Aircraft fatigue test hydraulic pump station with mute oil source

Abstract

The invention discloses an aircraft fatigue test hydraulic pump station with a mute oil source, which comprises an oil storage tank, a hydraulic pump station, a hydraulic pump station and a hydraulic pump station, the oil storage tank contains hydraulic oil, the hydraulic oil contains a defoaming agent, and the defoaming agent is an organic silicon defoaming agent; the hydraulic pipeline is used for allowing hydraulic oil to circulate, the hydraulic pipeline is at least provided with an oil inlet and an oil return port, and the oil inlet and the oil return port are both communicated with the containing space in the oil storage tank; the pump assembly is arranged at the top of the oil storage tank, and the pump assembly is used for driving the hydraulic oil to flow in the hydraulic pipeline; the silencing shell is arranged at the top of the oil storage tank, and the pump assembly and the hydraulic pipeline are both located in the silencing shell; and the silencing cover body is arranged in the silencing shell, the silencing cover body is arranged on the pump assembly in a covering mode, and the working noise can be greatly reduced.

Description

Technical Field

[0001] The present invention relates to the technical field of hydraulic equipment, and particularly relates to a hydraulic pump station for aircraft fatigue testing with a silent oil source. Background Art

[0002] During the aircraft fatigue test, a hydraulic system is required. The hydraulic system drives the execution components to move, thereby performing fatigue tests on certain specific structures of the aircraft. The hydraulic system mainly consists of an oil storage tank, a hydraulic pump unit, and hydraulic pipelines. The oil storage tank is used to hold hydraulic oil, and the hydraulic pump unit drives the hydraulic oil to flow in the hydraulic pipelines, thereby driving the execution components. The hydraulic pump unit generally includes a motor and a pump, and the motor drives the pump to work. In the prior art, a large amount of noise is generated during the operation of the hydraulic pump unit, causing noise pollution and resulting in a relatively harsh working environment. How to solve the problem of low-noise operation of the hydraulic pump station is an urgent technical problem to be solved. Summary of the Invention

[0003] The present invention provides a hydraulic pump station for aircraft fatigue testing with a silent oil source, which can greatly reduce the working noise.

[0004] In order to solve the above technical problems, the present invention provides a hydraulic pump station for aircraft fatigue testing with a silent oil source, including: An oil storage tank, in which hydraulic oil is contained, and an antifoaming agent is provided in the hydraulic oil. The antifoaming agent is a silicone-based antifoaming agent; Hydraulic pipelines for the flow of hydraulic oil. The hydraulic pipelines have at least an oil inlet and an oil return port, and both the oil inlet and the oil return port are communicated with the accommodation space inside the oil storage tank; A pump assembly disposed on the top of the oil storage tank, and the pump assembly is used to drive the hydraulic oil to flow in the hydraulic pipelines; A soundproof housing disposed on the top of the oil storage tank. The pump assembly and the hydraulic pipelines are both located inside the soundproof housing, and soundproof materials are provided on the inner wall of the soundproof housing; A soundproof cover disposed inside the soundproof housing, and the soundproof cover covers the pump assembly.

[0005] As a preference of the above technical solution, nanofluids are also provided in the hydraulic oil.

[0006] As a preference of the above technical solution, the hydraulic pump station for aircraft fatigue testing with a silent oil source further includes a cooling system for cooling the hydraulic oil.

[0007] As a preference of the above technical solution, the cooling system includes a cooling pipeline, a circulation pump, a first heat exchanger, a second heat exchanger and an external cold source. The circulation pump, the first heat exchanger and the second heat exchanger are all arranged on the cooling pipeline. The circulation pump is used to drive the liquid cooling working medium to flow in the cooling pipeline. The first heat exchanger is a plate heat exchanger, and the interior of the plate heat exchanger has a first space and a second space. The first space is communicated with the hydraulic pipeline so that the hydraulic oil can flow through the first space. The second space is communicated with the cooling pipeline. The hydraulic oil in the first space and the liquid cooling working medium in the second space can conduct heat exchange. The external cold source is connected to the second heat exchanger and is used to cool down the liquid cooling working medium flowing through the second heat exchanger.

[0008] As a preference of the above technical solution, a circulation space is formed inside the side wall of the sound insulation cover body, and the circulation space is communicated with the cooling pipeline so that the liquid cooling working medium can flow through the circulation space.

