Antenna device

Abstract

The invention discloses an antenna device, which is applied to the technical field of communication equipment, and comprises an antenna assembly and a fuselage installed on an airplane, the antenna assembly comprises a shell and an air duct arranged in the shell, a cavity is formed between the outer wall of the air duct and the inner wall of the shell, the end part of the air duct is provided with a vent hole, and the vent hole is communicated with the shell. The shell is provided with a ventilation opening communicated with the ventilation opening, the side wall of the air duct is provided with an air outlet, the air outlet is communicated with the cavity, and the shell is further provided with a mounting connector communicated with the cavity; and the heat dissipation assembly is detachably installed on the installation interface, the heat dissipation assembly comprises a heat dissipation fan, and the heat dissipation fan is used for leading air flow into the air channel from the air vent and discharging the air flow out of the shell through the air outlet and the cavity. The antenna device shortens the maintenance or replacement time.

Description

Technical Field

[0001] This invention relates to the field of communication equipment technology, and in particular to an antenna device. Background Technology

[0002] With the increasing demand for aviation communications, large satellite communication antenna equipment needs to be installed on aircraft. A typical configuration is an antenna device exposed on the fuselage, comprising a housing, an antenna radiator, and an antenna mounting bracket. These antennas are bulky, heavy, and generate significant heat, requiring cooling fans for reliable operation.

[0003] In existing technologies, cooling fans are typically integrated inside the antenna radiator or within the antenna mounting bracket. However, as high-speed rotating mechanical components, cooling fans suffer from short lifespans and low reliability. If a cooling fan fails, the entire antenna assembly must be removed from the fuselage for repair or replacement. This process involves core components such as the housing, antenna radiator, and antenna mounting bracket, making it complex and time-consuming. This directly leads to longer maintenance cycles and increased aircraft downtime, severely impacting airline operational efficiency and economic benefits.

[0004] Therefore, how to shorten the maintenance or replacement time of the cooling fan inside the antenna device has become an urgent problem to be solved by those skilled in the art. Summary of the Invention

[0005] The purpose of this invention is to provide an antenna device that shortens maintenance or replacement time.

[0006] To solve the above-mentioned technical problems, the present invention provides an antenna device, comprising:

[0007] An antenna assembly is installed on the fuselage of an aircraft. The antenna assembly includes a housing and an air duct disposed within the housing. A cavity is formed between the outer wall of the air duct and the inner wall of the housing. An air vent is provided at the end of the air duct. A ventilation port is provided in the housing and communicates with the air vent. An air outlet is provided on the side wall of the air duct and communicates with the cavity. The housing is also provided with an installation interface that communicates with the cavity.

[0008] A heat dissipation component is detachably installed on the mounting interface. The heat dissipation component includes a cooling fan for introducing airflow from the vent into the air duct, and then discharging it to the outside of the housing through the vent and the cavity.

[0009] Optionally, the air duct extends along the flight direction, and its two ends are sealed and fixed to the inner wall of the housing; the front end of the air duct forms a front vent, and the rear end forms a rear vent; the housing is provided with a front vent and a rear vent, wherein the rear vent is directly opposite the rear vent, and the front vents are arranged on the left and right sides of the front vent.

[0010] Optionally, each of the left and right side walls of the air duct is provided with an air outlet, and both air outlets are arranged on the side adjacent to the rear ventilation opening.

[0011] Optionally, it also includes:

[0012] Control valves are used to open and close the front vent and the rear vent.

[0013] The controller, electrically connected to the heat dissipation assembly, is configured to:

[0014] When the aircraft is stationary, the front vent and / or the rear vent are opened, and the heat dissipation components are activated.

[0015] When the aircraft is in flight, the front vent and the rear vent are opened, and the heat dissipation components are closed.

[0016] Optionally, the heat dissipation component further includes:

[0017] The grille panel has air vents.

[0018] A bracket is fixed to the inner side of the grille panel, the bracket is offset from the air outlet, and the cooling fan is installed on the bracket;

[0019] During installation, the cooling fan and the bracket are inserted into the mounting interface and extend into the cavity, and the grille panel is attached to the outer wall of the housing.

[0020] Optionally, a temperature detection unit is provided inside the air duct for collecting the air duct temperature;

[0021] The temperature detection unit is electrically connected to the controller, which is configured to activate the heat dissipation component when the air duct temperature exceeds a first threshold, and gradually increase its rotation speed as the temperature rises.

[0022] Optionally, the heat dissipation component includes multiple cooling fans, and the controller is configured to: whenever the air duct temperature rises by a set difference relative to the first threshold, turn on the cooling fans one by one until all the cooling fans are in operation.

[0023] Optionally, the inner side of the air outlet is covered with a microporous pressure balancing membrane, and the inner side of the lip of the air outlet is provided with an anti-icing heating ring.

[0024] Optionally, a locking mechanism is provided between the heat dissipation component and the mounting interface, the locking mechanism comprising:

[0025] A locking tongue is elastically hinged to the outer periphery of the bracket, and the locking tongue is provided with a handle.

[0026] A locking groove is provided on the side wall of the mounting interface;

[0027] When the heat dissipation component is pressed, the latch engages with the lock groove; when the handle is pulled, the latch disengages from the lock groove.

[0028] Optionally, the locking tongue is provided with an anti-loosening pawl, which is coaxially hinged to the locking tongue. The front end of the anti-loosening pawl is provided with teeth, and the bottom of the locking groove is provided with ratchet teeth. In the locked state, the teeth engage with the ratchet teeth.

