Airplane drainage equipment

Abstract

The aircraft drainage equipment comprises a chassis, an air compressor, a water receiving tank and a drainage pipe assembly, the air compressor comprises an air compressor body and an air supply pipe, the air compressor body is installed on the chassis, one end of the air supply pipe communicates with an air outlet of the air compressor, and the other end of the air supply pipe communicates with a water outlet of the water receiving tank; the water receiving tank is installed on the chassis, one end of the water discharging pipe assembly is used for being communicated with the water tank, and the other end of the water discharging pipe assembly is communicated with the water receiving tank. According to the airplane water drainage equipment, the water drainage pipe assembly is connected with the water drainage opening of the water tank of the airplane, and then the air compressor is used for pressurizing air and inputting the air into the air supply pipe till the air enters the water tank of the airplane. Water is quickly discharged from the water outlet by using internal and external pressure difference of the water tank. And the discharged water is collected into the water receiving tank through the water discharging pipe assembly, so that quick water discharging of the airplane is realized. The operation energy consumption of the air compressor is greatly reduced compared with that of an auxiliary power device of an airplane, and the strategic requirements of saving and emission reduction are met.

Description

Technical Field

[0001] The invention relates to the technical field of aircraft, and in particular to aircraft water release equipment. Background Art

[0002] This section merely provides background information related to the present disclosure and is not necessarily prior art.

[0003] In winter, when an aircraft performs long stopovers or overnight flights, in order to prevent the fresh water in the pipes stored on board from freezing and cracking, the drinking water in the aircraft water tank and pipes needs to be thoroughly drained and maintained if the aircraft is parked for more than 4 hours. The existing technology relies on the aircraft's auxiliary power unit for pressurized drainage, which has high fuel consumption, low efficiency of manual drainage, and does not meet the requirements of energy conservation and emission reduction. Summary of the invention

[0004] The purpose of the present invention is to at least solve the problem of high energy consumption and long drainage time of existing aircraft. This purpose is achieved through the following technical solutions:

[0005] The present invention provides an aircraft water release device, the aircraft water release device comprising:

[0006] Chassis;

[0007] An air compressor, comprising an air compressor body and an air supply pipe, wherein the air compressor body is mounted on the chassis, one end of the air supply pipe is connected to an air outlet of the air compressor, and the other end of the air supply pipe is used to connect to a ground pressurization interface of a water tank of the aircraft;

[0008] A water receiving tank, mounted on the chassis;

[0009] A drain pipe assembly, one end of which is used to be connected to the water tank, and the other end of which is connected to the water receiving tank.

[0010] The aircraft water discharge device proposed by the present invention is connected to the drain port of the aircraft's water tank through a drain pipe assembly, and then uses an air compressor to pressurize air and input it into the air supply pipe until the air enters the aircraft's water tank. The water is quickly discharged from the drain port by utilizing the pressure difference between the inside and outside of the water tank. The discharged water will be collected into the water receiving tank through the drain pipe assembly, thereby realizing the rapid water discharge of the aircraft. The operating energy consumption of the air compressor is greatly reduced compared to the auxiliary power unit of the aircraft, which meets the strategic requirements of saving and reducing emissions.

[0011] In addition, the aircraft water release device according to the present invention may also have the following additional technical features:

[0012] In some embodiments of the present invention, the aircraft water release equipment further includes a heating device, which is mounted on the chassis and disposed close to the air intake end of the air compressor, and is used to heat the air intake of the air compressor.

[0013] In some embodiments of the present invention, the aircraft water release equipment also includes a plurality of wheel assemblies arranged on the chassis, the wheel assemblies include a bracket and a wheel, the bracket is connected to the bottom side of the chassis, and the wheel is rotatably connected to the bracket.

[0014] In some embodiments of the present invention, the drain pipe assembly includes a plurality of coil mechanisms and a plurality of drain pipes, the coil mechanisms are arranged on the chassis, the plurality of drain pipes are coiled on the coil mechanisms in a one-to-one correspondence, the drain pipe assembly also includes a Y-shaped joint arranged on the drain pipe, a first interface of the Y-shaped joint is connected to an end of the drain pipe away from the coil mechanism, and the other two interfaces of the Y-shaped joint are used to connect two adjacent drain ports of the water tank of the aircraft.

