Hydraulic oil pump system for aircraft fatigue test

Abstract

The utility model discloses an aircraft fatigue test hydraulic oil pump system, which comprises a hydraulic oil tank, a hydraulic oil pump, a hydraulic oil pump, a hydraulic oil pump, a hydraulic oil pump and a hydraulic oil pump, and an accommodating space is formed in the hydraulic oil tank and is used for accommodating hydraulic oil; the hydraulic pipeline at least comprises an oil inlet pipeline and an oil return pipeline, the inlet end of the oil inlet pipeline extends into the containing space, and the oil outlet end of the oil return pipeline extends into the containing space; the hydraulic pump is installed on the hydraulic oil tank, the hydraulic pump is arranged on the oil inlet pipeline, and the hydraulic pump is used for driving the hydraulic oil to flow in the hydraulic pipeline; the heat exchange device is connected with the oil return pipeline, the heat exchange device exchanges heat with hydraulic oil flowing back in the oil return pipeline, and the hydraulic system can effectively prevent the temperature of the hydraulic oil from rising under high-load working in the fatigue test process, so that the working stability of the hydraulic system is ensured.

Description

TECHNICAL FIELD

[0001] The utility model relates to hydraulic system technical field especially relates to a kind of aircraft fatigue test hydraulic oil pump systems. BACKGROUND

[0002] The working principle of hydraulic device is to drive hydraulic oil to flow in oil pipe by hydraulic pump, and to drive actuating component to move by hydraulic oil, in the fatigue test process, hydraulic system is in working state for a long time, its operation load is larger, so in its long-term working process, it can cause the temperature of hydraulic oil to be too high, the performance of hydraulic oil is not stable after temperature rises, especially after temperature rises, it will affect the stability of hydraulic system work. SUMMARY

[0003] The utility model provides a kind of aircraft fatigue test hydraulic oil pump systems, it can effectively prevent the temperature of hydraulic oil from rising under high load work in fatigue test process, to ensure the stability of hydraulic system work.

[0004] To solve the above technical problem, the utility model provides a kind of aircraft fatigue test hydraulic oil pump systems, comprising:

[0005] Hydraulic oil tank, the inside of the hydraulic oil tank is formed with containing space, and the containing space is used to accommodate hydraulic oil;

[0006] Hydraulic pipeline, the hydraulic pipeline at least includes oil inlet pipeline and oil return pipeline, the inlet end of the oil inlet pipeline is inserted into the containing space, and the oil outlet end of the oil return pipeline is inserted into the containing space;

[0007] Hydraulic pump, installed on the hydraulic oil tank, the hydraulic pump is arranged on the oil inlet pipeline, and the hydraulic pump is used to drive the hydraulic oil to flow in the hydraulic pipeline;

[0008] Heat exchange device, connected with the oil return pipeline, and the heat exchange device exchanges heat with the hydraulic oil flowing back in the oil return pipeline.

[0009] As the preferred technical solution, the heat exchange device includes plate heat exchanger, heat exchange circulating pipeline, heat exchange drive pump and radiator, the plate heat exchanger, heat exchange drive pump and radiator are sequentially connected into the heat exchange circulating pipeline to form heat exchange loop, the inside of the plate heat exchanger is formed with first space and second space, the first space is connected into the heat exchange circulating pipeline, the heat exchange drive pump is used to drive heat exchange medium to circulate in the heat exchange loop, the oil return pipeline is communicated with the second space to enable the hydraulic oil flowing back in the oil return pipeline to flow through the second space, and the heat exchange medium in the first space and the hydraulic oil flowing back in the second space can exchange heat.

[0010] As the preferred of the above technical scheme, the hydraulic oil tank is fixed on the mounting base.

[0011] As the preferred of the above technical scheme, the bottom of the mounting base is provided with a shock absorber.

[0012] As the preferred of the above technical scheme, the shock absorber is a rubber shock absorber.

[0013] As the preferred of the above technical scheme, the outer wall of the hydraulic oil tank is provided with a reinforcing rib, which extends along the length direction of the hydraulic oil tank.