[0029] Compared to existing technologies, the antenna device provided in this embodiment completely eliminates the internal cooling fan of the antenna assembly, integrating the cooling function into an online replaceable heat dissipation component. The heat dissipation component is detachably embedded in the mounting interface; if the cooling fan fails, the entire antenna assembly does not need to be removed, but only the heat dissipation component needs to be pulled out laterally for replacement, significantly reducing line maintenance downtime. Simultaneously, the external cooling fan eliminates vibration transmission and oil mist contamination associated with traditional internal solutions, significantly improving the long-term operational reliability of the antenna assembly. Attached Figure Description

[0030] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, 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 embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the provided drawings without creative effort.

[0031] Figure 1 This is a schematic diagram showing the connection between the antenna assembly and the heat dissipation assembly in an antenna device provided according to a specific embodiment of the present invention.

[0032] Figure 2 This is a schematic diagram showing the antenna assembly and heat dissipation assembly not yet installed.

[0033] Figure 3 This is a magnified view of the antenna assembly and heat dissipation assembly before they are installed.

[0034] Figure 4 This is a schematic diagram of the heat dissipation component.

[0035] Figure 5 This is another schematic diagram of the heat dissipation component;

[0036] Figure 6 A schematic diagram of the airflow during the operation of the heat dissipation component;

[0037] Figure 7 This is a schematic diagram of the airflow when the heat dissipation components are not in operation.

[0038] Figure label:

[0039] 1-Antenna assembly; 11-Housing; 12-Mounting interface; 13-Air duct; 14-Rear ventilation port; 15-Rear vent; 16-Cavity; 17-Air outlet; 18-Front-end ventilation port; 19-Front-end ventilation port; 2-Heat dissipation assembly; 21-Heat dissipation fan; 22-Bracket; 23-Grate panel; 24-Power connector. Detailed Implementation

[0040] The core of this invention is to provide an antenna device that shortens maintenance or replacement time.

[0041] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0042] In one specific embodiment provided by the present invention, please refer to Figures 1-7 The antenna device mainly includes antenna assembly 1 and heat dissipation assembly 2.

[0043] Antenna assembly 1 is installed on the fuselage of an aircraft. Antenna assembly 1 includes a housing 11 and an air duct 13 disposed within the housing 11. A cavity 16 is formed between the outer wall of the air duct 13 and the inner wall of the housing 11. An air vent is provided at the end of the air duct 13. The housing 11 is provided with a ventilation port communicating with the air vent. An air outlet 17 is provided on the side wall of the air duct 13. The air outlet 17 communicates with the cavity 16. The housing 11 is also provided with an installation interface 12 communicating with the cavity 16.

[0044] The heat dissipation component 2 is detachably installed on the mounting interface 12. The heat dissipation component 2 includes a heat dissipation fan 21, which is used to introduce airflow from the vent into the air duct 13, and then discharge it to the outside of the housing 11 through the air outlet 17 and the cavity 16.

[0045] It should be noted that the antenna device mainly includes two functional modules: antenna assembly 1 and heat dissipation assembly 2. The two modules are connected to the mechanical and air circuits through the mounting interface 12 on the housing 11 to form a cooling structure that can be replaced online.

[0046] The antenna assembly 1 has a housing 11 as its outer contour. Inside the housing 11, an air duct 13 is arranged, which serves as the main airflow channel for flight. Both ends of the air duct 13 are sealed to the inner wall of the housing 11, forming an annular cavity 16 between the outer wall of the air duct 13 and the inner wall of the housing 11. Vents are provided at the ends of the air duct 13, and corresponding vents are provided in the housing 11 to ensure that external air can directly enter the interior of the air duct 13. An air outlet 17 is provided on the side wall of the air duct 13, directly communicating with the cavity 16. The cavity 16 then communicates with the outside through a pre-reserved mounting interface 12 on the side wall of the housing 11. Thus, the air duct 13, the cavity 16, and the mounting interface 12 are connected in series, forming an airflow path from the vent, the interior of the air duct 13, the air outlet 17, the cavity 16, to the mounting interface 12. This ensures that the heat-generating area inside the air duct 13 is directly flushed, while the cavity 16 buffers and equalizes the airflow, reducing outlet turbulence noise.

[0047] The heat dissipation assembly 2 is detachably embedded in the mounting interface 12. A cooling fan 21 is arranged on the side of the heat dissipation assembly 2 facing the cavity 16. Depending on the space height, the cooling fan 21 can be flexibly selected as an axial fan or a side-blowing turbine fan. The axis of the axial fan impeller is coaxial with the air outlet 17, while the axis of the side-blowing turbine fan impeller is perpendicular to the air outlet 17, achieving adaptation between high-profile axial exhaust and low-profile side exhaust. During operation, outside air flows into the air duct 13 through the vent, absorbs heat from the inner wall, and is then sprayed into the cavity 16 through the air outlet 17. The cooling fan 21 creates a negative pressure in the cavity 16, rapidly drawing in and expelling the hot air, thus completing active cooling. The entire heat dissipation assembly 2 contacts the housing 11 through the mounting interface 12, and replacement does not require disassembling the housing 11 or the air duct 13, achieving true online replacement. Meanwhile, the heat dissipation component 2 is located on the outer surface of the left and right sides of the antenna component 1, away from the main airflow channel of the flight, and the axis of the air inlet is perpendicular to the axis of the air outlet 17, forming a right-angle turning air path. The high-speed airflow will not directly impact the fan impeller, avoiding the forced rotation of the cooling fan 21 by the high-speed airflow, and significantly extending the service life of the cooling fan 21.

