CN111806726A - Main framework of small high-orbit satellite common platform - Google Patents
Main framework of small high-orbit satellite common platform Download PDFInfo
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- CN111806726A CN111806726A CN202010730104.3A CN202010730104A CN111806726A CN 111806726 A CN111806726 A CN 111806726A CN 202010730104 A CN202010730104 A CN 202010730104A CN 111806726 A CN111806726 A CN 111806726A
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- B64G1/00—Cosmonautic vehicles
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- B64—AIRCRAFT; AVIATION; COSMONAUTICS
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Abstract
The invention provides a main framework of a small-sized high-orbit satellite public platform, which comprises a shell, a middle partition plate, a platform cabin main bearing truss group and a load cabin bearing truss, wherein: the shell forms an accommodating space, and the accommodating space is divided into a platform cabin and a load cabin by the middle partition plate; the platform cabin main bearing truss group is arranged between a part of shell forming the platform cabin and the middle partition plate and applies supporting force to the part of shell forming the platform cabin and the middle partition plate; the load compartment bearing truss is arranged between a part of the outer shell forming the load compartment and the middle partition plate, and applies supporting force to the part of the outer shell forming the load compartment and the middle partition plate; the load cabin bearing truss is cylindrical, a satellite is connected above the load cabin bearing truss in series to enter a planet-planet series structure design and mechanical transmission, and the inter-planet series structure is used for a launching task of a small high-orbit satellite with one arrow and two stars.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a main framework of a small high-orbit satellite public platform.
Background
The main structure of the satellite platform is one of core technologies of satellite products, and the main structure which has high bearing ratio, high specific stiffness, high specific strength, low cost and easy batch development is effective guarantee of competitiveness of the satellite products. The truss type satellite main bearing structure has the advantages of high clear space value, concise and efficient force transmission characteristic, less limitation of carrying envelope and the like, has better rigidity and integrity, and is increasingly applied to satellite public platforms as the main bearing structure, such as BSS-601/BSS-702/BSS-702SP series platforms of the Boeing company in America. And to fully electrically propelled high earth orbit satellite common platforms.
The design of foreign communication satellite platforms is continuously developing towards high reliability, high bearing ratio, low cost, miniaturization, productization and type spectrometry, so as to achieve the purposes of reducing the satellite development cost/emission cost, shortening the satellite development period and improving the satellite reliability. Driven by the above-mentioned objectives, countries in europe and america compete to provide a full-electric push platform, in which the main platform framework uses a truss-type main load-bearing structure, which is an important development direction, such as BSS-702SP platform of boeing company in the united states, DFH-5 platform of oriental red company in china, and the like, and successfully occupies a large amount of high-orbit communication satellite markets at home and abroad. At the present stage, no full-electric push satellite platform is available in China, and a truss type main bearing structure which is high in bearing ratio, specific stiffness and specific strength, low in cost and easy to develop in batches is particularly urgent and important. Therefore, under the dual driving of technology and economy and under the task requirement of the satellite networking of the world integrated celestial-aircraft backbone nodes, the research of the full-electric push satellite public platform truss type main bearing structure completely belonging to the independent intellectual property rights of China is developed, which is very necessary and urgent.
Disclosure of Invention
The invention aims to provide a main framework of a small high-orbit satellite public platform so as to realize a satellite platform framework with high bearing ratio, high specific stiffness and high specific strength.
In order to solve the technical problems, the invention provides a main framework of a small-sized high-orbit satellite public platform, which comprises a shell, a middle partition plate, a platform cabin main bearing truss group and a load cabin bearing truss, wherein:
the shell forms an accommodating space, and the accommodating space is divided into a platform cabin and a load cabin by the middle partition plate;
the platform cabin main bearing truss group is arranged between a part of shell forming the platform cabin and the middle partition plate and applies supporting force to the part of shell forming the platform cabin and the middle partition plate;
the load compartment bearing truss is arranged between a part of the outer shell forming the load compartment and the middle partition plate, and applies supporting force to the part of the outer shell forming the load compartment and the middle partition plate;
the load cabin bearing truss is cylindrical, a satellite is connected above the load cabin bearing truss in series to enter a planet-planet series structure design and mechanical transmission, and the inter-planet series structure is used for a launching task of a small high-orbit satellite with one arrow and two stars.
