaranteed. The outer side of the grid is not covered with skin, so that the requirement of light weight is met; the two inner reinforcing V-shaped frames are respectively arranged on the inner sides of the upper end and the lower end of the bearing cylinder 1, and play a role in reinforcing the circumferential rigidity of the bearing cylinder 1. The first end 11 and the second end 12 (namely the upper end and the lower end) of the bearing cylinder 1 are respectively provided with a plurality of satellite supporting tables which are arranged on the outer side arc surface of the bearing cylinder 1, and the upper satellite supporting table and the lower satellite supporting table form a mounting point and a separating and releasing plane of 1 satellite, so that the use requirement that the bearing structure of the multi-satellite distributor can be simultaneously carried and released by a plurality of satellites is met. The multi-star distributor has the advantages of high bearing structure rigidity, light weight, integrated structure manufacturing, simple assembly, high reliability, good manufacturability and good product consistency.
In an alternative embodiment of the present invention, as shown in fig. 1 to 5, the lattice structure is a slanted lattice structure. The inclined grid structure is a rhombic grid or triangular grid structure with equal edge distance. According to the embodiment, the force bearing cylinder 1 adopts an integral structure in an inclined grid structure form, the inclined grid is in a rhombic grid or triangular grid structure with equal edge distance, and the capacity of bearing axial pressure and integral bending moment is high.
In an alternative embodiment of the invention, as shown in fig. 4, the first end 11 of the carrier tube 1 has a first length of skin structure 41 in the axial direction; the second end 12 of the bearing cylinder 1 is provided with a second section of skin structure 42 along the axial direction; an inclined grid structure 43 without a skin structure is arranged between the first section of skin structure 41 and the second section of skin structure 42 of the force bearing cylinder 1.
In the embodiment, the upper end and the lower end of the bearing cylinder 1 are arranged in a typical skin-inclined grid structure mode, the skins on the two sides of the bearing cylinder 1 only have one section of structure in the axial direction, the middle part of the bearing cylinder 1 is an inclined grid structure without the skins, local structures such as the inclined grid structure and the skins are manufactured in an integrated mode, and carbon fiber composite materials can be selected as manufacturing materials of the product. Because the inclined grating structure has the characteristic of high rigidity, the requirement of the whole structure for high rigidity can be met. Meanwhile, the carbon fiber composite material is adopted, so that the requirement for light weight is met.
As shown in fig. 6 to 10, in an alternative embodiment of the present invention, the grid structure is an orthorhombic grid structure. The orthorhombic grid structure is a rectangular or square grid structure. According to the embodiment, the force bearing cylinder 1 adopts an integral structure in an orthorhombic grid structure form, the orthorhombic grid structure is a rectangular or square grid structure, and the capacity of bearing axial pressure and integral bending moment is strong.
In an alternative embodiment of the invention, as shown in fig. 9, the first end 11 of the carrier tube 1 has a first length of skin structure 41 in the axial direction; the second end 12 of the bearing cylinder 1 is provided with a second section of skin structure 42 along the axial direction; an upright orthogonal grid structure 44 without a skin structure is arranged between the first section of skin structure 41 and the second section of skin structure 42 of the force bearing cylinder 1.
In the embodiment, the upper end and the lower end of the bearing cylinder 1 are arranged in a typical skin-upright orthogonal grid structure mode, the skins on the two sides of the bearing cylinder 1 only have one section of structure in the axial direction, the middle part of the bearing cylinder 1 is of a skin-free upright orthogonal grid structure, local structures such as upright orthogonal grids, skins and the like are manufactured in an integrated mode, and carbon fiber composite materials can be selected as manufacturing materials of products. The orthorhombic grids have the characteristic of high rigidity, so that the requirement of the whole structure on high rigidity can be met. Meanwhile, the carbon fiber composite material is adopted, so that the requirement for light weight is met.