[0048] By applying the technical solution provided in this invention, the internal cooling fan 21 of the antenna assembly 1 is completely eliminated, and the cooling function is integrated into the online replaceable heat dissipation component 2. If the cooling fan 21 fails, it is not necessary to remove the entire antenna assembly 1; simply pulling out the heat dissipation component 2 laterally is sufficient for replacement, significantly reducing downtime for line maintenance. Simultaneously, the external cooling fan 21 eliminates vibration transmission and oil mist contamination associated with traditional internal solutions, significantly improving the long-term operational reliability of the antenna assembly 1.

[0049] In some embodiments, the air duct 13 extends along the flight direction and its two ends are sealed and fixed to the inner wall of the housing 11; the front end of the air duct 13 forms a front vent 18 and the rear end forms a rear vent 15; the housing 11 is provided with a front vent 19 and a rear vent 14, wherein the rear vent 14 and the rear vent 15 are directly opposite each other, and the front vent 19 is arranged on the left and right sides of the front vent 18.

[0050] It should be noted that the air duct 13 extends in a straight line along the flight direction, and its front and rear end faces are sealed and fixed to the inner wall of the housing 11, forming a closed heat dissipation channel isolated from the main cavity of the housing 11. A front vent 18 is opened on the front wall of the air duct 13, and a rear vent 15 is opened on the rear wall. Preferably, the sealing and fixing of the air duct 13 to the inner wall of the housing 11 adopts a combination of continuous weld or adhesive bonding and riveting, which can withstand flight loads and prevent air short circuits, ensuring that the airflow flows along a fixed path of the front vent 18 and the rear vent 15, the interior of the air duct 13, the air outlet 17, the cavity 16, and the heat dissipation component 2, thereby achieving an efficient and maintainable cooling cycle.

[0051] Both vents face directly to the inner wall of the housing 11, allowing outside air to enter the air duct 13 through the front vent 19 and rear vent 14 located on the corresponding positions of the housing 11 wall. The rear vent 14 is aligned with the center of the rear vent 15, forming a straight flow path. The front vent 19 is configured as two symmetrical openings on the left and right, located on both sides of the front vent 18, expanding the air intake area through lateral airflow while avoiding airflow dead zones in the front area.

[0052] Because an annular cavity 16 is left between the outer wall of the air duct 13 and the inner wall of the housing 11, and the air outlet 17 is located on the side wall of the air duct 13 and faces the cavity 16, air is simultaneously drawn in through the front vent 19 and the rear vent 14. After heat exchange is completed in the air duct 13, the air is discharged into the annular cavity 16 through the air outlet 17 and then extracted by the heat dissipation component 2 installed on the side of the housing 11. The front and rear dual air intake layout ensures that the entire length of the air duct 13 is swept by airflow, resulting in a more uniform heat distribution. The air intakes on both sides at the front can utilize natural convection when the aircraft is parked on the ground, while the direct air intake at the rear enhances cooling under the ramjet effect of flight. The two complement each other, ensuring that the inner wall of the air duct 13 is in an effective heat dissipation state under different operating conditions.

[0053] In some embodiments, each of the left and right sidewalls of the air duct 13 is provided with an air outlet 17, and both air outlets 17 are arranged adjacent to the rear ventilation port 14. Preferably, the two air outlets 17 are symmetrically arranged with respect to the longitudinal center plane of the air duct 13. This dual-outlet structure creates a double-sided suction form in the rear section of the air duct 13. After the airflow enters the air duct 13 from the front ventilation port 18 and the rear ventilation port 15, it continuously absorbs heat from the wall surface during its backward flow. The temperature is highest when it reaches the rear area. At this point, the heat has not yet been transferred forward and is discharged simultaneously through the left and right air outlets 17, which can maximize the utilization of the temperature difference and improve the heat exchange efficiency. The left and right dual outlets also bring about a balanced flow distribution. When one side of the heat dissipation component 2 is running, the other side's air outlet 17 can still remain unobstructed, preventing overheating hotspots caused by blockage on one side. If the heat dissipation components 2 on both sides work simultaneously, their relative arrangement makes the lateral pressure gradient of the air duct 13 smaller, the cross-sectional flow velocity more uniform, and the wall surface temperature distribution more consistent, reducing thermal stress.

[0054] The air outlet 17 is located adjacent to the rear vent 14, meaning that the outlet and the rear direct intake airflow direction are nearly perpendicular, creating an airflow deflection effect. The high-speed intake air at the rear, under inertia, directly impacts the end wall of the duct 13, creating a local low-pressure zone upon encountering the lateral air outlet 17. This causes the hot air to flow out rapidly laterally, preventing heat from accumulating at the end of the duct 13. Since both air outlets 17 are located near the same cross-section of the duct 13, the front to middle sections of the duct 13 maintain an intact wall surface without additional openings, ensuring that the intake airflow maintains a high velocity in the main heat-generating areas, enhancing convective heat transfer. In the rear section, the symmetrical dual outlets reduce local pressure, forming a local circulation of suction and discharge, further removing accumulated heat. Thus, the entire length of the duct 13 is fully utilized, and the heat at the end is rapidly extracted laterally, achieving efficient, low-resistance, and balanced heat dissipation.

