Improved structure of airborne active phased-array antenna

Abstract

The invention discloses a modified structure of an airborne active phased-array antenna, and the structure comprises an active phased-array antenna which is used for the automatic tracking of a multi-orbit satellite; the bracket is arranged on an external aircraft skin; the active phased-array antenna is arranged on the bracket and is arranged on an external aircraft skin through the bracket; the maintenance covering cap is arranged on the bracket and used for later cable maintenance and component replacement, the independent maintenance covering cap is arranged to achieve the effect of conveniently opening and closing an operation channel, antenna cable maintenance and quick fault component replacement are achieved, and the maintenance time and cost are remarkably reduced.

Description

Technical Field

[0001] This invention relates to the field of airborne phased array antennas for satellite communication, and particularly to a modification structure for an airborne active phased array antenna. Background Technology

[0002] Currently, most civil aircraft use mechanically scanned antennas, which mainly consist of a servo motor, a transmission mechanism, and the antenna body. The servo motor drives the transmission mechanism, causing the antenna to rotate around a certain axis, similar to turning a handheld flashlight to illuminate different areas, enabling the antenna beam to scan in space to cover a certain airspace.

[0003] In the civil aviation sector, mechanically scanned antennas are still widely used in weather radar systems on some small and medium-sized aircraft and some large passenger aircraft. For example, some older civil aircraft use mechanically scanned weather radar to detect weather conditions ahead of the aircraft, such as rainfall, clouds, and turbulence, providing pilots with flight safety information.

[0004] However, mechanical scanning antennas also have some drawbacks, such as large differences in the mounting holes and installation space of different aircraft models, poor adaptability of traditional antenna structures, and the need to modify the main structure of the aircraft, which leads to high costs and long cycles. This paper proposes a modification structure for an airborne active phased array antenna to solve the above problems. Summary of the Invention

[0005] To overcome the shortcomings of existing technologies, this invention provides a modified structure for an airborne active phased array antenna.

[0006] The technical solution adopted by this invention to solve its technical problem is:

[0007] This invention provides a modification structure for an airborne active phased array antenna, the modification structure comprising:

[0008] An active phased array antenna is used for automatic tracking of multi-orbit satellites; a bracket is mounted on the external aircraft skin; the active phased array antenna is mounted on the bracket and then on the external aircraft skin via the bracket; a maintenance cover is opened and closed and mounted on the bracket for later cable maintenance and component replacement.

[0009] Preferably, the active phased array antenna includes: a multi-orbit satellite automatic tracking module for tracking satellites in orbits such as CEO (geostationary orbit), IGSO (inclined geosynchronous orbit), MEO (medium orbit), and LEO (low orbit); a satellite communication module that provides a channel for selecting national satellite internet broadband communication or anti-jamming communication functions as needed. By integrating the multi-orbit satellite automatic tracking module, it achieves compatibility with signals from various orbital satellites, enabling automatic tracking and seamless switching of the full spectrum of satellites, including geostationary, inclined geosynchronous, medium orbit, and low orbit satellites, on a single antenna; and the satellite communication module provides a selectable channel for flexible configuration of communication functions, enabling flexible switching between national satellite internet broadband communication and high-reliability anti-jamming communication modes according to mission requirements, while balancing high-speed data transmission and secure communication capabilities.

[0010] Preferably, the bracket includes a housing portion and a mounting portion disposed on the housing portion. The housing portion is used to fix the antenna and is compatible with active phased array antennas of different platforms. The mounting portion is used to connect to the aircraft skin via external fasteners and mainly supports the internal skeleton of the skin. By setting the housing portion and the mounting portion, functional separation and modular load-bearing are achieved, realizing the use of a universal housing to fix and be compatible with antennas of different platforms. At the same time, the load is effectively transferred to the aircraft structure through the dedicated mounting portion, achieving a unity of antenna platform adaptability and mounting structure strength.

