CN113922080A - Airborne conformal low-RCS antenna housing - Google Patents
Airborne conformal low-RCS antenna housing Download PDFInfo
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- CN113922080A CN113922080A CN202111124908.XA CN202111124908A CN113922080A CN 113922080 A CN113922080 A CN 113922080A CN 202111124908 A CN202111124908 A CN 202111124908A CN 113922080 A CN113922080 A CN 113922080A
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/42—Housings not intimately mechanically associated with radiating elements, e.g. radome
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
- H01Q1/285—Aircraft wire antennas
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q17/00—Devices for absorbing waves radiated from an antenna; Combinations of such devices with active antenna elements or systems
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- Aviation & Aerospace Engineering (AREA)
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Abstract
The invention provides an airborne conformal low-RCS radome, wherein a conformal wave-transmitting medium base material coated with a wave-absorbing material covers a conformal aluminum alloy frame, epoxy glue is coated on a low table top of the conformal aluminum alloy frame, the conformal wave-transmitting medium base material and the conformal aluminum alloy frame are bonded together, a V-shaped groove is formed by the edge chamfer angle of the conformal wave-transmitting medium base material and the step chamfer angle of the conformal aluminum alloy frame, and anti-tearing silicon rubber is filled in the V-shaped groove, so that the conformal low-RCS radome is formed. The invention enables scattered waves generated at discontinuous parts to be absorbed by wave-absorbing materials, realizes the purpose of low RCS, has no protrusion, no step and no depression on the surface except for the mounting hole, and avoids the scattered waves generated by discontinuous structures. The tear-resistant silicon rubber is used for filling the gap, so that the fatigue resistance of the surface coating can be improved, and the crack resistance of the surface of the antenna housing is improved.
Description
Technical Field
The invention relates to the field of radars, in particular to an airborne radome, and relates to a low Radar Cross Section (RCS) antenna technology.
Background
In modern war, stealth is one of the key factors for improving the survivability and the defense-breaking ability of the aircraft, and is also an important condition for ensuring that the first enemy can discover and attack the first enemy. The stealth technology is also called as a low detectable technology or a target characteristic control technology, and is a technology which makes enemies difficult to find or prompts detectors of the enemies to find a short distance by using a comprehensive means. The stealth technology generally refers to a radar stealth technology, and the technology mainly reduces the signal characteristics of detected radar waves by skillful design of structure and appearance or means of coating wave-absorbing materials and the like to realize stealth. RCS (Radar cross section) is a parameter for measuring the stealth performance of a target, and the dimension is square meter or dBsm (dBm)2)。
Airborne stealth antennas are a type of antenna mounted on the surface of the skin of a stealth aircraft. It not only satisfies corresponding radiation performance, but also possesses low RCS performance. Generally, the number of airborne antennas of a large aircraft is more than ten to dozens of antennas, the stealth performance of the whole aircraft is seriously deteriorated due to the superposition of scattered waves of a plurality of antennas, and therefore the RCS value of each antenna needs to be lower than-35 dBsm to-40 dBsm to meet the stealth requirement of the whole aircraft. Common airborne L-band antennas are mostly microstrip antennas, cavity antennas and the like, and RCS values of the antennas are about-30 dBsm; RCS values of airborne knife antennas, rod antennas and the like are about-25 dBsm, and stealth of the antennas cannot meet requirements of stealth aircrafts.
The airborne stealth antenna mainly reduces the RCS value through two technical means: firstly, loading a stealth antenna housing, and controlling and detecting the scattering direction of radar waves or absorbing the radar waves by using the antenna housing; secondly, a low RCS antenna radiator is designed to control the scattering of the antenna to the detection radar wave or directly absorb the radar wave. Because the antenna radiator needs certain appearance and can't carry out excessive low RCS design in order to satisfy the radiation performance, and the antenna house is as radar detection ripples direct irradiation's part, can more direct action produce low RCS effect and avoid the restriction of radiation performance to antenna radiator appearance in radar detection ripples, consequently a low RCS antenna house of a section has the effect of doing a lot of work to airborne stealth antenna.
Disclosure of Invention
To overcome the deficiencies of the prior art, the present invention provides an onboard conformal low RCS radome. The invention provides a low RCS antenna housing which can be widely applied to an airborne antenna, and meanwhile, the antenna housing also has the characteristics of simple structure and high and low temperature resistance.
