CN112208792A - Satellite standard structure and frame construction - Google Patents
Satellite standard structure and frame construction Download PDFInfo
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- CN112208792A CN112208792A CN201910629362.XA CN201910629362A CN112208792A CN 112208792 A CN112208792 A CN 112208792A CN 201910629362 A CN201910629362 A CN 201910629362A CN 112208792 A CN112208792 A CN 112208792A
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- 239000002360 explosive Substances 0.000 claims abstract description 8
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- 230000003014 reinforcing effect Effects 0.000 claims description 10
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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Abstract
The invention discloses a satellite standard structure and a frame structure, and relates to the technical field of satellite structure design. One embodiment of the satellite standard architecture comprises: the ejection mechanism comprises a main frame and at least one group of ejection assemblies; wherein, launch the subassembly and install on the bottom surface or side or the top surface of main frame, include: the ejector comprises an ejector adapter seat, an unlocking seat, an explosion bolt or a separation nut and an ejector seat; the catapult adapter is arranged on the bottom surface or the side surface or the top surface of the main frame and used for installing the catapult adapter on the main frame; the unlocking seat is assembled on the ejection seat; the explosive bolt or the separation nut is arranged on the unlocking seat and is used for being connected with the main frame of other satellite frame structures. The satellite standard structure can be used for conveniently splicing required structural space, and the trouble of designing a personalized structure for each satellite is avoided; the frame structure of the invention adopts the mode of mutual connection and mutual reinforcement among satellites, thus saving the weight consumed by independently supporting the satellite structure.
Description
Technical Field
The invention relates to the technical field of satellite structure design, in particular to a satellite standard structure and a frame structure.
Background
In the satellite frame structure in the prior art, a plurality of satellites are positioned in a fairing, generally, each satellite is arranged on a public supporting structure, each satellite is not connected with each other, and the satellites enter an orbit and are respectively released to the outer space.
In the process of implementing the invention, the inventor finds that at least the following problems exist in the prior art:
(1) the current small and medium-sized satellites (20kg to 200kg) have no standard structure, and each company needs to design the satellite structure independently, so that manpower and material resources are consumed;
(2) when a plurality of satellites are launched into orbit simultaneously, each satellite needs to be supported separately in a fairing of the carrier rocket, so that the space in the fairing is occupied, a large amount of redundant support structures generate large weight, the launching cost of the carrier rocket is about 2 ten thousand dollars/kg, and the redundant weight consumes millions of dollars.
Disclosure of Invention
In view of this, embodiments of the present invention provide a satellite standard structure and a frame structure, and the satellite standard structure of the present invention can be used to conveniently splice a required structural space, thereby avoiding the trouble of designing a personalized structure for each satellite; the frame structure of the invention adopts the mode of mutual connection and mutual reinforcement among satellites, thus saving the weight consumed by independently supporting the satellite structure.
According to a first aspect of embodiments of the present invention, there is provided a satellite standard architecture, comprising: the ejection mechanism comprises a main frame and at least one group of ejection assemblies; wherein, launch the subassembly and install on the bottom surface or side or the top surface of main frame, include: the ejector comprises an ejector adapter seat, an unlocking seat, an explosion bolt or a separation nut and an ejector seat;
the catapult adapter is arranged on the bottom surface or the side surface or the top surface of the main frame and used for installing the catapult adapter on the main frame; the unlocking seat is assembled on the ejection seat; the explosive bolt or the separation nut is arranged on the unlocking seat and is used for being connected with the main frame of other satellite frame structures.
Optionally, two corners of a diagonal line of the bottom surface of the main frame are respectively provided with a group of ejection assemblies; a group of ejection assemblies are arranged on the side face of the main frame.
Optionally, the top surface of the main frame is provided with a mounting seat and/or a reinforcing seat; the mounting seat is used for being connected with ejection assemblies of other satellite frame structures; the reinforcing seat is used for reinforcing a main frame of the satellite frame structure.
Optionally, the main frame comprises: a vertical frame and a cross beam; wherein, a plurality of grudging posts are parallel to each other, are equipped with a crossbeam between the top of two adjacent grudging posts and between the bottom.
Optionally, the main frame further comprises: the auxiliary cross beam and/or the auxiliary longitudinal beam are arranged on the main frame; the auxiliary cross beam is parallel to the cross beam in the main frame;
the auxiliary longitudinal beams are parallel to the upright frames in the main frame.
