Aircraft de-icing device

Abstract

The application provides an aircraft deicing device, which comprises a movable base, a traction frame, a first end of the traction frame being connected with the base in the moving direction of the base, a traction connecting position being arranged at a second end of the traction frame, the traction frame being connected with an external traction device through the traction connecting position, a climbing frame being movably arranged on the base along a first direction, the first direction being perpendicular to the moving direction of the base, and a liquid spraying assembly being arranged at the top end of the climbing frame, the liquid spraying assembly being arranged to be capable of spraying deicing liquid on an aircraft to be deiced. The aircraft deicing device is driven by the external traction device, which can reduce the manufacturing cost, save the arrangement space of the power component on the base, reduce the overall volume of the deicing device, and be flexible to move in a narrow area, so as to adapt to different deicing scene requirements.

Description

Technical Field

[0001] This application belongs to the field of aircraft de-icing technology, specifically relating to an aircraft de-icing device. Background Technology

[0002] When aircraft encounter cold weather conditions such as low temperatures, high humidity, rain, or snow, a layer of frost, snow, or ice will form on their surfaces. This ice and snow condensing on the wings roughens the wing surface, reducing the critical angle of attack and decreasing wing lift. This imbalance in lift between the two wings increases drag, which worsens the aircraft's aerodynamic performance at already low takeoff speeds, leading to premature stalls. This increases the difficulty of pilot control, affecting the aircraft's safety and maneuverability, and can even cause flight accidents.

[0003] In related technologies, there is already mature equipment for aircraft liquid spraying de-icing, namely, truck-transported liquid storage tanks, with operators carried by a robotic arm basket installed on the truck. The operators control the spray gun at the front end of the basket to carry out de-icing. However, this de-icing method has some drawbacks. Because the truck has a built-in power unit and is relatively large, it cannot pass through narrow spaces, causing inconvenience to the de-icing work. Utility Model Content

[0004] The purpose of this application is to at least solve the problem that existing aircraft de-icing equipment has a built-in power unit, resulting in a large equipment size, limited mobility, and inconvenience for de-icing operations. This objective is achieved through the following technical solution: The first aspect of this application discloses an aircraft de-icing device, comprising: Movable base; In the direction of movement of the base, the first end of the traction frame is connected to the base, and the second end of the traction frame is provided with a traction connection position, through which the traction frame is connected to an external traction device; A climbing frame, wherein the climbing frame is movably disposed on the base along a first direction, the first direction being perpendicular to the direction of movement of the base; A spraying assembly is located at the top of the climbing frame and is configured to spray de-icing fluid onto the aircraft to be de-iced.

[0005] According to the aircraft de-icing device of this application, when de-icing operations are required, the operator climbs onto the climbing frame and operates the spraying assembly to spray de-icing fluid onto the aircraft to be de-iced. By controlling the climbing frame to move up and down in a first direction, it is convenient to spray de-icing fluid onto the top and bottom of the aircraft. An external towing device can provide power to the aircraft de-icing device, enabling the de-icing device to move flexibly and achieve all-round de-icing. By flexibly adjusting the movement trajectory, the de-icing device can cover hard-to-clean areas such as the curved surfaces of the fuselage and the leading edges of the wings, and can also adapt to the size requirements of different aircraft types such as narrow-body and wide-body passenger aircraft, without the need for frequent replacement of dedicated de-icing equipment. Compared with traditional de-icing equipment, the aircraft de-icing device provided by this application can select towing vehicles with different powers according to de-icing needs. When it is necessary to pass through narrow spaces, a light towing vehicle can be selected. Since the aircraft de-icing device is driven by an external towing device, on the one hand, it can reduce manufacturing costs, and on the other hand, it can save the space for the power components on the base, reduce the overall size of the de-icing device, and make it easier to move flexibly in narrow areas such as airport aprons and under jet bridges.