The technical scheme adopted by the invention for solving the technical problems is as follows:
an airborne conformal low-RCS radome comprises a conformal aluminum alloy frame, a conformal wave-transmitting medium base material, a wave-absorbing material and tear-resistant silicon rubber; the conformal wave-transmitting medium base material coated with the wave-absorbing material covers the conformal aluminum alloy frame, the size of the conformal wave-transmitting medium base material completely covers the central cavity and the step width of the conformal aluminum alloy frame, epoxy glue is coated on the low table top of the conformal aluminum alloy frame, the conformal wave-transmitting medium base material is bonded with the conformal aluminum alloy frame, meanwhile, a rivet penetrates through a rivet hole to rivet the conformal wave-transmitting medium base material and the conformal aluminum alloy frame, a V-shaped groove is formed by the edge chamfer angle of the conformal wave-transmitting medium base material and the step chamfer angle of the conformal aluminum alloy frame, tear-resistant silicon rubber is filled in the V-shaped groove, the wave-absorbing material is coated on the surface of the tear-resistant silicon rubber, and the V-shaped groove is guaranteed to be filled completely and flatly, so that the conformal low RCS radome is formed; the conformal low-RCS antenna housing is loaded on an airborne array antenna, each radiating unit of the array antenna is just positioned below a projection of a conformal wave-transmitting medium substrate, each projection is used as a wave-transmitting window of a unit antenna to realize antenna radiation, and the antenna housing has stealth performance.
The conformal aluminum alloy frame is a rhombic frame with a central hole, the outline curved surface of the frame is conformal with the aircraft skin curved surface, the diagonal dimension of the outer edge of the frame is 10% -30% larger than that of the conformal wave-transmitting medium base material, and the thickness of the frame is 2-5 times that of the conformal wave-transmitting medium base material; the diagonal dimension of the central cavity of the frame is 10 to 30 percent smaller than that of the conformal wave-transmitting medium substrate; the cross section of the conformal aluminum alloy frame is a step, the table top at the outer edge is higher than the table top at the inner edge, the width of the low table top is 10-35 mm, a plurality of counter bores along the outline edge of the conformal aluminum alloy frame are uniformly distributed on the high table top at the position 5-25 mm away from the outer edge of the conformal aluminum alloy frame, and screws penetrate through the counter bores to be connected with the aircraft skin; the height difference of the high table top and the low table top is equal to the thickness of the conformal wave-transmitting medium base material coated with the wave-absorbing material, the joint of the high table top and the low table top is a chamfer angle, the height of the chamfer angle is the same as the height of the step, rivet holes are uniformly distributed on the low table top along the periphery of the step, and the center of each rivet hole is 2mm-10mm away from the inner edge of the high table top.
The conformal aluminum alloy frame is made of an aviation aluminum alloy material magnesium-aluminum alloy or aluminum-lithium alloy.
The conformal wave-transmitting medium substrate is a rigid wave-transmitting material and is made of epoxy glass fiber cloth or polycarbonate material; if the epoxy glass fiber cloth is adopted, a hot-pressing tank process is adopted for compression molding; if the polycarbonate is used, the polycarbonate is processed and molded by a precision milling machine.
The conformal wave-transmitting medium base material is a plate with the thickness of 0.5-5 mm and uniform thickness, the shape curved surface of the conformal wave-transmitting medium base material is conformal with the aircraft skin curved surface, the edge of the conformal wave-transmitting medium base material is a chamfer angle, the height of the chamfer angle is the same as the height of a step of a conformal aluminum alloy frame, the outline of the conformal wave-transmitting medium base material is a rhombus, and the acute angle inner angle of the rhombus is 50-80 degrees; the conformal wave-transmitting medium base material is characterized in that a bump is arranged at the intersection of a diamond diagonal of the conformal wave-transmitting medium base material, the height of the bump is 0.2 mm-2 mm, the shape curved surface of the bump is conformal with the aircraft skin curved surface, the outline of the bump is diamond-shaped, triangular or polygonal, the acute internal angle of the bump is the same as and parallel to the conformal wave-transmitting medium base material, and the area of the bump is 10% -80% smaller than that of the conformal wave-transmitting medium base material.
The wave-absorbing material is a coating type wave-absorbing material, the wave-absorbing material is uniformly coated on the surface of one side of the conformal wave-transmitting medium base material where the lug is positioned, the wave-absorbing material is coated in the region of the conformal wave-transmitting medium base material outside the lug, and the thickness of the wave-absorbing material is the same as the height of the lug.
