CN115642385A - Thermally decoupled satellite-borne multi-beam antenna feed source array metal supporting structure - Google Patents
Thermally decoupled satellite-borne multi-beam antenna feed source array metal supporting structure Download PDFInfo
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- CN115642385A CN115642385A CN202211176998.1A CN202211176998A CN115642385A CN 115642385 A CN115642385 A CN 115642385A CN 202211176998 A CN202211176998 A CN 202211176998A CN 115642385 A CN115642385 A CN 115642385A
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Abstract
The invention provides a thermally decoupled satellite-borne multi-beam antenna feed array metal supporting structure which comprises a front panel, a rear panel, a first side panel, a second side panel, a bottom plate and a mounting base, wherein the front panel is arranged on the front panel; the bottom plate is arranged at the bottom of a support frame structure surrounded by the front panel, the rear panel, the first side panel and the second side panel; the plurality of mounting bases are radially mounted on the lower surface of the frame of the bottom plate in a concentric circle mode by taking the projection point of the feed source array phase center on the bottom plate as the circle center. The invention solves the problem of plane shear thermal stress between the aluminum alloy material supporting structure and the composite material satellite cabin plate; the design of the detachable assembly structure improves the assembly precision and the assembly efficiency, reduces the development cost, and simultaneously, the rigidity and the strength of the assembly structure can meet the requirement of the launching environment of the expansion type platform.
Description
Technical Field
The invention relates to a thermally decoupled satellite-borne multi-beam antenna feed array metal supporting structure, and belongs to the technical field of large-scale feed assembly heat-structure of high-flux/very-high-flux satellite multi-beam antennas.
Background
The high-flux communication satellite is a hotspot technology in the international communication satellite industry at present, and a core load of the high-flux communication satellite, namely a Ka frequency band multi-beam antenna, is a key technology for improving the satellite communication capacity by ten times or even hundred times by virtue of high bandwidth, frequency multiplexing, dense high-gain beams and wide area coverage capacity; antenna design parameters related to communication capacity comprise spectral efficiency, beam bandwidth, beam number and the like, wherein the relationship between the two parameters and the type of the multi-beam antenna is relatively large, the working frequency, the coverage area gain, the C/I and the like, and the increase of the beam number is mainly realized by increasing the number of the feed sources, which means that the envelope size of the feed source array is larger, and in consideration of the thermal stress brought by the wide temperature range of-160-140 ℃ when the high-orbit communication satellite antenna works in orbit and the high pointing accuracy requirement of the multi-beam antenna, the design of the large-scale and high-concentration-quality feed source array and the support structure thereof puts forward more rigorous requirements:
1. the feed source array supporting structure needs to have certain rigidity and strength safety margin, so that the feed source array and the supporting structure thereof are kept in good condition under the action of periodic vibration load and random vibration load when the rocket is launched, and the design of the resistance to the mechanical environment is more rigorous for large-scale feed source arrays with large concentrated mass;
2. the application of the multi-beam antenna requires that the beam of the antenna points accurately, and in order to avoid the deflection problem of the edge position feed source, the pointing angle of the multi-beam antenna needs to be adjusted to the central position of the pointing reflector in design, so that the pointing angles and the installation angles of dozens or even hundreds of feed sources are different and have weak differences, and therefore, a structural plate of the supporting structure for installing the feed source horn needs to have the high-precision installation and positioning capabilities of the feed sources with different angles;
3. the in-orbit extreme high and low temperature range of the feed source array is close to minus 160-140 ℃, the feed part is of an aluminum alloy structure with a higher thermal expansion coefficient (24 e-6), the satellite cabin plate is made of a carbon fiber aluminum honeycomb sandwich structure with a lower thermal expansion coefficient (2-3 e-6), the antenna pointing precision can be influenced due to structural deformation caused by thermal stress between the metal feed part and the composite material cabin plate in a temperature change environment, and the failure damage of the satellite cabin plate interface connection embedded part can be caused by overlarge connection stress in severe cases.