[0006] In addition, the aircraft de-icing device according to this application may also have the following additional technical features: In some embodiments of this application, the climbing frame has a first extreme position and a second extreme position in the first direction, with the first extreme position located below the second extreme position; when the climbing frame moves to the first extreme position, in the first direction, the distance between the top of the spraying assembly and the ground is less than the height of the walkway.

[0007] In some embodiments of this application, the width of the traction frame in the second direction is smaller than the width of the base in the second direction, and the movement direction of the first direction and the base is perpendicular to the second direction.

[0008] In some embodiments of this application, the spraying assembly includes a spray gun that is movably and / or rotatably mounted on top of the climbing frame.

[0009] In some embodiments of this application, the spraying assembly includes a first support member and a first rotating shaft. The first support member is fixedly mounted on the climbing frame, and the first rotating shaft is rotatably mounted on the first support member. The axial direction of the first rotating shaft is arranged along the first direction. The first rotating shaft is connected to the spray gun so that the spray gun can rotate around the axial direction of the first rotating shaft under the action of external force.

[0010] In some embodiments of this application, the spraying assembly further includes a connecting seat, a second rotating shaft, and a turntable. The connecting seat is fixedly connected to the top end of the first rotating shaft, and the axial direction of the second rotating shaft is arranged along the moving direction of the base. A first end of the second rotating shaft along its axial direction is fixedly connected to the connecting seat, and a second end of the second rotating shaft is rotatably connected to the turntable. The turntable is connected to the spray gun so that the spray gun can rotate around the axial direction of the second rotating shaft under the action of an external force.

[0011] In some embodiments of this application, the spraying assembly further includes a buckle fixedly connected to the turntable, the buckle having an opening through which the spray gun movably passes, and a fastener provided at the opening for limiting the displacement of the spray gun in the first direction.

[0012] In some embodiments of this application, the climbing frame is provided with a storage component for storing the spray gun.

[0013] In some embodiments of this application, the aircraft de-icing device further includes a lifting mechanism disposed on the base and drivenly connected to the climbing frame to drive the climbing frame to reciprocate along the first direction.

[0014] In some embodiments of this application, the base is provided with at least one brake frame, and each end of the brake frame is provided with a telescopic rod, and the end of the telescopic rod is provided with a support leg. Attached Figure Description

[0015] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the scope of this application. Furthermore, the same reference numerals denote the same parts throughout the drawings. In the drawings: Figure 1 This is a front view of the aircraft de-icing device according to an embodiment of this application; Figure 2 This is a top view of the aircraft de-icing device according to an embodiment of this application; Figure 3 This is a left view of the aircraft de-icing device according to an embodiment of this application; Figure 4 This is a schematic diagram illustrating the usage state of the aircraft de-icing device according to an embodiment of this application. Figure 1 ; Figure 5 for Figure 1 Enlarged structural diagram of section A in the middle; Figure 6 For along Figure 5 A cross-sectional view along the CC direction; Figure 7 for Figure 2 Enlarged structural diagram of section B in the middle; Figure 8 This is a schematic diagram illustrating the usage state of the aircraft de-icing device according to an embodiment of this application. Figure 2 The spray gun is in a retracted state.

[0016] The attached figures are labeled as follows: 10. Base; 20. Traction frame; 21. Traction connection position; 30. Climbing frame; 31. Storage unit; 40. Spraying assembly; 41. Spray gun; 42. First support member; 421. First support plate; 422. Second support plate; 43. First rotating shaft; 44. Connecting seat; 441. Connecting plate; 442. U-shaped clamp; 45. Second rotating shaft; 46. Turntable; 47. Buckle; 471. Opening; 472. Fastener; 48. Second support member; 481. Support rod; 50. Lifting mechanism; 60. Brake bracket; 61. Telescopic rod; 62. Outrigger; 70. Storage tank; 71. Electric heating wire; 72. Liquid level indicator; 80. Booster pump; 90. Generator. Detailed Implementation

[0017] Exemplary embodiments of the present disclosure will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.

