Airplane ground static conversion power supply structure

Abstract

The utility model provides a ground static transformation power supply structure of an airplane, which relates to the field of 200V / 400HZ intermediate frequency power supply equipment, is suitable for lifting a gallery bridge and the structural installation of a ground static transformation power supply of a vehicle-mounted airplane, and comprises a cabinet body, a cabinet door and a heat dissipation air duct, and the top of the cabinet body is provided with a lifting part; the hoisting part is used for hoisting the cabinet body on an object to be fixed; the side part of the cabinet body is provided with an open side, the top side of the cabinet door is hinged with the upper edge of the open side, and the cabinet door can rotate and be opened by taking the top side as an axis; the heat dissipation air channel is located in the cabinet body, a heat dissipation fan is arranged in the heat dissipation air channel, and an air inlet and an air outlet of the heat dissipation air channel are located in different side walls of the cabinet body; by adopting an upward opening structure, the cabinet door is prevented from influencing the operation of maintenance personnel, and the maintenance work in the cabinet body is facilitated; the air outlet and the air inlet of the heat dissipation air channel are both located in the side wall of the cabinet body, and a side air inlet and outlet mode is adopted, so that the cabinet body can be cooled by sufficient space after being hoisted and installed.

Description

Technical Field

[0001] This utility model relates to the field of power supply equipment technology, and in particular to a ground static power supply structure for aircraft. Background Technology

[0002] An aircraft ground static power supply is a precision power supply device that uses power electronics technology to achieve independent frequency and voltage regulation and conversion. Its core function is to convert the 380V 50HZ grid input into a clean, frequency- and voltage-adjustable 200V 400HZ AC power supply for the aircraft. It features high-frequency response, precise control, and high efficiency.

[0003] Existing technologies, including intermediate frequency power supplies for aircraft grounds, mostly employ a vertical structure with the cabinet placed on the ground. The aircraft ground static power supply comprises a cabinet and a door; the left side of the door is hinged to the cabinet body, allowing it to be opened. The aircraft ground static power supply requires heat dissipation, with air intake at the front and rear of the cabinet and exhaust at the top. Utility Model Content

[0004] The purpose of this utility model is to provide a ground static power supply structure for aircraft to solve the problems existing in the structure of ground static power supplies for aircraft in the prior art; the various technical effects of the preferred technical solution among the many technical solutions provided by this utility model are described in detail below.

[0005] To achieve the above objectives, the present invention provides the following technical solution:

[0006] The aircraft ground static power supply structure provided by this utility model includes a cabinet, a cabinet door, and a heat dissipation duct, wherein:

[0007] The top of the cabinet is provided with a hoisting part, which is used to hoist the cabinet onto the object to be fixed.

[0008] The cabinet body has an open side, and the top side of the cabinet door is hinged to the upper edge of the open side, so that the cabinet door can rotate and open with its top side as the axis.

[0009] The heat dissipation duct is located inside the cabinet, and a heat dissipation fan is installed inside the heat dissipation duct. The air inlet and air outlet of the heat dissipation duct are located on different side walls of the cabinet.

[0010] Preferably, the hoisting part includes hoisting holes, and the number of hoisting holes is one or more sets.

[0011] Preferably, the number of cabinet doors is one or two. When the number of cabinet doors is two, the two cabinet doors are located on opposite sides of the cabinet body.

[0012] Preferably, the aircraft ground static power supply structure further includes a drive device, which is inclined and has two ends rotatably connected to the cabinet body and the corresponding cabinet door, respectively. When the drive device extends or retracts, it can drive the cabinet door to open or close.

[0013] Preferably, the air inlet and the air outlet are located on opposite sides of the cabinet, and the heat dissipation duct is a straight-through duct.

[0014] Preferably, the air inlet, the air outlet, and the cabinet door are located on different side walls of the cabinet.

[0015] Preferably, waterproof louvers are provided at the air inlet and the air outlet.

[0016] Preferably, the heat-generating components of the aircraft ground static power supply are located in the middle of the heat dissipation duct.