[0011] Preferably, the mounting part is arc-shaped to fit the external aircraft skin. By designing the mounting part as arc-shaped, it can conform to the curved surface of the aircraft skin, achieving seamless integration between the bracket and the aerodynamic shape of the aircraft. This effectively reduces the impact of the modification on the original aerodynamic characteristics and increases the mounting contact surface to improve connection rigidity and stability.

[0012] Preferably, the aircraft skin is used to provide a mounting position for the bracket and to form an aerodynamic shape to withstand aerodynamic loads. The inner side of the aircraft skin has an airframe. The mounting part of the bracket is set on the aircraft skin by fasteners, and the structural support of the bracket is transferred from the aircraft skin to the airframe, so that the airframe provides the main load-bearing support. This realizes the use of the aircraft's original strong airframe as the main load-bearing structure, ensuring the structural integrity of the antenna system under complex flight loads. At the same time, the skin mainly provides a mounting base and maintains the aerodynamic shape.

[0013] Preferably, the bracket has an opening, and a maintenance cover is detachable and located on the bracket at the opening. The maintenance cover is used to facilitate the maintenance and replacement of cables in the future. By setting an detachable maintenance cover on the bracket, a convenient maintenance channel is provided, which enables the inspection, maintenance and replacement of cables and components without large-scale disassembly of the antenna or bracket, which significantly improves the maintainability and maintenance efficiency of the equipment.

[0014] Preferably, the active phased array antenna includes several array modules, each of which is a standardized unit structure. Adjacent array modules are spliced ​​together through mechanical connectors and standardized electrical interfaces to form an antenna array. The antenna array size and interface position can be adjusted according to the installation space of different models, thereby achieving rapid adaptation and replacement between different platforms. By dividing the antenna array into a standardized unit structure, it plays a role in modular construction and flexible configuration. It enables flexible adjustment of antenna size and interface position by adding, removing or re-splicing array modules, thereby quickly adapting to the installation space and interface requirements of different models, and greatly improving the antenna's versatility and replacement speed between different platforms.

[0015] Preferably, the active phased array antenna has a heat-conducting substrate inside the array module, a heat-conducting connector is provided between the bracket and the heat-conducting substrate, and a heat dissipation structure is provided on the surface of the bracket. By setting up the heat-conducting substrate, the heat-conducting connector and the heat dissipation structure, an efficient thermal management path is constructed, which realizes the active conduction of the heat generated by the antenna array module to the bracket and dissipation through air convection, effectively controlling the antenna operating temperature and ensuring the reliability and performance stability of the system under long-term high-load operation.

[0016] Preferably, the active phased array antenna is connected to an external airborne communication system via a signal cable. The signal cable between the active phased array antenna and the airborne communication system is connected through an independent wiring channel inside the bracket, which is isolated from the power supply channel. Both ends of the signal cable are equipped with metal shielded connectors made of conductive alloy material, which are electrically connected to the grounding part of the bracket to form an electromagnetic shielding path. This reduces the impact of external electromagnetic interference on signal transmission. The independent wiring channel and the isolation of the signal from the power supply prevent signal crosstalk. By using metal shielded connectors at both ends of the signal cable and grounding them, a continuous electromagnetic shielding path is constructed. Together, these measures minimize the interference of the complex external airborne electromagnetic environment on the communication signal, ensuring the integrity and reliability of high-speed data transmission.

[0017] A civil aircraft, including a modification structure for an airborne active phased array antenna, enables the rapid installation of a high-performance satellite communication system on the civil aircraft without large-scale modifications to the main structure of the aircraft, significantly improving its broadband interconnection and reliable communication capabilities worldwide.

