Non-conformal split type impact-resistant and high-temperature-resistant data link antenna window

Abstract

The invention provides a non-conformal split type impact-resistant and high-temperature-resistant data link antenna window, and belongs to the field of aircraft communication protection devices. The non-conformal split type impact-resistant and high-temperature-resistant data link antenna window comprises a bearing antenna window and a wave-transparent antenna window, the bearing antenna window is detachably arranged on the bulkhead of an aircraft, and the bearing antenna window can bear pneumatic heating loads and impact loads so as to protect a data link antenna. And the wave-transparent antenna window is used for protecting the data link antenna and enabling the data link antenna to transmit signals. According to the data chain split type antenna window structure not conformal with the outer wall of the aircraft, the wave-transparent region and the bearing region are separately designed, so that the antenna window can tolerate a temperature load brought by high-speed flight and has the capability of resisting a strong impact load.

Description

Technical Field

[0001] This application relates to the field of aircraft communication protection devices, and in particular to a non-conformal split-type shock-resistant and high-temperature resistant data link antenna window. Background Technology

[0002] Data links are crucial components for information exchange between aircraft and ground control centers, launch platforms, or other aircraft during flight. Traditional data link antennas are generally conformally designed to fit the aircraft. Some data links, especially rearward data links responsible for interconnecting with ground radar, must be placed at the tail of the aircraft or the tail of the interstage compartment due to antenna beam pointing requirements. However, some aircraft, due to diameter limitations and obstructions from servos and engines, cannot provide the space required for rearward data links, forcing the antenna beam pointing rearward so that the main body protrudes from the aircraft bulkhead. Furthermore, some aircraft experience significant impact loads during interstage separation and ignition, making it impossible for traditional integral antenna windows to simultaneously meet the requirements for high-temperature resistance and high-impact resistance. Summary of the Invention

[0003] This application provides a non-conformal, split-type shock-resistant and high-temperature resistant data link antenna window to solve the problem that traditional integral antenna windows cannot simultaneously meet the requirements of high temperature resistance and high impact resistance.

[0004] In a first aspect, embodiments of this application provide a non-conformal, split-type, shock-resistant, high-temperature-resistant data link antenna window, comprising:

[0005] A carrier antenna window is used on the aircraft bulkhead. The interior of the carrier antenna window forms an installation space for installing a data link antenna. The carrier antenna window can withstand aerodynamic heating loads and impact loads to protect the data link antenna. The carrier antenna window has a transmission opening facing the leeward side of the aircraft.

[0006] A wave-transparent antenna window is detachably mounted on the carrier antenna window to block the transmission opening. The wave-transparent antenna window is used for the data link antenna to transmit signals.

[0007] In one exemplary embodiment of this application, the carrying antenna window has an inclined surface facing the windward side of the aircraft, the inclined surface being used to guide airflow toward the rear of the outer side of the aircraft bulkhead.

[0008] In one exemplary embodiment of this application, the carrier antenna window further has a side opening facing the aircraft cabin wall, the side opening communicating with the transmission opening, and a feed plate for sealing the side opening is detachably connected to the carrier antenna window.

[0009] In one exemplary embodiment of this application, a mounting box is also included. The mounting box is located within the mounting space and is detachably mounted on the antenna feed base plate. An antenna base plate is provided on the side of the mounting box facing the transmission opening, and the data link antenna is mounted on the antenna base plate.

[0010] In one exemplary embodiment of this application, the mounting box includes a box body and a bottom cover. The box body has an opening facing the antenna base plate, and the bottom cover covers the opening of the box body and is connected to the antenna base plate.

[0011] In one exemplary embodiment of this application, a fitting gap is provided between the wave-transparent antenna window and the carrier antenna window, and between the wave-transparent antenna window and the antenna feed base plate, and the fitting gap is filled with high-temperature resistant flexible silicone rubber.

[0012] In one exemplary embodiment of this application, the width of the mating gap is 0.1-0.2 mm.

[0013] In one exemplary embodiment of this application, the antenna window has flanges extending outward on both sides, and a plurality of first threaded holes are spaced apart on the flanges. A plurality of second threaded holes corresponding one-to-one with the first threaded holes are spaced apart on the antenna feed base plate. The flanges and the antenna feed base plate are connected by fastening screws that pass through the first threaded holes and the second threaded holes.

