Aircraft fuel pump work simulator

Abstract

The utility model relates to an aircraft fuel pump, in particular to an aircraft fuel pump work simulator. The performance parameters of the fuel pump under different working conditions can be effectively solved and verified, accurate simulation and verification are achieved, and meanwhile many problems existing in traditional test equipment can be solved. Comprising a rectangular main frame which is divided into an upper space and a lower space through a partition plate. Wherein the fuel tank is mounted in the upper space, and the fuel tank is connected with an aircraft fuel pump through a matched pipeline; the lower space is used for accommodating the electrical cabinet and a part of matched pipelines. Rib plates are arranged in the oil tank and used for strengthening stress of the oil tank. The two sides of the oil tank are respectively provided with an oil collecting tray, and the oil tank and the oil collecting trays are integrally formed. A strip-shaped liquid level indicating part is arranged on the side wall of the oil tank, is made of organic glass and is used for conveniently observing the height change of the liquid level of the oil tank; a fluororubber plate with the thickness of 3 mm is adopted between the liquid level indicating window and the oil tank to serve as a sealing gasket and used for guaranteeing the sealing performance.

Description

Technical Field

[0001] The utility model relates to an aircraft fuel pump, in particular to an aircraft fuel pump working simulator. Background Art

[0002] As one of the key components in the aircraft fuel system, the fuel pump undertakes the important responsibility of ensuring the smooth circulation of fuel in each fuel tank compartment. Therefore, accurately detecting the performance of the fuel pump is crucial for comprehensively evaluating the effectiveness of the entire aircraft fuel system and has far-reaching implications. The main performance indicators of the fuel pump include temperature, pressure, flow rate, and current parameters.

[0003] Currently, the testing of fuel pump performance usually needs to be completed with the help of a large test turntable. This test turntable consists of components such as an outer frame, an inner frame, and a simulated fuel tank. Among them, the fuel pump is placed inside the simulated fuel tank, and the installation of the fuel tank pipeline and other components mimics the real state on the aircraft. Under such conditions, relatively realistic performance test results of the fuel pump can be obtained.

[0004] The large test bench has extremely high requirements for the floor area and space of the workshop. Due to the generally large size of the test bench, the effective space of the workshop is generally required to be: the height is not less than 15 meters, the length is not less than 50 meters, and the width is not less than 30 meters. It also needs to be equipped with infrastructure such as an oil depot and a pit. Different aircraft models also need to be equipped with different test pieces such as inner frames and fuel tanks, as well as pipelines inside the fuel tank and other finished products. This makes the test cost extremely high.

[0005] In addition, the large test bench is actually a test of the entire fuel system, rather than a special test of the fuel pump performance. Often, the performance parameters of the fuel pump cannot be fully tested. Under the premise of the design principle of the fuel system and the technical requirements such as simulating the real form on the aircraft, it is impossible to randomly add or modify the original design structure on the fuel pipeline. This makes the "fuel pump performance test results" obtained in this ideal simulated test environment of the test bench may not be completely accurate.

[0006] Furthermore, the tests conducted on the large test bench are generally comprehensive tests of the entire fuel system. At this time, if the fuel pump fails, it will affect the normal progress of other test items. This means that all components, including the fuel pump, must work together to achieve the expected results. When there are significant differences between the results of the comprehensive simulation test and the theoretical calculation, it is very difficult to directly determine whether this is due to the problem of the fuel system structure design or the insufficient performance of the fuel pump. Even if the problem is found through system troubleshooting, it will waste a lot of time, greatly affect the test cycle, and extend the R & D cycle of related products. Summary of the Invention

[0007] The utility model aims at the defects existing in the prior art and provides an aircraft fuel pump working simulator.

[0008] To achieve the above object, the utility model adopts the following technical solutions, including a rectangular main frame, characterized in that the rectangular main frame is divided into upper and lower spaces by a partition board; wherein, the fuel tank is installed in the upper space, and the fuel tank is connected to the aircraft fuel pump through a supporting pipeline; the lower space is used to accommodate the electrical cabinet and a part of the supporting pipeline.

[0009] The fuel tank is internally provided with stiffening plates for strengthening the stress of the fuel tank; and an oil collecting tray is installed on each side of the fuel tank, and the fuel tank and the oil collecting tray are integrally formed.

[0010] A strip-shaped liquid level indicating part is arranged on the side wall of the fuel tank. The liquid level indicating part is made of plexiglass and is used to facilitate the observation of the change of the liquid level height of the fuel tank; a 3-mm-thick fluororubber plate is used as a gasket between the liquid level indicating window and the fuel tank to ensure the sealing performance.

