Aviation environment simulator

Abstract

The aviation environment simulator comprises an oil tank, a heating and pressurizing pipeline and a cooling pipeline, and the heating and pressurizing pipeline comprises an oil-gas separator, a circulating pump, a heater and an inlet of a three-way valve which are sequentially connected end to end through a pipeline. A first outlet of the three-way valve is sequentially connected with a sealed simulation cavity, a first valve, a second valve and a filter through pipelines, the filter is communicated with an oil-gas separator, and a second outlet of the three-way valve is sequentially connected with a second one-way valve and the oil-gas separator through pipelines; the cooling pipeline comprises a liquid cooling device, and the liquid cooling device communicates with the cooling water channel end to end through a first circulating cooling pipeline. The temperature and the pressure of the whole pipeline are dynamically adjusted through the heater, the circulating pump, the cooling pipeline and other components, the pressure in the sealed simulation cavity is ensured to be stable and constant, the high-temperature and high-pressure environment in aviation is simulated, and the service life and the degradation condition of components such as a bearing in the high-temperature and high-pressure environment of the sealed simulation cavity can be conveniently verified.

Description

Technical Field

[0001] The invention relates to the technical field of aviation test equipment, and in particular to an aviation environment simulator. Background Art

[0002] Aircraft bearings and other parts are important components of modern aircraft operating systems, and they need to operate in high-temperature, high-pressure aviation environments. Compared with general bearings, the operating environment of aircraft bearings is more severe, and their service life will also be affected. In order to evaluate the life and degradation of aircraft bearings under aviation operating conditions such as high temperature and high pressure, it is necessary to develop a special aviation environment simulation device to simulate the high-temperature and high-pressure environment of the actual use of the aircraft in the early design and later verification of the bearings, and verify the life and degradation of components such as bearings. Because the medium will generate heat in a high-pressure environment, causing the temperature to continue to rise, and the high-pressure environment needs to be achieved in a closed environment, the existing equipment cannot maintain a constant high-temperature and high-pressure environment at the same time.

[0003] Therefore, an aviation environment simulator is designed to simulate the life and degradation process of components such as bearings in a high temperature and high pressure environment of an aircraft, and to verify the performance of components such as bearings. Summary of the invention

[0004] The purpose of the present invention is to provide an aviation environment simulator, which uses components such as heaters, circulating pumps, cooling pipelines, etc. to dynamically adjust the temperature and pressure of the entire pipeline, ensure the pressure and stability in the sealed simulation cavity are constant, simulate the high temperature and high pressure environment in aviation, and facilitate verification of the life and degradation of components such as bearings in the high temperature and high pressure environment of the sealed simulation cavity.

[0005] The embodiment of the present invention is achieved as follows:

[0006] The present invention provides an aviation environment simulator, comprising a fuel tank, a heating and pressurizing pipeline and a cooling pipeline, wherein the fuel tank is higher than the heating and pressurizing pipeline and the cooling pipeline; the heating and pressurizing pipeline comprises an oil-gas separator, a circulation pump, a heater, and an inlet of a three-way valve which are connected in sequence through pipelines, wherein a first outlet of the three-way valve is connected in sequence with a sealed simulation cavity, a first valve, a second valve and a filter through a pipeline, wherein the filter is communicated with the oil-gas separator, and a second outlet of the three-way valve is connected in sequence with a second one-way valve and an oil-gas separator through a pipeline; the fuel tank is connected in sequence with a first one-way valve and an oil-gas separator through a pipeline; the cooling pipeline comprises a liquid cooling device, a cooling water channel is provided on the sealed simulation cavity, and the liquid cooling device is connected in sequence with the cooling water channel through a first circulating cooling pipeline, so as to cool the sealed simulation cavity.

[0007] Furthermore, the oil tank is provided with an oil filling port and an oil overflow port, a liquid level controller is provided in the oil tank, and a one-way throttle valve is provided on the pipeline between the oil tank and the first one-way valve. The oil tank is filled with hydraulic medium, such as hydraulic oil, through the oil filling port. If too much is filled, it can be discharged through the oil overflow port. At the same time, the liquid level controller can also sense the liquid level height of the medium in the oil tank in real time, which is convenient for filling or discharging the hydraulic medium.

[0008] Furthermore, an oil discharge port is provided on the pipeline between the oil-gas separator and the circulation pump to facilitate the discharge of the hydraulic medium.