Optionally, the auxiliary cross beam and/or the auxiliary longitudinal beam has a T-shaped structure.
Optionally, mounting holes are formed in the vertical frames, the cross beams, the auxiliary cross beams and the auxiliary longitudinal beams at intervals of preset distances.
Optionally, the predetermined distance is 50mm or 25 mm.
According to a second aspect of embodiments of the present invention, there is provided a satellite frame structure, including: the satellite standard structure comprises at least one layer of satellite standard structure group, wherein each layer of satellite standard structure group comprises at least one satellite standard structure, a main frame of each satellite standard structure is a cuboid structure, and the at least one satellite standard structure adopts a right-angle structure architecture; the side surfaces of two adjacent satellite standard structures on the same layer are connected through an ejection assembly, and the bottom of the satellite standard structure on the upper layer is connected with the top of the satellite standard structure on the lower layer through the ejection assembly.
According to a third aspect of embodiments of the present invention, there is provided another satellite frame structure, including: the satellite standard structure comprises at least one layer of satellite standard structure group, wherein each layer of satellite standard structure group comprises at least one satellite standard structure, a main frame of each satellite standard structure is a cuboid structure, and the at least one satellite standard structure adopts a right-angle structure architecture; the bottom of the upper layer of satellite standard structure is connected with the top of the lower layer of satellite standard structure through an ejection assembly, and the tops of the top layer of satellite standard structures are connected through a connecting piece.
One embodiment of the above invention has the following advantages or benefits: the ejection assembly connected with the main frame of other satellite frame structures is arranged on the bottom surface or the side surface or the top surface of the main frame, so that a user can conveniently splice required structural space by adopting the standard satellite structure, and the trouble of designing a personalized structure for each satellite is avoided; the frame structure of the invention adopts the mode of mutual connection and mutual reinforcement among satellites, thus saving the weight consumed by independently supporting the satellite structure.
Further effects of the above-mentioned non-conventional alternatives will be described below in connection with the embodiments.
Drawings
The drawings are included to provide a better understanding of the invention and are not to be construed as unduly limiting the invention. Wherein:
FIG. 1 is an exploded view of a standard architecture of a satellite according to an embodiment of the present invention;
FIG. 2 is a front view of a satellite standard architecture according to an embodiment of the present invention;
FIG. 3 is a top view of a satellite standard architecture according to an embodiment of the present invention;
FIG. 4 is a left side view of a satellite standard architecture according to an embodiment of the present invention;
FIG. 5 is a perspective view of a satellite standard architecture according to an embodiment of the present invention;
FIG. 6 is a front view of an auxiliary beam in a satellite standard architecture according to an embodiment of the present invention;
FIG. 7 is a top view of an auxiliary beam in a satellite standard architecture according to an embodiment of the present invention;
FIG. 8 is a left side view of an auxiliary beam in a satellite standard architecture according to an embodiment of the present invention;
FIG. 9 is a top view of a satellite frame structure according to a first embodiment of the present invention;
fig. 10 is a front view of a satellite frame structure in a first embodiment of the present invention;
fig. 11 is a perspective view of a satellite frame structure in a first embodiment of the present invention;
fig. 12 is a perspective view of a satellite frame structure in a second embodiment of the present invention.
Detailed Description
Exemplary embodiments of the present invention are described below with reference to the accompanying drawings, in which various details of embodiments of the invention are included to assist understanding, and which are to be considered as merely exemplary. Accordingly, those of ordinary skill in the art will recognize that various changes and modifications of the embodiments described herein can be made without departing from the scope and spirit of the invention. Also, descriptions of well-known functions and constructions are omitted in the following description for clarity and conciseness.
At present, medium and small satellites (20kg to 200kg) have no standard structure, and each company needs to design the satellite structure independently, so that manpower and material resources are consumed. In view of this, the embodiment of the present invention provides a satellite standard structure.