As shown in fig. 1, fig. 2, fig. 6 and fig. 7, in the above embodiment of the present invention, the first inner reinforcing n-shaped frame 21 of the first end 11 of the bearing cylinder 1 with the grid structure is connected to the inner side of the first end 11 of the bearing cylinder 1 by bolts; the second inner reinforcing n-shaped frame 22 of the second end 12 of the bearing cylinder 1 with the grid structure is connected with the inner side of the second end 12 of the bearing cylinder 1 through bolts.
In this embodiment, the first inner reinforcing n-shaped frame 21 and the second inner reinforcing n-shaped frame 22 are respectively installed inside the upper end and the lower end of the bearing cylinder 1 through bolt connection, and play a role in reinforcing the circumferential rigidity of the bearing cylinder 1. Of course, other fastening means may be used for this purpose.
As shown in fig. 1 and fig. 6, in the above embodiment of the present invention, four first satellite support platforms 31 are disposed on the outer circular arc surface of the first end 11 of the bearing cylinder 1;
the four first satellite supporting tables 31 are respectively connected with the outer side arc surface of the first end 11 of the bearing cylinder 1 through bolts, and the four first satellite supporting tables 31 are uniformly distributed on the outer side arc surface of the first end 11 of the bearing cylinder 1.
Four second satellite support platforms 32 are arranged on the outer circular arc surface of the second end 12 of the bearing cylinder 1;
the four second satellite support platforms 32 are respectively connected with the outer side arc surface of the second end 12 of the bearing cylinder 1 through bolts, and the four second satellite support platforms 32 are uniformly distributed on the outer side arc surface of the second end 12 of the bearing cylinder 1.
In this embodiment, the upper and lower end respectively has 4 satellite supporting platforms to install on the outside arc surface of a bearing section of thick bamboo 1 through bolted connection, and two upper and lower satellite supporting platforms constitute 1 satellite 4 point installation and separation release plane, and 4 installation points can set up connection and separation integrated device to realize the user demand that many stars distributor bearing structure can carry on simultaneously, release 4 satellites. Of course, the number of the satellite support platforms can be set according to actual requirements, and the use requirements of a plurality of satellites can be loaded and released at the same time.
In an alternative embodiment of the invention, as shown in fig. 1 to 10, the first end 11 of the carrier tube 1 has a first L-shaped everting frame connected to the adjacent cabin segment; the second end 12 of the bearing cylinder 1 is provided with a second L-shaped outward turned frame connected with the adjacent cabin section.
In the embodiment, the bearing cylinder 1 can be connected with adjacent cabin sections through the L-shaped outward-turning frame, and partial structures such as an inclined grid or a normal orthogonal grid, a skin and the L-shaped outward-turning frame can be integrally manufactured. The manufacturing material is carbon fiber composite material. The requirement of light weight is met while the requirement of rigidity is met.
As shown in fig. 11 and 12, in the above embodiment of the present invention, both the first inner reinforcing frame 21 and the second inner reinforcing frame 22 are axial cylindrical or conical structures. The shape of the bearing cylinder 1 is matched.
The first inner reinforcing n-shaped frame 21 and the second inner reinforcing n-shaped frame 22 have the same structure, and have a first flange structure 211 on one side and a second flange structure 212 on the other side.
The first satellite support platform 31 and the second satellite support platform 32 have the same structure and are both box-shaped thin-walled structures, the first arc-shaped edges of the first satellite support platform 31 and the second satellite support platform 32, which are matched with the bearing cylinder 1, are provided with third flanging structures 311, and the second arc-shaped edges are provided with fourth flanging structures 312;
the first satellite support platform 31 is fixedly connected with the first flanging structure 211 of the first inner reinforcing inverted-V-shaped frame 21 through the third flanging structure 311, and is fixedly connected with the second flanging structure 212 of the first inner reinforcing inverted-V-shaped frame 21 through the fourth flanging structure 312;
the second satellite support platform 32 is fixedly connected with the first flange structure 211 of the second inner reinforcing inverted-V-shaped frame 22 through the third flange structure 311, and is fixedly connected with the second flange structure 212 of the second inner reinforcing inverted-V-shaped frame 22 through the fourth flange structure 312.