[0055] In a preferred embodiment, the air outlet 17 may adopt a flanged reinforcement design, with the flange extending outward and integrally formed with the side wall of the air duct 13, which increases the opening rigidity and provides a continuous contact surface for the subsequent installation of the bracket 22. Preferably, an annular gap is maintained between the outer edge of the flange and the inner wall of the housing 11 to form a transition section, so that the high-speed exhaust air is decelerated and pressure equalized before entering the cavity 16, thereby reducing aerodynamic noise.

[0056] In some embodiments, the antenna device further includes control valves and a controller. The control valves are mounted on the housing 11 and are used to open or close the front vent 19 and the rear vent 14, respectively. The controller is electrically connected to the heat dissipation assembly 2 and outputs corresponding commands according to the aircraft's operating status. Specifically, when the aircraft is parked or in a low-speed taxiing phase, the controller drives the control valves to open the front vent 19 and / or the rear vent 14, simultaneously activating the heat dissipation assembly 2, allowing outside air to flow through the air duct 13 under the suction of the cooling fan 21 for active cooling. When the aircraft is in flight, the controller keeps the front vent 19 and the rear vent 14 fully open and closes the heat dissipation assembly 2, utilizing the ram air to form natural convection within the air duct 13 for passive cooling while still maintaining sufficient cooling capacity. Through the coordinated control of the valves and the cooling fan 21, the same airflow path can provide forced cooling on the ground and switch to zero-power self-cooling in the air, balancing energy consumption, noise, and reliability.

[0057] In some embodiments, the heat dissipation component 2 further includes:

[0058] Grille panel 23 is equipped with air vents.

[0059] Bracket 22 is fixed to the inside of grille panel 23. Bracket 22 is offset from air outlet. Cooling fan 21 is installed on bracket 22.

[0060] During installation, the cooling fan 21 and bracket 22 are inserted into the mounting interface 12 and extend into the cavity 16, and the grille panel 23 is attached to the outer wall of the housing 11.

[0061] It should be noted that the grille panel 23 is located on the outermost side of the heat dissipation assembly 2, and its surface has a through-hole for exhausting hot air from the cavity 16 to the housing 11. During flight, the exhaust vent also functions as a pressure relief port for the antenna assembly 1. The bracket 22 is fixed to the inner side of the grille panel 23, providing a support plane for the cooling fan 21. The exhaust vent and the bracket 22 are offset from each other to ensure that the bracket 22 does not obstruct the exhaust vent and that the exhaust high-speed airflow does not directly impact the bracket 22, thereby effectively reducing aerodynamic noise and flow resistance. Both the bracket 22 and the grille panel 23 can be made of metal. The bracket 22 can be welded or screwed to the inner side of the grille panel 23 in a ring or bridge shape to form a cantilever support structure. The bracket 22 has a mounting position, and the cooling fan 21 is fixed to this mounting position by radial screws or clips. Its air inlet side faces the cavity 16, and its air outlet side faces the exhaust vent, thus forming a straight or zigzag exhaust path. Preferably, the mounting interface 12 coincides with the axis of the air outlet 17, and the outer contour of the bracket 22 matches the inner cavity cross section of the mounting interface 12. After insertion, automatic alignment can be achieved, ensuring that the cooling fan 21 accurately enters the area opposite to the air outlet 17, forming an efficient exhaust channel.

[0062] During installation, the bracket 22, along with the cooling fan 21, is inserted into the mounting interface 12 and extends into the cavity 16. The grille panel 23 is then fitted against the outer wall of the housing 11, forming a continuous aerodynamic shape on the outer surface. The antenna assembly 1 has a power supply interface located deep within the mounting interface 12. When the cooling assembly 2 is inserted, the power connector 24, fixed to the rear of the bracket 22, automatically mates with the power supply interface, completing the integrated transmission of power and signal without the need for additional wiring or disassembly, enabling rapid assembly. Preferably, a sealing ring or labyrinth structure is provided between the outer edge of the bracket 22 and the mounting interface 12 to prevent air backflow and isolate moisture and dust. Since the bracket 22 and the grille panel 23 are fixedly connected, the vibration of the cooling fan 21 is first dispersed through the bracket 22 to the larger grille panel 23, and then attenuated by the outer wall of the housing 11, avoiding localized stress concentration.

[0063] The entire heat dissipation assembly 2 only contacts the housing 11 through the mounting interface 12. When disassembling, simply pull out the grille panel 23 to remove the bracket 22 and the cooling fan 21 together, achieving true online replacement without loosening the housing 11 or the air duct 13. As a result, the convenience of maintenance and reliability are improved simultaneously.

[0064] In some embodiments, a temperature detection unit is arranged inside the air duct 13. The temperature sensing probe of the unit extends into the central region of the air duct 13 cavity to collect the air duct temperature and forms a closed signal loop with the controller via wires. A heat insulation bushing may be provided between the housing of the temperature detection unit and the wall of the air duct 13 to prevent the wall heat conduction from causing lag in sampling and to provide shock absorption, avoiding fatigue breakage of the lead wire due to aircraft vibration. The position of the temperature sensing probe avoids the direct airflow impact area of ​​the vent and outlet 17, so that the collected temperature value can better reflect the average thermal state inside the air duct 13.