[0018] It should be understood that the terminology used herein is for the purpose of describing particular exemplary embodiments only and is not intended to be limiting. Unless the context clearly indicates otherwise, the singular forms “a,” “an,” and “described” as used herein may also include the plural forms. The terms “comprising,” “including,” “containing,” and “having” are inclusive and therefore indicate the presence of the stated features, steps, operations, elements, and / or components, but do not exclude the presence or addition of one or more other features, steps, operations, elements, components, and / or combinations thereof. The method steps, processes, and operations described herein are not construed as requiring them to be performed in a particular order described or illustrated unless the order of performance is explicitly indicated. It should also be understood that additional or alternative steps may be used.

[0019] Although terms such as first, second, third, etc., may be used in this document to describe multiple elements, components, regions, layers, and / or segments, these elements, components, regions, layers, and / or segments should not be limited by these terms. These terms may be used only to distinguish one element, component, region, layer, or segment from another. Unless the context clearly indicates otherwise, terms such as "first," "second," and other numerical terms used herein do not imply order or sequence. Therefore, the first element, component, region, layer, or segment discussed below may be referred to as the second element, component, region, layer, or segment without departing from the teachings of the exemplary embodiments.

[0020] For ease of description, spatial relative terms may be used in the text to describe the relationship of one element or feature relative to another element or feature, as shown in the figure. These relative terms include, for example, "inside," "outside," "middle," "outer," "below," "below," "above," "over," etc. Such spatial relative terms are intended to include different orientations of the device in use or operation, other than those depicted in the figure. For example, if the device in the figure is flipped, an element described as "below other elements or features" or "below other elements or features" would subsequently be oriented as "above other elements or features" or "above other elements or features." Therefore, the example term "below" can include both upper and lower orientations. The device may be otherwise oriented (rotated 90 degrees or in other directions), and the spatial relative descriptors used in the text will be interpreted accordingly.

[0021] In related technologies, aircraft liquid de-icing equipment is already mature. This involves transporting the liquid storage tank by truck, and then using a robotic arm-mounted basket to carry the operator. The operator controls a spray gun at the front of the basket to perform de-icing. However, this de-icing equipment has some drawbacks. Firstly, because the truck has a built-in power unit and a high chassis, coupled with the robotic arm, the overall width and height of the equipment are increased. This makes it difficult for the truck with the robotic arm to pass through narrow spaces such as jet bridges, causing inconvenience for de-icing operations. Secondly, this traditional de-icing equipment is expensive, resulting in high operating costs.

[0022] In this application, unless otherwise specified, the direction of movement of the base is the X direction shown in the figure, the first direction is the Z direction shown in the figure, and the second direction is the Y direction shown in the figure.

[0023] like Figure 1 and Figure 2As shown, according to an embodiment of this application, an aircraft de-icing device is proposed, including a towing frame 20, a climbing frame 30, a liquid spraying assembly 40, and a movable base 10. The base 10 can be configured as a flat plate component, and rollers are provided at the bottom of the base 10 to reduce the frictional resistance of the base 10 movement and facilitate the external towing device to drive the base 10.

[0024] Reference Figure 2 In the direction of movement of the base 10, the first end of the traction frame 20 is connected to the base 10, and the second end of the traction frame 20 is provided with a traction connection position 21. The traction frame 20 is connected to an external traction device (e.g., a tractor) through the traction connection position 21. Specifically, the traction connection position 21 is a pin hole provided at the second end of the traction frame 20, and a pin is provided on the pin hole.

[0025] An external towing device provides power to the aircraft de-icing unit, enabling it to move flexibly and perform all-around de-icing, thus covering various aircraft types such as narrow-body and wide-body passenger aircraft. Different power towing vehicles can be selected according to de-icing needs; a lightweight towing vehicle can be chosen when navigating narrow spaces. Since the aircraft de-icing unit is driven by an external towing device, manufacturing costs are reduced, and space for power components on the base 10 is saved, resulting in a smaller overall size of the de-icing unit and easier movement in narrow areas such as airport aprons and under jet bridges. The towing frame 20 is designed as a frame structure, achieving a lightweight design for the entire aircraft de-icing unit and saving energy consumption of the external towing device.