[0011] An oil baffle is further arranged on the top of the electrical cabinet to prevent the electrical cabinet from being affected by oil leakage.

[0012] Further, the fuel tank is welded and made of 5A06 aluminum plate with a thickness of 5 mm.

[0013] Further, a process lifting ring is arranged on the top of the rectangular main frame.

[0014] Further, a fuel filling port is arranged on the upper part of the fuel tank, an oil discharge port is arranged at the bottom of the fuel tank, and oil discharge ports are also arranged on both sides of the oil collecting tray.

[0015] Further, the fuel filling port has a flange structure, and the fuel filling port and the fuel filling cap are connected by threads; the fuel filling diameter of the fuel filling port is 48 mm.

[0016] Further, the oil discharge port is controlled by a manual ball valve with a pressure bearing of 3 MPa for oil discharge, and a flare fitting is installed in a supporting manner at the oil discharge port to extend the oil discharge pipeline.

[0017] Further, the size of the fuel tank matches the fuel pump, and the fuel tank is provided with an overflow hole.

[0018] Further, an observation window is also arranged on the outer wall of the fuel tank. The observation window is made of plexiglass and is used for observing the operating state of the fuel pump.

[0019] Furthermore, the aircraft fuel pump working simulator also includes a temperature sensor, a pressure sensor, a flow sensor and a current sensor; among them, the temperature sensor is used to monitor the fuel temperature, and is installed inside the fuel tank or at the inlet and outlet of the fuel pump; the pressure sensor is used to monitor the fuel pressure, and is installed at the outlet of the fuel pump or the supporting pipeline of the fuel pump; the current sensor is installed in the electrical cabinet, and is used to monitor the power supply line of the fuel pump motor to ensure the normal operation of the fuel pump; the flow sensor is used to monitor the flow of fuel, and the flow sensor is installed at the outlet of the fuel pump or the supporting pipeline of the fuel pump.

[0020] Compared with the prior art, the utility model has beneficial effects.

[0021] The aircraft fuel pump working simulator of the utility model can not only effectively solve and verify the performance parameters of the fuel pump under different working conditions and realize accurate simulation and verification, but also overcome many problems existing in traditional test equipment, such as long manufacturing cycle, complex structure, large size, insufficient flexibility, high cost and difficult test operation, thereby providing a more efficient, economical and flexible test solution. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] The utility model is further described below in conjunction with the accompanying drawings and specific implementation methods. The protection scope of the utility model is not limited to the following descriptions.

[0023] Figure 1 It is a structural diagram of an aircraft fuel pump working simulator.

[0024] Figure 2 Schematic diagram of the rectangular main frame structure in the embodiment.

[0025] Figure 3 Schematic diagram of the connection between the oil tank and the oil collecting pan in the embodiment.

[0026] Figure 4 2 is a schematic diagram of the fuel filler port structure in the embodiment.

[0027] Figure 5 Schematic diagram of the oil drain port structure in the embodiment.

[0028] Figure 6 Schematic diagram of the oil shield structure in the embodiment.

[0029] In the figure, 1. lifting ring; 2. oil tank; 3. liquid level indicator; 4. rectangular main frame; 5. observation window; 6. oil shield; 7. electrical cabinet; 8. adjustable feet; 9. casters; 10. partition; 11. upper space; 12. lower space; 13. oil collecting tray; 14. pagoda joint. DETAILED DESCRIPTION

[0030] To make the objectives, technical solutions, and beneficial effects of the embodiments of the present utility model clearer, the following will clearly and completely describe the technical solutions in the embodiments of the present utility model with reference to the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are some, but not all, of the embodiments of the present utility model.

[0031] As Figures 1-6 shown, the aircraft fuel pump working simulator includes a rectangular main frame 4, and adjustable floor feet 8 and casters 9 are provided at the bottom of the rectangular main frame 4; the rectangular main frame 4 is divided into upper and lower spaces by a partition 10; among them, the fuel tank 2 is installed in the upper space 11, and the fuel tank 2 is connected to the aircraft fuel pump through a matching pipeline; the lower space 12 is used to accommodate the electrical cabinet 7 and a part of the matching pipeline. The fuel tank 2 is internally provided with stiffeners for strengthening the force on the fuel tank 2; and an oil sump 13 is installed on each side of the fuel tank 2, and the fuel tank 2 and the oil sump 13 are integrally formed. A strip-shaped liquid level indicating portion 3 is provided on the side wall of the fuel tank 2, and the material of the liquid level indicating portion 3 is plexiglass, which is used to facilitate observing the change in the liquid level height of the fuel tank 2; a 3-mm-thick fluororubber sheet is used as a gasket between the liquid level indicating window and the fuel tank 2 to ensure the sealing performance. A splash guard 6 is also provided on the top of the electrical cabinet 7 to prevent the electrical cabinet 7 from being affected by oil leakage.