[0014] As the preferred of the above technical scheme, the outer side of the hydraulic oil tank is provided with a sound-absorbing felt, and the inside of the sound-absorbing felt is in a honeycomb structure.

[0015] As the preferred of the above technical scheme, a separation component is arranged in the accommodating space, the separation component separates the accommodating space into a first oil storage space and a second oil storage space, the separation component is a fine-meshed screen structure, the first oil storage space is arranged corresponding to the oil inlet pipeline, the second oil storage space is arranged corresponding to the oil return pipeline, and a defoaming device is arranged in the second oil storage space.

[0016] As the preferred of the above technical scheme, an air inlet is arranged on the hydraulic oil tank, and an air filter is arranged at the air inlet.

[0017] As the preferred of the above technical scheme, a liquid level meter is arranged on the hydraulic oil tank, and a magnet steel is arranged at the bottom of the accommodating space.

[0018] The hydraulic oil pump system for aircraft fatigue test provided by the utility model, which comprises a hydraulic oil tank, a hydraulic pipeline, a hydraulic pump and a heat exchange device, when working, the hydraulic oil stored in the accommodating space enters the hydraulic pipeline through the oil inlet pipeline under the action of the hydraulic pump, and then can drive the hydraulic actuating component to realize the aircraft fatigue test, and the backflow hydraulic oil flows back to the hydraulic oil tank through the oil return pipeline, the heat exchange device is arranged on the oil return pipeline, and the backflow hydraulic oil can be cooled through the heat exchange device, which can effectively prevent the temperature of the hydraulic oil from rising under high load in the fatigue test process, so as to ensure the stability of the hydraulic system.

[0019] The above description is only a summary of the technical scheme of the utility model, in order to more clearly understand the technical means of the utility model, the specific embodiments of the utility model can be implemented according to the content of the specification, and in order to make the above and other purposes, characteristics and advantages of the utility model more obvious and easy to understand, the specific embodiments of the utility model are described below. BRIEF DESCRIPTION OF DRAWINGS

[0020] Figure 1A front view of an aircraft fatigue test hydraulic oil pump system in the embodiment is shown;

[0021] Figure 2 A left view of an aircraft fatigue test hydraulic oil pump system in the embodiment is shown;

[0022] In the figure: 10, hydraulic oil tank; 20, mounting base; 30, shock absorber; 40, hydraulic pipeline; 50, heat exchange device; 60, air filter; 70, liquid level gauge; 80, reinforcing rib; 501, heat exchange circulation pipeline; 502, plate heat exchanger. DETAILED DESCRIPTION

[0023] In order to make the purpose, characteristics and advantages of the utility model more obvious and easy to understand, the technical scheme in the utility model embodiment will be described clearly and completely in combination with the drawings in the utility model embodiment. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by the person skilled in the art without creative labor belong to the protection scope of the utility model.

[0024] Referring to Figure 1 and Figure 2 , the utility model embodiment provides an aircraft fatigue test hydraulic oil pump system, comprising:

[0025] The hydraulic oil tank 10, the inside of the hydraulic oil tank 10 is formed with containing space, and the containing space is used for containing hydraulic oil;

[0026] The hydraulic pipeline 40, the hydraulic pipeline 40 at least includes oil inlet pipeline and oil return pipeline, the inlet end of the oil inlet pipeline is inserted into the containing space, and the oil outlet end of the oil return pipeline is inserted into the containing space;

[0027] The hydraulic pump (not shown in the figure) is installed on the hydraulic oil tank 10, and the hydraulic pump is arranged on the oil inlet pipeline, and the hydraulic pump is used to drive the hydraulic oil to flow in the hydraulic pipeline 40;

[0028] The heat exchange device 50 is connected with the oil return pipeline, and the heat exchange device 50 exchanges heat with the hydraulic oil flowing back in the oil return pipeline.

[0029] The embodiment provides a hydraulic oil pump system for aircraft fatigue test, which comprises a hydraulic oil tank 10, a hydraulic pipeline 40, a hydraulic pump and a heat exchange device 50.