The acute angle direction of the bump is consistent with the acute angle direction of the rhombus of the conformal wave-transmitting medium substrate.
The invention has the beneficial effects that:
(1) low RCS. Electromagnetic wave scattering occurs primarily in discrete regions, including discontinuous structures and discontinuous materials. The discontinuous structure mainly comprises steps, gaps, protrusions, depressions and the like, and the discontinuous material mainly refers to joints of different materials, such as joints of metal and nonmetal, joints of different nonmetal materials and the like. The invention adopts the method of covering the discontinuous part with the wave-absorbing material, so that scattered waves generated at the discontinuous part are absorbed by the wave-absorbing material, and the aim of low RCS is fulfilled. The wave-absorbing material is filled at the joint of the conformal aluminum alloy frame and the conformal wave-transmitting medium base material, so that scattered waves caused by discontinuity of the material are absorbed; the wave-absorbing material is coated on the surface of one side, provided with the bumps, of the conformal wave-transmitting medium base material, so that scattered waves caused by the discontinuity of the bumps are absorbed; the surface of the antenna housing has no protrusion, no step and no depression except for the mounting hole, so that scattered waves generated by discontinuous structure are avoided.
(2) And the high and low temperature environment can be resisted. Because the thermal expansion coefficients of the conformal wave-transmitting medium substrate and the conformal aluminum alloy frame are different in high and low temperature environments, coatings such as wave-absorbing materials on the surface of the antenna housing can be fatigue-torn after repeated high and low temperature transformation, and antenna housing cracks are caused. According to the invention, the tear-resistant silicon rubber is adopted to fill the gap, so that the fatigue resistance of the surface coating can be improved, and the anti-cracking capability of the surface of the antenna housing is improved.
Drawings
Fig. 1 is a profile view of an airborne conformal low RCS radome of the present invention.
FIG. 2 is an outline view of the aluminum alloy frame of the present invention.
FIG. 3 is a shape diagram of a wave-transparent medium substrate without a wave-absorbing material coating.
FIG. 4 is a cross-sectional view of the wave-transparent medium substrate coated with the wave-absorbing material.
Fig. 5 is an enlarged partial cross-sectional view of fig. 1.
FIG. 6 is a schematic view of example 2.
FIG. 7 is a schematic view of example 3.
FIG. 8 is a schematic view of example 4.
Fig. 9 is a graph comparing RCS test curves for examples 1, 2, 3, 4 and a reference radome.
The composite material comprises a 1-conformal aluminum alloy frame, a 2-conformal wave-transmitting medium base material, a 3-wave-absorbing material and 4-tear-resistant silicon rubber.
Detailed Description
The invention is further illustrated with reference to the following figures and examples.
The technical scheme of the invention is further explained by combining the drawings and the specific embodiments in the specification. It should be understood that these examples are for illustrative purposes only and are not intended to limit the scope of the present invention.
An airborne conformal low-RCS radome comprises a conformal aluminum alloy frame, a conformal wave-transmitting medium base material, a wave-absorbing material and tear-resistant silicon rubber; the conformal wave-transmitting medium base material coated with the wave-absorbing material covers the conformal aluminum alloy frame, the size of the conformal wave-transmitting medium base material completely covers the central cavity and the step width of the conformal aluminum alloy frame, epoxy glue is coated on the low table top of the conformal aluminum alloy frame, the conformal wave-transmitting medium base material is bonded with the conformal aluminum alloy frame, meanwhile, a rivet penetrates through a rivet hole to rivet the conformal wave-transmitting medium base material and the conformal aluminum alloy frame, a V-shaped groove is formed by the edge chamfer angle of the conformal wave-transmitting medium base material and the step chamfer angle of the conformal aluminum alloy frame, tear-resistant silicon rubber is filled in the V-shaped groove, the wave-absorbing material is coated on the surface of the tear-resistant silicon rubber, and the V-shaped groove is guaranteed to be filled completely and flatly, so that the conformal low RCS radome is formed; the conformal low-RCS antenna housing is loaded on an airborne array antenna, each radiating unit of the array antenna is just positioned below a projection of a conformal wave-transmitting medium substrate, each projection is used as a wave-transmitting window of a unit antenna to realize antenna radiation, and the antenna housing has stealth performance.
