CN113381179B - Bionic constant-temperature antenna shell structure - Google Patents
Bionic constant-temperature antenna shell structure Download PDFInfo
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- CN113381179B CN113381179B CN202110471562.4A CN202110471562A CN113381179B CN 113381179 B CN113381179 B CN 113381179B CN 202110471562 A CN202110471562 A CN 202110471562A CN 113381179 B CN113381179 B CN 113381179B
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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
- H01Q1/02—Arrangements for de-icing; Arrangements for drying-out ; Arrangements for cooling; Arrangements for preventing corrosion
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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
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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
- H01Q1/422—Housings not intimately mechanically associated with radiating elements, e.g. radome comprising two or more layers of dielectric material
Abstract
The invention provides a bionic constant-temperature antenna shell structure which comprises a surface layer, a leather layer and a framework layer, wherein the surface layer comprises an outer wall plate (1) and a wave-transmitting layer (5), the outer wall plate (1) is a thin-wall metal structure for maintaining a pneumatic appearance, and the wave-transmitting layer (5) is a high-temperature-resistant wave-transmitting nonmetal thin-wall structure; the dermis layer comprises a side wall plate (2), the side wall plate (2) is of a high-rigidity cavity structure, is integrally formed by hot blowing, is internally formed into a cavity structure imitating a biological circulation system, and is used for circulating cooling liquid; the framework layer is composed of a bottom plate (3), the bottom plate (3) is of a light high-rigidity bionic sandwich structure, and the core part is of a bionic sandwich layer and is of a bionic skeleton lattice structure, a deep sea cavernous body imitating porous structure or a honeycomb structure imitating a honeycomb. The invention develops the bionic structure form antenna shell structure integrating various biological structure characteristics, on one hand, the multifunctional integration of bearing/thermal control/loading of a structure system is realized; and on the other hand, the weight of the antenna structure is reduced.
Description
Technical Field
The invention relates to an airborne antenna structure of an aircraft, and belongs to the technical field of structural design of aircraft.
Background
As aircraft speeds increase, aerodynamic heating of the outer surface of the aircraft becomes more pronounced, requiring the addition of a thermal barrier to prevent heat from entering the aircraft. However, in order to ensure wave-transmitting performance of the antenna on the outer surface of the aircraft, the surface cannot be added with a heat-proof layer. Therefore, the design of the antenna shell needs to select high-temperature resistant materials, and the high temperature of the antenna cannot be conducted to the interior of the aircraft. Conventional antenna housing structures have not been suitable for use in high speed aircraft. A new airborne antenna structure scheme needs to be designed to meet the urgent needs in the field of airborne antennas. As aircraft speeds increase, aerodynamic heating of the outer surface of the aircraft becomes more pronounced, requiring the addition of a thermal barrier to prevent heat from entering the aircraft. However, in order to ensure wave-transmitting performance of the antenna on the outer surface of the aircraft, a thick and heavy heat-proof layer cannot be added on the surface. Therefore, the design of the antenna shell needs to select high-temperature-resistant materials, a layer of high-temperature-resistant anti-oxidation wave-transmitting material needs to be laid on the outer surface of the antenna shell under necessary conditions, the high temperature of the antenna cannot be conducted to the inside of the aircraft, and the weight of the antenna is reduced as much as possible under the condition that the strength and the rigidity of the antenna are met. Aiming at a high-temperature environment, the traditional scheme is to add a heat-proof layer on the surface, but the thicker the heat-proof layer is, the poorer the wave-transmitting performance is, and the traditional antenna shell structure is no longer suitable for a high-speed aircraft. In nature, animal bones, bird beaks and other structures have bearing capacity and are carriers of internal transmission systems of organisms. In order to seek a more reasonable solution, the natural world needs to be studied, and a novel airborne antenna structure scheme is designed to meet the urgent needs in the field of airborne antennas.
Disclosure of Invention
The technical problem to be solved by the invention is to provide a heat-resistant, heat-insulating and light bionic antenna shell structure.