Optionally, in the main structure of the small high-orbit satellite public platform, the housing includes a bottom plate, a top plate, a + X side plate, an-X side plate, a + Y side plate, and a-Y side plate, where:
the bottom plate and the top plate are arranged in a first direction and a second direction;
the + X side plate and the-X side plate are arranged along a second direction and a third direction;
the + Y side plate and the-Y side plate are arranged along a third direction and a first direction;
the first direction, the second direction and the third direction are mutually vertical.
Optionally, in the main framework of the small-sized high-orbit satellite public platform, the platform cabin main bearing truss group and the middle partition plate are connected by a partition plate embedded frame, and the platform cabin main bearing truss group and a part of outer shell of the platform cabin are connected by a bottom plate embedded frame;
the main bearing structure of the main framework of the small high-orbit satellite public platform consists of the platform cabin main bearing truss group, the load cabin bearing truss, the partition plate embedded frame and the bottom plate embedded frame.
Optionally, in the main framework of the small-sized high-orbit satellite common platform, the platform cabin main bearing truss group includes a satellite-rocket adapter cylinder, a first group of W-shaped planar trusses, a second group of W-shaped planar trusses and a third group of W-shaped planar trusses, wherein:
the satellite-rocket adapter cylinder is used for connecting a main framework of the small high-orbit satellite public platform with carrying equipment;
the first group of W-shaped plane trusses is parallel to the + Y side plate and the-Y side plate;
an included angle of 0-90 degrees is formed between the second group of W-shaped plane trusses and the + Y side plate and the-Y side plate;
an included angle of-90-0 degrees is formed between the third group of W-shaped plane trusses and the + Y side plate and the-Y side plate;
the connection points of the first group of W-shaped plane trusses, the second group of W-shaped plane trusses and the third group of W-shaped plane trusses and part of the shell are symmetrically and uniformly distributed in the circumference, and the connection points of the first group of W-shaped plane trusses, the second group of W-shaped plane trusses and the third group of W-shaped plane trusses and the middle partition plate are intersected in the center of the middle partition plate.
Optionally, in the main framework of the small-sized high-orbit satellite common platform, an included angle of 45 ° is formed between the second group of W-shaped plane trusses and the + Y side plate and the-Y side plate;
and an included angle of-45 degrees is formed between the third group of W-shaped plane trusses and the + Y side plate and the-Y side plate.
Optionally, in the main framework of the small-sized high-orbit satellite common platform, bottom joints of the first group of W-shaped plane trusses, the second group of W-shaped plane trusses and the third group of W-shaped plane trusses are connected with the satellite-rocket adapter cylinder through a bottom plate embedded frame; the top joints of the first group of W-shaped plane trusses, the second group of W-shaped plane trusses and the third group of W-shaped plane trusses are connected with the load cabin bearing truss through the partition plate embedded frame;
the bottom plate embedded frame and the partition plate embedded frame are used as a part of a main bearing structure of a main framework of the small-sized high-orbit satellite public platform and are embedded in the bottom plate and the middle partition plate respectively, so that the platform cabin main bearing truss group, the shell and the middle partition plate are connected, and the load in the load cabin is transmitted to the main bearing structure of the main framework of the small-sized high-orbit satellite public platform.
Optionally, in the main framework of the small-sized high-orbit satellite common platform, a first reinforcing rod and a second reinforcing rod are arranged between the + Y side plate and the-Y side plate, a solar cell array driving mechanism is arranged between the first reinforcing rod and the second reinforcing rod, so that the installation rigidity environment of the solar cell array driving mechanism and the rigidity characteristics of the + Y side plate and the-Y side plate are improved, and the first reinforcing rod and the second reinforcing rod are used for connecting the + Y side plate, the first group of W-shaped plane trusses and the-Y side plate, so that the load of the + Y side plate and the-Y side plate is transmitted to the main bearing framework of the main framework of the small-sized high-orbit satellite common platform.
Optionally, in the main framework of the small-sized high-orbit satellite common platform, the load compartment bearing truss is cylindrical, and a bottom joint and a top joint of the load compartment bearing truss are respectively connected with the middle partition plate and the top plate, so that the outer side of the top plate can be connected with other satellites in series for one-arrow two-satellite series launching.
Optionally, in the main structure of the small-sized high-orbit satellite public platform, the top plate completely or partially encloses the accommodating space.