[0065] After the controller is electrically connected to the temperature detection unit, it receives the air duct temperature signal in real time. When the air duct temperature exceeds a preset first threshold, the controller outputs a start signal to the heat dissipation component 2 and gradually increases the speed of the cooling fan 21 according to the rise in air duct temperature, achieving linear tracking between temperature and speed. This gradual increase allows the cooling fan 21 to transition from low speed to high speed in stages, reducing the starting inrush current and maintaining stable airflow within the air duct 13, preventing dust backflow caused by instantaneous high-pressure suction. Since the temperature detection unit is located inside the air duct 13, the controller can dynamically adjust the cooling intensity according to the actual heat generation, preventing energy waste from over-cooling and high temperature accumulation caused by insufficient cooling. This ensures effective heat dissipation while extending the service life of the cooling fan 21 and reducing load fluctuations in the aircraft's power system.

[0066] In some embodiments, multiple cooling fans 21 are arranged side-by-side inside the heat dissipation assembly 2. The power lines and control signal lines of each cooling fan 21 are respectively connected to the same power connector 24, and form an independent circuit with the controller through the power connector 24, realizing individual start-stop without interference. Multiple cooling fans 21 can share a bracket 22 as a common mounting base. The bracket 22 has independent positioning holes corresponding to the position of each cooling fan 21. The edge of the hole is provided with a flange. A shock-absorbing sleeve is provided between the inner circumference of the flange and the outer frame of the cooling fan 21, which not only ensures the perpendicularity of the axis of the cooling fan 21 to the plane of the bracket 22, but also isolates the vibration of the cooling fan 21 from being transmitted to the grille panel 23. It is preferable to provide a partition rib on the back of the bracket 22 to separate the air intake areas of adjacent cooling fans 21 from each other, so as to prevent the outflow of one cooling fan 21 from being re-intaken by the adjacent cooling fan 21, causing a short circuit.

[0067] The controller maintains real-time communication with the temperature detection unit. When the duct temperature exceeds a first threshold, the first cooling fan 21 is activated. Subsequently, whenever the temperature continues to rise and reaches a set difference, the controller sequentially activates the next cooling fan 21 in a predetermined order until all cooling fans 21 are operational. During the activation process, the controller verifies the Hall feedback signal of each cooling fan 21. If the speed is found to be zero, the controller skips the faulty cooling fan 21 and directly activates the next one, ensuring uninterrupted airflow output. Because the cooling fans 21 are activated one at a time, the airflow within the duct 13 increases in a stepped manner, the lateral pressure gradient is controlled within a small range, the airflow on the walls of the duct 13 is uniform, the temperature distribution becomes more consistent, and thermal stress is significantly reduced. At the same time, the stepped start-stop method avoids the current superposition impact caused by the simultaneous activation of multiple cooling fans 21, reduces the burden on the aircraft's DC busbars, and also reduces the impact of sudden noise changes on passengers in the cabin.

[0068] By mapping the temperature difference to the number of units, the controller can maintain the operation of at least 21 cooling fans under light load, and automatically expand the air volume as the heat load increases, so as to achieve a balance between on-demand cooling and optimal energy efficiency.

[0069] In a preferred embodiment, the controller has a built-in timer and is further configured to: start the timer to count down when the temperature inside the air duct 13 is below a first threshold and remains below the hysteresis range, and then gradually shut down the cooling fan 21 after the preset delay expires.

[0070] It should be noted that the controller integrates a timer, whose start and stop are driven by a real-time signal provided by the temperature detection unit, eliminating the need for additional hardware trigger lines. The timer's clock source is the same as the controller's main frequency, ensuring countdown accuracy. The timer's output is directly connected to the enable circuit of each cooling fan 21, allowing for sequential low-level pull-down of the corresponding circuits after the countdown ends, achieving step-by-step shutdown. The preset delay value written in the timer register can be modified online via maintenance software, thereby adjusting the minimum operating time of the cooling fans 21 under different flight routes or seasonal conditions, avoiding frequent start-stop cycles.

[0071] When the duct temperature is below the first threshold and remains below the hysteresis range, the controller starts a countdown timer. During the countdown, if the duct temperature rises again and exceeds the hysteresis limit, the timer automatically resets to zero, and the cooling fans 21 maintain their current operating number to prevent repeated start-stop cycles due to small temperature fluctuations. At the moment the countdown ends, the controller shuts down the cooling fans 21 in a step-by-step manner, with the last cooling fan 21 to start being shut down first, and the first cooling fan 21 to start being shut down last. This causes the airflow in the duct 13 to decrease in a stepped manner, preventing airflow backflow or dust backflow caused by sudden pressure changes. During the step-by-step shutdown process, the controller still confirms the Hall signal of each shut-down cooling fan 21 to ensure that the blades have completely stopped rotating before disconnecting the power supply, thus preventing the cooling fans 21 from generating braking sparks under residual voltage.

[0072] With its built-in timer, the controller provides a delayed shutdown path for the cooling system, ensuring that residual heat from the air duct 13 is fully removed while avoiding energy waste and bearing wear caused by prolonged idling of the cooling fan 21. This achieves a comprehensive balance of low noise, low power consumption, and long lifespan without adding external components. This function is fully encapsulated in the controller, resulting in a simple structure, high reliability, and direct application to existing cooling component 2 hardware platforms without requiring modifications to the bracket 22, grille panel 23, or power connector 24 layout.

[0073] In some embodiments, a microporous pressure balancing membrane is coated on the inner side of the air outlet. The microporous pressure balancing membrane is a flexible thin film element, and its outer periphery is clamped to the inner end face of the air outlet by an annular pressure frame. Continuous sealing ribs are provided between the pressure frame and the grille panel 23 to prevent the edge of the microporous pressure balancing membrane from being peeled off by the high-speed airflow. The thickness of the microporous pressure balancing membrane is much smaller than the depth of the air outlet, and an annular cavity 16 is left on its inner side, so that the microporous pressure balancing membrane can vibrate freely in a small amplitude under the action of bidirectional air pressure difference, so as to achieve instantaneous pressure balance inside and outside the shell 11, while blocking liquid water and solid particles from entering the cavity 16.