[0009] Furthermore, the pipeline between the oil discharge port and the circulation pump is connected to the oil tank through an oil replenishment pipeline. When the hydraulic medium in the pipeline is insufficient, it is directly replenished from the oil tank through the oil replenishment pipeline.

[0010] Furthermore, a heat exchanger is provided on the pipeline between the heater and the three-way valve, and the heat exchanger is connected end to end with the liquid cooling device through a second circulating cooling pipeline, so as to cool the hydraulic medium.

[0011] Furthermore, a first temperature sensor is provided on the pipe between the heater and the heat exchanger, a second temperature sensor is provided on the heater, a cooling solenoid valve is provided at the cooling water inlet of the heat exchanger, and a temperature controller is also provided on the heating and pressurizing pipeline, and the temperature controller is used to control the operation of the heater and the cooling solenoid valve.

[0012] Furthermore, a relief valve is provided on the pipeline between the sealing simulation chamber and the second valve, and the relief valve is arranged in parallel with the first valve. The relief valve functions as a safety valve and is used to control the pressure of the hydraulic medium at the outlet of the sealing simulation chamber.

[0013] Furthermore, a third one-way valve is provided on the pipeline between the circulation pump and the heater, and pressure sensors are provided on the pipeline between the heater and the three-way valve and between the circulation pump and the heater.

[0014] Furthermore, the oil tank, heating and pressurizing pipelines and cooling pipelines are all arranged in a test shell, the test shell is made of carbon fiber, and a universal wheel is arranged at the bottom of the test shell.

[0015] Compared with the prior art, the aviation environment simulator provided by the present invention has at least the following features:

[0016] Beneficial effects:

[0017] 1. Through the heater, circulation pump, cooling pipeline and other components, the temperature and pressure of the entire pipeline are adjusted dynamically to ensure the pressure and stability in the sealing simulation cavity, so that the hydraulic medium entering the sealing simulation cavity meets the set requirements. The bearings and other components to be tested are placed in the sealing simulation cavity to simulate the high temperature and high pressure environment in aviation, which is convenient for verifying the life and degradation of bearings and other components under high temperature and high pressure environment;

[0018] 2. The second outlet of the three-way valve is provided with a second one-way valve, which is used to separate the pressure of the hydraulic medium after the heater comes out, ensuring that the pressure of the hydraulic medium entering the sealed simulation chamber is too high, avoiding excessive pressure at the three-way valve, causing damage to the three-way valve, and at the same time, after the hydraulic medium in the sealed simulation chamber is filled, the hydraulic medium can be allowed to flow out directly from the second one-way valve, so that the pressure of the hydraulic medium entering the sealed simulation chamber is close to 0;

[0019] 3. An overflow valve and a first valve are connected in parallel between the sealed simulation chamber and the second valve. The overflow valve acts as a safety valve and can control the pressure of the hydraulic medium. Through the setting of mechanical valves such as the three-way valve, the second one-way valve, and the overflow valve, the temperature and pressure of the entire aviation environment simulator can reach above 200°C without being affected, thus avoiding the failure of existing electronic components in high temperature environments. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required for use in the embodiments are briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present invention and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without creative work.

[0021] Figure 1 It is a schematic diagram of the appearance structure of the present invention;

[0022] Figure 2 It is a schematic diagram of the internal pipeline flow of the present invention;

[0023] Figure 3 It is a structural schematic diagram of the heating and pressurizing pipeline in the present invention;

[0024] Figure 4 It is a schematic diagram of the structure of the cooling pipeline in the present invention;

[0025] Icons: 1. Oil tank; 11. Oil filling port; 12. Oil overflow port; 13. Liquid level controller; 14. One-way throttle valve; 15. Oil drain port; 16. Oil replenishment pipeline; 2. Oil-gas separator; 3. Circulation pump; 4. Heater; 5. Sealed simulation chamber; 6. Filter; 7. Liquid cooling device; 701. Cooling water channel; 702. First circulation cooling pipeline; 703. Heat exchanger; 704. Second circulation cooling pipeline; 705. Cooling solenoid valve; 8. Temperature controller; 9. Overflow valve; 10. Shell; 1001. Universal wheel; 101. Three-way valve; 102. First valve; 103. Second valve; 201. First one-way valve; 202. Second one-way valve; 203. Third one-way valve; 204. Fourth one-way valve; 301. First temperature sensor; 302. Second temperature sensor. DETAILED DESCRIPTION