[0014] In one exemplary embodiment of this application, the antenna feed base plate is provided with two positioning platforms protruding toward one side of the carrying antenna window. The two positioning platforms are symmetrically arranged on the antenna feed base plate for positioning and cooperating with the inner walls on both sides of the installation space, and an installation groove for installing the wave-transparent antenna window is formed between the two positioning platforms.

[0015] In one exemplary embodiment of this application, the material of the carrier antenna window is a quartz fiber reinforced phenolic resin-based composite material, and the material of the wave-transparent antenna window is a quartz fiber reinforced polyimide resin-based material.

[0016] The beneficial effects of the non-conformal split-type shock-resistant and high-temperature resistant data link antenna window provided in this application embodiment are as follows:

[0017] During installation, the data link antenna is first installed into the mounting space inside the carrier antenna window. Then, the wave-transparent antenna window is installed at the transmission opening. After the wave-transparent antenna window, data link antenna, and carrier antenna window are installed, the entire assembly is fixed to the designated location on the aircraft bulkhead using screws. During flight, the carrier antenna window directly bears the high-temperature load generated by aerodynamic heating, as well as the impact loads from interstage separation and ignition. The wave-transparent antenna window protects the data link antenna while ensuring smooth electromagnetic wave transmission for signal transmission. The separate design separates the wave-transparent and carrier functions, solving the technical challenge of traditional integral antenna windows that cannot simultaneously meet the requirements of high-temperature resistance and high-impact resistance. This design adapts to the installation space limitations at the tail of the aircraft or the tail of the interstage compartment. The selection of two specialized materials matches their respective functional requirements, ensuring stable operation of the data link antenna under complex force and heat environments. Attached Figure Description

[0018] To more clearly illustrate the technical solutions in the embodiments of this application, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0019] Figure 1 This is a schematic diagram of the structure of the non-conformal split-type shock-resistant and high-temperature resistant data link antenna window provided in the embodiments of this application;

[0020] Figure 2 This is a schematic diagram of the explosion of the non-conformal split-type impact-resistant and high-temperature resistant data link antenna window provided in the embodiments of this application;

[0021] Figure 3 This is a schematic diagram of the structure of the wave-transparent antenna window provided in the embodiments of this application;

[0022] Figure 4 yes Figure 3 Sectional view at point AA.

[0023] Among them: 1. Wave-transparent antenna window, 2. Data link antenna, 3. Antenna base plate, 4. Bearing antenna window, 40. Inclined surface, 41. First threaded hole, 42. Transmission opening, 43. Side opening, 44. Flanged edge, 5. Mounting box, 6. Bottom cover, 7. Antenna feed base plate, 71. Second threaded hole, 72. Positioning platform, 721. Mounting slot. Detailed Implementation

[0024] To enable those skilled in the art to better understand this solution, the technical solutions in the embodiments of this solution will be clearly described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of this solution, not all of them. Based on the embodiments of this solution, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of this solution.

[0025] The term "comprising" and any other variations thereof in the specification, claims, and accompanying drawings of this invention mean "including but not limited to," and are intended to cover a non-exclusive inclusion, not limited to the examples listed herein. Furthermore, the terms "first" and "second," etc., are used to distinguish different objects, not to describe a specific order.

[0026] The implementation of this application will be described in detail below with reference to the specific accompanying drawings:

[0027] Figure 1 This is a schematic diagram of a non-conformal, split-type, shock-resistant, high-temperature-resistant data link antenna window provided in an embodiment of this application. (Refer to...) Figure 1 The system includes a carrier antenna window 4 and a transmissive antenna window 1. The carrier antenna window 4 can be detachably mounted on the outer wall of the aircraft cabin. Inside the carrier antenna window 4 is a mounting space for installing the data link antenna 2. The carrier antenna window 4 can withstand aerodynamic heating loads and impact loads during aircraft flight to protect the data link antenna 2 located within the mounting space. The carrier antenna window 4 also has a transmission opening 42 facing the leeward side of the aircraft. The transmissive antenna window 1 is mounted at the transmission opening 42 and serves to seal the transmission opening 42. The transmissive antenna window 1 protects the data link antenna 2 while allowing the data link antenna 2 to transmit signals.