In order to solve the technical problems, the technical scheme adopted by the shell structure of the bionic constant-temperature antenna provided by the invention is as follows:
the antenna housing structure comprises an epidermal layer, a dermal layer and a framework layer,
the surface layer comprises an outer wall plate and a wave-transmitting layer, the outer wall plate is a thin-walled metal structure for maintaining the pneumatic appearance, and the wave-transmitting layer is a high-temperature-resistant wave-transmitting non-metal thin-walled structure;
the dermis layer comprises a side wall plate which is of a cavity structure, is integrally formed by hot blowing, and is internally formed into a cavity structure imitating a biological circulation system for circulation of cooling liquid;
the framework layers play a role in bearing and connecting and are composed of bottom plates, the bottom plates are of light high-rigidity bionic sandwich structures, and the core parts are of bionic sandwich layers and are of bionic skeleton lattice structures, deep sea sponge-like porous structures or honeycomb-like honeycomb structures.
Further, the outer wall plate and the side wall plate are respectively molded and are connected together by heating and diffusion, or the side wall plate is connected with the outer wall plate when the side wall plate is in a flat plate shape, and then the outer wall plate and the side wall plate are molded by inflation; the bottom plate and the side wall plate are nested together in a tight fit mode or are welded together.
Furthermore, the wave-transparent layer is composed of a high-temperature-resistant and oxidation-resistant ceramic heat-proof structure or a resin heat-resistant structure; the outer wall plate is of an aluminum alloy or titanium alloy structure; the side wall plates and the bottom plate are of metal structures, and are made of the same aluminum alloy and titanium alloy materials as the outer wall plates or different metal materials.
Further, the thickness of the outer wall plate and the side wall plate ranges from 1mm to 20 mm; the thickness range of the base plate is 1mm to 30mm, wherein the thickness of the bionic sandwich layer is 1mm to 30mm, and the thickness of thin plates on two sides of the sandwich layer is 0.1mm to 3 mm.
Furthermore, the bottom plate integrates a bionic circulating system, when the side wall plate is in a flat plate state, the side wall plate is connected with the outer wall plate and the bottom plate together, and then the side wall plate is integrally formed through inflation, and the side wall plate is communicated with a circulating channel of the bottom plate circulating system together.
Further, the cavity structure formed by expanding the side wall plates forms flow channels which are parallel to each other, are converged into a cavity at the front end and the rear end, and then are communicated with the outside, and the parallel flow channels include but are not limited to: single-channel spiral structures, multi-channel parallel structures, and multi-channel approximately parallel structures. The number of the parallel flow channels is designed comprehensively according to the thermal environment condition and the liquid flow rate.
Furthermore, the bionic cavity structure formed by expanding the side wall plate is divided into small channels from the main channel and further divided into capillary channels, and then the small channels are converged into the main channel; the length of the main channel and the small channel is as short as possible, and the length of the capillary channel is as long as possible; the number of the channels is designed comprehensively according to the thermal environment condition and the liquid flow rate.
The pipe joint is used for inflow and outflow of cooling liquid, an inner flow passage of the pipe joint adopts a bionic drag reduction design, the shape of an interface of the flow passage is gradually increased from outside to inside and is changed according to the shape of a parabola or a circle involute; and performing bionic drag reduction surface treatment on the internal flow channel to form the lotus leaf-like surface microstructure characteristic.
By applying the technical scheme of the invention, a novel bionic antenna shell structure for an aircraft is provided. The bionic antenna shell structure comprises the epidermal layer, the corium layer and the skeleton layer, and the cooling channel of the bionic circulation system is integrated, so that the heat-resistant wave-transmitting capability of the outer epidermal layer is achieved, the constant temperature control of the middle corium layer is achieved, the light bionic bearing capability of the inner skeleton layer is achieved, and the antenna and the cabin body can be cooled by using a cooling medium conveniently. By applying the invention, a large number of heat insulation layers can be avoided, and the wave-transmitting performance is reduced, so that the antenna performance is reduced; the weight of the antenna can be reduced, the light design is realized, and the volume of the aircraft is finally increased to improve the technical indexes of the aircraft. Meanwhile, the structural shape of the aircraft is not limited, so that the aircraft is high in adaptability and can be suitable for the aircraft with the special-shaped outer surface.
Compared with the prior art, the invention has the beneficial effects that:
(1) the bionic antenna shell is designed, and has the capabilities of resisting heat and transmitting waves of an outer skin layer, controlling the constant temperature of a middle corium layer and carrying light bionic of an inner skeleton layer. The high-speed air vehicle has the integrated characteristics of high wave-transmitting rate, constant temperature and light weight under the flight condition of the high-speed air vehicle, and finally improves the technical indexes of the air vehicle
(2) According to the invention, the fuel oil cooling channel of the bionic circulating system is integrated on the antenna shell, so that the heat is prevented from being transferred to the cabin body, the direct connection between the antenna and the cabin body is realized, and the heat insulation buffer design is not required;
(3) the cooling channels are distributed on the side face of the antenna, so that the periphery of the antenna is uniformly heated, and the situation that ablation damage or abnormal thermal deformation is caused by local overheating due to overlarge temperature difference of different parts of the aircraft is avoided.