[0009] As a preference of the above technical solution, a plurality of tabs are formed inside the circulation space. The tabs are respectively located on both sides of the circulation space. The plurality of tabs are connected to the inner wall of the circulation space. The plurality of tabs on both sides of the circulation space are equally spaced in the vertical direction, and the plurality of tabs on one side of the circulation space and the plurality of tabs on the other side of the circulation space are staggeredly distributed.

[0010] As a preference of the above technical solution, a heat conduction structure layer is arranged on the inner wall of the sound insulation cover body, and the heat conduction structure layer is in a honeycomb shape.

[0011] As a preference of the above technical solution, sound insulation cotton is coated on the outer wall of the sound insulation cover body.

[0012] As a preference of the above technical solution, a check valve, a pressure sensor and a temperature sensor are arranged on the cooling pipeline.

[0013] As a preference of the above technical solution, the oil storage tank is placed on the installation base. Connecting columns are arranged on the lower surface of the installation base, and shock absorbers are arranged at the lower ends of the connecting columns. The shock absorbers are made of rubber.

[0014] An aircraft fatigue test hydraulic pump station with a silent oil source provided by the present invention includes an oil storage tank, a hydraulic pipeline, a pump assembly, a sound insulation housing, and a sound insulation cover. The hydraulic oil is placed in the oil storage tank, and the pump assembly is installed on the top of the oil storage tank. The pump assembly is used to drive the hydraulic oil to flow in the hydraulic pipeline. The sound insulation housing covers the top of the oil storage tank so that the pump assembly and the hydraulic pipeline are both located inside the sound insulation housing. In addition, a sound insulation cover is provided inside the sound insulation housing, and the sound insulation housing covers the entire pump assembly. The present invention reduces the noise during the working process through the sound insulation cover and the sound insulation housing. In addition, the oil storage tank contains hydraulic oil, and an antifoaming agent is provided in the hydraulic oil. The antifoaming agent is a silicone-based antifoaming agent, which can inhibit the generation of bubbles in the hydraulic oil and thus inhibit the noise generated by the rupture of bubbles during the working process. Sound insulation materials are provided on the inner wall of the sound insulation housing, which can further reduce the noise, and can greatly reduce the noise intensity during the working process, forming a low-noise hydraulic working system.

[0015] The above description is only an overview of the technical solution of the present invention. In order to be able to understand the technical means of the present invention more clearly, it can be implemented according to the content of the description. And in order to make the above and other purposes, features and advantages of the present invention more obvious and understandable, the following specifically illustrates the specific embodiments of the present invention. Brief Description of the Drawings

[0016] Figure 1 Shows the top view of an aircraft fatigue test hydraulic pump station with a silent oil source in Embodiment 1; Figure 2 Shows the installation structure schematic diagram of the sound insulation housing in Embodiment 1; Figure 3 Shows the working principle schematic diagram of the cooling system in Embodiment 1; Figure 4 Shows the cross-sectional view of the sound insulation cover in Embodiment 1; Figure 5 Shows the cross-sectional view of the sound insulation cover in Embodiment 2; In the figure: 10, oil storage tank; 20, sound insulation housing; 30, shock absorber; 40, connecting column; 50, mounting base; 60, hydraulic pipeline; 70, sound insulation housing; 80, cooling system; 701, circulation space; 702, tab; 703, heat conduction structure layer; 704, sound insulation cotton; 705, outlet pipe; 706, inlet pipe; 7021,; 7022,; 801, hydraulic pipeline; 802, circulation pump; 803, temperature sensor; 804, external cold source; 805, second heat exchanger; 806, pressure sensor; 807, one-way valve; 808, first heat exchanger. Detailed Description of the Embodiments

[0017] To make the objectives, features, and advantages of the present invention more apparent and understandable, the following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Apparently, the described embodiments are only a part of the embodiments of the present invention, rather than all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative efforts belong to the scope of protection of the present invention.

[0018] See Figures 1 to 4 , the embodiment of the present invention provides a hydraulic pump station for aircraft fatigue testing with a silent oil source, including: A storage tank 10, in which hydraulic oil is accommodated, and an antifoaming agent is provided in the hydraulic oil, and the antifoaming agent is a silicone-based antifoaming agent; A hydraulic pipeline 60 for allowing the flow of hydraulic oil. The hydraulic pipeline 60 has at least an oil inlet and an oil return port, and both the oil inlet and the oil return port are communicated with the accommodation space inside the storage tank 10; A pump assembly, arranged on the top of the storage tank 10, and the pump assembly is used to drive the hydraulic oil to flow in the hydraulic pipeline 60; A soundproof housing 20, arranged on the top of the storage tank 10, and both the pump assembly and the hydraulic pipeline 60 are located inside the soundproof housing 20, and soundproof materials are provided on the inner wall of the soundproof housing 20; A soundproof cover 70, arranged inside the soundproof housing 20, and the soundproof cover 70 covers the pump assembly.

