CN114421124B - Airborne antenna installation structure and high-speed aircraft - Google Patents
Airborne antenna installation structure and high-speed aircraft Download PDFInfo
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- CN114421124B CN114421124B CN202111493435.0A CN202111493435A CN114421124B CN 114421124 B CN114421124 B CN 114421124B CN 202111493435 A CN202111493435 A CN 202111493435A CN 114421124 B CN114421124 B CN 114421124B
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/12—Supports; Mounting means
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/36—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like adapted to receive antennas or radomes
-
- 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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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
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- Astronomy & Astrophysics (AREA)
- General Physics & Mathematics (AREA)
- Mechanical Engineering (AREA)
- Details Of Aerials (AREA)
Abstract
本发明提供了一种机载天线安装结构及高速飞行器，该天线安装结构包括天线本体、飞行器壁板、透波盖板和防热层，所述天线本体设置在所述飞行器壁板内，所述透波盖板与所述飞行器壁板相连接，所述透波盖板位于所述天线本体上，所述透波盖板和所述天线本体之间形成空气层；所述防热层设置在所述透波盖板上。本发明方案在满足透波性能的同时，实现了飞行器的防隔热需求，且方便天线的拆装。由于本发明的结构形状没有限制，因此适应性强，适用范围广，能够适合异型外形面的飞行器。
The present invention provides an airborne antenna installation structure and a high-speed aircraft, the antenna installation structure comprising an antenna body, an aircraft wall panel, a wave-transparent cover plate and a heat-proof layer, the antenna body is arranged in the aircraft wall panel, the wave-transparent cover plate is connected to the aircraft wall panel, the wave-transparent cover plate is located on the antenna body, an air layer is formed between the wave-transparent cover plate and the antenna body; the heat-proof layer is arranged on the wave-transparent cover plate. The scheme of the present invention not only meets the wave-transparent performance, but also realizes the heat-insulating requirements of the aircraft, and facilitates the disassembly and assembly of the antenna. Since the structural shape of the present invention is not restricted, it has strong adaptability and a wide range of applications, and can be suitable for aircraft with special-shaped surfaces.
Description
Technical Field
The invention relates to the technical field of aviation antenna structures, in particular to an airborne antenna mounting structure and a high-speed aircraft.
Background
Aircraft generally mount antennas on exterior surfaces to facilitate communications. As aircraft speeds increase, the outer surface aerodynamic heating becomes more severe, requiring the addition of a heat shield to protect the aircraft. However, in order to ensure wave-transparent performance, the antenna on the outer surface of the aircraft cannot be directly coated with a heat-resistant layer. Therefore, the installation of the antenna structure and the heat-proof layer needs to be specially designed, and the wave-transmitting performance of the antenna is not affected while the heat-proof performance is ensured. A novel installation structure scheme of the airborne antenna needs to be designed to meet urgent requirements of the field of the airborne antenna.
Disclosure of Invention
The present invention aims to solve at least one of the technical problems existing in the prior art or related art.
Therefore, the invention provides an airborne antenna mounting structure and a high-speed aircraft.
The technical scheme of the invention is as follows:
according to an aspect, there is provided an airborne antenna mounting structure comprising
An antenna body;
An aircraft wall panel, the antenna body being disposed within the aircraft wall panel;
The wave-transmitting cover plate is connected with the wall plate of the aircraft, the wave-transmitting cover plate is positioned on the antenna body, and an air layer is formed between the wave-transmitting cover plate and the antenna body;
the heat-proof layer is arranged on the wave-transparent cover plate.
Further, the wave-transmitting cover plate is divided into a first area and a second area, the thickness of the first area is smaller than that of the second area, the second area is connected with the aircraft wall plate, the wave-transmitting surface of the antenna body is completely covered by the first area, and an air layer is formed between the first area and the wave-transmitting surface of the antenna body.
Further, the thickness of the first area is 0.2 mm-5 mm, and the thickness of the second area is 2 mm-10 mm.
Further, the wave-transparent cover plate adopts a square-shaped structure, the square-shaped structure is provided with a square groove, the square groove forms the first area, and the periphery parts of the square-shaped structure except the square groove form the second area.
Further, the thickness of the air layer is adjusted through the installation depth of the antenna body and/or the wave-transparent cover plate, and the thickness of the air layer is 0.1-5 mm.
Further, the thickness of the heat-proof layer is 0.5 mm-40 mm.
Further, the wave-transparent cover plate is made of quartz, polyimide resin or high-temperature-resistant glass wave-transparent material, and/or the heat-resistant layer is made of a non-ablative or micro-ablative structure, and the non-ablative or micro-ablative structure is made of ceramic tiles, quartz products, silicon oxide, silicon carbide or aluminum oxide materials.
