CN112124627A - Flexible satellite platform structure - Google Patents
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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
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/223—Modular spacecraft systems
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Abstract
The invention discloses a flexible satellite platform structure which is obtained by transversely and/or longitudinally expanding basic configuration. The basic configuration is a polygonal prism composed of joints and rod pieces, wherein the joints are polyhedrons with parallel bottom surfaces, grooves are arranged at the center of each surface of each polyhedron and used for connecting the rod pieces, each rod piece comprises a transverse rod piece and a longitudinal rod piece, the transverse rod pieces are connected to the side surfaces of the joints, and the longitudinal rod pieces are connected to the top surfaces and the bottom surfaces of the joints.
Description
Technical Field
The invention relates to the field of aerospace, in particular to a flexible satellite platform structure.
Background
With the vigorous development of the aerospace industry, all countries in the world actively develop own satellites, and China is the second largest aerospace country except the United states, and at present, more than three hundred artificial satellites are successfully launched in China. In view of the development of aerospace in recent years, commercialization of satellites is gradually being developed, and a satellite base consisting of hundreds of small satellites is increasingly sought.
Towards commercialization, the development and production of a single satellite configuration cannot adapt to the current development situation of a commercial satellite, and the shaped mass production of the satellite is undoubtedly the optimal way for shortening the period and reducing the cost, but the applied satellite has the characteristics of multiple types and small quantity, particularly, the types of effective loads are various, the requirements are different, and the mass production is difficult to realize.
Aiming at the problem, in the development of the satellite, the platform and the payload can be treated differently, and the platform is standardized as far as possible, so that the platform has universality on the payload in a certain range. At present, some famous space manufacturers provide different series of satellite public platforms for satellites with different purposes, so as to form a universal, serialized and modularized satellite platform product in a true sense. The method is based on a satellite common platform and spot products, and basically realizes the quasi-assembly line work of satellite model development and production, and the model development process is a process of mainly purchasing goods shelf products to carry out system rapid integration innovation. The method has the advantages that the development period is controlled and shortened, the product quality and reliability are guaranteed, the risk of projects is reduced, and great economic, military and social benefits are generated. For example, in the near 20 satellite platforms of the wave-sound BSS-301-393 series, the most successful is the BSS-376 satellite platform, the satellite platform is used for transmitting 60 satellites from the first transmission in 1980 to 2003, and the BSS-702 series satellite platform is proposed at present, the high-power BSS-702HP, the medium-power BSS-702MP and the full-electric propulsion BSS-702SP are developed, the available power range is 3-18 kW, and the maximum transmission quality of the satellite reaches 6116 kg. HS376, HS601, HS60lHP and HS702, large platforms of houss, usa, which are common platforms for geostationary orbit spin stabilized satellites; a2100 large platform of Rockschid Martin is a mainstream satellite platform which is introduced by a new generation of high-power and large-capacity geostationary orbit communication satellite, the design life is 15 years, and the power can be expanded to 15 kW. The main body of the device is of a box plate type structure, adopts a modular design, and supports various communication payloads such as moving, fixing and broadcasting; SpaceBus series from Aerosapatiale, France: SB-100, SB-100B, SB-2000 and SB-3000 can carry 150-650kg payload, respectively, provide 1500-3500W power, have a working life of 7-15 years, and have been used for DFS, Arabsat, Eutelsat, Turksat, TV-Sat (TDF) and Tele-X30, respectively, for a plurality of satellites; an MK public platform series is developed by French Matar company, an MK-1 public platform can carry 800-1100kg of effective load, provide 130-220w of power, carry 100-30kg of propellant and have a working life of 2-3 years and is used for satellites such as SPOT-1, SPOT-2, SPOT-3, ERS-1, ERS-2 and the like; the MK-2 public platform can carry 1700kg of payload, provides 5200w of power, has the service life of 5 years, and is already used for developing SPOT-4, SPOT-5, HELIOS and other satellites; fantay Rez-Alaniya developed two advanced multipurpose microsatellite platforms, "the Haishen" and the Italy Multi-application reconfigurable platform "(PRIMA). Among them, the "naval" satellite platform has been widely adopted by the "Globalstar" (Globalstar) constellation, the O3b constellation, the "Iridium" (Iridium) constellation, etc., with excellent performance after being modified, and so on.