[0018] The beneficial effects of this invention are as follows: Through the above-described structural design, the active phased array antenna is mounted on the aircraft skin via a bracket during use, providing load-bearing and support functions, thus achieving stable mounting and precise pointing of the active phased array antenna in complex flight environments; the multi-orbit satellite automatic tracking capability of the active phased array antenna enables dynamic beamforming and multi-target synchronous tracking, achieving continuous and stable high-speed data transmission with multiple satellites during flight; and the independent maintenance access cover facilitates convenient opening and closing and provides a work channel, enabling antenna cable maintenance and rapid replacement of faulty components, significantly reducing maintenance time and costs. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. The accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0020] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0021] Figure 1 This is one of the schematic diagrams of the modified structure of the present invention;

[0022] Figure 2 This is the second schematic diagram of the modified structure of the present invention;

[0023] Figure 3 This is a schematic diagram of the bracket of the present invention;

[0024] Figure 4 This is a schematic diagram of the modified structure of the present invention.

[0025] The reference numerals in the figures include:

[0026] 1. Active phased array antenna; 2. Bracket; 3. Maintenance access cover; 4. Aircraft skin; 21. Housing section; 211. Opening; 22. Mounting section. Detailed Implementation

[0027] Reference Figures 1 to 4 A modification structure for an airborne active phased array antenna, the modification structure comprising:

[0028] Active phased array antenna 1, used for automatic tracking of multi-orbit satellites;

[0029] The bracket 2 is mounted on the external aircraft skin 4; the active phased array antenna 1 is mounted on the bracket 2 and is mounted on the external aircraft skin 4 via the bracket 2.

[0030] The maintenance cover 3 is openable and closable on the bracket 2 for later cable maintenance and component replacement.

[0031] With the above structural design, during use, the bracket 2 is installed on the aircraft skin 4 to provide load-bearing and support, enabling the active phased array antenna 1 to be stably mounted and accurately pointed in complex flight environments; the multi-orbit satellite automatic tracking capability of the active phased array antenna 1 enables dynamic beamforming and multi-target synchronous tracking, achieving continuous and stable high-speed data transmission with multiple satellites during flight; and the independent maintenance access cover 3 provides convenient opening and closing and a working channel, enabling antenna cable maintenance and rapid replacement of faulty components, significantly reducing maintenance time and costs.

[0032] Bracket 2: The top platform can be used as a fixed antenna and is compatible with active phased array antenna 1 on different platforms; the lower edge is fixed to the skin, and the main support of bracket 2 is the skeleton inside the skin.

[0033] Maintenance cover 3: Through a small, localized, and low-cost cover design, it facilitates later cable maintenance, resulting in significant maintenance convenience, time and cost savings throughout the product's life cycle, and ensuring the structural integrity and operational reliability of the equipment.

[0034] Specifically, the active phased array antenna 1 includes: a multi-orbit satellite automatic tracking module for tracking satellites in orbits such as CEO (geostationary orbit), IGSO (inclined geosynchronous orbit), MEO (medium orbit), and LEO (low orbit); a satellite communication module that provides a channel for selecting national satellite internet broadband communication or anti-jamming communication functions as needed. By integrating the multi-orbit satellite automatic tracking module, it achieves compatibility with signals from various orbital satellites, enabling automatic tracking and seamless switching of the full spectrum of satellites, including geostationary, inclined geosynchronous, medium orbit, and low orbit satellites, on a single antenna; and the satellite communication module provides a selectable channel for flexible configuration of communication functions, enabling flexible switching between national satellite internet broadband communication and high-reliability anti-jamming communication modes according to mission requirements, while balancing high-speed data transmission and secure communication capabilities.

[0035] It is worth noting that the active phased array antenna 1 can be physically divided into at least a radiating array section and a rear-end electronic compartment section. The radiating array section of the active phased array antenna 1 is used for transmitting and receiving radio waves. The rear-end electronic compartment section is housed inside the bracket 2.

[0036] The radiating array is formed by splicing together multiple standardized array modules through mechanical connectors and standardized electrical interfaces to form an electromagnetic wave radiating / receiving plane facing the sky. After installation, this plane is flush with or slightly embedded in the upper edge of the cover 21 of the bracket 2, and ensures that there is no metal obstruction in front of it, or is covered with an antenna radome made of radio wave transparent material to ensure lossless signal transmission.