Further, the wall plate of the aircraft adopts a plate structure or a skin reinforcement lattice structure or a bionic interlayer skin structure with equal thickness.
Further, the aircraft wall board adopts bionical intermediate layer skin structure, bionical intermediate layer skin structure is honeycomb, dot matrix, buckled plate or inhomogeneous porous structure, the aircraft wall board includes cooling pipeline, cooling pipeline lays inside the intermediate layer skin of bionical intermediate layer skin structure, cooling pipeline is used for the cooling aircraft wallboard.
According to one aspect, there is provided a high speed aircraft comprising the antenna mounting structure described above.
Above-mentioned technical scheme is through the cooperation of wave-transparent cover plate and heat protection layer to and form the air bed between wave-transparent cover plate and antenna body, make at the outside non-contact heat protection structure of having installed of antenna, when satisfying the wave-transparent performance, realized the thermal-insulated demand of preventing of aircraft, and make things convenient for the dismouting of antenna. In addition, the invention has strong adaptability and wide application range because the structural shape is not limited, and can be suitable for the aircraft with the special-shaped appearance surface.
Drawings
The accompanying drawings, which are included to provide a further understanding of 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 evident that the drawings in the following description are only some embodiments of the present invention and that other drawings may be obtained from these drawings without inventive effort for a person of ordinary skill in the art.
Fig. 1 is a schematic diagram of an explosion structure of an airborne antenna mounting structure in an embodiment of the invention;
fig. 2 is a schematic view of a wave-transparent cover plate of an airborne antenna mounting structure according to an embodiment of the invention;
fig. 3 is a schematic longitudinal sectional view of an airborne antenna mounting structure according to an embodiment of the invention
Fig. 4 is a schematic view of a longitudinal section of an airborne antenna mounting structure (along the mounting Kong Pouqie) according to an embodiment of the present invention;
the above figures include the following reference numerals:
1. The panel comprises an aircraft panel, an air layer, a wave-transparent cover plate, a heat-proof layer and an antenna body.
Detailed Description
It should be noted that, without conflict, the embodiments of the present application and features of the embodiments may be combined with each other. The following description of the embodiments of the present application will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present application, but not all embodiments. The following description of at least one exemplary embodiment is merely exemplary in nature and is in no way intended to limit the application, its application, or uses. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of exemplary embodiments according to the present application. As used herein, the singular is also intended to include the plural unless the context clearly indicates otherwise, and furthermore, it is to be understood that the terms "comprises" and/or "comprising" when used in this specification are taken to specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof.
The relative arrangement of the components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless it is specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective parts shown in the drawings are not drawn in actual scale for convenience of description. Techniques, methods, and apparatus known to one of ordinary skill in the relevant art may not be discussed in detail, but should be considered part of the specification where appropriate. In all examples shown and discussed herein, any specific values should be construed as merely illustrative, and not a limitation. Thus, other examples of the exemplary embodiments may have different values. It should be noted that like reference numerals and letters refer to like items in the following figures, and thus once an item is defined in one figure, no further discussion thereof is necessary in subsequent figures.
As shown in fig. 1 to 4, in one embodiment of the present invention, there is provided an airborne antenna mounting structure, which comprises an antenna body 5, an aircraft panel 1, a wave transparent cover plate 3, and a heat-shielding layer 4, wherein the antenna body 5 is disposed in the aircraft panel 1, the wave transparent cover plate 3 is connected with the aircraft panel 1, the wave transparent cover plate 3 is disposed on the antenna body 5, an air layer 2 is formed between the wave transparent cover plate 3 and the antenna body 5, the heat-shielding layer 4 is disposed on the wave transparent cover plate 3, and the heat-shielding layer 4 is used for heat insulation of an aircraft surface.
According to the embodiment of the invention, the wave-transparent cover plate 3 is matched with the heat-proof layer 4, and the air layer 2 is formed between the wave-transparent cover plate 3 and the antenna body 5, so that the heat-proof structure is arranged outside the antenna in a non-contact manner, the wave-transparent performance is met, the heat-proof requirement of the aircraft is met, and the antenna is convenient to assemble and disassemble. In addition, the invention has strong adaptability and wide application range because the structural shape is not limited, and can be suitable for the aircraft with the special-shaped appearance surface.
In the above embodiment, in order to ensure better wave-transmitting performance of the antenna body, the wave-transmitting cover plate 3 is divided into a first area and a second area, the thickness of the first area is smaller than that of the second area, the second area is connected with the aircraft panel 1, the wave-transmitting surface of the antenna body 5 is completely covered by the first area, and an air layer 2 is formed between the first area and the wave-transmitting surface of the antenna body 5.