In order to avoid the problems, in the past, a carbon fiber-aluminum honeycomb sandwich structure is mostly adopted by a multi-beam feed source array as a support structure of a large-scale feed source array, a titanium alloy mounting plate which is formed by machining is arranged in front of the support structure and used for positioning and mounting a feed source loudspeaker, and the multi-beam feed source array has the design advantages that: the supporting structure material and the satellite deck plate material are both carbon fiber composite materials with lower thermal expansion coefficients, so that the thermal stress between the supporting structure and the satellite deck plate is reduced, and the problems are as follows:
1. the feed source number of the multi-beam antenna is as high as dozens, in order to ensure the feed source strength in a mechanical environment, a large number of support brackets are required to be arranged on the feed source and a waveguide at the rear end of the feed source, a corresponding number of metal embedded parts are required to be arranged in a carbon fiber honeycomb sandwich structure on connecting hole sites of the support brackets, a large number of embedded parts, foam adhesives around the embedded parts and structural adhesives for reinforcement are required to be filled and reinforced when a composite material honeycomb plate is spliced, a large amount of weight is generated, and the advantage of low original density of the carbon fiber-aluminum honeycomb sandwich structure can be almost ignored;
2. the carbon fiber composite material is a typical anisotropic material, the thermal expansion coefficient of the embedded part filled foam rubber is different from that of a honeycomb sandwich structure in magnitude, and an unexpected torsional deformation can be generated in a composite material support structure under the extremely high and low temperature application state of the rail, so that the pointing accuracy of the antenna is influenced;
3. although the horn positioning mounting hole position can also be precisely manufactured by the traditional milling method for the titanium alloy feed source mounting plate for positioning the feed source direction, the thermal expansion coefficient of the titanium alloy is 3-5 times of that of the carbon fiber composite material of the support structure and is half of that of the aluminum alloy feed source horn, the difference of the thermal expansion coefficients can generate thermal stress under high and low temperature environments to influence the antenna direction, and particularly, the horn can be extruded when the shaft hole between the titanium alloy mounting plate and the aluminum alloy horn is precisely matched with high temperature, and the risk of fatigue damage still exists when the rail works for a long service life;
4. the carbon fiber composite material has long forming time and high manufacturing cost, the main support structure becomes a closed structure after being formed, dozens of intensive feed source waveguides and bracket parts are combined in the closed installation space, the operation space is extremely limited, the design requirement on the human-computer operation environment is high, and meanwhile, great difficulty is brought to the precise installation of the feed source assembly.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: aiming at the problems existing in the traditional design method, the invention provides a thermally decoupled satellite-borne multi-beam antenna feed source array metal supporting structure, so that the situation that the thermal stress of a high-rigidity feed source array is randomly released to a certain rigidity weak point to influence the feed source direction or the fatigue stress damage of parts is avoided; meanwhile, the all-metal feed source array supporting structure has the advantages of high machining and assembling precision, low production cost, convenience in operation and the like, and can effectively improve the economic benefit and the working efficiency of the satellite-borne multi-beam antenna feed source.
The technical scheme adopted by the invention is as follows: a thermally decoupled metal support structure for a satellite-borne multi-beam antenna feed array comprises a front panel, a rear panel, a first side panel, a second side panel, a bottom plate and a mounting base; the bottom plate is arranged at the bottom of a support frame structure formed by the surrounding of the front panel, the rear panel, the first side panel and the second side panel; the plurality of mounting bases are radially mounted on the lower surface of the frame of the bottom plate in a concentric circle mode by taking the projection point of the center of the feed source array phase on the bottom plate as the circle center.
Furthermore, the front panel, the rear panel, the first side panel, the second side panel and the bottom plate are made of aluminum alloy materials, and a plurality of lightening cavities are arranged in the front panel, the rear panel, the first side panel, the second side panel and the bottom plate.
Furthermore, the front panel and the feed source horn of the feed part are positioned by adopting shaft hole matching, and the precision is H7/g7.
Further, the material of the mounting base is titanium alloy.
Furthermore, the mounting base comprises a transverse plate and supporting lug plates, the supporting lug plates are arranged on two sides of the transverse plate, and screw holes are respectively formed in the end portions of the supporting lug plates and the end portions of the transverse plate and used for connecting the bottom plate and the satellite cabin plate.
Further, the mounting base comprises a first mounting base and a second mounting base; the supporting lug of the first mounting base is arranged in the short side direction of the transverse plate; the support lug piece of second installation base sets up on the long limit direction of diaphragm.
Furthermore, stress release grooves are formed in the centers of the two short sides of the transverse plate respectively by the first mounting base.
Furthermore, the stress release groove of the second mounting base is connected with the central points of the two long edges of the transverse plate, and the stress release groove is also formed in the central points of the end parts of the two supporting lug pieces.
Furthermore, when the installation bases are installed, each installation base is in a pi shape on a tangent plane along the radiation direction of the feed source array.