The main framework of the small high-orbit satellite public platform can meet flexible load configuration and integrated design, is suitable for one-arrow two-satellite series emission, and solves the problems of long development period, high development cost and high carrying and emission cost of the rapid and flexible networking of high-orbit satellites.
In the main framework of the small-sized high-orbit satellite public platform provided by the invention, the main bearing structure of the main framework of the small-sized high-orbit satellite public platform consists of the platform cabin main bearing truss group, the load cabin bearing truss, the joint of the platform cabin main bearing truss group and the middle partition plate and the joint of the platform cabin main bearing truss group and part of the shell.
Furthermore, the bottom plate embedded frame and the partition plate embedded frame are used as a part of a main bearing structure of a main framework of the small high-orbit satellite public platform, the bottom plate embedded frame and the partition plate embedded frame are embedded in the bottom plate and the middle partition plate, so that the platform cabin main bearing truss group is connected with each side plate and the middle partition plate, the transverse rigidity of the main bearing structure is enhanced through the middle partition plate, the load of satellite single-machine equipment on the middle partition plate is easily and effectively transmitted to the main bearing structure, and the mechanical transmission path is clear and efficient. The top connector of the first group of W-shaped plane truss is connected with the first reinforcing rod, the bottom connector of the first group of W-shaped plane truss is connected with the second reinforcing rod, local low frequencies of the two side plates can be effectively eliminated when the + Y side plate and the-Y side plate are loaded with heavy equipment, and the whole star has high enough rigidity while layout space of the two side plates is not influenced.
In addition, the top panel may form a platform enclosure structure with other side panels; the weight reduction device can be integrally designed with the load, the load cabin is designed into a semi-closed body structure, and the weight reduction design of the satellite is easy on the basis of not influencing the mechanical property of the satellite. The load cabin bearing truss is cylindrical, so that the load of a satellite top plate is efficiently borne, and meanwhile, the design of a series structure and the mechanical transmission between the upper series-connection satellite and the planet are easy, and the load cabin bearing truss is suitable for the launching task of a high-orbit satellite, namely one arrow and two stars.
The main structure of the small high-orbit satellite public platform provided by the invention has the following advantages:
(1) the high-strength composite material has the advantages of high force transmission characteristic, high bearing ratio, high specific rigidity, high specific strength and the like.
(2) The main bearing structure can be flexibly adjusted to adapt to configurations with different section shapes, the load cabin can be integrally and flexibly designed to adapt to load configurations of different types, and the flexible load cabin has flexible design characteristics and higher cost performance.
(3) The satellite launching system has the advantages of small volume, light weight, low cost and capability of adapting to one-arrow two-star launching, adapts to the launching task of one-arrow two-star launching of the high-orbit satellite, and solves the problems of long development period, high development cost and high carrying and launching cost of the rapid and flexible networking of the high-orbit satellite.
The main framework of the small high-orbit satellite public platform is in a nearly cubic configuration, and is divided into two cabin sections, namely an internal service cabin and a load cabin; the full-truss main bearing structure is adopted to realize high bearing ratio, high specific stiffness, high specific strength and expandability, and ensure good mechanical environment, layout space and interfaces with carrying and ground equipment of the satellite.
Drawings
FIG. 1 is a schematic side plate closure diagram of a main frame of a small high-orbit satellite common platform according to an embodiment of the invention;
FIG. 2 is a schematic diagram of the opening of the main frame side plate of the small high orbit satellite common platform according to one embodiment of the present invention;
fig. 3 is a schematic view of a main bearing structure of a main framework of a small-sized high-orbit satellite common platform according to an embodiment of the invention;
fig. 4 is a schematic diagram of a mechanical transmission path of a main bearing structure of a main framework of a small-sized high-orbit satellite common platform according to an embodiment of the invention;
shown in the figure: 1-platform cabin main bearing truss group; 2-a load compartment bearing truss; 3-a bottom plate; 4- + Y side plate; 5- -Y side plate; 6- + X side plate; 7- -X side plate; 8-a middle partition board; 9-a top plate; 10-a satellite-rocket adapter cylinder; 11-a first set of W-shaped planar trusses; 12-a second set of W-shaped planar trusses; 13-a third set of W-shaped planar trusses; 14-bottom joint of the platform cabin main bearing truss group; 15-embedding a frame in the bottom plate; 16-top joint of the platform cabin main bearing truss group; 17-embedding a partition plate in a frame; 18-first/second stiffener.