[0015] In some embodiments of the present invention, the aircraft water release equipment further comprises a plurality of wave-breaking plates, the plurality of wave-breaking plates are arranged at intervals in the water receiving box, and the wave-breaking plates are arranged parallel to or at an angle to the height direction of the aircraft water release equipment.

[0016] In some embodiments of the present invention, the aircraft water release equipment further includes a hanging rod, one end of which is hinged to the chassis, and the other end of which forms a hanging hole for connecting a trailer.

[0017] In some embodiments of the present invention, the aircraft water discharge equipment further includes a first drain pipe and a second drain pipe, wherein the first end of the first drain pipe is connected to the bottom of the water receiving box, and the first drain pipe is a hose structure, and the first end of the second drain pipe is connected to the bottom of the water receiving box, and along the height direction of the aircraft water discharge equipment, the first end of the first drain pipe is located above the first end of the second drain pipe.

[0018] In some embodiments of the present invention, the heating device further comprises a water heating end disposed in the water receiving tank, and the water heating end is used to heat the liquid in the water receiving tank.

[0019] In some embodiments of the present invention, the aircraft water release equipment also includes a gas cylinder and a branch gas pipe, the gas cylinder is arranged on the chassis, the gas cylinder is used to contain pressurized gas, one end of the branch gas pipe is connected to the gas cylinder, and the other end of the branch gas pipe is connected to the gas supply pipe.

[0020] In some embodiments of the present invention, the aircraft water release equipment further includes a generator, which is disposed on the chassis and electrically connected to the air compressor. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] Various other advantages and benefits will become apparent to those of ordinary skill in the art by reading the detailed description of the preferred embodiments below. The accompanying drawings are only for the purpose of illustrating the preferred embodiments and are not to be considered as limiting the present invention. Moreover, the same reference numerals are used throughout the accompanying drawings to represent the same components. In the accompanying drawings:

[0022] Figure 1 A schematic diagram of the structure of an aircraft water releasing device from a first perspective according to an embodiment of the present invention is schematically shown;

[0023] Figure 2 A schematic diagram of the structure of an aircraft water releasing device from a second perspective according to an embodiment of the present invention is schematically shown;

[0024] Figure 3 It schematically shows a structural diagram of an aircraft water-releasing device according to an embodiment of the present invention from a first perspective with some structures omitted;

[0025] Figure 4 It schematically shows a structural diagram of an aircraft water releasing device according to an embodiment of the present invention from a second perspective with some structures omitted;

[0026] The reference numerals are as follows:

[0027] 10. chassis; 11. air compressor; 12. air supply pipe; 13. water tank; 131. water inlet joint; 14. drain pipe assembly; 141. coil mechanism; 142. drain pipe; 15. heating device; 16. wheel assembly; 161. wheel; 162. bracket; 17. hanging rod; 181. first drain pipe; 182. second drain pipe; 19. connecting rod; 20. generator; 21. fire extinguisher; 22. control device; DETAILED DESCRIPTION

[0028] The exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. Although the exemplary embodiments of the present disclosure are shown in the accompanying drawings, it should be understood that the present disclosure can be implemented in various forms and should not be limited by the embodiments described herein. On the contrary, these embodiments are provided in order to enable a more thorough understanding of the present disclosure and to fully convey the scope of the present disclosure to those skilled in the art.

[0029] It should be understood that the terms used herein are only for the purpose of describing specific example embodiments and are not intended to be limiting. Unless the context clearly indicates otherwise, the singular forms "one", "an" and "said" as used herein may also be meant to include plural forms. The terms "include", "comprise", "contain", and "have" are inclusive, and therefore specify the existence of stated features, steps, operations, elements and / or parts, but do not exclude the existence or addition of one or more other features, steps, operations, elements, parts, and / or combinations thereof. The method steps, processes, and operations described herein are not interpreted as necessarily requiring them to be performed in the specific order described or illustrated, unless the execution order is clearly indicated. It should also be understood that additional or alternative steps may be used.