In the above embodiment, in order to further ensure better wave-transmitting performance of the antenna body, the thickness of the first region is 0.2 mm-5 mm, and the thickness of the second region is 2 mm-10 mm.
In the above embodiment, in order to ensure wave transmission of the antenna body, the wave-transmitting cover plate 3 is made of quartz, polyimide resin or high-temperature-resistant glass wave-transmitting material. Furthermore, it is possible to provide a device for the treatment of a disease. The structural surface of the wave-transparent cover plate 3 is an aerodynamic surface of an aircraft, an antenna paraboloid or other needed surfaces, and is designed according to actual needs.
Preferably, the wave-transparent cover plate 3 adopts a square-shaped structure, the square-shaped structure is provided with square grooves, the square grooves form the first area, and the peripheral parts of the square-shaped structure except the square grooves form the second area.
In the above embodiment, in order to further ensure better wave-transmitting performance of the antenna body, the thickness of the air layer 2 is adjusted by the installation depth of the antenna body 5 and/or the wave-transmitting cover plate 3, and the thickness of the air layer 2 is 0.1-5 mm.
For example, the antenna body 5 is provided with a mounting flange, and 4 connecting through holes are provided for mechanical connection with the aircraft panel 1, the inner surface of the aircraft panel 1 is provided with a flange mounting surface on the antenna body 5, and the thickness of the air layer 2 is controlled by adjusting the depth of the inner and outer mounting surfaces. After all the mounting structures are mounted in place, the wave-transparent cover plate 3 is parallel to the outer surface of the aircraft wallboard 1, the counter sunk holes of the wave-transparent cover plate 3 ensure that the nail heads do not protrude out of the surface, and the whole laying of the heat-proof layer 4 is facilitated. By adjusting the installation depth of the antenna body 5, the thickness of the air layer 2 between the antenna body 5 and the wave-transparent cover plate 3 is controlled.
In the above embodiment, in order to better ensure the heat insulation effect, the thickness of the heat-proof layer 4 is 0.5mm to 40mm.
In the above embodiment, in order to ensure the heat insulation effect of the heat-proof layer, the heat-proof layer 4 is a non-ablative or micro-ablative structure, and the non-ablative or micro-ablative structure is made of ceramic tiles, quartz products, silicon oxide, silicon carbide or aluminum oxide materials.
According to an embodiment of the present invention, the aircraft panel 1 adopts a plate structure or a skin reinforcement lattice structure or a bionic interlayer skin structure with equal thickness.
Preferably, the aircraft panel 1 adopts a bionic sandwich skin structure, the bionic sandwich skin structure is a honeycomb, dot matrix, corrugated plate or non-uniform porous structure, the aircraft panel 1 comprises a cooling pipeline, the cooling pipeline is laid inside the sandwich skin of the bionic sandwich skin structure, and the cooling pipeline is used for cooling the aircraft panel 1.
According to an embodiment, there is also provided a high-speed aircraft comprising the antenna mounting structure described above. The high-speed aircraft has the advantages that the heat protection function is added, and meanwhile, the wave transmission performance of the antenna is not affected.
For a further understanding of the mounting structure of the on-board antenna according to the embodiments of the present invention, the following description is given by way of example only:
as shown in fig. 1 to 4, there is provided an on-board antenna mounting structure for mounting an antenna body 5 to an aircraft lower wall panel, the on-board antenna structure including the antenna body 5, an air layer 2, a wave-transparent cover plate 3, a heat-shielding layer 4 and an aircraft wall panel 1,
The antenna body 5 and the wave-transparent cover plate 3 are both arranged on the aircraft wallboard 1, the heat-resistant layer 4 is laid on the outer surface of the wave-transparent cover plate 3, and the air layer 2 is a gap between the wave-transparent cover plate 3 and the antenna body 5, wherein:
The antenna body 5 is provided with a mounting flange plate and 4 connecting through holes for mechanical connection with the aircraft wall plate 1;
the wave-transparent cover plate 3 is made of quartz/Dan Yingtou wave materials, and the appearance surface of the wave-transparent cover plate 33 is an aerodynamic surface of the aircraft;
Referring to fig. 2, the wave-transparent cover plate 3 is a square structure with a thin middle part and thick periphery, a thick peripheral frame is used for mechanical connection with the aircraft wall plate 1, a thin middle part area is used for wave transmission, the area of the thin area is larger than the wave-transparent size of the antenna, the thickness of the thick peripheral frame is 5mm, the thickness of the thin middle part area is 3mm, and 4 countersunk holes are formed in the thick peripheral frame, so that countersunk screws are convenient to install;
The heat-proof layer 4 adopts a non-ablative structure, and adopts quartz products with the thickness of 10mm;
The total thickness of the aircraft wallboard 1 is 32mm, the aircraft wallboard 1 is a bionic interlayer skin structure, a middle core layer is a honeycomb core, cooling channels are uniformly distributed and used for cooling the aircraft wallboard 1, a solid structure is arranged around an antenna mounting groove, the preparation of screw mounting holes is carried out, a mounting groove of a wave-transmitting cover plate 3 is reserved on the outer surface of the wallboard, a flange mounting surface on an antenna body 5 is reserved on the inner surface of the wallboard, and the thickness of an air layer 2 is controlled by adjusting the depth of the inner mounting surface and the outer mounting surface;
referring to fig. 3 and 4, after all the mounting structures are mounted in place, the wave-transparent cover plate 3 is parallel to the outer surface of the aircraft wallboard 1, the countersunk holes of the wave-transparent cover plate 3 ensure that the nail heads do not protrude from the surface, the whole laying of the heat-proof layer 4 is facilitated, and the thickness of the air layer 2 between the antenna body 5 and the wave-transparent cover plate 3 is controlled to be 2mm by adjusting the mounting depth of the antenna body 5.