Detailed Description
The main architecture of the small-scale high-orbit satellite common platform provided by the invention is further described in detail with reference to the accompanying drawings and specific embodiments. Advantages and features of the present invention will become apparent from the following description and from the claims. It is to be noted that the drawings are in a very simplified form and are not to precise scale, which is merely for the purpose of facilitating and distinctly claiming the embodiments of the present invention.
The core idea of the invention is to provide a main framework of a small-sized high-orbit satellite public platform so as to realize a satellite platform framework with high bearing ratio, high specific stiffness and high specific strength.
In order to realize the idea, the invention provides a main framework of a small-sized high-orbit satellite public platform, which comprises a shell, a middle partition plate, a platform cabin main bearing truss group and a load cabin bearing truss, wherein: the shell forms an accommodating space, and the accommodating space is divided into a platform cabin and a load cabin by the middle partition plate; the platform cabin main bearing truss group is arranged between a part of shell forming the platform cabin and the middle partition plate and applies supporting force to the part of shell forming the platform cabin and the middle partition plate; the load compartment bearing truss is arranged between a part of the outer shell forming the load compartment and the middle partition plate, and applies supporting force to the part of the outer shell forming the load compartment and the middle partition plate; the load cabin bearing truss is cylindrical, a satellite is connected above the load cabin bearing truss in series to enter a planet-planet series structure design and mechanical transmission, and the inter-planet series structure is used for a launching task of a small high-orbit satellite with one arrow and two stars.
The embodiment of the invention provides a main framework of a small-sized high-orbit satellite public platform, which comprises a shell, a middle partition plate 8, a platform cabin main bearing truss group 1 and a load cabin bearing truss 2, as shown in figures 1-2, wherein: the shell forms an accommodating space, and the accommodating space is divided into a platform cabin and a load cabin by the middle partition plate 8; the platform cabin main bearing truss group 1 applies supporting force to a part of shell forming the platform cabin and the middle partition plate 8; the load compartment carrying truss 2 applies supporting force to a part of the outer shell and the middle partition plate 8 which form the load compartment; the platform cabin main bearing truss group 1 and the middle partition plate 8 are connected through a partition plate embedded frame 17, and the platform cabin main bearing truss group 1 and the partial shell are connected through a bottom plate embedded frame 15; the main bearing structure of the main framework of the small high-orbit satellite public platform consists of the platform cabin main bearing truss group 1, the load cabin bearing truss 2, the partition plate embedded frame 17 and the bottom plate embedded frame 15.
Specifically, in the main structure of the small high-orbit satellite public platform, the housing includes a bottom plate 3, a top plate 9, a + X side plate 6, an-X side plate 7, a + Y side plate 4, and a-Y side plate 5, wherein: the bottom plate 3 and the top plate 9 are arranged in a first direction and a second direction (Z-axis direction); the + X side plate 6 and the-X side plate 7 are arranged in the second direction and the third direction (X-axis direction); the + Y-side plate 4 and the-Y-side plate 5 are arranged in a third direction and a first direction (Y-axis direction); the first direction, the second direction and the third direction are mutually vertical.
As shown in fig. 3, in the main framework of the small-scale high-orbit satellite common platform, the platform cabin main force-bearing truss group 1 includes a satellite-rocket adapter cylinder 10, a first group of W-shaped planar trusses 11, a second group of W-shaped planar trusses 12, and a third group of W-shaped planar trusses 13, wherein: the satellite-rocket adapter cylinder 10 is used for connecting a main framework of the small-sized high-orbit satellite public platform with carrying equipment; the first group of W-shaped plane trusses 11 is parallel to the + Y side plate 4 and the-Y side plate 5; an included angle of 0-90 degrees is formed between the second group of W-shaped plane trusses 12 and the + Y side plate 4 and the-Y side plate 5; an included angle of-90-0 degrees is formed between the third group of W-shaped plane trusses 13 and the + Y side plate 4 and the-Y side plate 5; the connection points of the first group of W-shaped plane trusses, the second group of W-shaped plane trusses and the third group of W-shaped plane trusses and part of the shell are symmetrically and uniformly distributed in the circumference, and the connection points of the first group of W-shaped plane trusses, the second group of W-shaped plane trusses and the third group of W-shaped plane trusses and the middle partition plate are intersected in the center of the middle partition plate. When the main framework of the small high-orbit satellite common platform is a cube, an included angle of 45 degrees is formed between the second group of W-shaped plane trusses 12 and the + Y side plate 4 and the-Y side plate 5; and an included angle of-45 degrees is formed between the third group of W-shaped plane trusses 13 and the + Y side plate 4 and the-Y side plate 5. When the cross section size of the platform is required to be designed to be non-square, included angles between the second group of W-shaped plane trusses and the third group of W-shaped plane trusses and the + Y side plate 4 and the-Y side plate 5 can be changed to be corresponding fixed values, and the second group of W-shaped plane trusses and the third group of W-shaped plane trusses are guaranteed to be symmetrically distributed with the X axis.