[0074] In some embodiments, an anti-icing heating ring is provided on the inner side of the lip of the air outlet. Exemplarily, the anti-icing heating ring is embedded in an annular groove on the inner side of the lip of the air outlet, the depth of the annular groove being the same as the thickness of the anti-icing heating ring, so that the outer surface of the anti-icing heating ring is flush with the outer surface of the lip, without disrupting the aerodynamic shape. A thermally conductive pad can be filled between the back of the anti-icing heating ring and the bottom of the annular groove, eliminating assembly gaps and evenly distributing the heat generated by the anti-icing heating ring to the entire circumference of the lip, preventing localized overheating that could lead to membrane aging.

[0075] Preferably, a microporous pressure balancing membrane and an anti-icing heating ring are sequentially arranged inside the air outlet of the grille panel 23. During operation, when the aircraft descends from high altitude to a warm and humid area, the lip surface reaches the freezing point first. The anti-icing heating ring is energized and heated under the drive of the controller. The heat is conducted to the lip through the thermally conductive pad, keeping the lip surface temperature above the freezing point, thereby preventing ice or frost from forming on the outer edge of the air outlet. The microporous pressure balancing membrane withstands the internal and external pressure difference during heating. Its microporous structure allows water molecules to pass through in both directions in gaseous form, but blocks liquid water droplets and defrosting water films, preventing ice crystals from accumulating on the membrane surface and clogging the micropores. Since the anti-icing heating ring is located on the outermost side of the lip and the microporous pressure balancing membrane is located on the inner side of the anti-icing heating ring, the heat from the anti-icing heating ring is transferred outward while also providing low-temperature insulation for the microporous pressure balancing membrane, reducing the shrinkage stress caused by sudden cooling of the membrane and extending its service life.

[0076] Structurally, the anti-icing heating ring and the microporous pressure balancing membrane share the same pressure frame for fixation. A stepped shoulder is provided on the inner edge of the pressure frame. The outer layer of the shoulder presses firmly against the anti-icing heating ring, while the inner layer presses firmly against the edge of the microporous pressure balancing membrane. A single tightening locks both components simultaneously, reducing the number of parts and assembly time. An O-ring is installed between the outer edge of the pressure frame and the inner wall of the air outlet of the grille panel 23, achieving dual isolation between the anti-icing heating ring, the microporous pressure balancing membrane, and the external environment, ensuring that the microporous pressure balancing membrane maintains its seal under heating, vibration, and humid heat cycling conditions.

[0077] With the above arrangement, the air outlet not only achieves the function of exhausting air, but also has comprehensive performance of anti-icing, dustproof and waterproof. All functional components are integrated within the available thickness of the heat dissipation component 2 without adding any extra protrusions. During maintenance, it can be replaced as a whole with the grille panel 23 without the need to separately replace the microporous pressure balance membrane and anti-icing heating ring, further improving the efficiency of line maintenance.

[0078] In some embodiments, the heat dissipation component 2 and the mounting interface 12 can be connected by screws, which facilitates connection and disassembly. A locking mechanism can also be provided between the heat dissipation component 2 and the mounting interface 12 to enable tool-free quick connection and separation. The locking mechanism includes a locking tongue and a locking groove. The locking tongue is elastically hinged to the outer periphery of the bracket 22 and has a handle. The locking groove is correspondingly formed on the side wall of the mounting interface 12.

[0079] During assembly, when the heat dissipation component 2 is pressed into the mounting interface 12, the front end of the locking tongue first contacts the entrance edge of the lock groove. Under the action of the thrust, the locking tongue overcomes the preload of the elastic hinge and rotates inward, causing its front end to slide into the lock groove. When the front end of the locking tongue is fully inserted into the lock socket, the elastic hinge is released, and the locking tongue rotates outward under the action of the rebound force, with its front end locking into the lock groove, achieving automatic locking. At this time, a mechanical limit is formed between the locking tongue and the lock groove, restricting the reverse movement of the heat dissipation component 2 along the insertion direction and ensuring that the position of the heat dissipation component 2 on the housing 11 is fixed and reliable.

[0080] During disassembly, pull up the handle of the latch, and the latch will rotate inward around the hinge axis. Its front end will disengage from the lock groove and release the limit. At this time, the heat dissipation component 2 can be pulled out smoothly.

[0081] Because the locking tongue achieves automatic reset and locking through an elastic hinge structure, the entire connection process requires no tools, making it simple and quick to operate, and suitable for use in line maintenance environments. The locking tongue and locking groove have a compact fit structure, integrated into the joint area of ​​the heat dissipation component 2 and the mounting interface 12, without occupying additional internal space of the cavity 16 or affecting the ventilation area, thus balancing connection reliability and structural simplicity.