[0019] A hydraulic pump station for aircraft fatigue testing with a silent oil source provided in this embodiment includes a storage tank 10, a hydraulic pipeline 60, a pump assembly, a soundproof housing 20, and a soundproof cover 70. The hydraulic oil is placed in the storage tank 10, and the pump assembly is installed on the top of the storage tank 10. The pump assembly is used to drive the hydraulic oil to flow in the hydraulic pipeline 60. The soundproof housing 20 covers the top of the storage tank 10 so that both the pump assembly and the hydraulic pipeline 60 are located inside the soundproof housing 20. In addition, a soundproof cover 70 is also provided inside the soundproof housing 20, and the soundproof housing 20 covers the entire pump assembly. In this embodiment, the noise during the working process is reduced by the soundproof cover 70 and the soundproof housing 20, and the noise intensity during the working process can be greatly reduced, forming a low-noise hydraulic working system. The storage tank 10 contains hydraulic oil, and an antifoaming agent is provided in the hydraulic oil. The antifoaming agent is a silicone-based antifoaming agent, which can inhibit the generation of bubbles in the hydraulic oil and thus inhibit the noise generated by the rupture of bubbles during the working process. Soundproof materials are provided on the inner wall of the soundproof housing, which can further reduce the noise.

[0020] In a further feasible implementation manner of this embodiment, nanofluids are also provided in the hydraulic oil.

[0021] In this embodiment, nanofluid is added to the hydraulic oil. The nanofluid is more conducive to heat dissipation. It can effectively reduce the oil temperature of the hydraulic oil in the working state. The hydraulic oil with a low oil temperature can not only ensure the more stable operation of the hydraulic system but also effectively inhibit the generation of bubbles in the hydraulic oil, and further effectively inhibit the noise generated by the bubble rupture.

[0022] In this embodiment, sound-absorbing materials are provided on the inner wall of the sound-absorbing housing 20, which can further reduce the noise during the working process. Specifically, the sound-absorbing materials in this embodiment can adopt materials such as sound-absorbing cotton.

[0023] In a further implementable manner of this embodiment, the aircraft fatigue test hydraulic pump station with a silent oil source further includes a cooling system 80, and the cooling system 80 is used to cool the hydraulic oil.

[0024] Since in the fatigue test, the hydraulic system is generally in a high-load long-term working state, the temperature of its hydraulic oil is relatively high. The high-temperature hydraulic oil will cause its working state to be unstable. Therefore, it is necessary to set up a cooling system 80 to cool the hydraulic oil. After the hydraulic oil is cooled by the cooling system 80, the working stability of the system can be improved.

[0025] In a further implementable manner of this embodiment, the cooling system 80 includes a cooling pipeline 801, a circulation pump 802, a first heat exchanger 808, a second heat exchanger 805, and an external cold source 804. The circulation pump 802, the first heat exchanger 808, and the second heat exchanger 805 are all arranged on the cooling pipeline 801. The circulation pump 802 is used to drive the liquid cooling working medium to flow in the cooling pipeline 801. The first heat exchanger 808 is a plate heat exchanger. The inside of the plate heat exchanger has a first space and a second space. The first space is communicated with the hydraulic pipeline 60 so that the hydraulic oil can flow through the first space. The second space is communicated with the cooling pipeline 801. The hydraulic oil in the first space and the liquid cooling working medium in the second space can perform heat exchange. The external cold source 804 is connected to the second heat exchanger 805 to cool the liquid cooling working medium flowing through the second heat exchanger 805.

[0026] In this embodiment, the second heat exchanger 805 is connected to the external cold source 804. The liquid cooling working medium inside the cooling pipeline 801 is cooled by the second heat exchanger 805, and the liquid cooling working medium cools and reduces the temperature of the hydraulic oil through the first heat exchanger 808. In this embodiment, the first heat exchanger 808 adopts a plate heat exchanger, which can not only exchange heat quickly, but also save space, and will not affect the original layout.

[0027] In a further implementable manner of this embodiment, a circulation space 701 is formed inside the side wall of the sound-absorbing cover 70, and the circulation space 701 is communicated with the cooling pipeline 801 so that the liquid cooling working medium can flow through the circulation space 701.