(4) According to the antenna shell, the side wall plate, the outer wall plate and the bottom plate are formed through an inflatable integral forming process, so that the component connection operation is reduced, the process is simple, and the assembly precision is high;
(5) the bottom core of the invention adopts a biological skeleton-imitated lattice structure, a deep sea cavernous body-imitated porous structure or a honeycomb-imitated structure, thereby realizing the characteristics of light weight and high strength.
(6) The bionic cavity structure of the antenna shell is divided into small channels by a main channel and further divided into capillary channels, and then the small channels are converged into the main channel; the capillary channel length is as long as possible. The structural characteristics can be comprehensively designed in a corresponding matching way according to the thermal environment condition and the liquid flow rate, and the cooling uniformity is good, the cooling efficiency is high and the universality is strong.
(7) The inner flow passage of the pipe joint adopts a bionic drag reduction design. The shape of the interface of the flow passage is gradually increased from outside to inside and is changed according to the shape of an involute of a parabola or a circle. The inner flow passage is subjected to bionic drag reduction surface treatment to form the lotus leaf-like surface microstructure characteristic. These features can achieve a substantial reduction in the flow resistance of the liquid and an increase in the antenna cooling efficiency.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
Fig. 1 is a schematic view illustrating a structure of a case of an antenna for constant temperature according to an embodiment of the present invention;
FIG. 2 illustrates a top view of a structure of a housing for a constant temperature antenna provided in accordance with an embodiment of the present invention;
FIG. 3 illustrates a front view of a structure of a housing of a constant temperature antenna provided in accordance with an embodiment of the present invention;
FIG. 4 is a cross-sectional view of FIG. 3;
fig. 5 shows a structural diagram of a bottom plate of a housing structure of a constant temperature antenna provided according to an embodiment of the present invention (including a schematic diagram of a pseudo-skeleton structure (fig. 5a) and a schematic diagram of the pseudo-skeleton integrated with a circulatory system (fig. 5 b));
fig. 6 is a schematic diagram illustrating a bionic sandwich layer structure of a housing structure of a constant-temperature antenna provided according to an embodiment of the invention.
Figure 7 shows a cross-sectional view of a pipe coupling provided in accordance with a specific embodiment of the present invention.
Wherein the figures include the following reference numerals:
1-outer wall plate, 2-side wall plate, 3-bottom plate, 4-pipe joint, 5-wave-transparent layer and 6-bionic sandwich layer.
Detailed Description
The invention is described in detail below with reference to the figures and specific embodiments.
In an embodiment of the present invention, a bionic constant temperature antenna casing structure includes an epidermis layer, a dermis layer, and a skeleton layer. The surface layer has the functions of bearing and insulating heat, and the use temperature of the surface layer is 100-2000 ℃. The skin layers comprise an outer wall plate 1 and a wave-transparent layer 5; the dermis layer comprises a sidewall plate 2 and a tube connector 4; the framework layer is composed of a bottom plate 3, and the structure of the framework layer is shown in figures 1-2.
The outer wall plate 1 is of a thin-wall metal structure for maintaining pneumatic appearance, and the wave-transmitting layer 5 is of a high-temperature-resistant wave-transmitting nonmetal thin-wall structure. The side wall plate 2 is of a cavity structure, the whole body is formed by hot blowing, and the inner part is formed into a cavity structure imitating a biological circulation system. The bottom plate 3 plays a role in bearing and connecting, is of a lightweight high-rigidity bionic sandwich structure (as shown in fig. 5 (a)), and the core part is of a bionic sandwich layer and is of a honeycomb structure imitating a honeycomb, a porous structure imitating a deep sea cavernous body or an bionic bone lattice structure (as shown in fig. 6). The pipe joint 4 is used for the inflow and outflow of cooling liquid, is used for blocking heat transfer to the inside of an aircraft cabin, and plays a role in preventing heat insulation and enabling the antenna to be constant in temperature.