Fig. 1-5 are schematic diagrams of a satellite standard architecture according to an embodiment of the present invention, and as shown in fig. 1, a satellite standard architecture 100 according to an embodiment of the present invention includes: a main frame 10 and at least one set of ejection assemblies 20; wherein the ejection assembly 20 is mounted on the bottom surface or the side surface of the main frame 10. For example, when two satellite standards are stacked one on top of the other, the ejection assembly of the upper satellite standard can be mounted on the bottom surface of the main frame; for another example, when two satellite standards are arranged side-to-side, the ejection assembly of the left satellite standard may be mounted on the right side of its main frame. The ejection assembly 20 includes: the ejector comprises an ejector adapter 5, an unlocking seat 6, an explosion bolt or a separation nut 7 and an ejector seat 8; the catapult adapter 5 is arranged on the bottom surface or the side surface or the top surface of the main frame 10 and is used for installing the catapult adapter 8 on the main frame 10; the unlocking seat 6 is assembled on the ejection seat 8, so that a certain supporting height can be realized; an explosive bolt or a separation nut 7 is provided on the unlocking seat 6 for connection with the main frame of the other satellite frame structure. The centre of the explosive bolt is filled with explosive, and when detonated, the explosive bolt 7 will be exploded into two sections, thereby forming separation of the two ends of the bolt. The separation nut is filled with explosive, and the nut is burst after detonation, so that the bolt screwed into the nut can be removed from the nut.
According to the invention, the ejection assembly connected with the main frame of other satellite frame structures is arranged on the bottom surface or the side surface of the main frame, so that a user can conveniently splice required structural space by adopting the standard satellite structure of the invention, and the trouble of designing a personalized structure for each satellite is avoided; when the satellite frame structure is constructed by adopting the satellite standard structure of the embodiment of the invention, the satellites are mutually connected and mutually strengthened, so that the weight consumed by independently supporting the satellite structure is saved, and the cost of satellite launching is greatly reduced.
The mounting position of the ejection assemblies 20 on the bottom surface, the side surface or the top surface of the main frame 10, and the number of the ejection assemblies 20 can be selectively set according to actual conditions. The ejection assembly 20 is arranged on the top surface of the main frame 10, and can connect the top surface of the satellite standard structure with other satellite standard structures; the ejection assembly 20 is arranged on the side surface of the main frame 10, and can connect the side surface of the satellite standard structure with other satellite standard structures; the ejector unit 20 is provided on the bottom surface of the main frame 10, and can connect the bottom surface of the satellite standard structure to another satellite standard structure. In the practical application process, the technical personnel can flexibly set according to the practical situation so as to flexibly splice the satellite frame structure for transmitting a plurality of satellites by adopting the satellite standard structure.
In some embodiments, the main frame 10 is a rectangular parallelepiped frame, one ejection assembly 20 is mounted at each of four corners of a bottom surface of the rectangular parallelepiped frame, and one ejection assembly 20 is mounted on one of side surfaces of the rectangular parallelepiped frame; in other embodiments, one ejection assembly 20 is mounted on each side of the rectangular parallelepiped frame, so that a satellite frame structure with a plurality of satellite standard structures connected with each other by taking the rectangular parallelepiped frame as a center can be realized. In an alternative embodiment shown in fig. 1-5, a group of ejection assemblies 20 are respectively disposed at two corners of a diagonal line of the bottom surface of the main frame 10; a group of ejection assemblies 20 are provided on the side of the main frame 10. Through being equipped with a set of subassembly 20 that launches respectively in two corners on the bottom diagonal, can reduce the weight of satellite standard architecture on the basis of guaranteeing to connect and support stability, and then reduce satellite launch cost.
The main frame 10 may further have a mounting seat 91 and/or a reinforcing seat 92 on the top surface thereof; the mounting seat 91 is used for connecting with ejection assemblies of other satellite frame structures; the reinforcing seat 92 is used to reinforce the main frame 10 of the satellite frame structure. In practice, the location and number of the mounting seats 91 and/or the reinforcing seats 92 on the main frame 10 may depend on the configuration and number of other satellite standard structures connected around it. As shown in fig. 1-4, two diagonal corners of the four corners of the top surface of the main frame are provided with mounting seats 91, and two diagonal corners of the top surface of the main frame are provided with reinforcing seats 92, so that the satellite standard structure can be arranged at a lower layer when being connected with other satellite standard structures, the bottom surface of the upper layer of satellite standard structure is provided with ejection assemblies 20 corresponding to the diagonal corners, and the connection between the upper layer of satellite standard structure and the lower layer of satellite standard structure is realized through the ejection assemblies at the bottom surface of the upper layer of satellite standard structure and the mounting seats at the top surface of the lower layer of satellite standard structure. As shown in fig. 5, reinforcing seats are disposed at four corners of the top surface of the main frame, and the satellite standard structure may be connected with other satellite standard structures to form a single-layer satellite frame structure, or may be located at the top layer of the frame structure when being connected with other satellite standard structures to form a multi-layer satellite frame structure.