[0017] Preferably, the rectifier, inverter, and control components inside the cabinet are located near one of the cabinet doors; the switches, contactors, relays, and capacitors inside the cabinet are located near the other cabinet door.

[0018] Preferably, the cabinet door is equipped with a door lock.

[0019] The aircraft ground static power supply structure provided by this utility model has the following advantages compared with the prior art: the hoisting part is located at the top of the cabinet, which makes it easy to hoist the cabinet onto the ceiling or other fixed objects. The cabinet door initially rotates on the top side, adopting an upward opening structure to prevent the cabinet door from affecting the operation of maintenance personnel and to facilitate maintenance work inside the cabinet. The air outlet and air inlet of the heat dissipation duct are both located on the side wall of the cabinet, adopting a side air inlet and outlet method, eliminating the need for an upward air outlet method, so that the cabinet can still have sufficient space for heat dissipation after hoisting and installation. Attached Figure Description

[0020] To more clearly illustrate the technical solutions in the embodiments of this utility model 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 some embodiments of this utility model. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0021] Figure 1 This is a schematic diagram of the overall structure of the aircraft ground static power supply.

[0022] Figure 2 This is a schematic diagram of the overall structure when the cabinet door is open;

[0023] Figure 3This is a side view of the cabinet door when it is open;

[0024] Figure 4 This is a schematic diagram of the heat dissipation air duct of the aircraft ground static power supply structure.

[0025] Figure 5 This is a schematic diagram of the component arrangement structure inside the cabinet.

[0026] In the diagram: 1. Cabinet body; 11. Open side; 2. Cabinet door; 3. Heat dissipation duct; 31. Air inlet; 4. Waterproof louvers; 5. Drive unit; 6. Heat dissipation fan; 7. Lifting hole; 8. Radiator; 9. Transformer; 10. Door lock. Detailed Implementation

[0027] To make the objectives, technical solutions, and advantages of this utility model clearer, the technical solutions of this utility model will be described in detail below. Obviously, the described embodiments are only a part of the embodiments of this utility model, and not all of them. Based on the embodiments of this utility model, all other implementation methods obtained by those skilled in the art without creative effort are within the scope of protection of this utility model.

[0028] In the description of this utility model, it should be understood that the terms "center," "length," "width," "height," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and "side," etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the accompanying drawings and are only for the convenience of describing this utility model and simplifying the description, and do not indicate or imply that the device or component referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this utility model. In the description of this utility model, unless otherwise stated, "a plurality of" means two or more.

[0029] In the description of this utility model, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0030] This utility model embodiment provides an aircraft ground static power supply structure, which adopts a top-opening door structure to prevent the cabinet door 2 from affecting the operation of maintenance personnel, and adopts a side air intake and exhaust method to ensure that the cabinet 1 can dissipate heat with sufficient space after hoisting and installation.

[0031] The following is combined Figures 1-5 The technical solution provided by this utility model will be described in more detail.

[0032] like Figures 1-5 As shown, the aircraft ground static power supply structure provided by this utility model includes a cabinet 1, a cabinet door 2, and a heat dissipation duct 3. The top of the cabinet 1 is provided with a hoisting part for hoisting the cabinet 1 onto the object to be fixed. The side of the cabinet 1 is provided with an open side 11. The top side of the cabinet door 2 is hinged to the upper edge of the open side 11, and the cabinet door 2 can rotate and open with its top side as the axis. The heat dissipation duct 3 is located inside the cabinet 1, and a heat dissipation fan 6 is provided inside the heat dissipation duct 3. The air inlet 31 and the air outlet of the heat dissipation duct 3 are located on different side walls of the cabinet 1.

[0033] The hoisting section refers to the structure at the top of the cabinet 1 used to connect external hoisting equipment. Specifically, it can be achieved using hoisting holes 7, such as one or two sets of symmetrically distributed round holes, which are fixed to the hoisting equipment by bolts.