[0026] Reference Figure 1 The climbing frame 30 is movably mounted on the base 10 along a first direction, which is perpendicular to the direction of movement of the base 10. (See reference...) Figure 3 The spraying assembly 40 is mounted at the top of the platform 30 and is configured to spray de-icing fluid onto the aircraft to be de-iced. The first direction is the height direction of the base 10, i.e., the Z-direction shown in the figure, and can be parallel to the vertical direction. The platform 30 supports the operator so that the operator can control the spraying assembly 40 to spray de-icing fluid onto the aircraft to be de-iced. The platform 30 can reciprocate along the first direction, expanding the operator's de-icing operation range and facilitating the spraying of de-icing fluid onto the top and bottom of the aircraft.

[0027] Understandably, when de-icing is required, the operator climbs onto the access platform 30 and operates the spraying assembly 40 to spray de-icing fluid onto the aircraft. By controlling the access platform 30 to move up and down in the first direction, it is convenient to spray de-icing fluid onto the top and bottom of the aircraft. An external towing device can provide power to the aircraft de-icing device, enabling it to move flexibly and achieve all-around de-icing. By flexibly adjusting the movement trajectory, the de-icing device can cover hard-to-clean areas such as the curved surfaces of the fuselage and the leading edges of the wings, and can also adapt to the size requirements of different aircraft types such as narrow-body and wide-body passenger aircraft, without the need for frequent replacement of dedicated de-icing equipment. Compared with traditional de-icing equipment, the aircraft de-icing device provided in this application can select towing vehicles with different powers according to de-icing needs. When it is necessary to pass through narrow spaces, a light towing vehicle can be selected. Since the aircraft de-icing device is driven by an external towing device, on the one hand, manufacturing costs can be reduced, and on the other hand, the space for power components on the base 10 can be saved, reducing the overall size of the de-icing device and making it easier to move flexibly in narrow areas such as airport aprons and under jet bridges.

[0028] In some application scenarios, the boarding bridges for some small and medium-sized aircraft are relatively low (some boarding bridges are only 2.3 meters above the ground). Therefore, it is necessary to ensure that the aircraft de-icing device can pass through narrow spaces smoothly. The specific design is described below.

[0029] In this embodiment, refer to Figure 4 The aerial work platform 30 has a first extreme position and a second extreme position in the first direction, with the first extreme position located below the second extreme position. When the aerial work platform 30 moves to the first extreme position, the distance between the top of the spray assembly 40 and the ground in the first direction is less than the height of the jet bridge. The aerial work platform 30 can move up and down along the first direction, with the first extreme position being the lowest position and the second extreme position being the highest position. It is understood that when the aerial work platform 30 moves to its lowest position, the vertical distance H1 between the top of the spray assembly 40 and the ground in the first direction is less than the height H2 of the jet bridge. This design ensures that the aircraft de-icing device can smoothly pass through narrow spaces, facilitating de-icing of all parts of the aircraft and avoiding cleaning dead zones.

[0030] The aircraft de-icing device also includes a lifting mechanism 50, which is mounted on the base 10 and is connected to the access frame 30 to drive the access frame 30 to move in a first direction. The lifting mechanism 50 can control the reciprocating movement of the access frame 30 between a first and a second extreme position. The lifting mechanism 50 can be an existing scissor lift or a robotic arm. Generally, for the same load capacity, the price of a scissor lift is lower than that of a robotic arm, and its installation, commissioning costs, and energy consumption are also lower, thus further reducing manufacturing and operating costs. In this embodiment, the lifting mechanism 50 is a scissor lift, with its top fixedly connected to the access frame 30, suitable for small and medium-sized airports or temporary de-icing needs.

[0031] In practical applications, airport de-icing operations are often concentrated during peak flight hours, and the distance between parking stands is generally close (the lateral distance between parking stands at some hub airports is only 5-8 meters), and ground support vehicles, boarding stairs, baggage conveyors and other equipment are often distributed around them.