The research on the public platform is started at present in China, and the Chinese space technology research institute has 4 public platforms which are subjected to or basically obtained through space flight tests: DJS-1, TTS-1, FWS-2 and CAST968, which are suitable for the development of medium and small satellites, and 2 new common platforms DJS-2 and TTS-2 for large and medium satellites are being developed. Although China has preliminarily formed a satellite public platform series type spectrum, the coverage of the type spectrum is not complete enough, the comprehensive technical capability has a certain gap, the degree of commercialization and generalization is low, the technology upgrade is slow, and the model development cost, the period and the market competitiveness are influenced.
Disclosure of Invention
Aiming at some or all problems in the prior art, the invention provides a flexible satellite platform structure, the basic configuration of which is a polygonal prism, the basic configuration consists of a joint and a rod piece, wherein:
the joint is a polyhedron, and grooves are uniformly arranged on each surface, wherein,
the top surface and the bottom surface of the joint are polygons with the same shape, and the top surfaces are parallel
On the bottom surface; and
each side surface is vertical to the top surface and the bottom surface;
the end part of the transverse rod is matched with the groove on the side surface in shape, the transverse rod is used for connecting a joint to form a polygon, and a boss is arranged on the transverse rod and used for connecting a honeycomb plate to install single-machine equipment; and
the end of the longitudinal rod is matched with the groove on the top surface and/or the bottom surface of the joint in shape, the longitudinal rod is used for vertically connecting the polygons to form a polygonal column body, and a boss is arranged on the longitudinal rod and used for connecting a honeycomb plate to install single equipment.
In the present invention, the term "basic configuration" refers to the main frame or main structure of the satellite. The expression "the basic configuration is polygonal" means that the main frame or structure of the satellite is prismatic, i.e. a geometry with parallel and congruent upper and lower base surfaces and parallel and equal lateral edges.
Further, the basic configuration is a hexagonal prism comprising 12 joints, 12 transverse bars and 6 longitudinal bars, wherein the joints are octahedral.
Further, the transverse rod piece and the longitudinal rod piece are of hollow structures.
Further, the transverse rods and the longitudinal rods are made of aluminum alloy and/or magnesium alloy and/or silicon carbide and/or carbon fiber.
Further, two ends of the transverse rod piece and/or the longitudinal rod piece are provided with first bosses, and the distance between each first boss and the end of the transverse rod piece and/or the end of the longitudinal rod piece is smaller than or equal to the depth of the groove, so that the first bosses can be in contact with the surface of the joint.
Further, first boss is provided with first through-hole, just first boss pass through the screw with connect fixed connection.
Further, the flexible satellite platform structure is a single-layer structure, and the single-layer structure is obtained by performing transverse expansion by taking a basic configuration as a center.
Furthermore, the flexible satellite platform structure is a two-layer structure, wherein the upper layer is a load cabin, the lower layer is a platform cabin, and the bottom surface of the load cabin and the top surface of the platform cabin share one plane.
Further, the load compartment and/or the platform compartment are/is obtained by taking the basic configuration as the center and performing transverse expansion.
According to the flexible satellite platform structure, the hexagonal prism structure is preferably selected as the basic configuration, the space of the fairing can be effectively utilized, the rod pieces and the joints forming the basic configuration are designed in a standardized mode, the same process flow or production tools are used for machining the same structural part, the mass production is realized, the satellite design complexity is greatly simplified, the satellite development period is effectively shortened, the production and machining of a plurality of satellite structures can be carried out simultaneously, the rapid production and assembly of the satellite are realized, the productivity is improved, and the time cost is saved. The platform structure can be expanded layer by layer on the basis of basic configuration, and the adaptive capacity from hundreds of kilograms to tons is realized.
Drawings
To further clarify the above and other advantages and features of embodiments of the present invention, a more particular description of embodiments of the present invention will be rendered by reference to the appended drawings. It is appreciated that these drawings depict only typical embodiments of the invention and are therefore not to be considered limiting of its scope. In the drawings, the same or corresponding parts will be denoted by the same or similar reference numerals for clarity.