[0028] First, it should be noted that the aircraft referred to in this embodiment includes, but is not limited to, rockets, missiles, airplanes, and drones. Specifically, the carrier antenna window 4 is made of quartz fiber reinforced phenolic resin matrix composite material, and the wall thickness of the carrier antenna window 4 is designed to be uniform. The carrier antenna window 4 is detachably installed on the outer wall of the aircraft cabin using fasteners such as screws and bolts. The interior of the carrier antenna window 4 forms an installation space for installing the data link antenna 2. The carrier antenna window 4 has a transmission opening 42 facing the leeward side of the aircraft. The wave-transparent antenna window 1 is made of quartz fiber reinforced polyimide resin matrix material and is detachably installed at the transmission opening 42, sealing the transmission opening 42. The carrier antenna window 4 and the wave-transparent antenna window 1 form a non-conformal split structure, respectively undertaking the functions of load-bearing protection and wave-transparent protection. Among them, the carrier antenna window 4 has almost no electromagnetic wave transmission, and there are no requirements for the dielectric constant, loss tangent, dielectric temperature drift, etc. of the material. Since it is located on the windward side and directly bears the impact load transmitted by the aircraft cabin, it must have high strength, high temperature resistance, low linear ablation rate, and good heat insulation performance. The antenna window in the wave-transparent region mainly needs to meet the requirements for electromagnetic wave transmission, including dielectric constant, loss tangent, and dielectric temperature drift. The wave-transparent antenna window 1 is located on the leeward side and does not directly bear impact loads, so the mechanical and thermal environment is relatively mild, and the requirements for the bending strength and temperature resistance of the material are relatively low.

[0029] Reference Figure 2 During installation, the data link antenna 2 is first installed into the mounting space inside the carrier antenna window 4. Then, the wave-transparent antenna window 1 is installed at the transmission opening 42. After the wave-transparent antenna window 1, data link antenna 2, and carrier antenna window 4 are installed, the entire assembly is fixed to the designated position on the aircraft cabin wall using screws. During flight, the carrier antenna window 4 directly bears the high-temperature load generated by aerodynamic heating, as well as the impact load from interstage separation and ignition. The wave-transparent antenna window 1 protects the data link antenna 2 while ensuring smooth electromagnetic wave transmission for signal transmission. The split design separates the wave-transparent function from the carrier function, solving the technical challenge of traditional integral antenna windows not being able to simultaneously meet the requirements of high-temperature resistance and high-impact resistance. This design adapts to the installation space limitations at the tail of the aircraft or the tail of the interstage compartment. The selection of two special materials matches their respective functional requirements, ensuring stable operation of the data link antenna 2 under complex force and heat environments.

[0030] Secondly, the antenna window 4 has an inclined surface 40 facing the windward side of the aircraft. When the aircraft is in flight, the inclined surface 40 is used to guide the airflow to flow to the rear of the outer side of the aircraft bulkhead.

[0031] Reference Figure 2In the above scheme, the inclined surface 40 adopts a smooth design adapted to the aerodynamic shape of the aircraft. The tilt angle of the inclined surface 40 can guide the airflow to flow towards the rear of the outer side of the aircraft bulkhead. Specifically, when the aircraft is flying at high speed, the oncoming airflow first contacts the inclined surface 40 that supports the antenna window 4. Under the guidance of the inclined surface 40, the airflow flows smoothly along the inclined trajectory towards the rear of the outer side of the aircraft bulkhead, avoiding the formation of strong impact airflow or vortices in the antenna window area, and reducing the direct impact and pressure of the airflow on the antenna window. Moreover, the inclined surface 40 effectively reduces the aerodynamic drag of the aircraft, maintains the integrity of the overall aerodynamic shape of the aircraft, reduces the impact damage of the airflow on the antenna window 4, and, combined with the high-strength material properties of the antenna window 4, further improves the structural stability and service life of the antenna window during high-speed flight, ensuring that the internal data link antenna 2 is not affected by the airflow.

[0032] Reference Figure 2 Additionally, the carrier antenna window 4 has a side opening 43 facing the aircraft cabin wall, which communicates with the transmission opening 42. A feed plate 7 for sealing the side opening 43 is detachably connected to the carrier antenna window 4. After the data link antenna 2 and the transparent antenna window 1 are installed, the feed plate 7 needs to be installed to ensure a stable connection between the data link antenna 2, the transparent antenna window 1, and the carrier antenna window 4. Furthermore, a through hole is provided on the feed plate 7, through which wires can pass.

[0033] Reference Figure 2 In the above structure, the antenna feed base plate 7 is detachably connected to the carrier antenna window 4, which can completely block the side opening 43. The carrier antenna window 4 has extended flanges 44 on both sides, and threaded holes are provided on the flanges 44 and the antenna feed base plate 7 respectively, and the connection is achieved by screws.