Furthermore, the base plate takes the projection point of the feed source array phase center on the base plate as the circle center, and a plurality of spokes are radially arranged along the radius direction and are connected with the frame of the base plate.
Compared with the prior art, the invention has the beneficial effects that:
(1) The invention adopts the unidirectional weak rigidity mounting base for the thermal decoupling design and the radiation circular layout mode which takes the phase center of the feed source array as the center of a circle, solves the problems of large thermal stress, possible fatigue damage and large pointing error caused by the difference of materials of large-size and large-scale feed source arrays and satellite deck plates, and can also meet the design requirements of high-concentration quality feed source array rigidity design and strength design by the unidirectional weak rigidity mounting base design and radial layout, so that the large-scale feed source array supporting structure with an all-metal structure is successfully applied to the design of the satellite-borne multi-beam antenna, and the advantages of the all-metal feed source array supporting structure, such as high processing and assembling precision, low production cost, convenient operation and the like, are comprehensively embodied.
(2) The invention adopts a novel all-metal multi-beam feed source supporting structure which takes aluminum alloy as a main material, and innovatively provides a thermal coupling type connection design based on the thermal stress problem, a projection point of a feed source array phase center on a mounting surface is taken as a circle center, a mounting base with a one-way weak rigidity design is arranged on a feed source supporting structure bottom plate according to a concentric circle radiation direction, the weak rigidity direction is a parallelogram 'pi' -shaped structure, the instability of the structure can realize weak structural deformation in high and low temperature environments, the integral deformation position of a feed source array is limited on the mounting base between the feed source array and a satellite cabin plate, and the situation that the thermal stress of the feed source array with a high rigidity design is randomly released to a certain weak rigidity point to influence the feed source direction or the fatigue stress damage of parts is avoided; meanwhile, the all-metal feed source array supporting structure has the advantages of high machining and assembling precision, low production cost, convenience in operation and the like, and can effectively improve the economic benefit and the working efficiency of the satellite-borne multi-beam antenna feed source.
Drawings
FIG. 1 is a schematic view of an all-metal feed array and its supporting structure according to the present invention;
1-a feeding means; 2-a waveguide assembly; 3-support structure
FIG. 2 is a schematic view of a feed array support structure of the present invention and an exploded view thereof;
4-a front panel; 5-a rear panel; 6-first side panel; 7-second side panel; 8, a bottom plate; 9-mounting base
FIG. 3 is a schematic view of two different forms of the mounting structure of the one-way weak stiffness mounting base of the present invention;
91 — a first mounting base; 92-second mounting base
FIG. 4 is a schematic view of a thermal pyrolytic coupling layout of a titanium alloy unidirectional weak stiffness mounting base of the present invention in a radial shape with a phase center as a center of circle;
FIG. 5 is a schematic view of two titanium alloy mounting bases of the present invention showing thermal stress relief slots;
FIG. 6 is a schematic diagram of the high-precision shaft hole fit between the feed horn and the front panel.
Detailed Description
The invention is further described below with reference to the accompanying drawings.
As shown in fig. 1 and 2, the invention provides a multi-beam antenna feed source supporting structure based on an all-metal material, wherein a feed part 1 (including a feed source horn, an orthomode coupler and the like) and a waveguide assembly 2 of a feed source array are assembled into a whole through a supporting structure 3 (including a front panel 4, a rear panel 5, a first side panel 6, a second side panel 7 and a bottom plate 8, as shown in fig. 2), all the materials are made of an aluminum alloy material, a mounting base 9 at the bottom of the bottom plate 8 is made of a titanium alloy material, and a connection interface is provided for a satellite cabin plate of a carbon fiber honeycomb sandwich structure.