[0034] The top-side hinge of cabinet door 2 refers to the connection between the upper edge of the door and cabinet body 1 via a pivot, such as a hinge or hinge mechanism, which allows the door to flip upwards when opened. The heat dissipation duct 3 refers to the air circulation channel that runs through the interior of cabinet body 1. Specifically, it can be a straight-through air duct surrounded by a metal plate. The air inlet 31 and the air outlet can be located on the left and right sides of cabinet body 1, forming a non-top heat dissipation path.

[0035] Specifically, after cabinet 1 is fixed by the top mounting bracket, cabinet door 2 opens upwards to avoid occupying lateral space, allowing maintenance personnel to operate directly in front of cabinet 1. Cooling fan 6 drives airflow into the duct through air inlet 31, flows past heat-generating components, and exits through air outlet. Because air inlet 31 and air outlet are located on different side walls, airflow can circulate without relying on top space, ensuring that cooling efficiency is not affected after mounting. For example, air inlet 31 can be located at the bottom of the front side wall, and air outlet at the top of the rear side wall, forming forced convection in conjunction with a straight-through duct.

[0036] In this embodiment of the aircraft ground static power supply structure, the hoisting part is located at the top of the cabinet 1, which facilitates the hoisting of the cabinet 1 onto the ceiling or other fixed objects. The cabinet door 2 initially has its top side as the rotating side, adopting an upward opening structure to prevent the cabinet door 2 from affecting the operation of maintenance personnel and to facilitate maintenance work inside the cabinet 1. The air outlet and air inlet 31 of the heat dissipation duct 3 are both located on the side wall of the cabinet 1, adopting a side air intake and exhaust method, eliminating the need for an upward exhaust method, so that the cabinet 1 can still have sufficient space for heat dissipation after hoisting and installation.

[0037] In this embodiment, the aircraft ground static power supply can be reliably installed in a hoisted state. The optimized opening direction of the cabinet door 2 reduces the maintenance space requirement, and the side heat dissipation duct 3 design avoids the decrease in heat dissipation efficiency caused by the enclosed top space, thus balancing installation flexibility and equipment operation stability.

[0038] As an optional implementation, see Figure 2 and Figure 3 As shown, the number of cabinet doors 2 is one or two. When there are two cabinet doors 2, the two cabinet doors 2 are located on opposite sides of the cabinet body 1.

[0039] When using double cabinet doors 2, the two doors are installed on the symmetrical side walls of cabinet 1, forming mirror images of each other in opening direction. During hoisting operations, operators can choose to open either cabinet door 2 according to the site space conditions, avoiding interference between the equipment and surrounding obstacles caused by the limited opening angle of a single door.

[0040] As an optional implementation, see Figure 2 and Figure 3 As shown, the aircraft ground static power supply structure also includes a drive device 5. The drive device 5 is tilted and its two ends are rotatably connected to the cabinet body 1 and the corresponding cabinet door 2, respectively. When the drive device 5 extends or retracts, it can drive the cabinet door 2 to open or close.

[0041] The tilted configuration of the drive unit 5 refers to the angle between its axis and the horizontal plane. This can be achieved using a hydraulic cylinder, electric push rod, or pneumatic telescopic rod, with the tilt angle ranging from 30° to 60°. This tilted arrangement prevents spatial interference between the drive unit 5 and the internal components of the cabinet 1. The rotatable connection refers to the movable connection between the two ends of the drive unit 5 and the cabinet 1 and cabinet door 2 via hinges or ball joints. This can be achieved using a pin-bearing structure, allowing the drive unit 5 to maintain rotational freedom during extension and retraction. This connection method ensures stable rotation of the cabinet door 2 around its top hinge axis.

[0042] Specifically, when the drive device 5 extends or retracts, the component force generated by its tilted arrangement is converted into a rotational torque on the cabinet door 2. As the length of the drive device 5 changes, the cabinet door 2 rotates around the top hinge axis to open or close. The tilt angle of the drive device 5 matches the extension / retraction trajectory with the rotation path of the cabinet door 2, avoiding dead spots. During the opening process, the cabinet door 2 only moves along a fixed rotational trajectory and does not need to translate outwards, thus reducing the space occupied by the surrounding area.