[0034] Reference Figure 1 , Figure 2 and Figure 3 It should be noted that the flange 44 has several first threaded holes 41 spaced apart for installing fastening screws, and the antenna base plate 7 has several second threaded holes 71 spaced apart. The first threaded holes 41 and the second threaded holes 71 correspond one-to-one. The fastening screws pass through the threaded holes to achieve a detachable connection between the carrier antenna window 4 and the antenna base plate 7. The carrier antenna window 4 is also fixed to the aircraft cabin by screws. When aligning the carrier antenna window 4 with the antenna base plate 7, adjust the position so that the first threaded holes 41 on the flange 44 are completely aligned with the second threaded holes 71 on the antenna base plate 7. Then, pass the fastening screws through the corresponding threaded holes one by one and tighten them to achieve a firm connection between the two. At the same time, the carrier antenna window 4 is fixed to the aircraft cabin by screws. During disassembly, simply unscrew the screws one by one to separate the components.

[0035] When assembling the carrier antenna window 4, data link antenna 2, and antenna feed base plate 7, the data link antenna 2 and related components are first placed into the installation space of the carrier antenna window 4 and positioned through the side opening 43 and transmission opening 42. Then, the antenna feed base plate 7 is aligned with the side opening 43, and screws are passed through the corresponding threaded holes to fix the antenna feed base plate 7 to the carrier antenna window 4, thus sealing the side opening 43. The antenna feed base plate 7 also secures the data link connection and reinforces the connection between the carrier antenna window 4 and the aircraft bulkhead. When maintenance or replacement of internal components is required, the screws are unscrewed to remove the antenna feed base plate 7, allowing operation through the side opening 43. The side opening 43 provides a convenient passage for the installation, maintenance, and replacement of internal components, reducing operational difficulty and maintenance costs. The sealing effect of the antenna feed base plate 7 ensures the airtightness of the installation space, preventing external dust, gas, and other impurities from entering.

[0036] Reference Figure 2 An installation box 5 is also installed in the installation space. The installation box 5 is located in the installation space and is detachably mounted on the antenna feed base plate 7. An antenna base plate 3 is provided on the side of the installation box 5 facing the transmission opening 42, and the data link antenna 2 is mounted on the antenna base plate 3.

[0037] It should be noted that the mounting box 5 is an integrated structure consisting of an antenna mounting frame and a TR component printed circuit board box. Located within the mounting space of the antenna window 4, it is detachably mounted to the antenna feed base plate 7 using screws. The antenna base plate 3 is fixedly mounted on the side of the mounting box 5 facing the transmission opening 42. The wave-transparent antenna window 1 is mounted on the antenna base plate 3 using screws, and the data link antenna 2 is fixed to the side of the antenna base plate 3 facing the wave-transparent antenna window 1. This avoids directly mounting the wave-transparent antenna window 1 onto the antenna feed base plate 7. During installation, first, the integrated mounting box 5 is fixed to the antenna feed base plate 7 using screws. Then, the antenna base plate 3 is installed on the side of the mounting box 5 facing the transmission opening 42. Next, the data link antenna 2 is installed on the antenna base plate 3. Finally, the wave-transparent antenna window 1 is installed, completing the overall assembly. During flight, the mounting box 5 provides stable support for the data link antenna 2, buffering the transmission of impact loads.

[0038] Reference Figure 2 Secondly, the mounting box 5 consists of a box body and a bottom cover 6. The box body is an integrated structure of the antenna mounting frame and the TR component printed circuit board box. The box body has an opening on the side facing the antenna feed base plate 7. The bottom cover 6 can completely cover the bottom opening of the box body. The bottom cover 6 and the antenna feed base plate 7 are detachably connected by screws. The interior of the box body has reserved space to accommodate related components. The detachable design of the box body and the bottom cover 6 facilitates the assembly and maintenance of the internal components of the mounting box 5. The integrated box body ensures the structural integrity of the antenna mounting frame and the TR component printed circuit board box. The screw connection between the bottom cover 6 and the antenna feed base plate 7 ensures the reliability of the mounting box 5. The overall structure takes into account both assembly convenience and connection stability, improving the overall assembly efficiency of the antenna window.