[0030] In a further implementable manner of the embodiment, the heat exchange device 50 comprises a plate heat exchanger 502, a heat exchange circulation pipeline 501, a heat exchange driving pump (not shown in the figure) and a radiator (not shown in the figure), the plate heat exchanger 502, the heat exchange driving pump and the radiator are sequentially connected to the heat exchange circulation pipeline 501 to form a heat exchange loop, the plate heat exchanger 502 comprises a first space and a second space, the first space is connected to the heat exchange circulation pipeline 501, the heat exchange driving pump is used for driving a heat exchange medium to circulate in the heat exchange loop, the oil return pipeline is in communication with the second space so that the hydraulic oil flowing back in the oil return pipeline can flow through the second space, and the heat exchange medium in the first space and the hydraulic oil flowing back in the second space can exchange heat.

[0031] The plate heat exchanger 502 is adopted in the heat exchange device 50, which not only facilitates the structural layout, but also has better heat exchange effect and can quickly cool the hydraulic oil.

[0032] In a further implementable manner of the embodiment, the hydraulic oil tank 10 is fixed on the mounting base 20.

[0033] In the embodiment, the hydraulic oil tank 10 is fixed on the mounting base 20, so that the structure is more stable.

[0034] In a further implementable manner of the embodiment, the bottom of the mounting base 20 is provided with a shock absorber 30.

[0035] In the embodiment, the bottom of the mounting base 20 is provided with the shock absorber 30, so that the shock absorber 30 can play a shock absorption role.

[0036] In a further implementable manner of the embodiment, the shock absorber is a rubber shock absorber.

[0037] In a further implementable manner of the embodiment, the outer wall of the hydraulic oil tank 10 is provided with a reinforcing rib 80, and the reinforcing rib 80 extends along the length direction of the hydraulic oil tank 10.

[0038] The reinforcing rib 80 in the embodiment can improve the strength of the hydraulic oil tank 10, and the hydraulic oil tank 10 in the embodiment is a stainless steel tank.

[0039] In a further implementable manner of the embodiment, a sound-absorbing felt is arranged on the outer side of the hydraulic oil tank 10, and the inside of the sound-absorbing felt is in a honeycomb structure.

[0040] In a further implementable manner of the embodiment, a separation component is arranged in the containing space, the separation component separates the containing space into a first oil storage space and a second oil storage space, the separation component is a fine-meshed screen structure, the first oil storage space is arranged corresponding to the oil inlet pipeline, the second oil storage space is arranged corresponding to the oil return pipeline, and a defoaming device is arranged in the second oil storage space.

[0041] In the embodiment, the separation component separates the containing space into a first oil storage space and a second oil storage space, the separation component is a fine-meshed screen structure, the first oil storage space is arranged corresponding to the oil inlet pipeline, which can effectively prevent the bubbles generated in the oil return process from directly entering the oil inlet pipeline, the defoaming device can eliminate the bubbles in the oil return, and the separation component is a fine-meshed screen structure, which not only has a separation function, but also has a defoaming function.

[0042] In a further implementable manner of the embodiment, an air inlet is arranged on the hydraulic oil tank 10, and an air filter 60 is arranged at the air inlet.

[0043] In a further implementable manner of the embodiment, a liquid level meter 70 is arranged on the hydraulic oil tank 10, and a magnetic steel is arranged at the bottom of the containing space.

[0044] In the embodiment, the bottom of the containing space is provided with a magnetic steel, which can adsorb iron filings in the oil, and facilitate maintenance.

[0045] In the description of the specification, the description of the terms "one embodiment", "some embodiments", "an example", "a specific example", 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 utility model. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, the skilled in the art can combine and combine the different embodiments or examples described in the specification and the features of the different embodiments or examples without contradiction.