[0028] After the soundproof cover body 70 in this embodiment covers the pump assembly, it will affect its original heat dissipation. However, the circulation space 701 and the cooling pipeline 801 can dissipate heat from the pump assembly through the cooling system 80. In addition, since liquid cooling is used for heat dissipation, compared with the original air cooling, the noise can be reduced.

[0029] In addition, the soundproof cover body 70 in this embodiment can be made of alloys or metals with good thermal conductivity such as aluminum alloy.

[0030] In a further implementable manner of this embodiment, a plurality of fins 702 are formed inside the circulation space 701. The fins 702 are respectively located on both sides of the circulation space 701. The plurality of fins 702 are connected to the inner wall of the circulation space 701. The plurality of fins 702 located on both sides of the circulation space 701 are equally spaced in the vertical direction, and the plurality of fins 702 located on one side of the circulation space 701 and the plurality of fins 702 located on the other side of the circulation space 701 are staggeredly distributed.

[0031] In this embodiment, an inlet pipe 706 and an outlet pipe 705 are respectively arranged on both sides of the cover body 70. The inlet pipe 706 and the outlet pipe 705 are connected to the cooling system 80. The position of the inlet pipe 706 is higher than the position of the outlet pipe 705. In this embodiment, the fact that the position of the inlet pipe 706 is higher than the position of the outlet pipe 705 is more conducive to the circulation of the liquid cooling working medium. The fin 702 includes a first fin 7021 and a second fin 7022. The first fin 7021 and the second fin 7022 are respectively located on both sides of the circulation space 701, and the first fin 7021 and the second fin 7022 are connected to the inner side wall of the circulation space 701.

[0032] In a further implementable manner of this embodiment, the number of both the first fins 7021 and the second fins 7022 is multiple. The multiple first fins 7021 are equally spaced in the vertical direction and parallel to the horizontal plane. The multiple second fins 7022 are equally spaced in the vertical direction and parallel to the horizontal plane. The first fins 7021 and the second fins 7022 are staggeredly arranged.

[0033] In this embodiment, since a plurality of fins 702 are formed inside the circulation space 701, the heat transfer efficiency can be improved, and further the heat dissipation and cooling effect on the pump assembly can be improved. In addition, in the working state, there is coolant inside the circulation space 701. When sound travels from a solid to a liquid, refraction will occur, and the refracted sound wave will change the propagation direction. Combined with the staggeredly distributed fins 702, it can cause the sound wave to be attenuated after multiple reflections, and further the noise can be reduced.

[0034] In a further implementable manner of this embodiment, a heat conduction structure layer 703 is provided on the inner wall of the sound insulation cover body 70, and the heat conduction structure layer 703 is in a honeycomb shape.

[0035] The heat conduction structure layer 703 in this embodiment is in a honeycomb shape, which can not only improve the heat exchange efficiency and the cooling effect on the pump assembly, but also, the honeycomb structure can further reduce noise.

[0036] In a further implementable manner of this embodiment, a sound insulation cotton 704 is covered and provided on the outer wall of the sound insulation cover body 70.

[0037] In this embodiment, the sound insulation cotton 704 is covered and provided on the outer wall of the sound insulation cover body 70, which can further reduce noise.

[0038] In a further implementable manner of this embodiment, a one-way valve 807, a pressure sensor 806, and a temperature sensor 803 are provided on the cooling pipeline 801.

[0039] In a further implementable manner of this embodiment, the fuel tank 10 is placed on the mounting base 50, a connecting column 40 is provided on the lower surface of the mounting base 50, a shock absorber 30 is provided at the lower end of the connecting column 40, and the shock absorber 30 is made of rubber.

[0040] In this embodiment, the shock absorber 30 is provided at the lower end of the connecting column 40, and the shock absorber 30 is made of rubber, which can have a good shock absorption effect. In addition, the setting of the shock absorber 30 can also reduce the noise generated during vibration.

[0041] Embodiment 2: Refer to Figure 5 As shown, the difference between this embodiment and Embodiment 1 is only that in this embodiment, the circulation space 701 is further filled with heat exchange particles 707, and the heat exchange particles 707 are metal oxide particles or graphene particles.

[0042] In this embodiment, the circulation space 701 is further filled with heat exchange particles 707, which can not only improve the heat exchange effect, but also further reduce noise.

[0043] In the description of this specification, the description with reference to terms such as "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" means that the specific features, structures, materials, or characteristics described in connection with the embodiment or example are included in at least one embodiment or example of the present invention. Moreover, the specific features, structures, materials, or characteristics described can be combined in a suitable manner in any one or more embodiments or examples. In addition, without contradiction, those skilled in the art can combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples.