Further, the outer wall plate 1 and the side wall plate 2 are respectively formed and are heated and diffused to be connected together, or the outer wall plate 1 is connected together when the side wall plate 2 is in a flat plate state, and then the side wall plate 2 is formed by inflation, so that the side wall plate 2 is expanded from a flat plate state to be in a high-rigidity cavity structure. The bottom plate 3 and the side wall plate 2 are nested together in a tight fit or welded together.
Further, the thickness of the outer wall plate 1 ranges from 1mm to 20 mm. The outer wall plate 1 is made of aluminum alloy or titanium alloy, and aluminum alloy such as 6061 or titanium alloy materials conventionally used at present such as TA15 and TC4 can be selected. The structural surface of the outer wall plate 1 is an aircraft aerodynamic outer surface, an antenna paraboloid or other required surface.
The thickness range of the wave-transparent layer 5 is 0.1mm to 10 mm. The wave-transmitting layer 5 is made of a high-temperature-resistant and oxidation-resistant ceramic heat-proof structure or a resin thermal structure, and can be selected from SiO2, C/SiC, C/C, quartz reinforced polyimide resin or A12O3 and the like. The structural surface of the wave-transparent layer 5 is an aircraft pneumatic outer surface, an antenna paraboloid or other required surfaces.
The side wall panels 2 range in thickness from 1mm to 20 mm. The side wall plate 2 is made of metal, and is made of aluminum alloy such as 6061 and the like, or titanium alloy material such as TA15, TC4 and the like which is the same as the outer wall plate 1 and is used conventionally or different metal materials.
The pipe joint 4 is made of metal and is made of aluminum alloy such as 6061 and the like or titanium alloy materials such as TA15, TC4 and the like which are conventionally used at present and are the same as the outer wall plate 1. Which may be machined from a rod, is welded to the side wall plate 2. The contact surface can be square, rectangular or round. The other end is a round structure, the outer side is provided with threads, and the front section is conical.
The bottom plate 3 is of a metal structure, metal thin plates are arranged on two sides of the bottom plate, the core part is a bionic sandwich layer, and high-density reinforcement is carried out on the area around the connecting hole. The bottom plate 3 is made of aluminum alloy such as 6061 and the like, or titanium alloy material such as TA15, TC4 and the like which is conventionally used at present, or different metal material. The periphery is provided with 4 connecting through holes for mechanical connection with the aircraft. The size of the bottom plate 3 is the largest, so that a light high-rigidity bionic sandwich structure is adopted, and the thickness range of the bottom plate 3 is 1 mm-30 mm. Wherein the thickness of the bionic sandwich layer is 1mm to 30mm, and the thickness of the thin plates on the two sides of the sandwich layer is 0.1mm to 3 mm. The wall thickness is selected according to the antenna working environment and the allowable deformation constraint of the antenna, and the wall thickness is selected to ensure that the ultimate strength of the material is not exceeded and the design weight is the lightest.
In some embodiments of the present invention, the cavity structure formed by expanding the sidewall plate 2 is divided into small channels by the main channel, and further divided into capillary channels, and then the small channels are converged into the main channel; the length of the main channel and the small channel is as short as possible, and the length of the capillary channel is as long as possible; the number of the channels is designed comprehensively according to the thermal environment condition and the liquid flow rate.
In some embodiments of the present invention, the side wall plate 2 is expanded to form a cavity structure, which forms flow channels parallel to each other, and converges at front and rear ends to form a cavity, and then communicates with the outside. The parallel flow channels include, but are not limited to: the antenna is characterized in that a single-channel spiral structure, a multi-channel parallel structure, a multi-channel approximate parallel structure and the like are reasonably selected and designed according to the size of an antenna opening face, the working time and the size of injected heat flow.
The selection of the type of the cooling flow channels of the sidewall plates 2 and the design of the geometrical parameters are designed according to the thermal control requirements of the aircraft.
In some embodiments of the present invention, a bionic circulation system is integrated in the bottom plate 3 (as shown in fig. 5 (b)), the side wall plate 2 is connected to the outer wall plate 1 and the bottom plate 3 in a flat state, and then the side wall plate 2 is integrally formed by inflation, the flow channel in the bottom plate 3 is communicated with the side wall plate 2, and the pipe joint 4 is directly connected to the bottom plate 3 and welded and communicated, so that the side wall plate 2 and the bottom plate 3 can simultaneously perform heat control.