Further, in the main framework of the small-sized high-orbit satellite common platform, bottom joints 14 of the first group of W-shaped plane trusses 11, the second group of W-shaped plane trusses 12 and the third group of W-shaped plane trusses 13 are connected with the satellite-rocket adapter cylinder 10 through a bottom plate embedded frame 15; the top joints 16 of the first group of W-shaped plane trusses 11, the second group of W-shaped plane trusses 12 and the third group of W-shaped plane trusses 13 are connected with the load cabin bearing truss 2 through a partition plate embedded frame 17; the bottom plate embedded frame 15 and the partition plate embedded frame 17 are used as a part of a main bearing structure of a main framework of the small-sized high-orbit satellite public platform and are respectively embedded in the bottom plate 3 and the middle partition plate 8, so that the platform cabin main bearing truss group 1, the shell and the middle partition plate 8 are connected, and the load in the load cabin is transmitted to the main bearing structure of the main framework of the small-sized high-orbit satellite public platform.
In addition, in the main framework of the small high-orbit satellite common platform, a first reinforcing rod and a second reinforcing rod 18 are arranged between the + Y side plate 4 and the-Y side plate 5, a solar cell array driving mechanism is arranged between the first reinforcing rod and the second reinforcing rod 18, the installation rigidity environment of the solar cell array driving mechanism and the rigidity characteristics of the + Y side plate 4 and the-Y side plate 5 are improved, and the first reinforcing rod and the second reinforcing rod 18 are used for connecting the + Y side plate 4, the first group of W-shaped plane trusses 11 and the-Y side plate 5, so that the loads of the + Y side plate 4 and the-Y side plate 5 are transmitted to the main bearing framework of the main framework of the small high-orbit satellite common platform. . The load compartment bearing truss 2 is cylindrical, and a bottom joint and a top joint of the load compartment bearing truss are respectively connected with the middle partition plate 8 and the top plate 9, so that the outer side of the top plate 9 can be connected with other satellites in series for one-arrow two-satellite series launching. Wherein the top plate 9 completely or partially encloses the receiving space.
In the main framework of the small-sized high-orbit satellite public platform provided by the invention, the main bearing structure of the main framework of the small-sized high-orbit satellite public platform consists of the platform cabin main bearing truss group 1, the load cabin bearing truss 2, the joint of the platform cabin main bearing truss group 1 and the middle partition plate 8 and the joint of the platform cabin main bearing truss group 1 and a part of shell.
The main framework of the small high-orbit satellite public platform can meet flexible load configuration and integrated design, is suitable for one-arrow two-satellite series emission, and solves the problems of long development period, high development cost and high carrying and emission cost of the rapid and flexible networking of high-orbit satellites.
Furthermore, as shown in fig. 4, the bottom plate embedded frame and the partition plate embedded frame are used as a part of a main bearing structure of a main framework of the small-sized high-orbit satellite public platform, and are embedded in the bottom plate and the middle partition plate, so that the platform cabin main bearing truss group is connected with each side plate and the middle partition plate, the transverse rigidity of the main bearing structure is enhanced through the middle partition plate, the load of satellite single-machine equipment on the middle partition plate is easily and effectively transmitted to the main bearing structure, and the mechanical transmission path is clear and efficient. The top connector of the first group of W-shaped plane truss is connected with the first reinforcing rod, the bottom connector of the first group of W-shaped plane truss is connected with the second reinforcing rod, local low frequencies of the two side plates can be effectively eliminated when the + Y side plate and the-Y side plate are loaded with heavy equipment, and the whole star has high enough rigidity while layout space of the two side plates is not influenced.