[0026] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0027] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0028] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0029] In addition, the terms "horizontal", "vertical" and the like do not mean that the components are required to be absolutely horizontal or suspended, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0030] In the description of the present invention, it is also necessary to explain that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two elements. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0031] Embodiment 1: Figure 1-4 As shown, the present invention provides an aviation environment simulator, including a fuel tank 1, a heating and pressurizing pipeline and a cooling pipeline, wherein the fuel tank 1 is higher than the heating and pressurizing pipeline and the cooling pipeline; the heating and pressurizing pipeline includes an oil-gas separator 2, a circulating pump 3, a heater 4, and an inlet of a three-way valve 101 connected in sequence through pipelines, the first outlet of the three-way valve 101 is connected in sequence with a sealed simulation cavity 5, a first valve 102, a second valve 103 and a filter 6 through a pipeline, the filter 6 is connected with the oil-gas separator 2, the second outlet of the three-way valve 101 is connected in sequence with a second one-way valve 202 and the oil-gas separator 2 through a pipeline; the fuel tank 1 is connected in sequence with a first one-way valve 201 and the oil-gas separator 2 through a pipeline; the cooling pipeline includes a liquid cooling device 7, a cooling water channel 701 is provided on the sealed simulation cavity 5, and the liquid cooling device 7 is connected in sequence with the cooling water channel 701 through a first circulating cooling pipeline 702, and is used to cool the sealed simulation cavity 5 and control the temperature in the sealed simulation cavity 5.

[0032] Through the heater 4, the circulating pump 3, the cooling pipeline and other components, the temperature and pressure of the entire pipeline are adjusted dynamically to ensure that the pressure and stability in the sealed simulation chamber 5 are constant, so that the hydraulic medium entering the sealed simulation chamber 5 meets the set requirements, and the bearings and other components that need to be tested are placed in the sealed simulation chamber 5 to simulate the high temperature and high pressure environment in aviation, so as to verify the life and degradation of bearings and other components under high temperature and high pressure environment; the second outlet of the three-way valve 101 is provided with a second one-way valve 202, and the second one-way valve 202 is used to separate the pressure of the hydraulic medium after the heater 4 comes out, so as to ensure that the pressure of the hydraulic medium entering the sealed simulation chamber 5 is too high, and avoid the pressure at the three-way valve 101 being too high, causing damage to the three-way valve 101, and at the same time, after the hydraulic medium in the sealed simulation chamber 5 is filled, the hydraulic medium can be allowed to flow out directly from the second one-way valve 202, so that the pressure of the hydraulic medium entering the sealed simulation chamber 5 is close to 0. The oil tank 1 is higher than the heating and pressurizing pipeline and the cooling pipeline, so that the hydraulic medium can flow into the oil-gas separator 2 through the first one-way valve 201 under the action of gravity.

[0033] That is, the hydraulic medium in the oil tank 1 flows into the oil-gas separator 2 through the first one-way valve 201, and the hydraulic medium passes through the oil-gas separator 2, the circulation pump 3, the heater 4, the three-way valve 101, the sealed simulation chamber 5, the first valve 102, the second valve 103, and the filter 6 in sequence, and then flows back to the oil-gas separator 2 to generate a circulating flow. During the flow of the hydraulic medium, the temperature and pressure in the sealed simulation chamber 5 are always maintained in a constant state through the pressurization of the circulation pump 3, the heating of the heater 4, the pressure reduction of the three-way valve 101, and the cooling of the cooling pipeline, so that the temperature and pressure in the sealed simulation chamber 5 are always maintained in a constant state to reach the set temperature and pressure required for the test. The bearings and other components to be tested are placed in the sealed simulation chamber 5, so that they are placed at the set temperature and pressure, and the life and degradation process of the bearings and other components under the high-temperature and high-pressure aviation environment can be simulated. The problem that the existing equipment cannot maintain a constant high-temperature and high-pressure environment at the same time because the medium generates heat in the high-pressure environment and the temperature continues to rise is solved. The oil tank 1 and the pipeline are both filled with aviation hydraulic oil, that is, the aviation hydraulic oil is used as the hydraulic medium.

[0034] The oil tank 1 is provided with an oil filling port 11 and an oil overflow port 12, a liquid level controller 13 is provided in the oil tank 1, and a one-way throttle valve 14 is provided on the pipeline between the oil tank 1 and the first one-way valve 201. The oil tank 1 is filled with hydraulic medium, such as hydraulic oil, through the oil filling port 11. If too much is added, it can be discharged through the oil overflow port 12. At the same time, the liquid level controller 13 can also sense the liquid level height of the medium in the oil tank 1 in real time, so as to facilitate the filling or discharge of the hydraulic medium.