[0044] Furthermore, the terms "first" and "second" are for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the quantity of the indicated technical features. Thus, features defined with "first" and "second" may explicitly or implicitly include at least one such feature. In the description of the present invention, "a plurality of" means two or more unless otherwise specifically defined.

[0045] As described above, the above are only specific embodiments of the present invention, but the protection scope of the present invention is not limited thereto. Any person skilled in the art within the technical scope disclosed by the present invention can easily conceive of changes or substitutions, which should all be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the protection scope of the claims.

Claims

1. An aircraft fatigue test hydraulic pump station with a silent oil source, characterized in that, Comprising: An oil storage tank, in which hydraulic oil is contained, and an antifoaming agent is provided in the hydraulic oil, and the antifoaming agent is a silicone-based antifoaming agent; A hydraulic pipeline for the circulation of hydraulic oil, the hydraulic pipeline having at least an oil inlet and an oil return port, and both the oil inlet and the oil return port are communicated with the accommodation space inside the oil storage tank; A pump assembly provided on the top of the oil storage tank, and the pump assembly is used to drive the hydraulic oil to flow in the hydraulic pipeline; A soundproof housing provided on the top of the oil storage tank, the pump assembly and the hydraulic pipeline are both located inside the soundproof housing, and soundproof materials are provided on the inner wall of the soundproof housing; A soundproof cover body provided inside the soundproof housing, and the soundproof cover body covers the pump assembly.

2. The aircraft fatigue test hydraulic pump station of a silent oil source according to claim 1, characterized in that, Nanofluids are also provided in the hydraulic oil.

3. The aircraft fatigue test hydraulic pump station of a silent oil source according to claim 1, characterized in that, The aircraft fatigue test hydraulic pump station of the silent oil source further includes a cooling system for cooling the hydraulic oil.

4. The aircraft fatigue test hydraulic pump station of the silent oil source according to claim 3, characterized in that The cooling system includes a cooling pipeline, a circulation pump, a first heat exchanger, a second heat exchanger and an external cold source. The circulation pump, the first heat exchanger and the second heat exchanger are all provided on the cooling pipeline. The circulation pump is used to drive the liquid cooling working medium to flow in the cooling pipeline. The first heat exchanger is a plate heat exchanger. The inside of the plate heat exchanger has a first space and a second space. The first space is communicated with the hydraulic pipeline so that the hydraulic oil can flow through the first space. The second space is communicated with the cooling pipeline. The hydraulic oil in the first space and the liquid cooling working medium in the second space can conduct heat exchange. The external cold source is connected to the second heat exchanger for cooling the liquid cooling working medium flowing through the second heat exchanger.

5. The aircraft fatigue test hydraulic pump station of the silent oil source according to claim 4, characterized in that A circulation space is formed inside the side wall of the soundproof cover body, and the circulation space is communicated with the cooling pipeline so that the liquid cooling working medium can flow through the circulation space.

6. The aircraft fatigue test hydraulic pump station of a silent oil source according to claim 5, characterized in that, A plurality of tabs are formed inside the circulation space, and the tabs are respectively located on both sides of the circulation space. The plurality of tabs are connected to the inner wall of the circulation space. The plurality of tabs on both sides of the circulation space are equally spaced in the vertical direction. The plurality of tabs on one side of the circulation space and the plurality of tabs on the other side of the circulation space are arranged in a staggered manner. The circulation space is filled with heat exchange particles, and the heat exchange particles are metal oxide particles or graphene particles.

7. The aircraft fatigue test hydraulic pump station of the silent oil source according to claim 6, characterized in that, A heat conduction structure layer is provided on the inner wall of the soundproof cover body, and the heat conduction structure layer is in a honeycomb shape.

8. The aircraft fatigue test hydraulic pump station of the silent oil source according to claim 7, characterized in that, Soundproof cotton is coated on the outer wall of the soundproof cover body.

9. The aircraft fatigue test hydraulic pump station of a silent oil source according to claim 4, characterized in that, A one-way valve, a pressure sensor and a temperature sensor are provided on the cooling pipeline.

10. The aircraft fatigue test hydraulic pump station of a silent oil source according to claim 9, characterized in that, The oil storage tank is placed on an installation base, and connecting columns are provided on the lower surface of the installation base. Shock absorbers are provided at the lower ends of the connecting columns, and the shock absorbers are made of rubber.

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