The shape of the main frame 10 may be selectively set according to actual conditions, for example, a fan-shaped structure or a rectangular parallelepiped structure. The main frame 10 may include: a vertical frame 1 and a cross beam 2; wherein, a plurality of grudging posts 1 are parallel to each other, are equipped with a crossbeam 2 between the top of two adjacent grudging posts 1 and between the bottom. For example, the main frame 10 is a rectangular parallelepiped structure, and includes four upright frames 1 and eight cross beams 2; for another example, the main frame is a triangular prism structure, and includes three upright frames 1 and 6 cross beams 2. The main frame structure comprising the vertical frame and the cross beam is adopted, the structure is simple, and the weight is light.
The main frame 10 may further include: auxiliary cross beams 3 and/or auxiliary longitudinal beams 4 provided on the main frame 10; wherein the auxiliary cross beam 3 is parallel to the cross beam 2 in the main frame 10; the auxiliary longitudinal beams 4 are parallel to the upright frame 1 in the main frame 10. By adjusting the installation positions of the auxiliary cross beam 3 and the auxiliary longitudinal beam 4 on the vertical frame 1 and the cross beam 2, the three-dimensional space with any side length in the satellite standard structure can be realized, and the installation and fixation requirements of products in the satellite standard structure are flexibly met. The structure of the auxiliary cross beam 3 and/or the auxiliary longitudinal beam 4 can be selectively set according to actual requirements, for example, a flat plate structure, an L-shaped structure or a T-shaped structure is adopted. In an alternative embodiment shown in fig. 6-8, the auxiliary beam 3 is in a T-shaped structure, wherein 31 represents a body of the T-shaped structure, 32 represents a protrusion disposed on the body 31, and the body 31 and the protrusion 32 form the T-shaped structure. Alternatively, the upright frames 1, the cross beams 2, the auxiliary cross beams 3 and the auxiliary longitudinal beams 4 may be provided with mounting holes at intervals of a preset distance. The size of the preset distance can be selectively set according to actual conditions, for example, the preset distance is 50mm or 25 mm. The installation holes are formed, so that the installation positions of the auxiliary cross beam 3 and the auxiliary longitudinal beam 4 on the vertical frame 1 and the cross beam 2 can be conveniently adjusted, and the cubic space with any length of 50mm or 25mm integral multiple in the satellite standard structure can be realized. The standard frame and the standard auxiliary beam are designed to flexibly meet the installation and fixation of products in the satellite structure body.
A single satellite standard architecture may employ a 3:3:4 ratio length to width high architecture, with typical values of 600mm x 800mm and 450mm x 600 mm. In the practical application process, a plurality of satellite standard structures can be vertically arranged, namely, the side surface of one satellite standard structure is connected with the side surface of the adjacent satellite standard structure through an ejection assembly; the satellite standard structures may also be positioned laterally, i.e., the top surface of one satellite standard structure is connected to the side surface of another satellite standard structure by a catapult assembly.
The satellite standard structure can be conveniently used by users, and the users do not need to carry out independent structural design aiming at each satellite. In addition, the standard satellite structure can meet the requirements of different small and medium-sized satellites on structure size and rigidity strength, and is very suitable for networking a plurality of satellites.
According to a second aspect of embodiments of the present invention, there is provided a satellite frame structure, including: the satellite standard structure comprises at least one layer of satellite standard structure group, wherein each layer of satellite standard structure group comprises at least one satellite standard structure, a main frame of each satellite standard structure is a cuboid structure, and the at least one satellite standard structure adopts a right-angle structure architecture; the side surfaces of two adjacent satellite standard structures on the same layer are connected through an ejection assembly, and the bottom of the satellite standard structure on the upper layer is connected with the top of the satellite standard structure on the lower layer through the ejection assembly.
In some embodiments, the satellite frame structure comprises a layer of satellite standard structure group, the group of satellite standard structure group comprises a plurality of satellite standard structures, and two adjacent satellite standard structure sides are connected through the ejection assembly.
In other embodiments, the satellite frame structure comprises a plurality of layers of satellite standard structure groups, each layer of satellite standard structure group comprises one satellite standard structure, and the bottom of the satellite standard structure in the upper layer is connected with the top of the satellite standard structure in the lower layer through the ejection assembly.