[0039] Reference Figure 1 and Figure 3 At the connection points between the wave-transparent antenna window 1 and the carrier antenna window 4, and between the wave-transparent antenna window 1 and the antenna feed base plate 7, pre-drilled fitting gaps are provided. The gap width is controlled within the range of 0.1-0.2 mm. These gaps are filled with HM306 high-temperature resistant flexible silicone rubber, which fully fills the gaps and fits tightly against each connection surface. When assembling the wave-transparent antenna window 1, the carrier antenna window 4, and the antenna feed base plate 7, the fitting gap dimensions at each connection point must be strictly controlled to ensure uniformity. Then, HM306 high-temperature resistant flexible silicone rubber is evenly filled into the gaps, forming a complete sealing layer. When the aircraft experiences high and low temperature changes and impact loads during flight, the silicone rubber can adaptively adjust to minor structural deformations. The filling of HM306 high-temperature resistant flexible silicone rubber effectively ensures the airtightness of the antenna feed system, preventing external gases, dust, and other impurities from entering the installation space and affecting the operation of internal components. The high-temperature resistance of the silicone rubber is suitable for the high-temperature environment during flight, and its flexibility can buffer impacts and absorb vibrations, preventing gaps from forming at the connections due to deformation, thus ensuring the sealing reliability and structural adaptability of the antenna window.

[0040] Reference Figure 2 , Figure 3 and Figure 4 Optionally, the antenna base plate 7 is provided with two positioning platforms 72 protruding towards the transmission opening 42. Because the carrier antenna window 4 has a flange 44, and the flange 44 is a rounded transition, if the data link antenna 2 window is directly installed at the transmission opening 42, a large gap will appear at the rounded transition section. By symmetrically setting the positioning platforms 72, after the antenna base plate 7 is connected to the carrier antenna window 4, the two positioning platforms 72 can respectively abut against the inner walls on both sides of the bottom of the transmission opening 42 of the carrier antenna window 4. In this way, there will be no gap when installing the transparent antenna window 1. Moreover, the shape between the two positioning platforms 72 is the same as the bottom contour of the transparent antenna window 1, which can form a mounting groove 721 for installing the transparent antenna window 1, which facilitates the installation and positioning of the transparent antenna window 1.

[0041] In the above scheme, when installing the antenna base plate 7, the two positioning platforms 72 are accurately aligned with the inner walls on both sides of the bottom of the transmission opening 42 of the carrier antenna window 4. After fixing the antenna base plate 7, the positioning platforms 72 are tightly abutted against the inner walls to achieve precise positioning. Then, the transparent antenna window 1 is embedded into the mounting groove 721 between the two positioning platforms 72. The installation and fixing of the transparent antenna window 1 is completed by overlapping, ensuring a sealed connection between the transparent antenna window 1 and the transmission opening 42. The positioning platforms 72 play an auxiliary positioning and support role for the carrier antenna window 4, improving the structural stability of the connection between the carrier antenna window 4 and the antenna base plate 7. The mounting groove 721 provides a precise installation positioning reference for the transparent antenna window 1, ensuring that the transparent antenna window 1 can accurately seal the transmission opening 42. The overlapping connection method simplifies the assembly process and improves the firmness and sealing of the installation of the transparent antenna window 1.

[0042] In addition, in the above scheme, the material of the supporting antenna window 4 is a quartz fiber reinforced phenolic resin-based composite material, which is molded by molding phenolic resin prepreg. The supporting antenna window 4 adopts a uniform thickness design of 5 mm, ensuring the continuity of the quartz fiber cloth in the reinforcing material. The material of the wave-transparent antenna window 1 is a quartz fiber reinforced polyimide resin-based material, which has good dielectric properties and meets the requirements of electromagnetic wave transmission. When the aircraft is in flight, the supporting antenna window 4 located on the windward side directly bears the high temperature load and impact load brought by aerodynamic heating. Its material has a room temperature bending strength of up to 300 MPa, a thermal conductivity of less than 0.8 W / m·K at room temperature, and an oxyacetylene ablation rate of less than 0.1 mm / s. With the uniform thickness design and continuous quartz fiber cloth reinforcement, even if partial ablation occurs, there will be no fabric peeling, maintaining the aerodynamic shape of the aircraft. The wave-transparent antenna window 1 located on the leeward side ensures the normal transmission and reception of the data link antenna 2 signal through its excellent dielectric properties under a mild force and heat environment.