[0037] The rear-end electronics compartment includes a T / R assembly corresponding to the radiating array, a beamforming network, a power module, and a control processor. The rear-end electronics compartment is installed and sealed inside the cavity formed by the housing 21 of the bracket 2, thereby isolating it from the harsh external environment.

[0038] Inside each array module of the active phased array antenna 1, the thermally conductive substrate is tightly thermally coupled to the T / R assembly. On the inner surface of the housing 21 of the bracket 2, corresponding to the position of the antenna's thermally conductive substrate, thermally conductive bosses or embedded heat pipes are provided. During installation, a flexible thermally conductive pad or thermal grease with a high thermal conductivity is used to form an efficient thermal connection interface between the antenna's thermally conductive substrate and the bracket's thermally conductive bosses / heat pipes.

[0039] The side walls and non-aerodynamically sensitive areas of the housing 21 of the bracket 2 can be provided with airflow channels and honeycomb-shaped heat dissipation ventilation holes. When the aircraft is in flight, the high-speed external airflow flows through these structures, forming a negative pressure zone that actively extracts hot air from the cavity of the bracket 2 while introducing cooler air, achieving convection-enhanced heat dissipation. The bracket material can be made of a metal with good thermal conductivity, such as aluminum alloy, to act as heat dissipation fins.

[0040] Alternatively, flow channels and honeycomb-shaped heat dissipation and ventilation holes can be provided. The flow channels and honeycomb-shaped heat dissipation and ventilation holes are connected through external pipes, which can cool the hot air inside the cavity of bracket 2.

[0041] Specifically, the bracket 2 includes a housing part 21 and a mounting part 22 disposed on the housing part 21. The housing part 21 is used to fix the antenna and is compatible with active phased array antennas 1 of different platforms. The mounting part 22 is used to connect to the aircraft skin 4 via external fasteners and to transfer the main supporting load to the airframe inside the skin. By setting the housing part 21 and the mounting part 22, functional separation and modular load-bearing are achieved. This realizes the use of a universal housing to fix and be compatible with antennas of different platforms. At the same time, the load is effectively transferred to the aircraft structure through the dedicated mounting part 22, thus achieving the unity of antenna platform adaptability and mounting structure strength.

[0042] Specifically, external fasteners can be rivets.

[0043] Specifically, a flexible heat-conducting pad layer can be provided between the aircraft skin 4 and the mounting part 22, and a curved surface fine-tuning pad set can be provided between the flexible heat-conducting pad layer and the aircraft skin 4.

[0044] Curved surface fine-tuning shim set: It consists of a series of prefabricated thin titanium alloy shims with different radii of curvature, used to initially achieve macroscopic fit with the skin surface.

[0045] Flexible thermal conductive pad: It is a sheet material with one side being flat and bonded to the mounting part 22; the other side is a slightly tacky surface that fits against the top surface of the selected curved fine-tuning pad assembly. The pad is uniformly embedded with diamond-shaped thermal conductive fibers.

[0046] Specifically, the mounting part 22 is arc-shaped to fit against the external aircraft skin 4. By designing the mounting part 22 as arc-shaped, it conforms to the curved surface of the aircraft skin 4, achieving seamless integration between the bracket 2 and the aerodynamic shape of the aircraft. This effectively reduces the impact of the modification on the original aerodynamic characteristics and increases the mounting contact surface to improve connection rigidity and stability.

[0047] Specifically, the aircraft skin 4 provides the mounting position for the bracket 2 and forms an aerodynamic shape to withstand aerodynamic loads. The inner side of the aircraft skin 4 has an airframe. The mounting part 22 of the bracket 2 is fastened to the aircraft skin 4, and the structural support of the bracket 2 is transferred to the airframe by the aircraft skin 4, so that the airframe provides the main load-bearing support. This realizes the use of the aircraft's original strong airframe as the main load-bearing structure, ensuring the structural integrity of the antenna system under complex flight loads. At the same time, the skin mainly provides the mounting base and maintains the aerodynamic shape.