[0082] In a preferred embodiment, the latch is fixed to the outer periphery of the bracket 22 by an elastic hinge. Specifically, the hinge axis of the latch is perpendicular to the insertion direction of the bracket 22, allowing the latch to rotate in a plane perpendicular to the insertion direction. A torsion spring is fitted on the hinge axis, with its two ends pressing against the spring post of the bracket 22 and the boss on the back of the latch, respectively, continuously providing an outward locking torque. This torque is limited by the spring post extending from the outer periphery of the bracket 22 and the boss on the back of the latch, ensuring that the front end of the latch automatically adheres to the bottom of the latch groove after insertion and maintains a constant preload throughout the locking cycle, thereby maintaining a reliable locking tendency even under aircraft vibration or impact conditions. The cantilever end of the latch extends outward and passes through a reserved notch in the grille panel 23, forming a handle on the outer side of the grille panel 23. The surface of the handle may be provided with anti-slip texture for easy gripping and lifting. A locking groove is correspondingly formed on the side wall of the mounting interface 12. Its entrance is preferably flared, guiding the front end of the locking tongue during insertion and allowing it to automatically center and slide in. The interior of the locking groove has a recess that matches the contour of the front end of the locking tongue. The bottom surface of the recess is preferably designed as a slope, forming a self-locking angle. Under the continuous torque of the torsion spring, the front end of the locking tongue slides down the slope and fully engages in the recess, achieving reliable locking. This sloped fit structure effectively prevents the locking tongue from rotating in the opposite direction under aircraft vibration or impact conditions, thereby avoiding accidental disengagement and ensuring a stable locking state.

[0083] During assembly, align the cooling fan 21 and bracket 22 with the mounting interface 12 and push them inward. The front end of the locking tongue first contacts the flared guide surface at the entrance of the lock groove. The pushing force overcomes the torque of the torsion spring, causing the locking tongue to rotate inward. When the front end of the locking tongue passes the highest point of the guide surface, the torsion spring is released, and the locking tongue quickly rebounds and locks into the socket of the lock groove, completing the automatic locking. During disassembly, pull the handle upward, and the locking tongue rotates inward around the hinge axis. The front teeth disengage from the socket of the lock groove, allowing the cooling component 2 to be pulled outward. The locking tongue is in a compressed state during the pulling process to avoid secondary jamming with the edge of the lock groove.

[0084] In some embodiments, the back of the locking tongue is provided with an anti-loosening pawl, which is coaxially hinged to the locking tongue. The front end of the anti-loosening pawl is provided with teeth, and the bottom of the locking groove is provided with ratchet teeth. In the locked state, the teeth engage with the ratchet teeth.

[0085] An anti-loosening pawl is added to the back of the latch. This anti-loosening pawl shares the same hinge axis with the latch, forming a coaxial hinge relationship, eliminating the need for additional pins and resulting in a compact structure. The front end of the anti-loosening pawl has teeth facing the bottom of the lock groove. Correspondingly, a ratchet is provided at the bottom of the lock groove, with the tooth shape direction opposite to the latch's disengagement direction, forming a one-way anti-retraction slope. Preferably, the meshing surface of the teeth and the ratchet uses a combination of sloped and straight surfaces. The straight surface bears the locking load, while the sloped surface guides retraction, ensuring reliable locking and smooth unlocking. The anti-loosening pawl is located in a pre-set concave groove on the back of the latch. The sidewall of the concave groove provides lateral restraint for the pawl, allowing it to swing only within a set angle range, preventing excessive outward or inward retraction.

[0086] During the locking process, the front end of the latch slides into the inclined surface of the lock groove, and the teeth of the anti-loosening pawl retract inward under the push of the inclined surface, while the torsion spring generates additional deformation. When the front end of the latch falls completely into the receiving socket of the lock groove, the teeth of the anti-loosening pawl quickly pop out under its own elastic recovery action and engage with the ratchet at the bottom of the lock groove. At this time, the straight section of the ratchet prevents the teeth of the anti-loosening pawl from moving outward, thereby preventing the latch from having a tendency to rotate. Even if the latch is subjected to outward torque due to aircraft vibration or impact, the engagement surface can still form a mechanical stop to prevent the latch from accidentally disengaging.

[0087] During disassembly, pull up the handle of the latch, and the latch will rotate outward around the hinge axis. The limiting platform on the back of the latch will simultaneously push the tail of the anti-loosening pawl, forcing the teeth of the anti-loosening pawl to retract inward and disengage from the ratchet teeth. After the front end of the latch completely exits the socket of the lock groove, the anti-loosening pawl will reset under its own elasticity, and the entire lock will then be unlocked.

[0088] Through the above structure, the locking mechanism provides mechanical anti-loosening function while maintaining the convenience of one-handed operation, meeting the airworthiness requirements that it cannot be accidentally dislodged due to impact or vibration in airborne vibration environment, and further improving the safety and maintainability of online replacement of heat dissipation component 2.

[0089] In a preferred embodiment, the bracket 22 is provided with at least two guide positioning pins on its outer periphery, and the corresponding position of the mounting interface 12 is provided with a guide groove; when inserted, the guide positioning pin slides along the guide groove to guide the cooling fan 21 to be coaxially positioned with the air outlet 17.

[0090] It should be noted that the guide positioning pin is a cylindrical or elliptical cylindrical boss, integrally machined or welded to the bracket 22. The axis of the boss is parallel to the insertion direction of the bracket 22, and the front end is chamfered for automatic alignment during initial insertion. The guide groove is recessed into the inner wall of the mounting interface 12. The width of the guide groove is slightly larger than the diameter of the guide positioning pin, and its length extends through the entire insertion depth of the mounting interface 12, forming a straight slide. The entrance of the guide groove is flared to facilitate the smooth entry of the guide positioning pin; the bottom surface of the guide groove is a smooth plane to reduce sliding friction resistance and prevent scratches on the pin surface.