In some embodiments of the present invention, the pipe joint 4 has a structure as shown in fig. 7, and the inner flow passage of the pipe joint adopts a bionic drag reduction design. The shape of the interface of the flow passage is gradually increased from outside to inside and is changed according to the shape of an involute of a parabola or a circle. And performing bionic drag reduction surface treatment on the internal flow channel to form the lotus leaf-like surface microstructure characteristic. According to different selected metals, the surface microstructure is prepared by methods of electrochemical deposition, anodic oxidation, chemical corrosion and the like. Through the design, the resistance of the liquid flowing from the pipe joint is greatly reduced, and the cooling efficiency of the antenna is improved.
The invention is further explained by combining a specific example of the shell structure of the bionic constant-temperature antenna of an aircraft.
The bionic constant-temperature antenna shell structure of a certain aircraft is a TA15 titanium alloy antenna shell structure. The outer wall plate 1 is used to maintain the aerodynamic profile of the aircraft, and the side wall plate 2 is used to protect the antenna and cool the surrounding structures, ensuring that the temperature of the antenna and the temperature of the surrounding cabin are not too high. The bottom plate 3 is a light high-rigidity bionic interlayer structure and plays a role in bearing and connecting. The wave-transparent layer 5 is used to resist the impact of hot air flow and the effect of wave-transparency.
The outer wall plate 1 is made of TA15 titanium alloy and has a thickness of 1 mm. The dimensional requirement under the pneumatic pressure is met.
The wave-transparent layer 5 is made of SiO2/SiO2 plates, and the structural surface is the aerodynamic external surface of the aircraft. The thickness is selected to be 1mm according to the surface temperature environment of the antenna and the requirement of wave transmission.
As is clear from fig. 3 and 4, the cooling passages are uniformly arranged inside the side wall plate 2. The forming mode is that three-layer plates are subjected to bulging treatment, and a reinforcing structure similar to an omega rib is formed. The cross section shows that the metal connection area is small, the heat conduction is slow, and in addition, the liquid cooling can effectively reduce the conduction of external heat to the internal part.
In the embodiment of the present invention, the sidewall plate 2 may adopt 2 molding methods: 1) the two skins and the ribbed plate are respectively subjected to sheet metal forming and then are connected together in a hot pressing mode in the die; 2) in a flat plate state before the metal plate forming of the side wall plate 2, the flat plate is tightly attached to the outer wall plate 1 and placed in a grinding tool, and then the channels with the set numbers of the outer wall plate 1 and the side wall plate 2 are inflated and pressurized, so that the side wall plate 2 is expanded to be a required cavity structure. The cover structure prepared by the two methods can realize the maximum utilization of materials, reduce the structure weight to the maximum extent and realize a cavity structure. And (3) punching the bottom of the cavity structure of the side wall plate 2 to connect a pipe joint.
The bottom plate 3 is of a flat plate structure and made of TA15 titanium alloy material. The wall thickness is selected to not only ensure that the ultimate strength of the material is not exceeded, but also to meet the minimum design weight, depending on the loading characteristics over the antenna's duty cycle and the maximum allowable deformation constraints of the antenna. Therefore, the thickness of the bionic sandwich layer structure is 4mm, and the thickness of the thin plates on the two sides is 0.5 mm.
Are joined together with the side wall plates 2 by welding. The plate is integrally formed and is nested outside the side wall plate 2. The periphery is provided with 4 connecting through holes for mechanical connection with the aircraft.
Two circular holes with the diameter of 1 mm-10 mm are arranged on the side wall plate 2, and the side wall plate 2 and the pipe joint 4 are connected together by welding.
The pipe joint 4 is of a metal structure, and adopts TA15 which is the same as the outer wall plate 1. Is machined and formed for the bar material and is welded with the side wall plate 2. The contact surface is rectangular. The other end is a round structure, the outer side is provided with threads, and the front section is conical. The shape of the interface of the inner flow passage of the pipe joint is gradually increased from outside to inside and is changed according to the shape of a parabola. And performing bionic drag reduction surface treatment on the internal flow channel to form the lotus leaf-like surface microstructure characteristic. And preparing a surface microstructure by adopting a chemical corrosion method.
The antenna has universality, and the outer wall plate 1 and the wave-transmitting layer 5 of the antenna are determined by the design of the appearance structure of the aircraft.