The conformal aluminum alloy frame is a rhombic frame with a central hole, the outline curved surface of the frame is conformal with the aircraft skin curved surface, the diagonal dimension of the outer edge of the frame is 10% -30% larger than that of the conformal wave-transmitting medium base material, and the thickness of the frame is 2-5 times that of the conformal wave-transmitting medium base material; the diagonal dimension of the central cavity of the frame is 10 to 30 percent smaller than that of the conformal wave-transmitting medium substrate; the cross section of the conformal aluminum alloy frame is a step, the table top at the outer edge is higher than the table top at the inner edge, the width of the low table top is 10-35 mm, a plurality of counter bores along the outline edge of the conformal aluminum alloy frame are uniformly distributed on the high table top at the position 5-25 mm away from the outer edge of the conformal aluminum alloy frame, and screws penetrate through the counter bores to be connected with the aircraft skin; the height difference of the high table top and the low table top is equal to the thickness of the conformal wave-transmitting medium base material coated with the wave-absorbing material, the joint of the high table top and the low table top is a chamfer angle, the height of the chamfer angle is the same as the height of the step, rivet holes are uniformly distributed on the low table top along the periphery of the step, and the center of each rivet hole is 2mm-10mm away from the inner edge of the high table top.
The conformal aluminum alloy frame is made of an aviation aluminum alloy material magnesium-aluminum alloy or aluminum-lithium alloy.
The conformal wave-transmitting medium substrate is a rigid wave-transmitting material and is made of epoxy glass fiber cloth or polycarbonate material; if the epoxy glass fiber cloth is adopted, a hot-pressing tank process is adopted for compression molding; if the polycarbonate is used, the polycarbonate is processed and molded by a precision milling machine.
The conformal wave-transmitting medium base material is a plate with the thickness of 0.5-5 mm and uniform thickness, the shape curved surface of the conformal wave-transmitting medium base material is conformal with the aircraft skin curved surface, the edge of the conformal wave-transmitting medium base material is a chamfer angle, the height of the chamfer angle is the same as the height of a step of a conformal aluminum alloy frame, the outline of the conformal wave-transmitting medium base material is a rhombus, and the acute angle inner angle of the rhombus is 50-80 degrees; the conformal wave-transmitting medium base material is characterized in that a bump is arranged at the intersection of a diamond diagonal of the conformal wave-transmitting medium base material, the height of the bump is 0.2 mm-2 mm, the shape curved surface of the bump is conformal with the aircraft skin curved surface, the outline of the bump is diamond-shaped, triangular or polygonal, the acute internal angle of the bump is the same as and parallel to the conformal wave-transmitting medium base material, and the area of the bump is 10% -80% smaller than that of the conformal wave-transmitting medium base material.
The wave-absorbing material is a coating type wave-absorbing material, the wave-absorbing material is uniformly coated on the surface of one side of the conformal wave-transmitting medium base material where the lug is positioned, the wave-absorbing material is coated in the region of the conformal wave-transmitting medium base material outside the lug, and the thickness of the wave-absorbing material is the same as the height of the lug.
The acute angle direction of the bump is consistent with the acute angle direction of the rhombus of the conformal wave-transmitting medium substrate.
Example 1:
the wave-absorbing material comprises a conformal aluminum alloy frame (1), a conformal wave-transmitting medium base material (2), a wave-absorbing material (3) and tear-resistant silicon rubber (4).
As shown in fig. 1 and 2, the conformal aluminum alloy frame (1) has a shape curved surface conformal to the aircraft, the outline is a diamond shape, the length of the diagonal line of the diamond shape is 240mm and 169mm respectively, the acute angle and the internal angle of the diamond shape are 72 degrees, and 16 counter bores on the edge of the diamond shape are connecting holes for the radome and the aircraft skin. The center of the conformal aluminum alloy frame (1) is a rhombic cavity, steps are arranged between the edges of the rhombic cavity and connecting lines of centers of 16 counter bores, the height of each step is 2mm, the width of each step is 20mm, the edges of the steps are chamfered, and the height of each chamfer is 2 mm. Near the step chamfer edge are 8 rivet holes.
As shown in fig. 3, the conformal wave-transmitting medium substrate (2) is made of epoxy glass fiber cloth, is molded by autoclave process, and has a thickness of 1mm and is uniform. The outline of the conformal wave-transmitting medium substrate (2) is a rhombus, and the diagonal lengths of the rhombus are 177mm and 125mm respectively. The conformal wave-transmitting medium substrate (2) is provided with 4 diamond-shaped bumps at diamond-shaped diagonal intersection points, and the length of each bump diagonal is as follows: 49.5mm and 35 mm.