[0091] When inserting the heat dissipation component 2, first align the guide positioning pin with the guide slot, and then push it inward. During the sliding process, the guide positioning pin contacts the two walls of the guide slot, restricting the circumferential rotation and lateral displacement of the bracket 22, so that the impeller axis of the cooling fan 21 remains coaxial with the axis of the air outlet 17. Through the parallel constraint of at least two guide positioning pins, the degree of freedom of the bracket 22 in the circumferential direction is restricted, achieving a self-positioning effect.

[0092] This guiding structure not only ensures the coaxiality of the cooling fan 21 and the air outlet 17, avoiding airflow loss and increased noise caused by eccentricity, but also provides temporary support before the locking tongue is fully locked, preventing the heat dissipation component 2 from tilting due to its own weight or improper operation, which could lead to misalignment between the locking tongue and the locking groove. Since the guide positioning pin and the guide groove are both hidden inside the mounting interface 12, they do not occupy the flow channel area of ​​the cavity 16, nor do they increase the radial dimension of the heat dissipation component 2. The structure is compact and easy to maintain, further improving the efficiency of online replacement and the reliability of installation of the heat dissipation component 2.

[0093] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0094] The above description of the disclosed embodiments enables those skilled in the art to make or use the invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the general principles defined herein may be implemented in other embodiments without departing from the spirit or scope of the invention. Therefore, the invention is not to be limited to the embodiments shown herein, but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. An antenna device, characterized in that, include: Antenna assembly (1) is installed on the fuselage of an aircraft. The antenna assembly (1) includes a housing (11) and an air duct (13) disposed within the housing (11). A cavity (16) is formed between the outer wall of the air duct (13) and the inner wall of the housing (11). An air vent is provided at the end of the air duct (13). The housing (11) is provided with a ventilation port that communicates with the air vent. An air outlet (17) is provided on the side wall of the air duct (13). The air outlet (17) communicates with the cavity (16). The housing (11) is also provided with an installation interface (12) that communicates with the cavity (16). The heat dissipation assembly (2) is detachably installed on the mounting interface (12). The heat dissipation assembly (2) includes a heat dissipation fan (21) for introducing airflow from the vent into the air duct (13) and then discharging it to the outside of the housing (11) through the air outlet (17) and the cavity (16).

2. The antenna device according to claim 1, characterized in that, The air duct (13) extends along the flight direction, and its two ends are sealed and fixed to the inner wall of the housing (11); the front end of the air duct (13) forms a front air vent (18), and the rear end forms a rear air vent (15); the housing (11) is provided with a front air vent (19) and a rear air vent (14), wherein the rear air vent (14) is directly opposite the rear air vent (15), and the front air vent (19) is arranged on the left and right sides of the front air vent (18).

3. The antenna device according to claim 2, characterized in that, Each of the air ducts (13) has an air outlet (17) on its left and right side walls, and both air outlets (17) are arranged close to the rear ventilation opening (14).

4. The antenna device according to claim 2, characterized in that, Also includes: Control valves are used to open and close the front vent (19) and the rear vent (14). The controller is electrically connected to the heat dissipation assembly (2) and is configured to: When the aircraft is in a parked state, the front vent (19) and / or the rear vent (14) are opened, and the heat dissipation assembly (2) is activated. When the aircraft is in flight, the front vent (19) and the rear vent (14) are opened, and the heat dissipation assembly (2) is closed.

5. The antenna device according to claim 4, characterized in that, The heat dissipation assembly (2) also includes: The grille panel (23) is equipped with an air outlet. The bracket (22) is fixed to the inner side of the grille panel (23). The bracket (22) is offset from the air outlet. The cooling fan (21) is installed on the bracket (22). During installation, the cooling fan (21) and the bracket (22) are inserted into the mounting interface (12) and extend into the cavity (16), and the grille panel (23) is attached to the outer wall of the housing (11).

6. The antenna device according to claim 5, characterized in that, The air duct (13) is equipped with a temperature detection unit for collecting the air duct temperature; The temperature detection unit is electrically connected to the controller, which is configured to: activate the heat dissipation component (2) when the temperature of the air duct exceeds a first threshold, and gradually increase its rotation speed as the temperature rises.

7. The antenna device according to claim 6, characterized in that, The heat dissipation component (2) includes multiple cooling fans (21), and the controller is configured to: whenever the air duct temperature rises by a set difference relative to the first threshold, turn on each cooling fan (21) one by one until all the cooling fans (21) are put into operation.

8. The antenna device according to claim 5, characterized in that, The inner side of the air outlet is covered with a microporous pressure balancing membrane, and the inner side of the lip of the air outlet is provided with an anti-icing heating ring.

9. The antenna device according to claim 5, characterized in that, A locking mechanism is provided between the heat dissipation component (2) and the mounting interface (12), the locking mechanism comprising: The locking tongue is elastically hinged to the outer periphery of the bracket (22), and the locking tongue is provided with a handle; A locking groove is provided on the side wall of the mounting interface (12); When the heat dissipation component (2) is pressed, the latch engages with the lock groove; when the handle is pulled, the latch disengages from the lock groove.

10. The antenna device according to claim 9, characterized in that, The locking tongue is provided with an anti-loosening pawl, which is coaxially hinged to the locking tongue. The front end of the anti-loosening pawl is provided with teeth, and the bottom of the locking groove is provided with ratchet teeth. In the locked state, the teeth engage with the ratchet teeth.

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