In addition, the top panel may form a platform enclosure structure with other side panels; the weight reduction device can be integrally designed with the load, the load cabin is designed into a semi-closed body structure, and the weight reduction design of the satellite is easy on the basis of not influencing the mechanical property of the satellite. The load cabin bearing truss is cylindrical, so that the load of a satellite top plate is efficiently borne, and meanwhile, the design of a series structure and the mechanical transmission between the upper series-connection satellite and the planet are easy, and the load cabin bearing truss is suitable for the launching task of a high-orbit satellite, namely one arrow and two stars.
The main structure of the small high-orbit satellite public platform provided by the invention has the following advantages:
(1) the high-strength composite material has the advantages of high force transmission characteristic, high bearing ratio, high specific rigidity, high specific strength and the like.
(2) The main bearing structure can be flexibly adjusted to adapt to configurations with different section shapes, the load cabin can be integrally and flexibly designed to adapt to load configurations of different types, and the flexible load cabin has flexible design characteristics and higher cost performance.
(3) The satellite launching system has the advantages of small volume, light weight, low cost and capability of adapting to one-arrow two-star launching, adapts to the launching task of one-arrow two-star launching of the high-orbit satellite, and solves the problems of long development period, high development cost and high carrying and launching cost of the rapid and flexible networking of the high-orbit satellite.
The main framework of the small high-orbit satellite public platform is in a nearly cubic configuration, and is divided into two cabin sections, namely an internal service cabin and a load cabin; the full-truss main bearing structure is adopted to realize high bearing ratio, high specific stiffness, high specific strength and expandability, and ensure good mechanical environment, layout space and interfaces with carrying and ground equipment of the satellite.
In summary, the above embodiments have described in detail different configurations of the main architecture of the small-scale high-orbit satellite common platform, and it is needless to say that the present invention includes but is not limited to the configurations listed in the above embodiments, and any modifications based on the configurations provided by the above embodiments are within the scope of the present invention. One skilled in the art can take the contents of the above embodiments to take a counter-measure.
The above description is only for the purpose of describing the preferred embodiments of the present invention, and is not intended to limit the scope of the present invention, and any variations and modifications made by those skilled in the art based on the above disclosure are within the scope of the appended claims.
Claims (9)
1. The utility model provides a main framework of public platform of small-size high orbit satellite which characterized in that, main framework of public platform of small-size high orbit satellite includes shell, intermediate bottom, platform cabin owner load truss group and load cabin bears the truss, wherein:
the shell forms an accommodating space, and the accommodating space is divided into a platform cabin and a load cabin by the middle partition plate;
the platform cabin main bearing truss group is arranged between a part of shell forming the platform cabin and the middle partition plate and applies supporting force to the part of shell forming the platform cabin and the middle partition plate;
the load compartment bearing truss is arranged between a part of the outer shell forming the load compartment and the middle partition plate, and applies supporting force to the part of the outer shell forming the load compartment and the middle partition plate;
the load cabin bearing truss is cylindrical, a satellite is connected above the load cabin bearing truss in series to enter a planet-planet series structure design and mechanical transmission, and the inter-planet series structure is used for a launching task of a small high-orbit satellite with one arrow and two stars.
2. The main framework of a small high-orbit satellite utility platform according to claim 1, wherein the housing comprises a bottom plate, a top plate, + X-side plate, -X-side plate, + Y-side plate, and-Y-side plate, wherein:
the bottom plate and the top plate are arranged in a first direction and a second direction;
the + X side plate and the-X side plate are arranged along a second direction and a third direction;
the + Y side plate and the-Y side plate are arranged along a third direction and a first direction;
the first direction, the second direction and the third direction are mutually vertical.
3. The main framework of a small-scale high-orbit satellite utility platform as claimed in claim 2, wherein the platform cabin main load-bearing truss group and the middle partition plate are connected by a partition plate embedded frame, and the platform cabin main load-bearing truss group and a part of the outer shell of the platform cabin are connected by a bottom plate embedded frame;
the main bearing structure of the main framework of the small high-orbit satellite public platform consists of the platform cabin main bearing truss group, the load cabin bearing truss, the partition plate embedded frame and the bottom plate embedded frame.