The antenna of the embodiment needs to satisfy the requirements of larger injection heat flow, short working time and smaller overall volume of the antenna, so that the cooling channel of the embodiment is designed and used in a pipeline structure with a large parallel aperture. The cooling medium can be selected from fuel oil, water and the like according to design requirements. The cooling medium needs to ensure purity, and is convenient to flow smoothly inside the antenna.
The invention has not been described in detail and is in part known to those of skill in the art.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (9)
1. A bionic constant-temperature antenna shell structure is characterized in that the antenna shell structure comprises a epidermis layer, a dermis layer and a framework layer,
the surface layer comprises an outer wall plate (1) and a wave-transmitting layer (5), the outer wall plate (1) is a thin-wall metal structure maintaining a pneumatic appearance, and the wave-transmitting layer (5) is a high-temperature-resistant wave-transmitting nonmetal thin-wall structure;
the dermis layer comprises a side wall plate (2), the side wall plate (2) is of a high-rigidity cavity structure, is integrally formed by hot blowing, is internally formed into a cavity structure imitating a biological circulation system, and is used for circulating cooling liquid;
the framework layers play a role in bearing and connecting and are composed of base plates (3), the base plates (3) are of light high-rigidity bionic sandwich structures, and the core parts are of bionic sandwich layers and are of bionic skeleton lattice structures, deep sea sponge-like porous structures or honeycomb-like honeycomb structures.
2. The bionic constant temperature antenna shell structure as claimed in claim 1, characterized in that the outer wall plate (1) and the side wall plate (2) are formed separately and connected together by heating and diffusion, or connected with the outer wall plate (1) when the side wall plate (2) is in a flat plate state and then formed by inflation; the bottom plate (3) and the side wall plate (2) are nested together in a close fit manner or are welded together.
3. The bionic constant-temperature antenna shell structure as claimed in claim 1, wherein the wave-transparent layer (5) is composed of a high-temperature-resistant and oxidation-resistant ceramic heat-proof structure or a resin thermal structure; the outer wall plate (1) is of an aluminum alloy or titanium alloy structure; the side wall plates (2) and the bottom plate (3) are of metal structures, and are made of the same aluminum alloy and titanium alloy materials as the outer wall plates (1) or different metal materials.
4. The bionic constant-temperature antenna shell structure as claimed in claim 3, wherein the thickness of the outer wall plate (1) and the side wall plate (2) ranges from 1mm to 20 mm; the thickness range of the bottom plate (3) is 1mm to 30mm, wherein the thickness of the bionic sandwich layer is 1mm to 30mm, and the thickness of thin plates on two sides of the sandwich layer is 0.1mm to 3 mm.
5. The bionic constant-temperature antenna shell structure as claimed in claim 1, wherein the bottom plate (3) is integrated with a bionic circulating system, the side wall plate (2) is connected with the outer wall plate (1) and the bottom plate (3) when the side wall plate (2) is in a flat plate shape, and then the side wall plate (2) and the circulating channel of the bottom plate (3) are communicated together through integral molding by air inflation.
6. The bionic constant-temperature antenna shell structure as claimed in claim 1, wherein the side wall plate (2) is expanded to form a cavity structure, and the cavity structure is divided into small channels from a main channel and further divided into capillary channels, and then the small channels are converged to further converge to a main channel; the length of the main channel and the small channel is as short as possible, and the length of the capillary channel is as long as possible; the number of the channels is designed comprehensively according to the thermal environment condition and the liquid flow rate.
7. The bionic constant-temperature antenna shell structure as claimed in claim 1, wherein the side wall plate (2) is formed into a cavity structure by expansion, so as to form parallel flow channels, and the parallel flow channels converge into a cavity at the front end and the rear end and then communicate with the outside, and the parallel flow channels include but are not limited to: single channel helical structure, multichannel parallel structure, multichannel approximate parallel structure.
8. The bionic constant-temperature antenna shell structure as claimed in claim 1, further comprising a pipe joint (4) for inflow and outflow of cooling liquid, wherein an inner flow passage of the pipe joint (4) adopts a bionic drag reduction design, and the shape of an interface of the flow passage is gradually enlarged from outside to inside and is changed according to the shape of an involute of a parabola or a circle; and performing bionic drag reduction surface treatment on the internal flow channel to form the lotus leaf-like surface microstructure characteristic.
9. The bionic constant-temperature antenna shell structure as claimed in claim 8, wherein the pipe joint (4) is prepared with a surface microstructure by electrochemical deposition, anodic oxidation and chemical corrosion methods according to different selected metals.
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