[0035] The pipeline between the oil-gas separator 2 and the circulating pump 3 is provided with an oil discharge port 15, and the oil discharge port 15 is provided with a valve. It is convenient to discharge the hydraulic medium. The pipeline between the oil discharge port 15 and the circulating pump 3 is connected to the oil tank 1 through the oil replenishment pipeline 16. The oil replenishment pipeline 16 is provided with a one-way valve to prevent the hydraulic medium from flowing back from the pipeline to the oil tank 1 when the pressure in the pipeline is too high. When the hydraulic medium in the pipeline is insufficient, it is directly replenished from the oil tank 1 through the oil replenishment pipeline 16.

[0036] A relief valve 9 is also provided on the pipeline between the sealed simulation chamber 5 and the second valve 103, and the relief valve 9 is arranged in parallel with the first valve 102. The relief valve 9 is equivalent to a safety valve, and is used to control the pressure of the hydraulic medium at the outlet of the sealed simulation chamber 5. Through the arrangement of mechanical valves such as the three-way valve 101, the second one-way valve 202, and the relief valve 9, the temperature and pressure of the entire aviation environment simulator can reach above 200°C without being affected, avoiding the failure of existing electronic components in high temperature environments.

[0037] Through the design of the heater 4 and the cooling pipeline, the sealed simulation chamber 5 can reach any temperature of 0-200°C and remain stable under the flowing hydraulic medium. At the same time, through the design of the circulation pump 3, the three-way valve 101, the second one-way valve 202, and the overflow valve 9, the sealed simulation chamber 5 can reach any pressure of 0-10Mpa and remain stable under the flowing hydraulic medium. That is, the temperature and pressure in the sealed simulation chamber 5 can be kept constant under the flow of the hydraulic medium to meet the test requirements.

[0038] The oil-gas separator 2 is used to separate the hydraulic medium and the gas generated after pressurization in the hydraulic medium, so that only the hydraulic medium can enter the next cycle. The circulation pump 3 provides pressure for the hydraulic medium. The heater 4 is an electric heater 4, which heats the hydraulic medium. The cooling pipeline is used to cool the hydraulic medium. The sealed simulation chamber is provided with temperature and pressure sensors. According to the actual requirements, the first circulation cooling pipeline and the heat exchanger of the liquid cooling device can be cooled, the circulation pump can be pressurized, the heater can be heated, and the three-way valve can be depressurized, so as to ensure the constant temperature and pressure in the sealed simulation chamber.

[0039] Embodiment 2: Figure 4 As shown, based on the first embodiment, a heat exchanger 703 is provided on the pipeline between the heater 4 and the three-way valve 101, and the heat exchanger 703 is connected end to end with the liquid cooling device 7 through a second circulating cooling pipeline 704 for cooling the hydraulic medium.

[0040] A first temperature sensor 301 is arranged on the pipeline between the heater 4 and the heat exchanger 703, a second temperature sensor 302 is arranged on the heater 4, a cooling solenoid valve 705 is arranged at the cooling water inlet of the heat exchanger 703, and a temperature controller 8 is also arranged on the heating and pressurizing pipeline, and the temperature controller 8 is used to control the operation of the heater 4 and the cooling solenoid valve 705.

[0041] The thermostat 8 can control the operation of the heater 4 and the cooling solenoid valve 705, and further control the temperature of the hydraulic medium heated by the electric heater, and can control the operation of the cooling solenoid valve 705, that is, control the flow of cooling water entering the heat exchanger 703, thereby controlling the temperature of the hydraulic medium entering the sealed simulation chamber 5, so that it reaches the set temperature, and further ensures the temperature condition in the sealed simulation chamber 5. The liquid cooling device 7 is a water cooler, and the cooling water comes out from the outlet of the water cooler, and passes through the cooling solenoid valve 705 to adjust the opening and closing and flow rate of the cooling water, enters the heat exchanger, exchanges heat with the hydraulic medium coming out of the heater 4, and then flows back into the water cooler through the fourth one-way valve 204. The arrow direction in the figure is the flow direction of the cooling water.

[0042] Embodiment 3: Figure 2-3As shown, on the basis of the first or second embodiment, a third one-way valve 203 is provided on the pipeline between the circulation pump 3 and the heater 4, and pressure sensors are provided on the pipelines between the heater 4 and the three-way valve 101, and between the circulation pump 3 and the heater 4. The one-way flow of the hydraulic medium is ensured, and the pressure at each location in the pipeline can be clearly known.