[0032] In this embodiment, looking back Figure 2 The width L1 of the tow frame 20 in the second direction is less than the width L2 of the base 10 in the second direction. The movement direction of the first direction and the base 10 is perpendicular to the second direction. The second direction can be a horizontal direction, i.e., the Y direction shown in the figure. If L1 < L2, then the arrangement space of the tow frame 20 in the width direction can be reduced, and collisions between the aircraft de-icing device and the environment of the aircraft to be de-iced can be reduced or avoided during movement, significantly reducing the risk of environmental collisions and making it easier for the aircraft de-icing device to pass through narrow spaces.

[0033] In some embodiments, such as Figures 5 to 7 As shown, the spraying assembly 40 includes a spray gun 41, which is movably and / or rotatably mounted on top of the ladder 30. The movable mounting of the spray gun 41 on top of the ladder 30 allows the operator to adjust the spray distance between the nozzle of the spray gun 41 and the aircraft to be de-iced, thereby adjusting the spray range according to de-icing requirements. The rotatable mounting of the spray gun 41 on top of the ladder 30 allows the operator to adjust the spray angle of the nozzle, thereby adjusting the spray range according to de-icing requirements.

[0034] It should be noted that the flow rate of the spray gun 41 can be controlled by the switch of the spray gun 41, thereby achieving the adjustment of the spray flow rate.

[0035] Combination Figure 1 , Figure 5 and Figure 6The spray assembly 40 includes a first support member 42 and a first rotating shaft 43. The first support member 42 is fixedly mounted on the top of the climbing frame 30, and the first rotating shaft 43 is rotatably mounted on the first support member 42. The first rotating shaft 43 is connected to the body of the spray gun 41 so that the spray gun 41 can rotate around the axial direction of the first rotating shaft 43 under the action of an external force. The axial direction of the first rotating shaft 43 is arranged along a first direction, that is, the axial direction of the first rotating shaft 43 is parallel to the Z direction. When the operator applies a first external force to the spray gun 41, the external force generates a first torque. The direction of the first torque is the R1 direction shown in the figure, which causes the spray gun 41 to rotate around the first rotating shaft 43 under the action of the first torque. That is, the spray gun 41 can swing left and right in the horizontal plane, thereby adjusting the angle of the spray gun 41 and thus adjusting the spray width of the de-icing fluid.

[0036] Specifically, the first support member 42 includes a first support plate 421 and a second support plate 422 spaced apart in a first direction, both of which are fixedly connected to the climbing frame 30. Each of the first support plate 421 and the second support plate 422 is provided with a bearing seat, and the first rotating shaft 43 is rotatably connected to the bearing in the bearing seat, thereby supporting the first rotating shaft 43.

[0037] Combination Figure 2 , Figure 6 and Figure 7 The spray assembly 40 also includes a connecting seat 44, a second rotating shaft 45, and a turntable 46. The connecting seat 44 is fixedly connected to the top end of the first rotating shaft 43. The axial direction of the second rotating shaft 45 is arranged along the moving direction of the base 10, that is, the axial direction of the second rotating shaft 45 is parallel to the X-direction. Along the moving direction of the base 10, the first end of the second rotating shaft 45 along its axial direction is fixedly connected to the connecting seat 44, and the second end of the second rotating shaft 45 is rotatably connected to the turntable 46. The turntable 46 is connected to the gun body of the spray gun 41, so that the spray gun 41 can rotate around the axial direction of the second rotating shaft 45 under the action of an external force. When the operator applies a second external force to the spray gun 41, the second external force forms a second torque. The direction of the second torque is the R2 direction shown in the figure, which causes the spray gun 41 to rotate around the second rotating shaft 45 under the action of the second torque. That is, the spray gun 41 can swing up and down in the vertical plane, thereby adjusting the angle of the spray gun 41 and thus adjusting the spray height of the de-icing fluid.