FIG. 1 is a schematic structural diagram of a flexible satellite platform structure according to an embodiment of the invention;
FIG. 2 is a schematic structural diagram of a flexible satellite platform structure according to yet another embodiment of the invention;
FIG. 3 is a schematic structural diagram of a flexible satellite platform according to yet another embodiment of the invention;
FIG. 4 is a schematic structural diagram of a flexible satellite platform structure according to another embodiment of the invention;
FIG. 5 is a schematic view of a joint structure of a flexible satellite platform structure according to an embodiment of the invention;
FIG. 6 is a schematic diagram of a transverse bar structure of a flexible satellite platform structure according to an embodiment of the invention;
FIG. 7 is a schematic diagram of a longitudinal bar structure of a flexible satellite platform structure according to an embodiment of the invention;
FIG. 8 is a schematic view of the connection of the joints and the cross-bar of a flexible satellite platform structure according to one embodiment of the invention;
FIG. 9 is a schematic diagram illustrating the expansion connection of the joints and the transverse rods of a flexible satellite platform structure according to an embodiment of the invention; and
fig. 10 is a schematic diagram illustrating the connection of the joints with the transverse rods and the longitudinal rods of a flexible satellite platform structure according to an embodiment of the invention.
Detailed Description
In the following description, the present invention is described with reference to examples. One skilled in the relevant art will recognize, however, that the embodiments may be practiced without one or more of the specific details, or with other alternative and/or additional methods, materials, or components. In other instances, well-known structures, materials, or operations are not shown or described in detail to avoid obscuring aspects of the invention. Similarly, for purposes of explanation, specific numbers, materials and configurations are set forth in order to provide a thorough understanding of the embodiments of the invention. However, the invention is not limited to these specific details. Further, it should be understood that the embodiments shown in the figures are illustrative representations and are not necessarily drawn to scale.
Reference in the specification to "one embodiment" or "the embodiment" means that a particular feature, structure, or characteristic described in connection with the embodiment is included in at least one embodiment of the invention. The appearances of the phrase "in one embodiment" in various places in the specification are not necessarily all referring to the same embodiment.
It should be noted that the embodiment of the present invention describes the process steps in a specific order, however, this is only for the purpose of illustrating the specific embodiment, and does not limit the sequence of the steps. Rather, in various embodiments of the present invention, the order of the steps may be adjusted according to process adjustments.
In order to accelerate the construction of a new system of the aerospace science and technology industry in China and realize the higher requirement of the transformation of the satellite development capacity from the large country to the strong country, it is necessary to plan and perfect the satellite public platform type spectrum, organize and purposefully strengthen the technical upgrade of the satellite public platform, establish a product type spectrum system matched with the healthy satellite public platform and promote the satellite public platform to develop more quickly and better. In order to complete these tasks quickly, well and economically, a rough production mode for developing a platform of a satellite must be abandoned, and a limited number of standardized public platforms should be established. By using the idea of modularization and standardization, the satellite platform can greatly reduce the complexity of parts, simplify the construction process, improve the on-orbit reliability and reduce the quality and cost of the satellite.
In order to achieve the aim, the invention discloses a flexible expandable satellite platform structure, which is a standard and modularized public satellite platform compared with a extensive production mode of one satellite and one platform adopted in the traditional satellite development process, and can comprehensively meet the requirements of various series and multi-model satellites.
The platform structure has a basic configuration of a polygonal prism and can be longitudinally expanded into a multilayer structure or transversely expanded. The polygon prism body is formed by connecting a rod piece and a joint, the rod piece and the joint are in standardized design, and the polygon prism body comprises:
the joint is the polyhedron, and the centre equipartition of each face has put the recess, wherein:
the top surface and the bottom surface of the joint are polygons with the same shape, and the top surface is parallel to the bottom surface; and
each side surface of the joint is vertical to the top surface and the bottom surface; and
the rod member includes:
the end part of the transverse rod is matched with the groove on the side surface of the joint in shape, the transverse rod is used for connecting the joint to form a polygon, and a boss is arranged on the transverse rod and used for connecting a honeycomb plate to install single-machine equipment; and
the end of the longitudinal rod is matched with the groove on the top surface and/or the bottom surface of the joint in shape, the longitudinal rod is used for vertically connecting the polygons to form a polygonal column body, and a boss is arranged on the longitudinal rod and used for connecting a honeycomb plate to install single equipment.