[0030] Although the terms first, second, third, etc. can be used in the text to describe multiple elements, components, regions, layers and / or sections, these elements, components, regions, layers and / or sections should not be limited by these terms. These terms can only be used to distinguish an element, component, region, layer or section from another region, layer or section. Unless the context clearly indicates, terms such as "first", "second" and other numerical terms do not imply order or sequence when used in the text. Therefore, the first element, component, region, layer or section discussed below can be referred to as the second element, component, region, layer or section without departing from the teaching of the example embodiments.

[0031] For ease of description, spatial relative terms may be used herein to describe the relationship of one element or feature relative to another element or feature as shown in the figure, such as "inside", "outside", "inner side", "outer side", "below", "below", "above", "above", etc. Such spatial relative terms are intended to include different orientations of the device in use or operation in addition to the orientation depicted in the figure. For example, if the device in the figure is turned over, then the elements described as "below other elements or features" or "below other elements or features" will 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 can be oriented otherwise (rotated 90 degrees or in other directions) and the spatial relative descriptors used in the text are interpreted accordingly.

[0032] like Figures 1 to 4As shown, the present invention proposes an aircraft water discharge device, which includes a chassis 10, an air compressor 11, a water receiving tank 13 and a water discharge pipe assembly 14. The air compressor 11 includes an air compressor 11 body and an air supply pipe 12. The air compressor 11 body is installed on the chassis 10. One end of the air supply pipe 12 is connected to the air outlet of the air compressor 11, and the other end of the air supply pipe 12 is used to connect to the ground pressurization interface of the aircraft's water tank. The water receiving tank 13 is installed on the chassis 10. The water discharge pipe assembly 14, one end of the water discharge pipe assembly 14 is used to connect to the water tank, and the other end of the water discharge pipe assembly 14 is connected to the water receiving tank 13.

[0033] It is understandable that the chassis 10 can be a rectangular plate structure, or a chassis 10 designed as other shapes as required. The chassis 10 can be formed by welding of profiles or steel sections, and multiple installation positions can be set on the chassis 10, for example, multiple accommodating spaces can be separated by partitions to place multiple components of the aircraft water discharge equipment therein, so as to facilitate storage and improve aesthetics. Wheels 161 can be set below the chassis 10, so that the user can easily move the chassis 10 to the aircraft position. The air compressor 11 can select an existing screw air compressor 11 or a centrifugal air compressor 11, and the gas is drawn into the air compressor 11 and pressurized and output through the rotational movement inside the compressor. The air compressor 11 can be fixed to the chassis 10 by bolts. One end of the drain pipe assembly 14 can be fixed to the output end of the air compressor 11 by a clamp or a pipe fixing, and the other end of the drain pipe 142 can be provided with a pipe joint adapted to the drain port of the aircraft water tank to facilitate connection with the aircraft water tank. The drain pipe assembly 14 may also be provided with a pipeline winding mechanism and a pipeline storage mechanism, and the specific structure may refer to the prior art to facilitate the winding and storage of the drain pipe assembly 14, and to retract it when idle.

[0034] The aircraft water discharge equipment proposed in the present invention is connected to the drain port of the aircraft's water tank through a drain pipe assembly 14, and then uses an air compressor 11 to pressurize the air and input it into the air supply pipe 12 until the air enters the ground pressurization interface of the aircraft's water tank. The water is quickly discharged from the drain port by utilizing the pressure difference between the inside and outside of the water tank. The discharged water will be collected into the water receiving tank 13 through the drain pipe assembly 14. The breath-holding link in the water discharge service is simulated to drain the clean water in the water tank pipeline, further avoiding water freezing and causing pipeline damage, thereby realizing rapid water discharge from the aircraft. The operating energy consumption of the air compressor 11 is greatly reduced compared to the auxiliary power unit of the aircraft, which meets the strategic requirements of saving and reducing emissions. At the same time, the equipment can also use the air compressor 11 to perform pipeline leakage detection and real-time pipeline sealing detection.