As shown in fig. 4, the wave-absorbing material (3) is uniformly coated on the surface of the conformal wave-transmitting medium substrate (2) on the side with the bumps, and the rest surface areas except the raised surface of the bumps are coated. The thickness of the wave-absorbing material is 1mm as same as the height of the bump.
As shown in fig. 5, the edge of the conformal wave-transparent medium substrate (2) is chamfered. And a tear-resistant silicon rubber (4) is smeared in a V-shaped groove formed by the chamfer of the conformal wave-transmitting medium substrate (2) and the step chamfer of the conformal aluminum alloy frame (1). The surface of the tear-resistant silicon rubber (4) is coated with the wave-absorbing material (3) and the V-shaped grooves are filled to be full and smooth.
As shown in fig. 1, when the antenna cover of the present invention is loaded onto a 4-element microstrip antenna array, the electromagnetic wave radiated by each microstrip antenna element is radiated through 4 bumps on the antenna cover, thereby avoiding the influence of the wave-absorbing material on the radiated electromagnetic wave and satisfying the radiation performance of the antenna. Meanwhile, the radome of the invention reduces and absorbs scattered waves caused by various discontinuities, and reduces the RCS value of the antenna.
As shown in figure 5, the anti-tear silicon rubber (4) is filled in the connecting gap of different materials of the radome, so that the fatigue tear of the wave-absorbing material caused by repeated high-low temperature environment change can be relieved, and the radome crack is completely eradicated.
Example 2:
the structure of this embodiment is the same as that of embodiment 1, and is adjusted as follows:
as shown in fig. 6, the number of diamond-shaped bumps on one side surface of the conformal wave-transmitting medium substrate (2) is 1, 3 and 2 respectively.
Example 3:
the structure of this embodiment is the same as that of embodiment 1, and is adjusted as follows:
as shown in FIG. 7, the shapes of the bumps on one side surface of the conformal wave-transmitting medium substrate (2) are respectively triangular, hexagonal and zigzag.
Example 4:
the structure of the present embodiment is the same as that of embodiment 1, and the following adjustments are made:
as shown in fig. 8, the shape of the conformal aluminum alloy frame (1) and the shape of the conformal wave-transparent medium substrate (2) simultaneously become triangular, hexagonal and zigzag.
The above are only preferred embodiments of the present invention, and are not intended to limit the scope of the present invention, and all equivalent modifications of the present invention, or direct/indirect applications of the present invention to specific devices or other related fields are included in the scope of the present invention.
The technical effects of the present invention are further explained below with reference to the test results:
1. test conditions and contents:
a conventional epoxy glass fiber cloth flat radome is adopted as a reference radome. Example 1 and a reference radome were loaded on a 4-element microstrip antenna array to form two antennas. The RCS values of the two antennas are respectively tested in a compact range microwave dark room, the testing frequency is 4GHz-18GHz, the frequency interval is 1GHz, the incident wave direction is the X-axis negative direction, and the incident wave polarization is the Y-axis direction.
2. And (3) testing results:
referring to fig. 9, the horizontal axis represents frequency and the vertical axis represents RCS value, and the RCS values of the radomes respectively using the embodiments 1, 2, 3 and 4 are reduced by 2dB to 20dB from the RCS value of the reference radome under the same array antenna.
Claims (7)
1. The utility model provides an airborne conformal low RCS antenna house, includes conformal aluminum alloy frame, conformal wave-transmitting medium substrate, absorbing material and anti-tear silicon rubber, its characterized in that:
the airborne conformal low RCS radome; the conformal wave-transmitting medium base material coated with the wave-absorbing material covers the conformal aluminum alloy frame, the size of the conformal wave-transmitting medium base material completely covers the central cavity and the step width of the conformal aluminum alloy frame, epoxy glue is coated on the low table top of the conformal aluminum alloy frame, the conformal wave-transmitting medium base material is bonded with the conformal aluminum alloy frame, meanwhile, a rivet penetrates through a rivet hole to rivet the conformal wave-transmitting medium base material and the conformal aluminum alloy frame, a V-shaped groove is formed by the edge chamfer angle of the conformal wave-transmitting medium base material and the step chamfer angle of the conformal aluminum alloy frame, tear-resistant silicon rubber is filled in the V-shaped groove, the wave-absorbing material is coated on the surface of the tear-resistant silicon rubber, and the V-shaped groove is guaranteed to be filled completely and flatly, so that the conformal low RCS radome is formed; the conformal low-RCS antenna housing is loaded on an airborne array antenna, each radiating unit of the array antenna is just positioned below a projection of a conformal wave-transmitting medium substrate, each projection is used as a wave-transmitting window of a unit antenna to realize antenna radiation, and the antenna housing has stealth performance.