[0043] The drive unit 5 replaces manual operation to realize the automatic opening and closing of the cabinet door 2, which solves the problem of insufficient maintenance space during hoisting and installation, thus reducing the safety hazards caused by accidental swinging of the door.

[0044] As an optional implementation, see Figure 4 As shown, the air inlet 31 and the air outlet are located on opposite sides of the cabinet 1, and the heat dissipation duct 3 is a straight-through duct.

[0045] When the cooling fan 6 is running, outside air enters the straight-through air duct from the air inlet 31 on one side, flows along a straight path through the heat-generating component area inside the cabinet 1, and is then discharged from the air outlet on the opposite side. The straight structure of the straight-through air duct avoids the energy loss caused by frequent changes in airflow direction in traditional curved air ducts, allowing the cooling airflow to circulate with lower air pressure loss. Thus, effective heat dissipation can be achieved without relying on the top air outlet space when the unit is suspended.

[0046] As an optional implementation, see Figure 4 As shown, the air inlet 31, air outlet, and cabinet door 2 are located on different side walls of the cabinet 1. The air outlet is obstructed in the figure, and the arrows in the figure indicate the direction of airflow.

[0047] In the suspended state, there is no need to reserve heat dissipation space at the top of the cabinet 1. The heat dissipation duct 3 maintains complete airflow circulation due to the separation of the inlet and outlet sidewalls. At the same time, the opening direction of the cabinet door 2 and the heat dissipation path do not interfere with each other in three-dimensional space.

[0048] As an optional implementation, see Figure 1 Waterproof louvers are installed at the air inlet 31 and the air outlet 4.

[0049] Waterproof louvers (4) refer to a ventilation structure formed by multiple parallel, inclined blades, which can be made of aluminum alloy or engineering plastics. The gaps between the blades create airflow channels. This structure allows airflow while preventing vertically falling liquid from entering the air duct through the angle of the blades.

[0050] As an optional implementation, see Figure 4 The heat-generating components of the aircraft ground static power supply are located in the middle of the heat dissipation duct 3. These components include the heat sink 8 and the transformer 9.

[0051] Since the heat-generating components are located in the middle of the air duct, the airflow velocity is relatively uniform when it flows through this area, which can avoid local heat accumulation. At the same time, the layout of the air inlets and outlets on both sides ensures that the top space is closed when the device is suspended, which will not obstruct the airflow path and ensure that the heat dissipation efficiency is not affected by the installation method.

[0052] As an optional implementation, see Figure 5 The rectifier, inverter, and control components inside cabinet 1 are located near one of the cabinet doors 2; the switches, contactors, relays, and capacitors inside cabinet 1 are located near the other cabinet door 2.

[0053] Specifically, cabinet 1 is divided into four areas: A, B, C, and D. Figure 5 As shown, rectifier components, inverter components, and control components are arranged in area A; incoming and outgoing wiring is arranged in area B; transformer 9 is arranged in area C; and switches, contactors, switching power supplies, relays, supercapacitors, displays, indicator lights, emergency stop devices, and other components are arranged in area D.

[0054] Among them, rectifier components refer to power devices used to convert alternating current (AC) to direct current (DC), specifically implemented using thyristors or diode bridge circuits, and are responsible for input-side power conversion in aircraft ground static power supplies. Inverter components refer to power modules that convert DC to AC, specifically implemented using IGBTs or MOSFET devices, and are responsible for output-side frequency regulation. Control components refer to circuit units used for signal processing and logic control, specifically implemented using PLCs or microprocessor modules, and are responsible for system parameter monitoring and adjustment. Switches refer to mechanical or electronic devices used for circuit switching, specifically implemented using air switches or solid-state relays, and are responsible for main circuit current control. Contactors refer to electromagnetic devices used for high-current switching, specifically implemented using AC contactors, and are responsible for load switching. Relays refer to electromagnetic switches used for low-current signal control, specifically implemented using intermediate relays, and are responsible for transmitting control circuit commands. Capacitors refer to passive components used for energy storage and filtering, specifically implemented using electrolytic capacitors or film capacitors, and are responsible for DC bus voltage stabilization. All of the above components are existing technologies and will not be elaborated further here.