[0035] In some embodiments of the present invention, the aircraft water release equipment further includes a heating device 15 , which is mounted on the chassis 10 and disposed close to the air intake end of the air compressor 11 , and is used to heat the air intake of the air compressor 11 .

[0036] It is understandable that the heating device 15 can be an electric heating device, which heats the air intake of the air compressor 11 through the electric heating wire, so that the air intake temperature of the air compressor 11 increases, and then the air supply temperature of the water tank of the aircraft by the air compressor 11 increases. In some colder areas, the heating device 15 can reduce the freezing of the air supply pipe 12 and the freezing of the water tank of the aircraft, thereby reducing the phenomenon of freezing and cracking of the pipeline and the water tank, and improving reliability. The heating device 15 can also use the waste heat of the generator 20 to guide the preheating of the diesel generator 20 to the air intake end of the air compressor 11, which can also achieve the effect of increasing the air supply temperature of the air compressor 11.

[0037] In some embodiments of the present invention, the aircraft water release equipment also includes a plurality of wheel assemblies 16 arranged on the chassis 10, the wheel assembly 16 includes a bracket 162 and a wheel 161, the bracket 162 is connected to the bottom side of the chassis 10, and the wheel 161 is rotatably connected to the bracket 162.

[0038] It can be understood that a plurality of vehicle components can be arranged under the chassis 10. For example, when the chassis 10 is rectangular, a wheel assembly 16 is arranged at each of the four corners of the chassis 10. The wheel 161 is connected to the chassis 10 through a U-shaped bracket 162, and the wheel 161 can be rotatably arranged. By arranging the wheel assembly 16, it is convenient to move the aircraft water release equipment to the water tank of the aircraft by manpower or vehicle towing, thereby improving the user experience.

[0039] In some embodiments of the present invention, the drain pipe assembly 14 includes a plurality of coil mechanisms 141 and a plurality of drain pipes 142, the coil mechanism 141 is arranged on the chassis 10, and the plurality of drain pipes 142 are coiled on the coil mechanism 141 in a one-to-one correspondence. The drain pipe assembly 14 also includes a Y-shaped joint arranged on the drain pipe 142, and the first interface of the Y-shaped joint is connected to one end of the drain pipe 142 away from the coil mechanism 141, and the other two interfaces of the Y-shaped joint are used to connect two adjacent drain ports of the aircraft's water tank.

[0040] It is understandable that the drain pipe assembly 14 may include a plurality of drain pipes 142, each drain pipe 142 is fixed to the chassis 10 via a coil mechanism 141, the coil mechanism 141 may include a coil rod, the coil rod is spaced apart from the chassis 10 and connected via a connecting rod, the drain pipe 142 is wound around the coil rod to save storage space, and the coil rod is rotatably connected to the connecting rod, so that when in use, the user can pull one end of the drain pipe 142 to pull out the drain pipe 142 for easy use. A Y-type connector may be provided at one end of the drain pipe 142 connected to the water tank of the aircraft, the Y-type connector having three interfaces, the three interfaces may be arranged to communicate with each other, one of the interfaces is communicated with the drain pipe 142, and the other two interfaces may be communicated with two adjacent drain ports on the water tank of the aircraft.

[0041] In some embodiments of the present invention, the aircraft water release equipment further comprises a plurality of wave-breaking plates, which are arranged at intervals in the water receiving box 13, and the wave-breaking plates are arranged parallel to or at an angle to the height direction of the aircraft water release equipment.

[0042] It is understandable that a plurality of spaced wave-breaking plates may be provided in the water receiving box 13, and the wave-breaking plates may be adapted to the shape of the cross section of the water receiving box 13. For example, when the water receiving box 13 is in a cubic shape, the wave-breaking plates are in a rectangular shape. A plurality of through holes may be provided on the wave-breaking plates to connect a plurality of water chambers separated by a plurality of wave-breaking plates. By providing the wave-breaking plates, the degree of water fluctuation in the water receiving box 13 is reduced when the aircraft water discharge device moves, and the impact of water is reduced, so that the structure of the water receiving box 13 is more stable.