Of course, the satellite frame structure may also include a plurality of layers of satellite standard structure groups, each layer of satellite standard structure group includes a plurality of satellite standard structures, the side surfaces of two adjacent satellite standard structures on the same layer are connected through an ejection assembly, and the bottom of the satellite standard structure on the upper layer is connected with the top of the satellite standard structure on the lower layer through the ejection assembly.
As shown in fig. 9-11, the satellite frame structure includes three layers of satellite standard structure groups, each layer of satellite standard structure group includes four satellite standard structures, the main frame of each satellite standard structure is a cuboid structure, the four satellite standard structures on the same layer adopt right-angle structures (2 × 2 placement, namely two satellite standard structures on the horizontal direction and two satellite standard structures on the vertical direction), two adjacent satellite standard structure sides on the same layer are connected through an ejection assembly, and the bottom of the satellite standard structure on the upper layer is connected with the top of the satellite standard structure on the lower layer through the ejection assembly. In this embodiment, 2 × 2 and 4 satellite standard structures are placed in each layer, or 3 × 3 and 9 cube structures may be placed in each layer.
At present, for the situation that a plurality of satellites are launched and put into orbit simultaneously, a mode of carrying out independent structural support on each satellite is adopted, the independent support structure in the mode occupies large weight and consumes launching cost, and the invention adopts a mode of mutually connecting and mutually reinforcing the standard satellite structures, thereby saving the weight consumed by independently supporting the satellite structures. The satellite standard structure can be used for conveniently splicing required structural space, and the trouble of designing a personalized structure for each satellite is avoided.
According to a third aspect of embodiments of the present invention, there is provided another satellite frame structure, including: the satellite standard structure comprises at least one layer of satellite standard structure group, wherein each layer of satellite standard structure group comprises at least one satellite standard structure, a main frame of each satellite standard structure is a cuboid structure, and the at least one satellite standard structure adopts a right-angle structure architecture; the bottom of the upper layer of satellite standard structure is connected with the top of the lower layer of satellite standard structure through an ejection assembly, and the tops of the top layer of satellite standard structures are connected through a connecting piece.
In some embodiments, the satellite frame structure comprises a layer of satellite standard structure group, the group of satellite standard structure group comprises a plurality of satellite standard structures, and two adjacent satellite standard structure sides are connected through the ejection assembly.
In other embodiments, the satellite frame structure comprises a plurality of layers of satellite standard structure groups, each layer of satellite standard structure group comprises one satellite standard structure, and the bottom of the satellite standard structure in the upper layer is connected with the top of the satellite standard structure in the lower layer through the ejection assembly.
Of course, the satellite frame structure may also include a plurality of layers of satellite standard structure groups, each layer of satellite standard structure group includes a plurality of satellite standard structures, the side surfaces of two adjacent satellite standard structures on the same layer are connected through an ejection assembly, and the bottom of the satellite standard structure on the upper layer is connected with the top of the satellite standard structure on the lower layer through the ejection assembly.
As shown in fig. 12, the satellite frame structure includes three layers of satellite standard structure groups, each layer of satellite standard structure group includes four satellite standard structures, the main frame of each satellite standard structure is a cuboid structure, the four satellite standard structures on the same layer adopt right-angle structures (2 x 2 is placed, namely, two satellite standard structures on the horizontal direction, two satellite standard structures on the vertical direction), two adjacent satellite standard structure sides on the same layer are connected through an ejection assembly, the bottom of the satellite standard structure on the upper layer is connected with the top of the satellite standard structure on the lower layer through an ejection assembly, and the tops of the satellite standard structures on the top layer are connected through a connecting piece. In this embodiment, 2 × 2 and 4 satellite standard structures are placed in each layer, or 3 × 3 and 9 cube structures may be placed in each layer.
According to the technical scheme of the embodiment of the invention, the ejection assembly connected with the main frame of other satellite frame structures is arranged on the bottom surface or the side surface or the top surface of the main frame, so that a user can conveniently splice required structural space by adopting the standard satellite structure of the invention, and the trouble of designing a personalized structure for each satellite is avoided; the frame structure of the invention adopts the mode of mutual connection and mutual reinforcement among satellites, thus saving the weight consumed by independently supporting the satellite structure.