The mounting surfaces 313 of the first satellite support platform 31 and the second satellite support platform 32 have at least one mounting hole 314. Preferably, the mounting surface 313 has two mounting holes 314, and the mounting holes 314 are located at ends of the mounting surface 313.
In the embodiment, the two inner reinforcing n-shaped frames are of a typical n-shaped frame turning structure, the whole carbon fiber composite material is adopted for manufacturing, and the inner reinforcing n-shaped frames can be manufactured into an axial cylinder or a cone structure according to the structural appearance of the middle bearing cylinder 1. The flanging structures at two sides of the internal reinforcing inverted V-shaped frame directly correspond to the flanging of the satellite supporting table at the outer side of the bearing cylinder 1 so as to enhance the strength and rigidity of the whole structure.
The satellite support platform is a typical box-shaped thin-wall structure, and the mounting surface 313 is provided with two mounting holes 314 for mounting satellites and the like; the satellite supporting platform is provided with the flanging structure with a bearing cylinder 1 matched arc edge, and the satellite supporting platform is fixedly connected with the bearing cylinder 1 and the inner reinforcing n-shaped frame through the flanging structure on the arc edge. And 4 annular turned-over edges of the satellite support tables can be connected into a whole, so that the integral rigidity of the force bearing cylinder of the multi-satellite distributor is enhanced again.
In the above embodiment of the present invention, the grid structure is not limited to the above inclined grid or orthogonal grid structure, but may be other grid structures capable of ensuring the rigidity requirement of the force-bearing cylinder 1, the force-bearing cylinder 1 having the inclined grid or orthogonal grid structure has the outward turned frames at the upper and lower parts for butt joint, the force-bearing cylinder is in a typical partial skin (no skin at the middle part) -grid structure form, and local structures such as grids, skins, end frames, etc. are manufactured uniformly, and the grid structure has a large rigidity characteristic, so that the large rigidity requirement of the whole structure can be ensured. And the force bearing structure of the multi-star distributor has high rigidity, light weight, integrated structure manufacture, simple assembly, high reliability, good manufacturability and good product consistency.
In the above description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means at least two, e.g., two, three, etc., unless specifically limited otherwise.
In the present invention, unless otherwise expressly stated or limited, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can, for example, be fixedly connected, detachably connected, or integrally formed; can be mechanically connected, electrically connected or can communicate with each other; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.
In the present invention, unless otherwise expressly stated or limited, "above" or "below" a first feature means that the first and second features are in direct contact, or that the first and second features are not in direct contact but are in contact with each other via another feature therebetween. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. The first characteristic "below" the second characteristic,
"below" and "beneath" include the first feature being directly beneath and obliquely below the second feature, or merely indicating that the first feature is at a lesser level than the second feature.
While the foregoing is directed to the preferred embodiment of the present invention, it will be understood by those skilled in the art that various changes and modifications may be made without departing from the spirit and scope of the invention as defined in the appended claims.