[0048] Specifically, the bracket 2 has a cross-shaped reinforcing rib inside, and an arc-shaped structure is provided between the mounting part 22 and the cover part 21, with its extended end tangentially connected to the arc-shaped structure of the mounting part 22.

[0049] Specifically, the bracket 2 has an opening 211, and the maintenance cover 3 is openable and closable on the bracket 2 and located at the opening 211. The maintenance cover 3 is used to facilitate the maintenance and replacement of cables in the future. By setting the openable and closable maintenance cover 3 on the bracket 2, a convenient maintenance channel is provided, which enables the subsequent cable connection inspection, maintenance and component replacement without large-scale disassembly of the antenna or bracket 2, which significantly improves the maintainability and maintenance efficiency of the equipment.

[0050] Specifically, opening 211 is provided in the cover portion 21, and there is at least one opening.

[0051] Specifically, the edge of the maintenance cover 3 is equipped with a magnetically coded positioning pin, and a Hall sensor is installed at the corresponding bracket opening 211. When the maintenance cover 3 is closed relative to the cover part 21, the positioning pin triggers the sensor to generate an electrical signal, and the status of the cover is displayed on the maintenance terminal; an annular sealing strip is embedded on the side of the maintenance cover 3 near the inside of the bracket 2. Its cross-section is a hollow hexagonal structure, which expands evenly in all directions after being compressed to form an airtight seal.

[0052] Specifically, the active phased array antenna 1 includes several array modules, each of which is a standardized unit structure. Adjacent array modules are spliced ​​together through mechanical connectors and standardized electrical interfaces to form an antenna array. The antenna array size and interface position can be adjusted according to the installation space of different models, thereby achieving rapid adaptation and replacement between different platforms. By dividing the antenna array into a standardized unit structure, it plays a role in modular construction and flexible configuration. It enables flexible adjustment of antenna size and interface position by adding, removing or re-splicing array modules, thereby quickly adapting to the installation space and interface requirements of different models, and greatly improving the antenna's versatility and replacement speed between different platforms.

[0053] Specifically, the active phased array antenna 1 has a heat-conducting substrate inside its array module, and a heat-conducting connector is provided between the bracket 2 and the heat-conducting substrate. The surface of the bracket 2 is provided with a heat dissipation structure. By setting up the heat-conducting substrate, the heat-conducting connector and the heat dissipation structure, an efficient thermal management path is constructed, which realizes the active conduction of the heat generated by the antenna array module to the bracket 2 and dissipation through air convection, effectively controlling the antenna operating temperature and ensuring the reliability and performance stability of the system under long-term high-load operation.

[0054] Specifically, the heat dissipation structure can be slots or heat sinks.

[0055] Specifically, the active phased array antenna 1 is connected to an external airborne communication system via a signal cable. The signal cable between the active phased array antenna 1 and the airborne communication system is connected through an independent wiring channel inside the bracket 2, which is isolated from the power supply channel. Both ends of the signal cable are equipped with metal shielded connectors made of conductive alloy material. The metal shielded connectors are electrically connected to the grounding part of the bracket 2 to form an electromagnetic shielding path, thereby reducing the impact of external electromagnetic interference on signal transmission. By setting up an independent wiring channel and isolating the signal from the power supply, signal crosstalk is prevented. By using metal shielded connectors at both ends of the signal cable and grounding them, a continuous electromagnetic shielding path is constructed. Together, these measures minimize the interference of the complex external airborne electromagnetic environment on communication signals, ensuring the integrity and reliability of high-speed data transmission.

[0056] A civil aircraft, including a modification structure for an airborne active phased array antenna, enables the rapid installation of a high-performance satellite communication system on the civil aircraft without large-scale modifications to the main structure of the aircraft, significantly improving its broadband interconnection and reliable communication capabilities worldwide.