The above-described embodiments should not be construed as limiting the scope of the invention. Those skilled in the art will appreciate that various modifications, combinations, sub-combinations, and substitutions can occur, depending on design requirements and other factors. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (10)
1. A satellite standard architecture (100), comprising: a main frame (10) and at least one set of ejection assemblies (20); wherein, launch subassembly (20) and install on the bottom surface or side or the top surface of main frame (10), include: the ejector comprises an ejector adapter (5), an unlocking seat (6), an explosion bolt or a separation nut (7) and an ejection seat (8);
the catapult adapter (5) is arranged on the bottom surface or the side surface or the top surface of the main frame (10) and is used for installing the catapult adapter (8) on the main frame (10); the unlocking seat (6) is assembled on the ejection seat (8); the explosive bolt or the separation nut (7) is arranged on the unlocking seat (6) and is used for being connected with the main frame of other satellite frame structures.
2. The satellite substructure (100) of claim 1, wherein a set of said ejection assemblies (20) are disposed at each of two corners of a diagonal of a bottom surface of said main frame (10); a group of ejection assemblies (20) are arranged on the side surface of the main frame (10).
3. Satellite substructure (100) according to claim 1, characterized in that the main frame (10) is provided on its top side with mounting seats (91) and/or reinforcement seats (92);
the mounting seat (91) is used for connecting with an ejection assembly of other satellite frame structures;
the reinforcement socket (92) is used for reinforcing a main frame (10) of a satellite frame structure.
4. A satellite substructure (100) according to any of claims 1 to 3, characterized in that the main frame (10) comprises: a vertical frame (1) and a cross beam (2); wherein, a plurality of grudging posts (1) are parallel to each other, are equipped with a crossbeam (2) between the top of two adjacent grudging posts (1) and between the bottom.
5. The satellite substructure (100) of claim 4, wherein the main frame (10) further comprises: an auxiliary cross beam (3) and/or an auxiliary longitudinal beam (4) arranged on the main frame (10); wherein the auxiliary cross beam (3) is parallel to the cross beam (2) in the main frame (10);
the auxiliary longitudinal beam (4) is parallel to the vertical frame (1) in the main frame (10).
6. Satellite substructure (100) according to claim 5, characterized in that the auxiliary transverse girders (3) and/or the auxiliary longitudinal girders (4) have a T-shaped configuration.
7. The satellite modular structure (100) according to claim 5, characterized in that the uprights (1), the cross-members (2), the auxiliary cross-members (3) and the auxiliary longitudinal-members (4) are provided with mounting holes at predetermined intervals.
8. The satellite standard architecture (100) of claim 7, wherein the predetermined distance is 50mm or 25 mm.
9. A satellite frame structure, comprising: at least one layer of satellite standard structure group, wherein each layer of satellite standard structure group comprises at least one satellite standard structure which adopts a right-angle structure architecture; the side surfaces of two adjacent satellite standard structures on the same layer are connected through an ejection assembly, and the bottom of the satellite standard structure on the upper layer is connected with the top of the satellite standard structure on the lower layer through the ejection assembly.
10. A satellite frame structure, comprising: at least one layer of satellite standard structure group, wherein each layer of satellite standard structure group comprises at least one satellite standard structure which adopts a right-angle structure architecture; the bottom of the upper layer of satellite standard structure is connected with the top of the lower layer of satellite standard structure through an ejection assembly, and the tops of the top layer of satellite standard structures are connected through a connecting piece.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113879561A (en) * | 2021-11-16 | 2022-01-04 | 北京微纳星空科技有限公司 | CubeSat Platform and CubeSat |
| CN117622518A (en) * | 2023-12-20 | 2024-03-01 | 北华航天工业学院 | Main structure device of spacecraft platform |
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| CN108791956A (en) * | 2018-08-23 | 2018-11-13 | 西北工业大学 | A kind of cube star plug and play reed-type structural module package assembly and method |
| CN210592491U (en) * | 2019-07-12 | 2020-05-22 | 北京前沿探索深空科技有限公司 | Satellite standard structure and frame construction |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN113879561A (en) * | 2021-11-16 | 2022-01-04 | 北京微纳星空科技有限公司 | CubeSat Platform and CubeSat |
| CN113879561B (en) * | 2021-11-16 | 2022-09-16 | 北京微纳星空科技有限公司 | Cube star platform and cube star |
| CN117622518A (en) * | 2023-12-20 | 2024-03-01 | 北华航天工业学院 | Main structure device of spacecraft platform |
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