In one embodiment of the invention, the basic configuration is preferably a hexagonal prism, as shown in fig. 1, comprising 12 joints 1, 12 transverse rods 2 and 6 longitudinal rods 3, wherein:
the adapter 1 is an octahedron, and its structure is shown in fig. 5, its top surface 14 and bottom surface are hexagons, and top surface and bottom surface are parallel to each other, and its side 11 is a square, and is perpendicular to top surface 14. A groove 12 is arranged right in the middle of each side surface of the joint 1, in one embodiment of the invention, threaded holes 13 are further arranged on the periphery of the groove 12, and in another embodiment of the invention, 4 threaded holes 13 are arranged on each side surface; a groove 15 is arranged right in the middle of the top surface and the bottom surface of the joint, in one embodiment of the invention, a threaded hole 16 is further arranged on the periphery of the groove 15, and in another embodiment of the invention, 6 threaded holes 16 are arranged on the top surface and/or the bottom surface;
the transverse bar 2 is constructed as shown in figure 6 and can be subjected to axial loads. The ends 24 and 25 of the transverse bar 2 are shaped to fit into the grooves 12 of the side of the joint 1, able to withstand the bending moment of the transverse bar 2. In one embodiment of the invention, the groove 12 is circular. Furthermore, the transverse bar 2 is provided with one or more second bosses 26, in one embodiment of the invention, the second bosses 26 are quadrilateral with circular arcs, and the four sides of the second bosses are provided with threaded holes 23, the threaded holes 23 are used for connecting cellular boards, and the cellular boards can provide a mounting surface for single equipment on one hand and provide in-plane shear rigidity for satellites on the other hand. In another embodiment of the present invention, the two ends of the transverse rod 2 are further provided with first bosses 27, the distance between the first bosses 27 and the ends of the transverse rod 2 is less than or equal to the depth of the grooves 12, so that when the transverse rod 2 is connected to the joint 1, the end surfaces 21 of the first bosses 27 can contact with the side surfaces 11 of the joint 1, in one embodiment of the present invention, the first bosses 27 are square, and the four corners of the first bosses 27 are respectively provided with a through hole 22, the position of the through hole 22 corresponds to the threaded hole 13 on the side surface of the joint 1, and the transverse rod 2 can be further fixed on the side surfaces 11 of the joint 1 by passing a screw through the through hole 22. The joints 1 can be connected with six transverse rod pieces 2 at most, a star-shaped structure is formed in the same plane, and the included angle between every two adjacent rod pieces is 60 degrees; fig. 8 provides a connection mode of the joint 1 and the transverse rod 2, but the invention is not limited to the connection mode, and the joint 1 and the transverse rod 2 can be expanded and connected into structures with different shapes according to the needs of the structures, as shown in fig. 9; and
the longitudinal bars 3 are constructed as shown in figure 7 and can be subjected to longitudinal loads. The ends 35 and 36 of the longitudinal bars 3 are shaped to fit into the grooves 15 of the top and bottom faces of the joint 1. In one embodiment of the invention, the recess 15 is circular. Furthermore, one or more fourth bosses 34 are provided on the longitudinal bar 3, in one embodiment of the invention, the fourth bosses 34 are hexagonal, and the hexagonal part of the fourth bosses is provided with threaded holes 33, the threaded holes 33 are used for connecting cellular boards, and the cellular boards can provide a mounting surface for stand-alone equipment on one hand and provide in-plane shear rigidity for satellites on the other hand. In another embodiment of the present invention, the longitudinal rod 3 is further provided with third bosses 37 at both ends thereof, the third bosses 37 are spaced from the ends of the longitudinal rod 3 by a distance less than or equal to the depth of the grooves 15, so that when the longitudinal rod 3 is connected to the joint 1, the end surfaces 31 of the third bosses 37 can contact the top and bottom surfaces of the joint 1, in one embodiment of the present invention, the third bosses 37 are circular, and six through holes 32 are formed around the center of the longitudinal rod 3, the positions of the through holes 32 correspond to the threaded holes 16 on the top and bottom surfaces of the joint 1, and the longitudinal rod 3 can be further fixed on the top or bottom surface of the joint 1 by passing screws through the through holes 32. The number of 1 joints 1 can be connected with at most two longitudinal rods 3, as shown in fig. 10, one joint 1 can be connected with six transverse rods 2 and two longitudinal rods 3 in a space range, wherein the transverse rods 2 can bear transverse loads, the longitudinal rods 3 can bear longitudinal loads, and the loads of the planes of the longitudinal rods 3 and the transverse rods 2 can be increased by increasing shear loads and bending loads in the bearing planes of the honeycomb panel, but the invention is not limited to the connection mode, and the joints 1, the transverse rods 2 and the longitudinal rods 3 can be expanded to be connected into structures with different shapes according to the needs of the structures.
