Hydraulic refueling system for airplane

Abstract

The invention belongs to the technical field of aircraft hydraulic pressure, and provides an aircraft hydraulic refueling system which comprises an oil tank, a pump-motor set, a one-way valve, an energy accumulator and a refueling valve. The pump-motor set pumps oil in the oil tank through a pressure supply pipeline and then outputs the oil to the energy accumulator and the refueling valve which are connected to the pressure supply pipeline in parallel through the one-way valve; the energy accumulator and the pump-motor set provide high-pressure oil which is jointly output to a hydraulic oil tank of the airplane through the refueling valve, and the refueling valve is provided with a quick plug matched with a refueling port of the hydraulic oil tank of the airplane. According to the pressure refueling device, refueling or oil discharging operation can be carried out on an aircraft hydraulic system, the refueling operation can be carried out without pressure relief on an aircraft oil tank by adopting a pressure refueling mode, and rapidness is achieved.

Description

Technical Field

[0001] This invention belongs to the field of aircraft hydraulic technology, and specifically relates to an aircraft hydraulic refueling system. Background Technology

[0002] As a core component of aircraft control, the hydraulic system provides power support for the aircraft and mainly functions to drive the aircraft's controls, takeoff and landing systems, and critical equipment. Before flight, it is necessary to check whether the hydraulic system's oil level is sufficient; if the level is insufficient, oil needs to be added. When the aircraft's pipes are being installed or removed, the hydraulic system needs to be drained; this is where the hydraulic refueling system comes in.

[0003] Because aircraft hydraulic oil tanks are generally piston-type tanks, the air chamber in the tank needs to be depressurized before refueling. The hydraulic oil tank is also located relatively deep inside the aircraft. Therefore, hydraulic oil is usually replenished through a special refueling pipeline, which is also relatively complex in structure, making it difficult to complete the hydraulic oil replenishment work in the field environment. Summary of the Invention

[0004] To address the aforementioned problems, this invention provides an aircraft hydraulic refueling system that allows for the refueling and draining of the aircraft's hydraulic system in the field without depressurizing the pressurized oil tank.

[0005] The technical solution of the present invention is as follows: An aircraft hydraulic refueling system includes an oil tank, a pump-motor unit, a check valve, an accumulator, and a refueling valve. The pump-motor unit draws oil from the oil tank through a pressure supply line and outputs it through the check valve to the accumulator and the refueling valve, which are connected in parallel to the pressure supply line. The accumulator and the pump-motor unit provide high-pressure oil, which is then output to the aircraft's hydraulic oil tank through the refueling valve. The refueling valve is equipped with a quick-connect plug that matches the refueling port of the aircraft's hydraulic oil tank.

[0006] Furthermore, a pressure oil filter is provided at the outlet of the check valve.

[0007] Furthermore, the accumulator and the refueling valve are also equipped with a pilot relief valve in parallel. The outlet of the pilot relief valve is connected to the oil drain line, and the outlet of the oil drain line is connected to the oil tank. The refueling pressure of the pressure supply line is adjusted by controlling the pilot relief valve.

[0008] Furthermore, the refueling valve and the pressure supply line are connected and disassembled automatically via quick couplings.

[0009] Furthermore, it also includes a drain valve and a radiator. The drain valve is connected to the fuel tank through a drain line, and a radiator is installed in the drain line. The drain valve is equipped with a quick-connect plug that matches the drain port of the aircraft's hydraulic fuel tank.

[0010] Furthermore, the drain valve and drain line are connected and disassembled automatically via quick couplings.

[0011] Furthermore, the fuel tank is equipped with a liquid level and temperature gauge and an air filter.

[0012] Furthermore, a shut-off valve is installed between the pump-motor unit and the oil tank.

[0013] The advantages of this invention are as follows: 1. This invention can be used to add or drain oil from the hydraulic system of an aircraft.

[0014] 2. This invention prevents overpressure caused by misoperation, which could lead to conduit rupture or damage to accessories, by setting a safety valve.

[0015] 3. This invention uses pressure refueling, which eliminates the need to depressurize the aircraft fuel tank, making the refueling operation faster.

[0016] 4. This invention adopts a quick-connect coupling, which is convenient to operate, eliminates the need for conduit disassembly and assembly, and can be adapted to different refueling valves and drain valves to achieve compatibility with different aircraft.