[0032] Preferably, the fuel tank 2 is welded and made of 5A06 aluminum plate with a thickness of 5 mm. First of all, 5A06 is an aluminum alloy material. Compared with other metal materials such as steel, it has a lower density, which can significantly reduce the weight of the fuel tank 2, thereby reducing the weight of the entire aircraft, improving fuel efficiency and flight performance. Secondly, 5A06 aluminum alloy has good corrosion resistance and can maintain stable performance for a long time in a harsh environment, extending the service life of the fuel tank 2 and reducing maintenance costs. Moreover, 5A06 aluminum alloy has good welding performance, which can ensure the quality of the weld seam, improve the overall structural strength and sealing performance of the fuel tank 2, and prevent fuel leakage.

[0033] Embodiment 1: A process lifting ring 1 is provided at the top of the rectangular main frame 4. During the manufacturing process of the bench (rectangular main frame 4), it is necessary to adjust the angle and size of the bench, especially during the painting and transportation of the bench. As an indispensable part for the movement of the auxiliary equipment. Although the lifting ring 1 uses high-strength large-sized bolts, due to the large weight of the overall equipment after assembly, in order to reduce the overall weight of the equipment, except for the main load-bearing frame using large-sized profiles, the upper support columns use profiles with smaller specifications, and there is a risk of deformation of the upper frame after being stressed by hoisting. Therefore, the process lifting ring 1 cannot be used for the hoisting of the final overall equipment.

[0034] To sum up, the process lifting ring 1 plays an important auxiliary role during the manufacturing and transportation processes. However, due to the reasons of structural design and weight distribution, it cannot be used for the overall hoisting of the final equipment to avoid frame deformation.

[0035] Embodiment 2, fuel tank 2:

[0036] The oil tank 2 is welded with 5mm thick 5A06 aluminum plate, and the appearance of the oil tank 2 is sprayed to make the oil tank 2 have a good appearance. The internal rib plate of the oil tank 2 effectively strengthens the force performance of the oil tank 2. The oil tank 2 and the oil collecting pan 13 are integrally formed. Generally, since there are many joints on the pipeline, oil leakage is easy to occur, so the oil collecting pan 13 is placed on both sides of the pipeline to meet the needs. At the same time, the effective volume of the oil tank 2 can be increased to the maximum.

[0037] The top of the fuel tank 2 is provided with a refueling port, and the bottom is provided with an oil drain port. The oil drain ports are arranged on both sides of the oil collecting pan 13. The refueling port adopts a flange design and is threadedly connected to the refueling cap. The refueling port diameter is 48 mm. It meets the diameter of most refueling guns on the market. The size of the fuel tank 2 is designed according to the size of the fuel pump of the main models on the market. The overflow hole is designed at the bottom of the bulkhead of the fuel tank 2, and the oil return compartment of the fuel tank 2 is heightened to prevent the return oil from affecting the oil inlet of the pump.

[0038] The integrated design of the oil collecting pan 13 and the oil tank 2 is easier to process. According to past experience, oil leakage often occurs at the joints. An integrated integrated oil collecting pan 13 is provided for targeted oil collection, which can save space and prevent the defect of incomplete oil collection in the secondary designed oiling pan. In summary, the integrated design of the oil collecting pan 13 and the oil tank 2 not only simplifies the processing technology, but also improves the sealing and reliability of the system, saves space, and effectively prevents secondary pollution.

[0039] The oil drain port uses a manual ball valve with a pressure of 3 MPa for oil drain control. A pagoda connector 14 is installed to extend the oil drain pipeline. Among them:

[0040] Manual ball valve: The oil drain port uses a manual ball valve with a pressure resistance of 3 MPa for oil drain control, ensuring that the oil drain can be safely and reliably controlled even in a high-pressure environment.

[0041] Pagoda connector 14: The pagoda connector 14 is installed to extend the oil drain line to increase the flexibility and reliability of the oil drain line.

[0042] In summary, the oil drain port uses a manual ball valve with a pressure resistance of 3 MPa and a pagoda connector 14 to extend the oil drain pipeline, aiming to ensure safe and reliable oil draining operations under high pressure environments while increasing the flexibility and reliability of the pipeline.

[0043] Embodiment 3, liquid level indication:

[0044] The liquid level indicator is made of organic glass, through which the change of the liquid level height in the oil tank 2 can be visually seen. A 3 mm thick fluororubber plate is used as a sealing gasket between the liquid level gauge and the oil tank 2, which can effectively ensure the sealing of the liquid level indicator.