In one embodiment of the invention, the transverse bars 2 and/or the longitudinal bars 3 are hollow, and in another embodiment of the invention, the transverse bars 2 and/or the longitudinal bars 3 are made of aluminum alloy and/or magnesium alloy and/or silicon carbide and/or carbon fiber composite material, which has high rigidity and strength and low density, so that all fuel tanks and most propulsion equipment can be directly connected to the main frame.
Based on the basic configuration of the hexagonal prism, according to the connection manner as described above, the transverse and/or longitudinal expansion can be realized, so as to form the satellite platform structure shown in fig. 2, 3 and 4:
as shown in fig. 2, the satellite platform structure may be a single-layer structure, which illustrates that the basic configuration is a center, and is obtained by lateral expansion, specifically, twenty-four joints 1, sixty transverse rods 2, and twelve longitudinal rods 3 are added, and a layer of hexagonal prism is laterally expanded, so that the hexagonal cross-sectional area of the overall hexagonal prism is increased by three times, the area of the side quadrilateral is increased by two times, and the volume of the satellite is increased by three times. Eight honeycomb plates can be respectively installed on eight surfaces of the hexagonal prism body, and the honeycomb plates can provide installation surfaces for single-machine equipment and can also be combined with a main structure to bear force. The hexagonal surface of the hexagonal prism can be used as the ground and the back ground of the satellite, the quadrilateral surface can be used as the mounting surface of single-machine equipment, and simultaneously, the heat dissipation surface of the whole satellite and the mounting surface of the solar sailboard are also used, the satellite with the structure can be stacked in series in the fairing, the space of the fairing is efficiently utilized, and the one-arrow-shaped multi-star emission is realized; and
as shown in fig. 3 and 4, the satellite platform may have a two-layer structure, and the two-layer structure is obtained by performing longitudinal expansion on the basis of a single-layer structure, specifically:
the satellite platform shown in fig. 3 is obtained by adding six joints 1, six transverse rods 2 and six longitudinal rods 3 on the basis of the basic configuration, namely, longitudinally expanding a layer of hexagonal prism. The hexagonal cross-sectional area of the hexagonal prism is unchanged, but the area of the side quadrilateral is increased by two times, and the height of the hexagonal prism is increased by one time, so that the volume of the satellite is increased by one time. The hexagonal prism can be divided into an upper part and a lower part which can be respectively used as a load cabin and a platform cabin of the satellite, a middle layer plate can be arranged between the load cabin and the platform cabin, so that the platform and the load belong to different cabin sections, and meanwhile, the battery is independently installed on a base of the satellite platform in a module form, thereby facilitating installation and thermal isolation. The mounting area and heat dissipation capacity of the payload can be improved by simply lengthening or shortening the rod structure and the radiator panel; and
the satellite platform shown in fig. 4 is formed by adding forty-two joints 1, ninety-six transverse rods 2 and thirty-three longitudinal rods 3 on the basis of a basic configuration, namely, a layer of hexagonal prism is transversely expanded and a layer of hexagonal prism is longitudinally expanded, so that the hexagonal cross-sectional area of the hexagonal prism is increased by three times, the area of a side quadrilateral is increased by four times, the height of the hexagonal prism is increased by one time, and further the volume of the satellite is increased by seven times, the satellite platform is integrally of an octahedral structure and can be divided into an upper cabin and a lower cabin, the upper cabin is a load cabin and can be used for placing equipment of various loads, and the lower cabin is a platform cabin and can be used for installing single machines required by various platforms; the hexagonal bottom plate can be used for arrangement of a propulsion pipeline and a storage box structure, the outer side of the bottom plate can be used for arrangement of ground-backed off-satellite loads such as measurement and control antennas, space sensitivity, satellite sensitivity and other equipment, meanwhile, the bottom plate is connected with a hexagonal prism integral frame, and the hexagonal prism integral frame is connected with a butt joint ring of a satellite and a rocket; the hexagonal top surface can be used as the ground of a satellite, and various ground antenna loads and feed sources are installed; six quadrilateral sides can be used as the installation surface of a single machine, various unfolding mechanisms, reflector antennas and the like can be hung and placed on the outer side of the star body, and in addition, the battery is independently installed on the base of the satellite platform in a module form, so that the installation and the thermal isolation are convenient. The mounting area and heat dissipation capacity of the payload can be improved simply by lengthening or shortening the rod structure and the radiator plate.