[0055] Specifically, rectifier components, inverter components, and control components are concentrated in an area near one cabinet door 2. This area corresponds to the core control and energy conversion module of the system, which requires less frequent maintenance but precise debugging. Switches, contactors, relays, and capacitors are concentrated in an area near another cabinet door 2. This area corresponds to the power on / off and energy storage module, which requires frequent inspection or replacement. In hoisting scenarios, maintenance personnel can directly access the target module by opening the corresponding cabinet door 2, avoiding operational space conflicts caused by the dispersed arrangement of multiple functional components. Through functional zoning, opening a single cabinet door 2 only exposes a specific operating interface, reducing the space occupied around cabinet 1 during maintenance and avoiding the risk of accidental contact with unrelated components.

[0056] As an optional implementation, a door lock 10 is provided on the cabinet door 2 to facilitate locking the cabinet door 2 with the cabinet body 1 and prevent the cabinet door 2 from being opened accidentally.

[0057] The specific features, structures, or characteristics described in this specification may be combined in any suitable manner in one or more embodiments or examples.

[0058] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0059] The above description is merely a specific embodiment of this utility model, but the protection scope of this utility model is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this utility model should be included within the protection scope of this utility model. Therefore, the protection scope of this utility model should be determined by the protection scope of the claims.

Claims

1. An aircraft ground static power supply structure, characterized in that, This includes the cabinet body, cabinet doors, and ventilation ducts, among which: The top of the cabinet is provided with a hoisting part, which is used to hoist the cabinet onto the object to be fixed. The cabinet body has an open side, and the top side of the cabinet door is hinged to the upper edge of the open side, so that the cabinet door can rotate and open with its top side as the axis. The heat dissipation duct is located inside the cabinet, and a heat dissipation fan is installed inside the heat dissipation duct. The air inlet and air outlet of the heat dissipation duct are located on different side walls of the cabinet.

2. The aircraft ground static power supply structure according to claim 1, characterized in that, The hoisting part includes hoisting holes, and the number of hoisting holes is one or more sets.

3. The aircraft ground static power supply structure according to claim 1, characterized in that, The cabinet doors are one or two. When there are two cabinet doors, the two cabinet doors are located on opposite sides of the cabinet body.

4. The aircraft ground static power supply structure according to claim 1, characterized in that, The aircraft ground static power supply structure also includes a drive device. The drive device is inclined and its two ends are respectively rotatably connected to the cabinet and the corresponding cabinet door. When the drive device extends or retracts, it can drive the cabinet door to open or close.

5. The aircraft ground static power supply structure according to claim 1, characterized in that, The air inlet and the air outlet are located on opposite sides of the cabinet, and the heat dissipation duct is a straight-through duct.

6. The aircraft ground static power supply structure according to claim 5, characterized in that, The air inlet, the air outlet, and the cabinet door are located on different side walls of the cabinet.

7. The aircraft ground static power supply structure according to claim 1, characterized in that, Waterproof louvers are provided at the air inlet and the air outlet.

8. The aircraft ground static power supply structure according to claim 1, characterized in that, The heat-generating components of the aircraft ground static variable power supply are located in the middle of the heat dissipation duct.

9. The aircraft ground static power supply structure according to claim 1, characterized in that, The rectifier, inverter, and control components inside the cabinet are located near one of the cabinet doors; the switches, contactors, relays, and capacitors inside the cabinet are located near the other cabinet door.

10. The aircraft ground static power supply structure according to claim 1, characterized in that, The cabinet door is equipped with a lock.

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