[0057] The design process and core steps of the modified structure of the airborne active phased array antenna are as follows:

[0058] Step 1: System Analysis and Interface Definition;

[0059] Platform analysis: Obtain partial three-dimensional surface data of the aircraft skin of the target aircraft model, internal frame layout, available installation space, and information on original embedded parts / holes.

[0060] Antenna requirements definition: Determine the performance specifications (frequency band, power, number of array elements, tracking track type) and physical boundary dimensions of the active phased array antenna.

[0061] Interface definition: Clearly define the mechanical interface (mounting point, positioning pin), thermal interface (heat-conducting surface), electrical interface (cable connector) between the antenna and the bracket, as well as the mounting interface between the bracket and the aircraft skin.

[0062] Step 2: Modular bracket structure design;

[0063] Integrated support and protection enclosure design:

[0064] Function: Design a cavity structure (shell section) with an open top or a covered top of the wave shield.

[0065] Method: The radiating array of the antenna is mounted on the aircraft skin 4 or bracket 2, and the entire rear electronic compartment is housed inside the cavity. The cavity structure itself serves as the antenna mounting base and environmental protection housing.

[0066] Optimization: Reinforcing ribs (such as cross-shaped ones) are arranged inside the cover part 21 to improve local rigidity; maintenance openings and corresponding cover installation interfaces are designed on the side wall.

[0067] Adaptive installation interface design:

[0068] Function: Enables seamless and rigid connection between the bracket and aircraft skins with various curvatures.

[0069] Method: Design an arc-shaped mounting part extending from the casing, the curvature of which is determined by analyzing the greatest common divisor of the target model group or by designing a micro-deformation structure.

[0070] Adaptor layer design: A composite interface of "curved fine-tuning gasket set" and "flexible thermal conductive pad layer" is introduced between the mounting part and the skin to compensate for manufacturing tolerances and surface differences, while establishing an auxiliary heat conduction path.

[0071] Step 3: Design of a high-efficiency thermal management system;

[0072] Internal heat conduction path construction:

[0073] Method: Integrate a thermally conductive substrate within each antenna array module. Design thermally conductive protrusions or embed heat pipes at corresponding positions on the inner wall of the bracket housing.

[0074] Interface treatment: A high thermal conductivity flexible pad or thermal grease is used to fill the gap between the antenna thermal conductive substrate and the bracket thermal conductive boss to form a low thermal resistance interface.

[0075] Enhanced external convection cooling:

[0076] Method: In the area of ​​the non-main aerodynamic surface of the support shell, aerodynamically optimized honeycomb ventilation holes or guide channels are opened.

[0077] Principle and application: Utilizing the negative pressure effect generated by the high-speed airflow at the ventilation holes during flight, hot air inside the bracket cavity is actively drawn in, forming a "breathing" type of forced convection cooling.

[0078] Material selection: Lightweight, high thermal conductivity materials such as aluminum alloys are preferred for manufacturing the bracket, making it a large heat sink itself.

[0079] Step 4: High-reliability connection and maintenance design;

[0080] Main load-bearing connection design:

[0081] Method: The mounting part 22 of bracket 2 is connected to the aircraft skin through multiple rows of high-locking-force fasteners (such as high-locking bolts and ring groove rivets). During the design phase, in collaboration with the aircraft manufacturer, load-bearing frame joints are arranged or reinforced at corresponding positions on the inner side of the skin to ensure that the load is directly transferred to the main structure.

[0082] Maintainable access design:

[0083] Method: A standardized maintenance access cover is provided on the side or rear of the bracket housing. The cover uses a quick-lock mechanism and integrates a hollow section sealing ring to ensure convenient opening and closing and reliable sealing.

[0084] Status monitoring: Optionally, a magnetic coded positioning pin and a Hall sensor can be integrated into the lid to achieve electronic monitoring and recording of the lid's closing status.

[0085] Step 5: Electromagnetic compatibility and cable management design;

[0086] Zoned isolation cabling:

[0087] Method: Separate signal cable channels and power cable channels are set up inside the bracket cavity for physical isolation to avoid crosstalk.