[0017] 5. The refueling pressure of this invention is adjustable and can be adapted to the hydraulic systems of different aircraft models.

[0018] 6. The overall structure of this invention is relatively small, so it can be designed to be portable, making it convenient for refueling or dumping fuel on different types of aircraft. Attached Figure Description

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

[0020] Figure 1 This is a schematic diagram of an embodiment of the present invention.

[0021] Figure 2 This is a schematic diagram of the design and layout of the present invention.

[0022] Figure 1 In the diagram, 1—Stop valve, 2—Oil tank, 3—Pump-motor unit, 4—Check valve, 5—Pressure supply oil filter, 6—Safety valve, 7—Pressure sensor, 8—Pressure gauge, 9—Accumulator, 10—Quick connector, 11—Add oil valve, 12—Drain valve, 13—Pilot relief valve, 14—Return oil filter, 15—Air-cooled radiator, 16—Liquid level and temperature gauge, 17—Air filter. Detailed Implementation

[0023] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0024] The features and illustrative embodiments of various aspects of the present invention will now be described in detail. Numerous specific details are set forth in the following detailed description to provide a thorough understanding of the invention. However, it will be apparent to those skilled in the art that the invention may be practiced without requiring some of these specific details. The following description of embodiments is merely intended to provide a better understanding of the invention by illustrating examples of the invention. The invention is by no means limited to any specific setups and methods set forth below, but covers any improvements, substitutions, and modifications to structures, methods, and devices without departing from the spirit of the invention. Well-known structures and techniques are not shown in the drawings and the following description to avoid unnecessarily obscuring the invention.

[0025] In the description of this invention, it should be noted that the directions or positional relationships indicated by terms such as "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer" are based on the directions or positional relationships shown in the accompanying drawings and are only for the convenience of describing and simplifying the invention, and should not be construed as limiting the invention. Furthermore, the use of ordinal numbers (e.g., "first and second," etc.) is for distinguishing objects and is not limited to this order, and should not be construed as indicating or implying relative importance.

[0026] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly, encompassing both direct connection and indirect connection via an intermediate medium. Those skilled in the art can understand the specific meaning of these terms in this invention based on the specific circumstances.

[0027] It should be noted that, unless otherwise specified, the embodiments of the present invention and the features thereof can be combined with each other, and the various embodiments can be referenced and cited in each other. The present invention will now be described in detail with reference to the accompanying drawings and embodiments.

[0028] Example 1: An aircraft hydraulic refueling system includes an oil tank 2, a pump-motor unit 3, a one-way valve 4, an accumulator 9, and a refueling valve 11. The pump-motor unit 3 draws oil from the oil tank 2 through a pressure supply line and outputs it through the one-way valve 4 to the accumulator 9 and the refueling valve 11, which are connected in parallel to the pressure supply line. The accumulator 9 and the pump-motor unit 3 provide high-pressure oil, which is output to the aircraft's hydraulic oil tank through the refueling valve 11. The refueling valve 11 is equipped with a quick-connect plug that matches the refueling port of the aircraft's hydraulic oil tank.

[0029] A pressure oil filter is provided at the outlet of check valve 4.

[0030] The accumulator 9 and the refueling valve 11 are also equipped with a pilot relief valve 13 in parallel. The outlet of the pilot relief valve 13 is connected to the oil drain line, and the outlet of the oil drain line is connected to the oil tank 2. The refueling pressure of the pressure supply line is adjusted by controlling the pilot relief valve 13.

[0031] The refueling valve 11 and the pressure supply line are connected and disassembled quickly via quick connector 10.

[0032] It also includes an oil drain valve 12 and a radiator 15. The oil drain valve 12 is connected to the oil tank 2 through an oil drain line. The oil drain line is equipped with a radiator 15. The oil drain valve 12 is equipped with a quick plug that matches the oil drain port of the aircraft's hydraulic oil tank.

[0033] The oil drain valve 12 and the oil drain line are connected and disassembled automatically via quick connector 10.

[0034] The oil tank 2 is equipped with a liquid level and temperature gauge 16 and an air filter 17.

[0035] A shut-off valve 1 is installed between the pump-motor unit 3 and the oil tank 2.