The antenna installation structure scheme provided by the embodiment of the invention has universality, and the wave-transparent cover plate 3 is determined by the design of the appearance structure of the aircraft. The wall thickness of the aircraft wall panel 1 according to the embodiment of the invention is determined by the aircraft load. The wall thickness is selected to ensure that the ultimate strength of the material is not exceeded and to meet the minimum design weight. The thickness of the heat protection layer 4 according to the embodiment of the invention is determined by the thermal environment of the surface of the aircraft and the cooling effect in the cabin. The thickness is selected to meet both the ambient temperature requirements in the cabin and the design weight minimum.
Spatially relative terms, such as "above," "upper" and "upper surface," "above" and the like, may be used herein for ease of description to describe one device or feature's spatial relationship to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the process is carried out, the exemplary term "above" may be included. Upper and lower. Two orientations below. The device may also be positioned in other different ways (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.
In addition, the terms "first", "second", etc. are used to define the components, and are only for convenience of distinguishing the corresponding components, and the terms have no special meaning unless otherwise stated, and therefore should not be construed as limiting the scope of the present invention.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (6)
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
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| CN202111493435.0A CN114421124B (en) | 2021-12-08 | 2021-12-08 | Airborne antenna installation structure and high-speed aircraft |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111493435.0A CN114421124B (en) | 2021-12-08 | 2021-12-08 | Airborne antenna installation structure and high-speed aircraft |
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| CN114421124A CN114421124A (en) | 2022-04-29 |
| CN114421124B true CN114421124B (en) | 2025-03-14 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN103545594A (en) * | 2013-09-30 | 2014-01-29 | 中国人民解放军国防科学技术大学 | A hypersonic vehicle telemetry antenna window installation device |
| CN108454132A (en) * | 2018-02-02 | 2018-08-28 | 航天特种材料及工艺技术研究所 | A kind of wave transparent heat insulation structural and preparation method |
| CN113381179A (en) * | 2021-04-29 | 2021-09-10 | 北京机电工程研究所 | Bionic constant-temperature antenna shell structure |
Family Cites Families (4)
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|---|---|---|---|---|
| CN202678517U (en) * | 2012-06-28 | 2013-01-16 | 上海海积信息科技有限公司 | Speeding and high-temperature resistant combined multi-frequency antenna |
| US10727574B2 (en) * | 2017-06-05 | 2020-07-28 | The Nordam Group Llc | Accessible radome assembly |
| CN207947378U (en) * | 2018-04-13 | 2018-10-09 | 哈尔滨哈玻拓普复合材料有限公司 | A kind of D shipborne radar cover |
| CN213401527U (en) * | 2020-11-30 | 2021-06-08 | 湖北三江航天险峰电子信息有限公司 | Hypersonic wave-rider aircraft satellite navigation antenna |
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2021
- 2021-12-08 CN CN202111493435.0A patent/CN114421124B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103545594A (en) * | 2013-09-30 | 2014-01-29 | 中国人民解放军国防科学技术大学 | A hypersonic vehicle telemetry antenna window installation device |
| CN108454132A (en) * | 2018-02-02 | 2018-08-28 | 航天特种材料及工艺技术研究所 | A kind of wave transparent heat insulation structural and preparation method |
| CN113381179A (en) * | 2021-04-29 | 2021-09-10 | 北京机电工程研究所 | Bionic constant-temperature antenna shell structure |
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| CN114421124A (en) | 2022-04-29 |
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