[0043] Therefore, the selection of quartz fiber reinforced phenolic resin matrix composite material meets the requirements of high temperature resistance, impact resistance, and erosion resistance for the antenna window 4. Compared with carbon fiber materials, it has a shorter production cycle and lower cost. The uniform thickness design further ensures structural stability and meets the requirements of high temperature resistance, impact resistance, and erosion resistance. The quartz fiber reinforced polyimide resin matrix material precisely matches the wave transmission function requirements. The overall design does not require additional heat protection layers and shock absorption devices, making the antenna window structure simple, cost controllable, and significantly shortening the production and assembly cycle.

[0044] The above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this application.

Claims

1. A non-conformal, split-type, shock-resistant, high-temperature resistant data link antenna window, characterized in that, include: The carrier antenna window (4) is used on the aircraft bulkhead. The carrier antenna window (4) forms an installation space for installing the data link antenna (2). The carrier antenna window (4) can withstand aerodynamic heating loads and impact loads to protect the data link antenna (2). The carrier antenna window (4) has a transmission opening (42) facing the leeward side of the aircraft. A wave-transparent antenna window (1) is detachably mounted on the carrier antenna window (4) to block the transmission opening (42). The wave-transparent antenna window (1) is used for the data link antenna (2) to transmit signals.

2. The non-conformal, split-type, shock-resistant, high-temperature resistant data link antenna window as described in claim 1, characterized in that, The antenna window (4) has an inclined surface (40) facing the windward side of the aircraft, which is used to guide the airflow to flow to the rear of the outer side of the aircraft bulkhead.

3. The non-conformal, split-type, shock-resistant, high-temperature resistant data link antenna window as described in claim 1, characterized in that, The carrying antenna window (4) also has a side opening (43) facing the aircraft cabin wall, the side opening (43) communicating with the transmission opening (42), and a feed plate (7) for sealing the side opening (43) is detachably connected to the carrying antenna window (4).

4. The non-conformal, split-type, shock-resistant, high-temperature resistant data link antenna window as described in claim 3, characterized in that, It also includes a mounting box (5), which is located in the mounting space and is detachably mounted on the antenna base plate (7). An antenna base plate (3) is provided on the side of the mounting box (5) facing the transmission opening (42), and the data link antenna (2) is mounted on the antenna base plate (3).

5. The non-conformal, split-type, shock-resistant, high-temperature resistant data link antenna window as described in claim 4, characterized in that, The mounting box (5) includes a box body and a bottom cover (6). The box body has an opening facing the antenna base plate (7). The bottom cover (6) covers the opening of the box body and is connected to the antenna base plate (7).

6. The non-conformal, split-type, shock-resistant, high-temperature resistant data link antenna window as described in claim 3, characterized in that, There are fitting gaps between the wave-transparent antenna window (1) and the carrier antenna window (4), and between the wave-transparent antenna window (1) and the antenna feed base plate (7). The fitting gaps are filled with high-temperature resistant flexible silicone rubber.

7. The non-conformal, split-type, shock-resistant, high-temperature resistant data link antenna window as described in claim 6, characterized in that, The width of the fitting gap is 0.1-0.2 mm.

8. The non-conformal, split-type, shock-resistant, high-temperature resistant data link antenna window as described in claim 3, characterized in that, The antenna window (4) has outwardly extending flanges (44) on both sides. Several first threaded holes (41) are spaced apart on the flanges (44). Several second threaded holes (71) corresponding to the first threaded holes (41) are spaced apart on the antenna base plate (7). The flanges (44) and the antenna base plate (7) are connected by fastening screws that pass through the first threaded holes (41) and the second threaded holes (71).

9. A non-conformal, split-type, shock-resistant, high-temperature resistant data link antenna window as described in claim 3, characterized in that, The antenna base plate (7) is provided with two positioning platforms (72) protruding towards one side of the carrying antenna window (4). The two positioning platforms (72) are symmetrically arranged on the antenna base plate (7) for positioning and cooperating with the inner walls on both sides of the installation space, and a mounting groove (721) for installing the wave-transparent antenna window (1) is formed between the two positioning platforms (72).

10. A non-conformal, split-type, shock-resistant, high-temperature resistant data link antenna window as described in any one of claims 1-9, characterized in that, The material of the carrier antenna window (4) is quartz fiber reinforced phenolic resin matrix composite material, and the material of the wave-transparent antenna window (1) is quartz fiber reinforced polyimide resin matrix material.

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