[0045] Example 4, oil baffle 6:

[0046] To prevent oil leakage that may occur when the lower pipelines of the fuel tank 2 shake or are affected by external forces during transportation. To protect the electrical cabinet 7 from being affected by oil leakage.

[0047] Example 5, observation window 5: Made of plexiglass, mainly used for observing the operating state of the fuel pump. The sealing condition and structural form are the same as those of the liquid level indicator.

[0048] Preferably, the aircraft fuel pump working simulator further includes a temperature sensor, a pressure sensor, a flow sensor and a current sensor; wherein, the temperature sensor is used to monitor the fuel temperature and is installed inside the fuel tank 2 or at the inlet and outlet of the fuel pump; the pressure sensor is used to monitor the fuel pressure and is installed at the outlet of the fuel pump or on the pipeline supporting the fuel pump; the current sensor is installed inside the electrical cabinet 7 and is used to monitor the power supply line of the fuel pump motor to ensure the normal operation of the fuel pump; the flow sensor is used to monitor the fuel flow rate and is installed at the outlet of the fuel pump or on the pipeline supporting the fuel pump.

[0049] The above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements on some or all of the technical features; therefore, these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the scope defined by the claims of the present invention.

Claims

1. An aircraft fuel pump working simulator, comprising a rectangular main frame (4), characterized in that: The rectangular main frame (4) is divided into an upper space and a lower space by a partition (10); wherein the oil tank (2) is installed in the upper space (11), and the oil tank (2) is connected to the aircraft fuel pump through a matching pipeline; the lower space (12) is used to accommodate the electrical cabinet (7) and a part of the matching pipeline; The oil tank (2) has a built-in rib plate for strengthening the force applied to the oil tank (2); an oil collecting pan (13) is installed on each side of the oil tank (2), and the oil tank (2) and the oil collecting pan (13) are integrally formed; The side wall of the oil tank (2) is provided with a strip-shaped liquid level indicator (3), the liquid level indicator (3) being made of organic glass and being used to facilitate observation of changes in the liquid level height of the oil tank (2); a 3 mm thick fluororubber sheet is used as a sealing gasket between the liquid level indicator window and the oil tank (2) to ensure sealing performance; An oil shield (6) is also provided on the top of the electrical cabinet (7) to prevent the electrical cabinet (7) from being affected by oil leakage.

2. The aircraft fuel pump operation simulator according to claim 1, characterized in that: The oil tank (2) is made by welding 5 mm thick 5A06 aluminum plates.

3. The aircraft fuel pump operation simulator according to claim 1, characterized in that: A process hanging ring (1) is provided on the top of the rectangular main frame (4).

4. The aircraft fuel pump operation simulator according to claim 1, characterized in that: The top of the oil tank (2) is provided with a refueling port, the bottom of the oil tank (2) is provided with an oil drain port, and both sides of the oil collecting pan (13) are also provided with oil drain ports.

5. The aircraft fuel pump operation simulator according to claim 4, characterized in that: The refueling port has a flange structure, and the refueling port and the refueling cap are connected by threads; the refueling port diameter of the refueling port is 48 mm.

6. The aircraft fuel pump operation simulator according to claim 4, characterized in that: The oil drain port adopts a manual ball valve with a pressure bearing capacity of 3 MPa for oil drain control, and a pagoda connector (14) is installed in the oil drain port to extend the oil drain pipeline.

7. The aircraft fuel pump operation simulator according to claim 1, characterized in that: The size of the oil tank (2) matches that of the fuel pump, and the oil tank (2) is provided with an overflow hole.

8. The aircraft fuel pump operation simulator according to claim 1, characterized in that: The outer wall of the fuel tank (2) is also provided with an observation window (5), the observation window (5) being made of organic glass and being used for observing the operating status of the fuel pump.

9. The aircraft fuel pump operation simulator according to claim 1, characterized in that: The aircraft fuel pump working simulator also includes a temperature sensor, a pressure sensor, a flow sensor and a current sensor; wherein the temperature sensor is used to monitor the fuel temperature and is installed inside the fuel tank (2) or at the inlet and outlet of the fuel pump; the pressure sensor is used to monitor the fuel pressure and is installed at the outlet of the fuel pump or at the supporting pipeline of the fuel pump; the current sensor is installed in the electrical cabinet (7) and is used to monitor the power supply line of the fuel pump motor to ensure the normal operation of the fuel pump; the flow sensor is used to monitor the flow of the fuel and is installed at the outlet of the fuel pump or at the supporting pipeline of the fuel pump.

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