[0038] Specifically, the connecting seat 44 includes an integrally formed connecting plate 441 and a U-shaped clamp 442. The U-shaped clamp 442 is snapped onto the top of the first rotating shaft 43 and fixedly connected to the first rotating shaft 43 by bolts. The second rotating shaft 45 is fixedly connected to the connecting plate 441. A bearing seat is provided inside the turntable 46, and the second rotating shaft 45 is rotatably connected to the bearing in the bearing seat.

[0039] Reference Figure 7The spraying assembly 40 also includes a second support member 48, which is provided with a bearing seat. The middle part of the second rotating shaft 45 is rotatably connected to the second support member 48 through the bearing seat. The second support member 48 is a plate-shaped member, and the second support member 48 is connected to the connecting plate 441 of the connecting seat 44 through a support rod 481, thereby playing an auxiliary support role. Multiple support rods 481 can be provided, and multiple support rods 481 are evenly arranged around the periphery of the second rotating shaft 45.

[0040] Combination Figure 6 and Figure 7 The spray assembly 40 also includes a latch 47 fixedly connected to the turntable 46. The latch 47 has an opening 471 on the side facing away from the turntable 46. The spray gun 41 is movably inserted through the opening 471 of the latch 47. A fastener 472 (e.g., a pin) is provided at the opening 471 to limit the displacement of the spray gun 41 in the first direction. The pin on the latch 47 prevents the spray gun 41 from detaching from the latch 47, while allowing the spray gun 41 to move back and forth relative to the latch 47 in the second direction.

[0041] Reference Figure 8 The climbing frame 30 is equipped with a storage component 31 for storing the spray gun 41. Specifically, the storage component 31 includes multiple hanging plates spaced apart in the second direction, each with a groove to accommodate the spray gun 41. When de-icing is required, the spray gun 41 is removed from the storage component 31 and movably inserted into the opening 471 of the buckle 47, and then secured by a pin.

[0042] Furthermore, referring to Figure 8 The base 10 is provided with at least one brake frame 60, which is movably disposed on the base 10 along a first direction. Exemplarily, the base 10 is provided with an electric actuator, the output end of which is fixedly connected to the brake frame 60. The electric actuator can control the raising and lowering of the brake frame 60. Alternatively, the brake frame 60 can be connected to the base 10 via other drives and transmission mechanisms. Telescopic rods 61 are respectively provided at both ends of the brake frame 60, and support legs 62 are provided at the ends of the telescopic rods 61. When an external traction device drives the aircraft de-icing device to move to the wing side of the aircraft to be de-iced, the telescopic rods 61 extend from both ends of the brake frame 60 and drive the support legs 62 to descend via the brake frame 60, adjusting the height of the support legs 62 until they touch the ground, thereby achieving stable support for the de-icing device.

[0043] In this embodiment, refer to Figure 2 There are two brake brackets 60, which are spaced apart in the first direction. The telescopic rod 61 is movable on the brake bracket 60 in the second direction. The four legs are respectively arranged at the four corners of the base 10.

[0044] Reference Figure 2 The base 10 is equipped with a storage tank 70 and a booster pump 80. The storage tank 70 stores de-icing fluid and has an insulation layer to keep the de-icing fluid warm. The booster pump 80 is connected to the spray gun 41 and can increase the pressure of the sprayed fluid. Electric heating wires 71 and a level indicator 72 are respectively installed on both sides of the storage tank 70. Activating the electric heating wires 71 heats the de-icing fluid, and automatically maintains the temperature when it reaches a suitable operating temperature. The base 10 also has a generator 90 (e.g., a diesel generator 90) that provides power to the electrical components of the de-icing device.

[0045] An electrical box and a fire extinguisher are installed on the base 10. The electrical box distributes and controls the power to the electrical components of the de-icing device, ensuring the rational allocation of power. The base 10 is also equipped with a cable tray to facilitate the storage of wires connecting the electrical box and the electrical components.