4. The main framework of a small-scale high-orbit satellite utility platform according to claim 3, wherein the platform bay main force-bearing truss set comprises a satellite-rocket adapter cylinder, a first set of W-shaped planar trusses, a second set of W-shaped planar trusses and a third set of W-shaped planar trusses, wherein:
the satellite-rocket adapter cylinder is used for connecting a main framework of the small high-orbit satellite public platform with carrying equipment;
the first group of W-shaped plane trusses is parallel to the + Y side plate and the-Y side plate;
an included angle of 0-90 degrees is formed between the second group of W-shaped plane trusses and the + Y side plate and the-Y side plate;
an included angle of-90-0 degrees is formed between the third group of W-shaped plane trusses and the + Y side plate and the-Y side plate;
the connecting points of the first group of W-shaped plane trusses, the second group of W-shaped plane trusses and the third group of W-shaped plane trusses and part of the outer shell of the platform cabin are symmetrically and uniformly distributed in the circumference, and the connecting points of the first group of W-shaped plane trusses, the second group of W-shaped plane trusses and the third group of W-shaped plane trusses and the middle partition plate are intersected in the center of the middle partition plate.
5. The main framework for a compact, high-orbit satellite utility platform according to claim 4, wherein the second set of W-shaped planar trusses have an angle of 45 ° with the + Y side panel and the-Y side panel;
and an included angle of-45 degrees is formed between the third group of W-shaped plane trusses and the + Y side plate and the-Y side plate.
6. The main framework of a small-scale high-orbit satellite utility platform according to claim 4, wherein the bottom joints of the first, second and third sets of W-shaped planar trusses are connected with the satellite-rocket adapter cylinder through a bottom plate embedded frame; the top joints of the first group of W-shaped plane trusses, the second group of W-shaped plane trusses and the third group of W-shaped plane trusses are connected with the load cabin bearing truss through the partition plate embedded frame;
the bottom plate embedded frame and the partition plate embedded frame are used as a part of a main bearing structure of a main framework of the small-sized high-orbit satellite public platform and are embedded in the bottom plate and the middle partition plate respectively, so that the platform cabin main bearing truss group, the shell and the middle partition plate are connected, and the load in the load cabin is transmitted to the main bearing structure of the main framework of the small-sized high-orbit satellite public platform.
7. The main framework of the small-scale high-orbit satellite utility platform as claimed in claim 4, wherein a first stiffener and a second stiffener are arranged between the + Y side plate and the-Y side plate, a solar cell array driving mechanism is arranged between the first stiffener and the second stiffener, so as to improve the installation rigidity environment of the solar cell array driving mechanism and the rigidity characteristics of the + Y side plate and the-Y side plate, and the first stiffener and the second stiffener are used for connecting the + Y side plate, the first group of W-shaped plane trusses and the-Y side plate, so that the load of the + Y side plate and the-Y side plate is transferred to the main bearing structure of the main framework of the small-scale high-orbit satellite utility platform.
8. A main structure of a small-sized high-orbit satellite common platform according to claim 3, wherein the load compartment bearing truss is cylindrical, and the bottom joint and the top joint of the load compartment bearing truss are respectively connected with the middle partition plate and the top plate, so that the outer side of the top plate can be connected with other satellites in series for one-arrow two-satellite series launching.
9. A framework for a small-scale, high-orbit satellite utility platform according to claim 3, wherein said ceiling completely encloses, or partially encloses said housing space.
Priority Applications (1)
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| CN113650807A (en) * | 2021-03-26 | 2021-11-16 | 中国空间技术研究院 | Open satellite configuration suitable for multilayer stacking |
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| CN111003213B (en) * | 2019-12-17 | 2021-03-30 | 中国空间技术研究院 | Satellite vibration elimination method and system |
| CN111891393B (en) * | 2020-08-11 | 2022-03-15 | 中国科学院微小卫星创新研究院 | Hybrid propulsion cabin of small high-orbit satellite common platform |
| CN111891397A (en) * | 2020-08-12 | 2020-11-06 | 中国科学院微小卫星创新研究院 | One-rocket multi-satellite self-series-connection launching structure of small high-orbit satellite |
| CN112550761B (en) * | 2020-12-21 | 2021-09-21 | 中国人民解放军国防科技大学 | Integrated truss type minisatellite main bearing structure and design optimization method |
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Also Published As
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| CN110065653B (en) | 2020-08-04 |
| CN111806726B (en) | 2022-03-15 |
| CN110065653A (en) | 2019-07-30 |
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