[0043] In some embodiments of the present invention, the aircraft water release device further includes a hanging rod 17, one end of the hanging rod 17 is hinged to the chassis 10, and the other end of the hanging rod 17 forms a hanging hole for connecting a trailer.

[0044] It is understandable that the hanging rod 17 can be a rod-type structure, one end of which is hinged to the connecting rod 19 extending from the chassis 10 to facilitate rotation and adjust the towing angle. A hanging hole can be set at the position of the hanging rod 17 away from the chassis 10, and the hook of the trailer can be connected through the hanging hole to facilitate the aircraft water release device to be moved to the position of the aircraft through the trailer. When the hanging rod 17 rotates to contact the ground, it can play a braking role and can lock the aircraft water release device in time, which meets the airport's emergency stop and parking requirements for non-powered vehicles.

[0045] In some embodiments of the present invention, the aircraft water discharge equipment further includes a first drain pipe 181 and a second drain pipe 182, wherein a first end of the first drain pipe 181 is connected to the bottom of the water receiving box 13, and the first drain pipe 181 is a hose structure, and a first end of the second drain pipe 182 is connected to the bottom of the water receiving box 13, and along the height direction of the aircraft water discharge equipment, the first end of the first drain pipe 181 is located above the first end of the second drain pipe 182.

[0046] It can be understood that two drain pipes can be set on the water receiving box 13. The first drain pipe 181 can use a corrugated hose for easy bending and plugging into the drainage position. The second drain pipe 182 can be set on the bottom side of the water receiving box 13. The second drain pipe 182 can adopt the structure of a drainage joint. When draining, the second drain pipe 182 can be directly aligned with the drain outlet or drain channel on the ground to facilitate drainage.

[0047] In some embodiments of the present invention, the heating device 15 further includes a water heating end disposed in the water receiving tank 13 , and the water heating end is used to heat the liquid in the water receiving tank 15 .

[0048] It is understandable that the water heating end can be a plurality of heating tubes arranged in the water receiving box 13, which can maintain the liquid in the water receiving box 13 at a certain temperature through electric heating, reduce the freezing of the liquid in the water receiving box 13, and improve the reliability of the water receiving box 13.

[0049] In some embodiments of the present invention, the aircraft water release equipment also includes a gas cylinder and a branch gas pipe. The gas cylinder is arranged on the chassis 10. The gas cylinder is used to contain pressurized gas. One end of the branch gas pipe is connected to the gas cylinder, and the other end of the branch gas pipe is connected to the air supply pipe 12.

[0050] It is understandable that additional gas cylinders can be provided. When the air compressor 11 cannot be used normally and the gas supply is insufficient, the pressurized gas in the gas cylinders can be used to supplement the gas, so that the pressure and gas volume of the gas input into the water tank of the aircraft meet the required standards.

[0051] In some embodiments of the present invention, the aircraft water release device further includes a generator 20 , which is disposed on the chassis 10 and electrically connected to the air compressor 11 .

[0052] It is understandable that the generator 20 can be a diesel generator 20, and a fuel tank is provided on the chassis 10 to facilitate power generation at any location. The generator 20 can also be omitted and a ground interface is used, and the air compressor 11 is connected to the power interface on the airport ground through the ground interface, so that the power supply of the air compressor 11 is supplied.

[0053] In some embodiments of the present invention, the aircraft water release device further includes a pressure gauge. When the air compressor 11 starts to supply air to the air supply pipe 12, the pressure gauge can detect the pressure inside the air supply pipe 12, and then determine whether the pipeline is leaking. Specifically, the pressure gauge can be set on the air supply pipe 12 or on the air path of the air compressor 11.

[0054] In some embodiments of the present invention, a fire extinguisher 21 is also provided on the chassis 10 to reduce the potential fire hazard.