[0046] In addition, the terms "first", "second", "third", "fourth", "fifth", "sixth", "seventh" and "eighth" are only used for descriptive purpose and are not to be construed as indicating or implying relative importance or a specific number of the technical features indicated. Thus, the features defined with "first", "second", "third", "fourth", "fifth", "sixth", "seventh" and "eighth" can explicitly or implicitly include at least one of the features. In the description of the present application, the meaning of "a plurality of" is two or more than two, unless otherwise specifically limited.

[0047] The above description is merely a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any person skilled in the art can easily think of changes or replacements within the technical range disclosed by the present application, which should be covered within the protection scope of the present application. Therefore, the protection scope of the present application should be subject to the protection scope of the claims.

Claims

1. An aircraft fatigue test hydraulic oil pump system, characterized by, The application relates to a hydraulic oil tank. The hydraulic oil tank comprises a hydraulic oil tank body, a hydraulic oil tank cover, a hydraulic oil tank bottom, a hydraulic oil tank inlet, a hydraulic oil tank outlet, a hydraulic oil tank air inlet, a hydraulic oil tank liquid level meter, a hydraulic oil tank magnetic steel, a hydraulic oil tank reinforcing rib, a hydraulic oil tank sound-absorbing felt, a hydraulic oil tank mounting base, a hydraulic oil tank shock absorber, a hydraulic oil tank partition component, a hydraulic oil tank oil defoaming device, a hydraulic oil tank heat exchange device, a hydraulic oil tank hydraulic pump, a hydraulic oil tank oil inlet pipeline, a hydraulic oil tank oil return pipeline, a hydraulic oil tank heat exchange circulating pipeline, a hydraulic oil tank heat exchange driving pump, a hydraulic oil tank heat exchange plate, and a hydraulic oil tank heat radiator. The hydraulic oil tank heat exchange device comprises a heat exchange plate, a heat exchange circulating pipeline, a heat exchange driving pump, and a heat radiator. The heat exchange plate, the heat exchange driving pump, and the heat radiator are sequentially connected to the heat exchange circulating pipeline to form a heat exchange loop. The first space of the heat exchange plate is connected to the heat exchange circulating pipeline.

2. The aircraft fatigue test hydraulic pump system of claim 1, wherein, The heat exchange driving pump is used for driving a heat exchange medium to circularly flow in the heat exchange loop.

3. The hydraulic oil pump system for fatigue testing of an aircraft as defined in claim 1, wherein, The second space of the heat exchange plate is connected to the oil return pipeline.

4. The aircraft fatigue test hydraulic pump system of claim 3, wherein, The heat exchange medium in the first space and the returned hydraulic oil in the second space can exchange heat.

5. The aircraft fatigue test hydraulic pump system of claim 4, wherein, The hydraulic oil tank is fixed on the mounting base.

6. The hydraulic oil pump system for fatigue testing of an aircraft as defined in claim 1, wherein, The bottom of the mounting base is provided with a shock absorber.

7. The hydraulic oil pump system for fatigue testing of an aircraft as defined in claim 1, wherein, The shock absorber is a rubber shock absorber.

8. The hydraulic oil pump system for fatigue testing of an aircraft as defined in claim 1, wherein, The outer wall of the hydraulic oil tank is provided with a reinforcing rib which extends along the length direction of the hydraulic oil tank.

9. The hydraulic oil pump system for fatigue testing of an aircraft as defined in claim 1, wherein, The outer side of the hydraulic oil tank is provided with sound-absorbing felt.

10. The hydraulic fluid pump system for aircraft fatigue testing of any one of claims 1 to 9, wherein, The inside of the sound-absorbing felt is in a honeycomb structure. The inside of the hydraulic oil tank is provided with a partition component. The partition component is a fine-meshed screen structure. The first oil storage space is correspondingly arranged with the oil inlet pipeline. The second oil storage space is correspondingly arranged with the oil return pipeline. The second oil storage space is provided with an oil defoaming device. The hydraulic oil tank is provided with an air inlet. The air inlet is provided with an air filter. The hydraulic oil tank is provided with a liquid level meter. The bottom of the hydraulic oil tank is provided with a magnetic steel.

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