The supporting structure 3 and the feeding component 1 are made of aluminum alloy materials, and the thermal expansion coefficients of all parts are completely consistent, so that the problem of connection thermal stress between the feeding component 1 and the supporting structure 3 caused by different material thermal expansion coefficients is solved;
as shown in fig. 6, the front panel 4 and the feed source horn are positioned by adopting high-precision shaft hole matching (H7/g 7), the purpose is to provide different pointing angle installation precision guarantee for the feed components 1 of dozens of circuits, the high-precision structural dimension requirement can be met by high-precision milling, and meanwhile, the extrusion fatigue damage of the thin-wall horn caused by the change of the shaft hole matching dimension under the high-temperature and low-temperature conditions can be effectively avoided by the same aluminum alloy material;
the supporting structure 3 of the all-aluminum alloy structure assembles the front panel 4, the rear panel 5, the first side panel 6, the second side panel 7 and the bottom panel 8 together in a screw connection mode, the bottom panel 8 is arranged at the bottom of a supporting frame structure enclosed by the front panel 4, the rear panel 5, the first side panel 6 and the second side panel 7, flat panel type panel parts can obtain higher machining precision through conventional milling processing, the better size precision of the parts brings higher assembling precision, the first side panel 6 and the second side panel 7 can not be arranged in the assembling process, and larger operation space can be provided for operation workers; the five panels are provided with a large number of lightening cavities except the screw connecting part of the main bearing force on the design, the wall thickness is set to be 2 mm-2.5 mm, and the weight index can be kept at the same level as that of a carbon fiber aluminum honeycomb sandwich supporting structure applied by multi-beam with the same scale;
the principle of the thermal decoupling design is that an installation base 9 with one-way weak rigidity design is arranged between a base plate 8 of the feed source array support structure 3 and the satellite cabin plate, the installation base comprises a transverse plate and supporting lugs, the supporting lugs are arranged on two sides of the transverse plate in parallel to form a pi-shaped structure with weak rigidity directions as parallel, the supporting lugs and the end parts of the transverse plate are respectively provided with screw holes, the projection point 10 of the phase center of the feed source array on the installation surface is used as a circle center, the installation base 9 is arranged in a concentric circle type radial mode in the weak rigidity direction of the installation base 9 under the environment with high and low temperature, the deformation of the installation base of the feed source array support structure 9 is greatly limited relative to the deformation of the installation base of the quadrilateral base 9, the deformation of the installation base 9 is greatly limited by the deformation of the thermal deformation of the feed source array support structure, the deformation of the feed source array support structure is reduced, and the deformation of the feed source array support structure is greatly reduced, a plurality of spokes are radially arranged along the radius direction and are connected with the frame of the bottom plate 8.
The mounting base 9 is arranged in the weak stiffness direction of a parallelogram in the radiation direction with a phase center as a circle center, and the equivalent thickness in other directions is larger, so that the mounting base can still provide larger stiffness, and the number of the mounting bases 9 is increased during design to improve the first-order fundamental frequency of the feed source array 1, wherein the first-order fundamental frequencies in three directions of the feed source component X, Y, Z are 145.73Hz/X direction, 163.82Hz/Y direction and 91.89Hz/Z direction respectively, so that the requirements that the first-order frequency X, Y direction of the satellite feed source is higher than 30Hz and the Z direction is higher than 60Hz are met, and the structural strength risk brought by main frequency resonance of a satellite structure is avoided;
the mounting base 9 is made of titanium alloy with the mark TC4-R, and the aim of selecting the titanium alloy material is as follows: the interface position of the feed source array 1 and the satellite deck plate, namely the mounting base 9 is the maximum stress part in the emission mechanical environment of the feed source array, and the titanium alloy material has the yield strength close to that of a steel material, so that the design requirement of large stress can be met; secondly, the titanium alloy has good elasticity and is suitable for the application requirement of on-orbit weak elastic strain for a long time; meanwhile, the titanium alloy material has the advantages of low density and light weight, so that the titanium alloy material becomes a preferable material for the mounting base.
As shown in fig. 3 to 5, the mounting base plate 8 of the feed source array supporting structure 3 is lower in height from the satellite deck, the mounting base plate 8 in this embodiment is 42mm in height, so that the operating space is limited, and in order to meet the operating space requirement when the mounting base 9 and the satellite deck are installed by screws, two different types of parallelogram mounting bases, namely a first mounting base 91 and a second mounting base 92, are designed, so that all mounting interfaces are completely arranged on the outer side of the periphery of the base plate 8, and sufficient mounting space is reserved for mounting the feed source array and the supporting structure thereof on the satellite deck; the mounting base 9 itself is also designed with stress relief grooves 93 for reducing thermal coupling deformation, which can further reduce thermal coupling shear stress between the mounting base 9 and the embedded parts of the satellite deck. The supporting lug pieces of the first mounting base 91 are arranged in the direction of the short sides of the transverse plate, and stress release grooves 93 are respectively formed in the centers of the two short sides of the transverse plate; the supporting lugs of the second mounting base 92 are arranged in the long edge direction of the transverse plate, the stress releasing grooves 93 are connected with the central points of the two long edges of the transverse plate, and meanwhile, the stress releasing grooves 93 are also formed in the central points of the end parts of the two supporting lugs.