The flexible satellite platform structure in the embodiment of the invention can realize the adaptability from hundreds of kilograms to tons: the bearing capacity of the single-layer hexagonal prism configuration satellite can achieve 100-500 Kg, the bearing capacity of the two-layer hexagonal prism configuration satellite can achieve 1 ton, the bearing capacity of the single-layer hexagonal prism extension structure can achieve 1-1.5 ton, and the bearing capacity of the two-layer hexagonal prism extension structure can achieve 3 tons. The hexagonal prism frame realizes the flexible bearing of the satellite platform by increasing the number of the rods and the joints, and can provide 3000Kg of satellite launching mass at most.
In addition, the flexible satellite platform structure in the embodiment of the invention adopts a frame structure formed by connecting the rod pieces and the joints, can cut the configuration of the satellite platform according to the load condition so as to match different requirements of the load, and can select a single-layer, double-layer or double-layer expandable frame structure according to the load configuration condition in the future so as to form a satellite platform series, the adaptability of the satellite platform series to various loads is greatly enhanced, and the satellite platform series not only can be used for navigation satellite loads, but also can be used for communication satellites, scientific test satellites, geostationary orbit missile early warning satellites and the like. The satellite platform propulsion can use a chemical propulsion system, an electric propulsion system or an electric hybrid propulsion system to meet various task requirements, and the requirements on the loading amounts of different propellants can be met only by lengthening or shortening the cylindrical section of the storage tank.
The rod piece and the joint in the flexible satellite platform structure in the embodiment of the invention are in standardized design, so that the design complexity of the satellite can be greatly simplified, the development period of the satellite is shortened, and the rapid production and assembly of the satellite are realized; meanwhile, the main frame only comprises the rod piece and the joint, so that the utilization rate and the reliability of parts of the satellite platform are improved, and the satellite platform is simple in design, high in structural component standardization degree, replaceable and capable of meeting the requirements of mass production aiming at the development of the current commercial satellite.
While various embodiments of the present invention have been described above, it should be understood that they have been presented by way of example only, and not limitation. It will be apparent to persons skilled in the relevant art that various combinations, modifications, and changes can be made thereto without departing from the spirit and scope of the invention. Thus, the breadth and scope of the present invention disclosed herein should not be limited by any of the above-described exemplary embodiments, but should be defined only in accordance with the following claims and their equivalents.
Claims (9)
1. A flexible satellite platform structure, characterized in that its basic configuration is a polygonal prism, which is composed of joints and rods, wherein:
the joints are polyhedrons, and the central position of each surface is provided with a groove, wherein,
the top surface and the bottom surface of the joint are polygons with the same shape, and the top surface is parallel to the bottom surface; and
each side surface of the joint is vertical to the top surface and the bottom surface;
the end part of the transverse rod is matched with the groove of the side surface in shape, the transverse rod is used for connecting joints to form a polygon, and a boss is arranged on the transverse rod and is configured to be capable of connecting a honeycomb plate to install single equipment; and
longitudinal bars, the end shape of which is adapted to the grooves of the top and/or bottom faces of the joint, for connecting the polygons perpendicularly to form a polygonal prism, and on which bosses are arranged, which are configured to be able to connect honeycomb panels for the installation of stand-alone equipment.
2. The structure of claim 1, wherein the basic configuration is a hexagonal prism comprising 12 joints, 12 transverse rods, and 6 longitudinal rods, wherein the joints are octahedrons, the bottom faces and bottom faces of the octahedrons are hexagons, and the sides of the octahedrons are squares.
3. The flexible satellite platform structure of claim 1, wherein the transverse and/or longitudinal rods are hollow structures.
4. The flexible satellite platform structure of claim 1, wherein the material of the transverse rods and/or the longitudinal rods is an aluminum alloy and/or a magnesium alloy and/or silicon carbide and/or carbon fiber.
5. The structure of claim 1, wherein the two ends of the transverse rod are provided with first bosses, and/or the two ends of the longitudinal rod are provided with third bosses, and the distance between the first bosses and the ends of the transverse rod, and/or the distance between the third bosses and the ends of the longitudinal rod are less than or equal to the depth of the grooves, so that the end surfaces of the first bosses and the third bosses can contact with the surface of the joint after the transverse rod and/or the longitudinal rod are inserted into the joint.