2. The airborne conformal low RCS radome of claim 1 wherein:
the conformal aluminum alloy frame is a rhombic frame with a central hole, the outline curved surface of the frame is conformal with the aircraft skin curved surface, the diagonal dimension of the outer edge of the frame is 10% -30% larger than that of the conformal wave-transmitting medium base material, and the thickness of the frame is 2-5 times that of the conformal wave-transmitting medium base material; the diagonal dimension of the central cavity of the frame is 10 to 30 percent smaller than that of the conformal wave-transmitting medium substrate; the cross section of the conformal aluminum alloy frame is a step, the table top at the outer edge is higher than the table top at the inner edge, the width of the low table top is 10-35 mm, a plurality of counter bores along the outline edge of the conformal aluminum alloy frame are uniformly distributed on the high table top at the position 5-25 mm away from the outer edge of the conformal aluminum alloy frame, and screws penetrate through the counter bores to be connected with the aircraft skin; the height difference of the high table top and the low table top is equal to the thickness of the conformal wave-transmitting medium base material coated with the wave-absorbing material, the joint of the high table top and the low table top is a chamfer angle, the height of the chamfer angle is the same as the height of the step, rivet holes are uniformly distributed on the low table top along the periphery of the step, and the center of each rivet hole is 2mm-10mm away from the inner edge of the high table top.
3. The airborne conformal low RCS radome of claim 1 wherein:
the conformal aluminum alloy frame is made of an aviation aluminum alloy material magnesium-aluminum alloy or aluminum-lithium alloy.
4. The airborne conformal low RCS radome of claim 1 wherein:
the conformal wave-transmitting medium substrate is a rigid wave-transmitting material and is made of epoxy glass fiber cloth or polycarbonate material; if the epoxy glass fiber cloth is adopted, a hot-pressing tank process is adopted for compression molding; if the polycarbonate is used, the polycarbonate is processed and molded by a precision milling machine.
5. The airborne conformal low RCS radome of claim 1 wherein:
the conformal wave-transmitting medium base material is a plate with the thickness of 0.5-5 mm and uniform thickness, the shape curved surface of the conformal wave-transmitting medium base material is conformal with the aircraft skin curved surface, the edge of the conformal wave-transmitting medium base material is a chamfer angle, the height of the chamfer angle is the same as the height of a step of a conformal aluminum alloy frame, the outline of the conformal wave-transmitting medium base material is a rhombus, and the acute angle inner angle of the rhombus is 50-80 degrees; the conformal wave-transmitting medium base material is characterized in that a bump is arranged at the intersection of a diamond diagonal of the conformal wave-transmitting medium base material, the height of the bump is 0.2 mm-2 mm, the shape curved surface of the bump is conformal with the aircraft skin curved surface, the outline of the bump is diamond-shaped, triangular or polygonal, the acute internal angle of the bump is the same as and parallel to the conformal wave-transmitting medium base material, and the area of the bump is 10% -80% smaller than that of the conformal wave-transmitting medium base material.
6. The airborne conformal low RCS radome of claim 1 wherein:
the wave-absorbing material is a coating type wave-absorbing material, the wave-absorbing material is uniformly coated on the surface of one side of the conformal wave-transmitting medium base material where the lug is positioned, the wave-absorbing material is coated in the region of the conformal wave-transmitting medium base material outside the lug, and the thickness of the wave-absorbing material is the same as the height of the lug.
7. The airborne conformal low RCS radome of claim 1 wherein:
the acute angle direction of the bump is consistent with the acute angle direction of the rhombus of the conformal wave-transmitting medium substrate.
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| CN202111124908.XA CN113922080A (en) | 2021-09-25 | 2021-09-25 | Airborne conformal low-RCS antenna housing |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN117978260A (en) * | 2024-03-29 | 2024-05-03 | 浙江中星光电子科技有限公司 | Satellite communication terminal and installation method |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117978260A (en) * | 2024-03-29 | 2024-05-03 | 浙江中星光电子科技有限公司 | Satellite communication terminal and installation method |
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