When the antenna works in orbit, the feed source array realizes thermal stress decoupling between the metal feed source array and the carbon fiber structure satellite cabin plate through weak deformation of the first mounting base 91 and the second mounting base 92 below the bottom plate 8 in the weak rigidity direction.
The unidirectional weak rigidity mounting base 9 adopted by the invention is designed according to the radiation direction of a concentric circle taking the phase center of the feed source array as the center of the circle, and other realization forms of similar radial structures such as I-shaped structures are also the protection objects of the invention.
The object applied by the invention is not limited to the support design of the large-scale feed source array of the multi-beam antenna, and other C, ku and Ka frequency band double feed source and multi-feed source support structure designs can be developed according to the invention and are also the protection objects of the invention.
The above description is only for the best mode of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention.
Those skilled in the art will appreciate that the details of the invention not described in detail in this specification are well within the skill of those in the art.
Claims (10)
1. The utility model provides a thermally decoupled satellite-borne multi-beam antenna feed array metal bearing structure which characterized in that: comprises a front panel (4), a rear panel (5), a first side panel (6), a second side panel (7), a bottom plate (8) and a mounting base (9); the bottom plate (8) is arranged at the bottom of a supporting frame structure surrounded by the front panel (4), the rear panel (5), the first side panel (6) and the second side panel (7); the plurality of mounting bases (9) are radially mounted on the lower surface of the frame of the bottom plate (8) in a concentric circle mode by taking a projection point (10) of a feed source array phase center on the bottom plate (8) as a circle center.
2. The structure of claim 1, wherein the front panel (4), the rear panel (5), the first side panel (6), the second side panel (7), and the bottom panel (8) are made of aluminum alloy, and a plurality of lightening cavities are formed in the front panel (4), the rear panel (5), the first side panel (6), the second side panel (7), and the bottom panel (8).
3. The structure of claim 1, wherein the front panel (4) and the feed horn of the feed component (1) are positioned by shaft hole matching with an accuracy of H7/g7.
4. A thermally decoupled satellite-borne multi-beam antenna feed array support structure according to claim 1, characterized in that the material of said mounting base (9) is titanium alloy.
5. The structure of claim 4, wherein the mounting base (9) comprises a transverse plate and supporting lugs, the supporting lugs are arranged on two sides of the transverse plate, and screw holes are respectively arranged at the ends of the supporting lugs and the transverse plate for connecting the bottom plate (8) and the satellite cabin plate.
6. A thermally decoupled on-board multi-beam antenna feed array support structure according to claim 5, characterized in that said mounting base (9) comprises a first mounting base (91) and a second mounting base (92); the supporting lug of the first mounting base (91) is arranged in the short side direction of the transverse plate; the supporting lug pieces of the second mounting base (92) are arranged in the long edge direction of the transverse plate.
7. The structure according to claim 6, wherein the first mounting base (91) is opened with stress relief grooves (93) at the center of two short sides of the horizontal plate.
8. A thermally decoupled satellite borne multibeam antenna feed array support structure according to claim 6, wherein the stress relief slots (93) of the second mounting base (92) connect the center points of the two long sides of the transverse plate, and the stress relief slots (93) are also opened at the center points of the ends of the two supporting tabs.
9. The structure according to claim 8, wherein each mounting base (9) is installed in a pi-shaped manner on a tangent plane along the radiation direction of the feed array.
10. The feed array support structure of claim 1, wherein the base plate (8) is connected to the frame of the base plate (8) by radially arranging a plurality of spokes around a radial direction, with a center of a phase of the feed array projected on a projection point (10) of the base plate (8) as a center.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211176998.1A CN115642385A (en) | 2022-09-26 | 2022-09-26 | Thermally decoupled satellite-borne multi-beam antenna feed source array metal supporting structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211176998.1A CN115642385A (en) | 2022-09-26 | 2022-09-26 | Thermally decoupled satellite-borne multi-beam antenna feed source array metal supporting structure |
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| Publication Number | Publication Date |
|---|---|
| CN115642385A true CN115642385A (en) | 2023-01-24 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211176998.1A Pending CN115642385A (en) | 2022-09-26 | 2022-09-26 | Thermally decoupled satellite-borne multi-beam antenna feed source array metal supporting structure |
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| CN (1) | CN115642385A (en) |
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- 2022-09-26 CN CN202211176998.1A patent/CN115642385A/en active Pending
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