[0088] End-to-end shielding design:

[0089] Method: Metal shielded connectors are used at both ends of the signal cable. During installation, the shielded connectors are reliably connected to the grounding posts on the bracket housing via conductive lap strips or direct contact.

[0090] System grounding: The bracket housing is electrically connected to the aircraft skin by installing fasteners, thereby connecting to the aircraft's overall grounding network and forming a complete electromagnetic shield.

[0091] The above descriptions provide one or more embodiments in conjunction with specific details, but do not imply that the specific implementation of the present invention is limited to these descriptions. Any methods or structures that are similar to or identical to those of the present invention, or any technical deductions or substitutions made based on the concept of the present invention, should be considered within the scope of protection of the present invention.

Claims

1. A modification structure for an airborne active phased array antenna, characterized in that, The modified structure includes: An active phased array antenna (1) is used for automatic tracking of multi-orbit satellites; The bracket (2) is mounted on the outer aircraft skin (4); the active phased array antenna (1) is mounted on the bracket (2) and is mounted on the outer aircraft skin (4) via the bracket (2); The maintenance cover (3) can be opened and closed and is located on the bracket (2) for later cable maintenance and component replacement.

2. The modification structure for an airborne active phased array antenna according to claim 1, characterized in that, The active phased array antenna (1) includes: Multi-orbit satellite automatic tracking module for tracking satellites in orbits such as CEO, IGSO, MEO, and LEO; The satellite communication module provides a channel for enabling national satellite internet broadband communication or anti-jamming communication.

3. The modification structure of an airborne active phased array antenna according to claim 1, characterized in that: The bracket (2) includes a housing part (21) and a mounting part (22) provided on the housing part (21). The housing part (21) is used to fix the antenna and is compatible with active phased array antennas (1) of different platforms. The mounting part (22) is used to connect to the aircraft skin (4) via external fasteners and to transfer the main support load to the airframe inside the skin.

4. The modification structure of an airborne active phased array antenna according to claim 3, characterized in that: The mounting section (22) is arc-shaped to fit the aircraft skin (4) to the outside.

5. The modification structure of an airborne active phased array antenna according to claim 3, characterized in that: The aircraft skin (4) is used to provide the mounting position of the bracket (2) and to form an aerodynamic shape to bear aerodynamic loads. The inner side of the aircraft skin (4) has a fuselage frame. The mounting part (22) of the bracket (2) is set on the aircraft skin (4) by fasteners, and the structural support of the bracket (2) is transferred from the aircraft skin (4) to the fuselage frame so that the fuselage frame provides the main load-bearing support.

6. The modification structure of an airborne active phased array antenna according to claim 3, characterized in that: The bracket (2) has an opening (211), and the maintenance cover (3) is openable and closed on the bracket (2) and located at the opening (211). The maintenance cover (3) is used to facilitate the maintenance and replacement of cables in the future.

7. The modification structure of an airborne active phased array antenna according to claim 1, characterized in that: An active phased array antenna (1) includes several array modules. Adjacent array modules are spliced ​​together through mechanical connectors and standardized electrical interfaces to form an antenna array. The size and interface position of the antenna array can be adjusted according to the installation space of different models.

8. The modification structure of an airborne active phased array antenna according to claim 7, characterized in that: The active phased array antenna (1) has a heat-conducting substrate inside the array module, and a heat-conducting connector is provided between the bracket (2) and the heat-conducting substrate. The surface of the bracket (2) is provided with a heat dissipation structure.

9. The modification structure of an airborne active phased array antenna according to claim 8, characterized in that: The active phased array antenna (1) is connected to an external airborne communication system via a signal cable. Both ends of the signal cable are equipped with metal shielding connectors made of conductive alloy material. The metal shielding connectors are electrically connected to the bracket (2) to form an electromagnetic shielding path, thereby reducing the impact of external electromagnetic interference on signal transmission.

10. A civil aircraft, characterized in that: This includes a modification structure for an airborne active phased array antenna as described in any one of claims 1-9.

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