6. The flexible satellite platform structure of claim 5, wherein the first boss and the third boss are fixedly connected to the joint by screws.
7. The flexible satellite platform structure of claim 1, wherein the flexible satellite platform structure is a single layer structure that is laterally extended centered on a base configuration.
8. The flexible satellite platform structure of claim 1, wherein the flexible satellite platform structure is a two-layer structure, wherein the upper layer is a load compartment and the lower layer is a platform compartment, and wherein the bottom surface of the load compartment and the top surface of the platform compartment share a common plane.
9. The flexible satellite platform structure of claim 8, wherein the payload bay and/or the platform bay are laterally expanded centered on a base configuration.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113932782A (en) * | 2021-10-15 | 2022-01-14 | 北京卫星环境工程研究所 | Coordinate system establishing and reference transferring method suitable for spacecraft large-size cabin structure |
| CN113955161A (en) * | 2021-12-10 | 2022-01-21 | 北京科技大学 | Space non-cooperative target capturing device and capturing method thereof |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20130036702A1 (en) * | 2011-06-15 | 2013-02-14 | Selex Sistemi Integrati S.P.A. | Shelter |
| CN102975867A (en) * | 2012-11-13 | 2013-03-20 | 上海微小卫星工程中心 | Satellite module and modularized satellite |
| CN103863577A (en) * | 2014-02-25 | 2014-06-18 | 上海微小卫星工程中心 | Frame panel type satellite configuration and modular satellite |
| US20160251093A1 (en) * | 2015-02-27 | 2016-09-01 | Space Systems/Loral, Llc | Truss structure |
| CN106564619A (en) * | 2016-10-28 | 2017-04-19 | 航天东方红卫星有限公司 | Novel commercial remote sensing satellite configuration layout |
| CN109442151A (en) * | 2018-10-23 | 2019-03-08 | 中国科学院光电研究院 | The Formwork Support for External structure of space wide cut camera |
| CN110512745A (en) * | 2019-09-04 | 2019-11-29 | 上海宇航***工程研究所 | A kind of application space truss structure assembling is inserted radially into from locking quick coupling |
| US20200216201A1 (en) * | 2017-08-07 | 2020-07-09 | Picosats S.R.L. | Structured set to make satellite structures |
-
2020
- 2020-09-28 CN CN202011041757.7A patent/CN112124627A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20130036702A1 (en) * | 2011-06-15 | 2013-02-14 | Selex Sistemi Integrati S.P.A. | Shelter |
| CN102975867A (en) * | 2012-11-13 | 2013-03-20 | 上海微小卫星工程中心 | Satellite module and modularized satellite |
| CN103863577A (en) * | 2014-02-25 | 2014-06-18 | 上海微小卫星工程中心 | Frame panel type satellite configuration and modular satellite |
| US20160251093A1 (en) * | 2015-02-27 | 2016-09-01 | Space Systems/Loral, Llc | Truss structure |
| CN106564619A (en) * | 2016-10-28 | 2017-04-19 | 航天东方红卫星有限公司 | Novel commercial remote sensing satellite configuration layout |
| US20200216201A1 (en) * | 2017-08-07 | 2020-07-09 | Picosats S.R.L. | Structured set to make satellite structures |
| CN109442151A (en) * | 2018-10-23 | 2019-03-08 | 中国科学院光电研究院 | The Formwork Support for External structure of space wide cut camera |
| CN110512745A (en) * | 2019-09-04 | 2019-11-29 | 上海宇航***工程研究所 | A kind of application space truss structure assembling is inserted radially into from locking quick coupling |
Non-Patent Citations (2)
| Title |
|---|
| ALI ABOREHAB等: "Configuration design and modeling of an efficient small satellite structure", 《ENGINEERING SOLID MECHANICS》 * |
| 王兴泽、徐燕菱等: "基于敏度分析的可展开桁架刚度优化设计", 《航天器工程》 * |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113932782A (en) * | 2021-10-15 | 2022-01-14 | 北京卫星环境工程研究所 | Coordinate system establishing and reference transferring method suitable for spacecraft large-size cabin structure |
| CN113955161A (en) * | 2021-12-10 | 2022-01-21 | 北京科技大学 | Space non-cooperative target capturing device and capturing method thereof |
| CN113955161B (en) * | 2021-12-10 | 2023-06-20 | 北京科技大学 | Capturing device and capturing method for space non-cooperative target |
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