Claims (8)
1. A force bearing structure of a multi-star distributor is characterized by comprising: the bearing cylinder (1) is provided with a grid structure, and the grid structure is a non-skin grid structure;
a first inner reinforcing V-shaped frame (21) is arranged at the first end (11) of the bearing cylinder (1), and a second inner reinforcing V-shaped frame (22) is arranged at the second end (12) of the bearing cylinder (1);
at least one first satellite support platform (31) is arranged on the outer side arc surface of the first end (11) of the bearing cylinder (1), and at least one second satellite support platform (32) is arranged on the outer side arc surface of the second end (12) of the bearing cylinder (1);
the grid structure is an inclined grid structure or an orthorhombic grid structure;
the first end (11) of the bearing cylinder (1) is provided with a first section of skin structure (41) along the axial direction;
the second end (12) of the bearing cylinder (1) is provided with a second section of skin structure (42) along the axial direction;
when the grid structure is an inclined grid structure, an inclined grid structure (43) without a skin is arranged between the first section of skin structure (41) and the second section of skin structure (42) of the bearing cylinder (1); the bearing cylinder (1) is characterized in that two side skin shafts of the bearing cylinder (1) are only provided with a section of structure, the middle part of the bearing cylinder (1) is an inclined grid structure without skin, the inclined grid structure and the skin are integrally manufactured, and a product manufacturing material adopts a carbon fiber composite material;
when the grid structure is an orthorhombic grid structure, an orthorhombic grid structure (44) without a skin is arranged between the first section of skin structure (41) and the second section of skin structure (42) of the bearing cylinder (1); the bearing cylinder (1) is characterized in that two sides of skins of the bearing cylinder (1) are only provided with a section of structure in the axial direction, the middle part of the bearing cylinder (1) is of a skin-free orthogonal grid structure, the orthogonal grid and the skins are integrally manufactured, and a product manufacturing material adopts a carbon fiber composite material;
four first satellite supporting tables (31) are arranged on the outer side arc surface of the first end of the bearing cylinder (1); the four first satellite supporting tables (31) are respectively connected with the outer side arc surface of the first end (11) of the bearing cylinder (1) through bolts, and the four first satellite supporting tables (31) are uniformly distributed on the outer side arc surface of the first end (11) of the bearing cylinder (1);
four second satellite support platforms (32) are arranged on the outer side arc surface of the second end (12) of the bearing cylinder (1); the four second satellite support tables (32) are respectively connected with the outer circular arc surface of the second end (12) of the bearing cylinder (1) through bolts, and the four second satellite support tables (32) are uniformly distributed on the outer circular arc surface of the second end (12) of the bearing cylinder (1);
a first satellite supporting platform (31) and a second satellite supporting platform (32) form 1 satellite 4-point installation and separation release plane, and 4 installation points are provided with a connection and separation integrated device.
2. The force-bearing structure of the multi-star distributor of claim 1,
the inclined grating structure is a rhombic grid or triangular grid structure with equal edge distance;
the orthorhombic grid structure is a rectangular or square grid structure.
3. The force-bearing structure of the multi-star distributor of claim 1,
the first inner reinforcing V-shaped frame (21) is connected with the inner side of the first end (11) of the bearing cylinder (1) through a bolt;
the second inner reinforcing V-shaped frame (22) is connected with the inner side of the second end (12) of the bearing cylinder (1) through a bolt.
4. The force-bearing structure of the multi-star distributor of claim 1,
the first end (11) of the bearing cylinder (1) is provided with a first L-shaped outward-turning frame connected with the adjacent cabin section;
the second end (12) of the bearing cylinder (1) is provided with a second L-shaped outward-turned frame connected with the adjacent cabin section.
5. The force-bearing structure of the multi-star distributor as claimed in claim 1, wherein the force-bearing cylinder (1) is an axial cylinder or cone structure, and the first inner reinforcing n-shaped frame (21) and the second inner reinforcing n-shaped frame (22) are both axial cylinder or cone structures.
6. The force-bearing structure of the multi-star distributor as claimed in claim 1, wherein the first inner reinforcing n-shaped frame (21) and the second inner reinforcing n-shaped frame (22) are provided with a first flanging structure (211) on one side and a second flanging structure (212) on the other side.
7. The force-bearing structure of the multi-satellite distributor according to claim 6, wherein the first satellite support platform (31) and the second satellite support platform (32) are both box-type thin-walled structures, a third flanging structure (311) is arranged on a first arc-shaped edge of the first satellite support platform (31) and the second satellite support platform (32) which are matched with the force-bearing cylinder (1), and a fourth flanging structure (312) is arranged on a second arc-shaped edge;
at least one first satellite support platform (31) is fixedly connected with a first flanging structure (211) of the first inner reinforcing inverted-V-shaped frame (21) through a third flanging structure (311) and is fixedly connected with a second flanging structure (212) of the first inner reinforcing inverted-V-shaped frame (21) through a fourth flanging structure (312);
at least one second satellite support platform (32) is fixedly connected with a first flanging structure (211) of the second internal reinforcing inverted-V-shaped frame (22) through a third flanging structure (311) and is fixedly connected with a second flanging structure (212) of the second internal reinforcing inverted-V-shaped frame (22) through a fourth flanging structure (312).