[0046] The working process of the de-icing device provided in this application is as follows: 1. When working, first mix an appropriate amount of de-icing fluid with water and pour it into the storage tank 70; 2. Drive the base 10 through the external traction device to move the de-icing device to the wing on one side of the aircraft, control the brake frame 60 to descend, automatically brake, and extend the outrigger 62 to touch the ground; 3. Heat the de-icing fluid until it reaches the operating temperature; 4. The operator climbs onto the elevated platform 30, removes the spray gun 41 from the storage unit 31, and installs the spray gun 41 onto the clip 47 of the spray assembly 40; 5. Start the booster pump 80 to perform de-icing on the aircraft wings. Adjust the spray gun 41 so that it can swing left and right around the first rotating shaft 43 and up and down around the second rotating shaft 45, thereby ensuring that liquid is sprayed to de-ic every part of the aircraft wings and other outer surfaces of the aircraft fuselage.

[0047] The above description is merely a preferred embodiment of this application, but the scope of protection of this application 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 application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

[0048] The above description is merely a preferred embodiment of this application, but the scope of protection of this application 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 application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. An aircraft de-icing device, characterized in that, include: Movable base; In the direction of movement of the base, the first end of the traction frame is connected to the base, and the second end of the traction frame is provided with a traction connection position, through which the traction frame is connected to an external traction device; A climbing frame, wherein the climbing frame is movably disposed on the base along a first direction, the first direction being perpendicular to the direction of movement of the base; A spraying assembly is located at the top of the climbing frame and is configured to spray de-icing fluid onto the aircraft to be de-iced.

2. The aircraft de-icing device according to claim 1, characterized in that, The climbing frame has a first extreme position and a second extreme position in the first direction, with the first extreme position located below the second extreme position; when the climbing frame moves to the first extreme position, in the first direction, the distance between the top of the spraying assembly and the ground is less than the height of the walkway.

3. The aircraft de-icing device according to claim 2, characterized in that, The width of the traction frame in the second direction is smaller than the width of the base in the second direction, and the movement direction of the first direction and the base is perpendicular to the second direction.

4. The aircraft de-icing device according to claim 1, characterized in that, The spraying assembly includes a spray gun, which is movably and / or rotatably mounted on top of the climbing frame.

5. The aircraft de-icing device according to claim 4, characterized in that, The spraying assembly includes a first support member and a first rotating shaft. The first support member is fixedly mounted on the climbing frame, and the first rotating shaft is rotatably mounted on the first support member. The axial direction of the first rotating shaft is arranged along the first direction. The first rotating shaft is connected to the spray gun so that the spray gun can rotate around the axial direction of the first rotating shaft under the action of external force.

6. The aircraft de-icing device according to claim 5, characterized in that, The spraying assembly further includes a connecting seat, a second rotating shaft, and a turntable. The connecting seat is fixedly connected to the top end of the first rotating shaft. The axial direction of the second rotating shaft is arranged along the moving direction of the base. The first end of the second rotating shaft along its axial direction is fixedly connected to the connecting seat. The second end of the second rotating shaft is rotatably connected to the turntable. The turntable is connected to the spray gun so that the spray gun can rotate around the axial direction of the second rotating shaft under the action of external force.

7. The aircraft de-icing device according to claim 6, characterized in that, The spraying assembly also includes a buckle fixedly connected to the turntable. The buckle has an opening through which the spray gun is movably inserted. A fastener is provided at the opening to limit the displacement of the spray gun in the first direction.

8. The aircraft de-icing device according to claim 4, characterized in that, The climbing frame is equipped with a storage unit for storing the spray gun.

9. The aircraft de-icing device according to any one of claims 1 to 8, characterized in that, The aircraft de-icing device also includes a lifting mechanism, which is mounted on the base and is connected to the climbing frame to drive the climbing frame to reciprocate along the first direction.

10. The aircraft de-icing device according to any one of claims 1 to 8, characterized in that, The base is provided with at least one brake frame, and each of the two ends of the brake frame is provided with a telescopic rod, and the end of the telescopic rod is provided with a support leg.

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