[0055] In some embodiments of the present invention, a control device 22 is also provided on the chassis 10. The control device 22 is electrically connected to electrical equipment such as the air compressor 11 and the heating device 15. The control device 22 is provided with control buttons for controlling the operation of the air compressor 11 and the heating device 15, which is convenient for users to manually control.

[0056] In some embodiments of the present invention, a water inlet joint 131 is provided on the water receiving box 13, and the water inlet joint 131 has a plurality of interconnected interfaces, one of which is connected to the water receiving box 13, and the remaining interfaces can be provided with plugs to be sealed when not in use. By providing a plurality of interfaces, it is convenient to connect drain pipes 142 of different specifications, thereby improving the adaptability of the equipment.

[0057] The above is only a preferred specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed by the present invention should be included in the protection scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the claims.

Claims

1. An aircraft water release device, characterized in that: The aircraft water release equipment comprises: Chassis; An air compressor, comprising an air compressor body and an air supply pipe, wherein the air compressor body is mounted on the chassis, one end of the air supply pipe is connected to an air outlet of the air compressor, and the other end of the air supply pipe is used to connect to a ground pressurization interface of a water tank of the aircraft; A water receiving tank, mounted on the chassis; A drain pipe assembly, one end of which is used to be connected to the water tank, and the other end of which is connected to the water receiving tank.

2. The aircraft water release device according to claim 1, characterized in that: The aircraft water release equipment also includes a heating device, which is installed on the chassis and arranged at the air intake end of the air compressor. The heating device is used to heat the air intake of the air compressor or the liquid in the water tank.

3. The aircraft water release equipment according to claim 2, characterized in that: The aircraft water release equipment also includes a plurality of wheel assemblies arranged on the chassis, and the wheel assemblies include a bracket and a wheel, the bracket is connected to the bottom side of the chassis, and the wheel is rotatably connected to the bracket.

4. The aircraft water release device according to claim 3, characterized in that: The drain pipe assembly includes a plurality of coil mechanisms and a plurality of drain pipes, the coil mechanisms are arranged on the chassis, the plurality of drain pipes are coiled on the coil mechanisms in a one-to-one correspondence, the drain pipe assembly also includes a Y-shaped joint arranged on the drain pipe, a first interface of the Y-shaped joint is connected to an end of the drain pipe away from the coil mechanism, and the other two interfaces of the Y-shaped joint are used to connect two adjacent drain ports of the water tank.

5. The aircraft water release device according to claim 4, characterized in that: The aircraft water-releasing equipment further comprises a plurality of wave-breaking plates, which are arranged in the water receiving box at intervals, and the wave-breaking plates are arranged parallel to or at an angle to the height direction of the aircraft water-releasing equipment.

6. The aircraft water release device according to claim 5, characterized in that: The aircraft water release equipment also includes a hanging rod, one end of which is hinged to the chassis, and the other end of which forms a hanging hole for connecting a trailer.

7. The aircraft water release device according to claim 6, characterized in that: The aircraft water discharge equipment further includes a first drain pipe and a second drain pipe, wherein a first end of the first drain pipe is communicated with a bottom of the water receiving box, and the first drain pipe is a hose structure, and a first end of the second drain pipe is communicated with the bottom of the water receiving box, and along a height direction of the aircraft water discharge equipment, the first end of the first drain pipe is located above the first end of the second drain pipe.

8. The aircraft water release device according to claim 7, characterized in that: The heating device also has a water heating end arranged in the water receiving box, and the water heating end is used to heat the liquid in the water receiving box.

9. The aircraft water release device according to claim 8, characterized in that: The aircraft water release equipment also includes a gas cylinder and a branch gas pipe. The gas cylinder is arranged on the chassis and is used to contain pressurized gas. One end of the branch gas pipe is connected to the gas cylinder, and the other end of the branch gas pipe is connected to the gas supply pipe.

10. The aircraft water release device according to any one of claims 1 to 9, characterized in that: The aircraft water release equipment also includes a generator, which is arranged on the chassis and electrically connected to the air compressor.

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