[0036] Example 2: An aircraft hydraulic refueling system includes an oil tank, a pump-motor unit, a check valve, a pressure supply oil filter, a safety valve, a pressure sensor, a pressure gauge, an accumulator, a quick connector, a refueling valve, a drain valve, a pilot-operated relief valve, a return oil filter, a level and temperature gauge, an air filter, a shut-off valve, and corresponding pipelines.

[0037] The oil tank is used to store hydraulic oil; The pump motor unit is used to inject hydraulic oil from the tank into the aircraft's hydraulic system; Pressure oil filters and return oil filters are used for hydraulic oil filtration and cleaning. Pressure sensors and pressure gauges are used for system status monitoring; Check valves, safety valves, pilot-operated relief valves, and shut-off valves are used for system status control; The accumulator serves to instantly replenish oil and stabilize pressure; Air-cooled radiators are used to dissipate heat from hydraulic refueling systems; Quick couplings facilitate the connection and disconnection of conduits and are generally used for troubleshooting. The refueling (dumping) valve can be used with the aircraft's refueling (dumping) valve and is also a type of quick connector.

[0038] Compared to the previous hydraulic refueling system: This invention uses pressure lubrication and quick-connect couplings, making it more convenient and faster than previous hydraulic lubrication systems.

[0039] 1. Composition and specific structure: The composition and specific structure of the hydraulic refueling system are as follows: Figure 1 and Figure 2 As shown.

[0040] 2. Functionality Implementation: Refilling the aircraft's hydraulic system: The system powers on and waits for initialization. The refueling valve 11 is connected to the aircraft's refueling valve; the pump-motor unit 3 is started, the pilot overflow valve 13 is adjusted to the appropriate pressure, and the pressure is observed through the pressure sensor 7 and the pressure gauge 8; When the aircraft hydraulic system is refueled to the appropriate level, stop pump 3-motor unit and disconnect refueling valve 11 from the aircraft's refueling valve.

[0041] To drain oil from the aircraft hydraulic system: First, power on the system and wait for initialization; then connect drain valve 12 to the aircraft's drain valve, and the aircraft hydraulic system will automatically drain oil to the hydraulic refueling system's tank under pressurization; when the aircraft hydraulic system's oil level drops to 0, disconnect drain valve 12 from the aircraft's drain valve.

Claims

1. An aircraft hydraulic refueling system, characterized in that, It includes an oil tank (2), a pump-motor unit (3), a check valve (4), an accumulator (9), and a refueling valve (11). The pump-motor unit (3) draws the oil in the oil tank (2) through the pressure supply line and outputs it through the check valve (4) to the accumulator (9) and the refueling valve (11) connected in parallel on the pressure supply line. The accumulator (9) and the pump-motor unit (3) provide high-pressure oil and output it to the hydraulic oil tank of the aircraft through the refueling valve (11). The refueling valve (11) is equipped with a quick plug that matches the refueling port of the hydraulic oil tank of the aircraft.

2. The aircraft hydraulic refueling system according to claim 1, characterized in that, A pressure oil filter is provided at the outlet of the check valve (4).

3. The aircraft hydraulic refueling system according to claim 1, characterized in that, The accumulator (9) and the refueling valve (11) are also equipped with a pilot relief valve (13) in parallel. The outlet of the pilot relief valve (13) is connected to the oil drain line, and the outlet of the oil drain line is connected to the oil tank (2). The refueling pressure of the pressure supply line is adjusted by controlling the pilot relief valve (13).

4. The aircraft hydraulic refueling system according to claim 1, characterized in that, The refueling valve (11) and the pressure supply line are connected and disassembled quickly via a quick connector (10).

5. The aircraft hydraulic refueling system according to claim 1, characterized in that, It also includes an oil drain valve (12) and a radiator (15). The oil drain valve (12) is connected to the oil tank (2) through an oil drain line. The oil drain line is equipped with a radiator (15). The oil drain valve (12) is equipped with a quick plug that matches the oil drain port of the aircraft's hydraulic oil tank.

6. The aircraft hydraulic refueling system according to claim 5, characterized in that, The drain valve (12) and the drain line are connected and disassembled quickly and automatically sealed via a quick connector (10).

7. The aircraft hydraulic refueling system according to claim 1, characterized in that, The oil tank (2) is equipped with a liquid level and temperature gauge (16) and an air filter (17).

8. The aircraft hydraulic refueling system according to claim 1, characterized in that, A shut-off valve (1) is provided between the pump-motor unit (3) and the oil tank (2).

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