[0043] Embodiment 4: Figure 1 As shown, on the basis of the first to third embodiments, the oil tank 1, the heating and pressurizing pipeline and the cooling pipeline are all arranged in the test shell 10, the test shell 10 is made of carbon fiber, and a universal wheel 1001 is arranged at the bottom of the test shell 10. The carbon fiber shell 10 has the characteristics of light weight, etc., which can greatly reduce the weight of the aviation environment simulator, and at the same time, the cooperation with the universal wheel 1001 improves its flexibility and facilitates its movement.

[0044] The aviation environment simulator of the present invention uses components such as a heater 4, a circulation pump 3, and a cooling pipeline to dynamically adjust the temperature and pressure of the entire pipeline, thereby ensuring that the pressure and pressure in the sealed simulation chamber 5 are stable and constant, simulating the high temperature and high pressure environment in aviation, and facilitating verification of the life and degradation of components such as bearings in the high temperature and high pressure environment of the sealed simulation chamber 5.

[0045] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. For those skilled in the art, the present invention may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. An aviation environment simulator, characterized in that: It comprises an oil tank (1), a heating and pressurizing pipeline and a cooling pipeline, wherein the oil tank (1) is higher than the heating and pressurizing pipeline and the cooling pipeline; The heating and pressurizing pipeline comprises an oil-gas separator (2), a circulation pump (3), a heater (4), and an inlet of a three-way valve (101) which are connected in sequence through a pipeline; a first outlet of the three-way valve (101) is connected in sequence to a sealing simulation chamber (5), a first valve (102), a second valve (103), and a filter (6) through a pipeline; the filter (6) is communicated with the oil-gas separator (2); and a second outlet of the three-way valve (101) is connected in sequence to a second one-way valve (202) and the oil-gas separator (2) through a pipeline; The oil tank (1) is connected in sequence to a first one-way valve (201) and an oil-gas separator (2) via pipelines; The cooling pipeline comprises a liquid cooling device (7), a cooling water channel (701) is provided on the sealed simulation cavity (5), and the liquid cooling device (7) is connected end to end with the cooling water channel (701) through a first circulating cooling pipeline (702) for cooling the sealed simulation cavity (5).

2. The aviation environment simulator according to claim 1, characterized in that: The oil tank (1) is provided with an oil filling port (11) and an oil overflow port (12), a liquid level controller (13) is provided inside the oil tank (1), and a one-way throttle valve (14) is provided on the pipeline between the oil tank (1) and the first one-way valve (201).

3. The aviation environment simulator according to claim 1, characterized in that: An oil discharge port (15) is provided on the pipeline between the oil-gas separator (2) and the circulation pump (3).

4. The aviation environment simulator according to claim 3, characterized in that: The pipeline between the oil discharge port (15) and the circulation pump (3) is connected to the oil tank (1) via an oil replenishment pipeline (16).

5. The aviation environment simulator according to claim 1, characterized in that: A heat exchanger (703) is provided on the pipeline between the heater (4) and the three-way valve (101). The heat exchanger (703) is connected end to end with the liquid cooling device (7) through a second circulating cooling pipeline (704) and is used to cool the hydraulic medium.

6. The aviation environment simulator according to claim 5, characterized in that: A first temperature sensor (301) is provided on the pipeline between the heater (4) and the heat exchanger (703), a second temperature sensor (302) is provided on the heater (4), a cooling solenoid valve (705) is provided at the cooling water inlet of the heat exchanger (703), and a temperature controller (8) is also provided on the heating and pressurizing pipeline, and the temperature controller (8) is used to control the operation of the heater (4) and the cooling solenoid valve (705).

7. The aviation environment simulator according to claim 1, characterized in that: An overflow valve (9) is also provided on the pipeline between the sealing simulation chamber (5) and the second valve (103), and the overflow valve (9) is arranged in parallel with the first valve (102).

8. The aviation environment simulator according to claim 1, characterized in that: A third one-way valve (203) is provided on the pipeline between the circulation pump (3) and the heater (4), and pressure sensors are provided on the pipelines between the heater (4) and the three-way valve (101) and between the circulation pump (3) and the heater (4).

9. The aviation environment simulator according to claim 1, characterized in that: The oil tank (1), the heating and pressurizing pipeline, and the cooling pipeline are all arranged in a test shell (10); the test shell (10) is made of carbon fiber; and a universal wheel (1001) is arranged at the bottom of the test shell (10).

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