8. The force-bearing structure of the multi-satellite distributor as claimed in claim 7, wherein the mounting surfaces (313) of the first satellite support platform (31) and the second satellite support platform (32) are provided with at least one mounting hole (314).
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| CN202010420938.4A CN111532452B (en) | 2020-05-18 | 2020-05-18 | Force bearing structure of multi-star distributor |
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| CN202010420938.4A CN111532452B (en) | 2020-05-18 | 2020-05-18 | Force bearing structure of multi-star distributor |
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| US11802606B2 (en) | 2020-05-18 | 2023-10-31 | The Boeing Company | Planate dynamic isolator |
| US11827389B2 (en) | 2020-05-18 | 2023-11-28 | The Boeing Company | Additively manufactured satellite |
| US11542041B2 (en) | 2020-05-18 | 2023-01-03 | The Boeing Company | Additively manufactured satellite panel with damping |
| AU2021273575A1 (en) | 2020-12-17 | 2022-07-07 | The Boeing Company | Satellite thermal enclosure |
| AU2021273577A1 (en) * | 2020-12-17 | 2022-07-07 | The Boeing Company | Stacked satellite assemblies and related methods |
| RU210094U1 (en) * | 2021-12-15 | 2022-03-28 | Акционерное общество "Информационные спутниковые системы" имени академика М.Ф. Решетнёва" | POWER STRUCTURE FOR ONBOARD EQUIPMENT OF SPACE VEHICLE |
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| DE19856670B4 (en) * | 1998-12-09 | 2004-12-02 | Eads Space Transportation Gmbh | Satellite launching device |
| CN103072704A (en) * | 2011-10-26 | 2013-05-01 | 上海卫星工程研究所 | Aluminum alloy riveted bearing cylinder for installing 200L propellant storage box |
| CN103738509A (en) * | 2014-01-21 | 2014-04-23 | 北京航空航天大学 | Novel multi-satellite separating, unlocking and releasing device |
| US10486837B2 (en) * | 2015-06-22 | 2019-11-26 | Worldvu Satellites Limited | Payload dispensing system |
| CN109850186B (en) * | 2019-02-28 | 2021-02-09 | 中国空间技术研究院 | Plate frame type satellite structure for one-rocket multi-satellite parallel transmission and assembly method |
| CN110104213B (en) * | 2019-04-23 | 2022-08-12 | 上海宇航系统工程研究所 | Wall-mounted satellite adapter |
| CN110395408B (en) * | 2019-07-03 | 2020-11-20 | 北京空间飞行器总体设计部 | Interface structure of grid type force bearing structure |
-
2020
- 2020-05-18 CN CN202010420938.4A patent/CN111532452B/en active Active
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Address after: 300000 No.2 workshop of high power bulldozer, No.18 Yingchun Road, Huaming hi tech Industrial Zone, Dongli District, Tianjin Patentee after: Tianjin istar-space Technology Co.,Ltd. Patentee after: Tianjin aisida New Material Technology Co.,Ltd. Patentee after: Beijing aistar Aerospace Technology Co.,Ltd. Address before: 300000 No.2 workshop of high power bulldozer, No.18 Yingchun Road, Huaming hi tech Industrial Zone, Dongli District, Tianjin Patentee before: SUZHOU ISTAR AVIATION TECHNOLOGY Co.,Ltd. Patentee before: Tianjin aisida New Material Technology Co.,Ltd. Patentee before: Beijing aistar Aerospace Technology Co.,Ltd. |