An aviation environment simulator

Abstract

This invention discloses an aviation environment simulator, comprising a fuel tank, heating and pressurizing pipelines, and cooling pipelines. The heating and pressurizing pipelines include an oil-gas separator, a circulating pump, a heater, and the inlet of a three-way valve, connected sequentially from end to end. The first outlet of the three-way valve is connected sequentially from end to end to a sealed simulation chamber, a first valve, a second valve, and a filter. The filter is connected to the oil-gas separator. The second outlet of the three-way valve is connected sequentially from end to end to a second check valve and the oil-gas separator. The cooling pipelines include a liquid cooling device, which is connected to a cooling water channel from end to end via a first circulating cooling pipeline. Through components such as the heater, circulating pump, and cooling pipelines, the temperature and pressure of the entire pipeline are dynamically adjusted to ensure stable and constant pressure within the sealed simulation chamber, simulating the high-temperature and high-pressure environment in aviation. This facilitates the verification of the lifespan and degradation of components such as bearings under the high-temperature and high-pressure environment of the sealed simulation chamber.

Description

Technical Field

[0001] This invention relates to the field of aviation test equipment technology, and more specifically, to an aviation environment simulator. Background Technology

[0002] Aerospace bearings and other components are essential parts of modern aircraft operating systems, requiring operation in the high-temperature, high-pressure environment of aviation. Compared to general bearings, aerospace bearings operate in harsher environments, impacting their lifespan. To assess the lifespan and degradation of aerospace bearings under high-temperature, high-pressure conditions, specialized aviation environment simulation devices are needed. These devices can simulate the high-temperature, high-pressure environments encountered during actual aircraft use during the early design and later verification stages of bearings, thus verifying the lifespan and degradation of bearings and other components. Because the medium generates heat under high pressure, causing a continuous rise in temperature, and because high pressure requires a sealed environment, existing equipment cannot simultaneously maintain a constant high-temperature, high-pressure environment.

[0003] Therefore, an aviation environment simulator was designed to simulate the lifespan and degradation process of bearings and other components of an aircraft under high temperature and high pressure conditions, and to verify the performance of bearings and other components. Summary of the Invention

[0004] The purpose of this invention is to provide an aviation environment simulator, which uses components such as heaters, circulating pumps, and cooling pipes to dynamically adjust the temperature and pressure of the entire pipeline, ensuring that the pressure and stability within the sealed simulation chamber are constant, simulating the high temperature and high pressure environment in aviation, and facilitating the verification of the lifespan and degradation of components such as bearings under the high temperature and high pressure environment of the sealed simulation chamber.

[0005] The embodiments of the present invention are implemented as follows:

[0006] This invention provides an aviation environment simulator, including a fuel tank, a heating and pressurizing pipeline, and a cooling pipeline. The fuel tank is higher than the heating and pressurizing pipeline and the cooling pipeline. The heating and pressurizing pipeline includes an oil-gas separator, a circulating pump, a heater, and the inlet of a three-way valve connected sequentially from end to end. The first outlet of the three-way valve is connected sequentially from end to end to a sealed simulation chamber, a first valve, a second valve, and a filter. The filter is connected to the oil-gas separator. The second outlet of the three-way valve is connected sequentially from end to end to a second check valve and the oil-gas separator. The fuel tank is connected sequentially from end to end to the first check valve and the oil-gas separator. The cooling pipeline includes a liquid cooling device. A cooling water channel is provided on the sealed simulation chamber. The liquid cooling device is connected to the cooling water channel from end to end through a first circulating cooling pipeline for cooling the sealed simulation chamber.

[0007] Furthermore, the oil tank is equipped with an oil filling port and an overflow port, and a level controller is installed inside the oil tank. A one-way throttle valve is installed on the pipeline between the oil tank and the first one-way valve. Hydraulic media, such as hydraulic oil, is added to the oil tank through the oil filling port. If too much is added, it can be discharged through the overflow port. At the same time, the level controller can also sense the liquid level in the oil tank in real time, facilitating the addition or discharge of hydraulic media.

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

[0009] Furthermore, the pipeline between the drain port and the circulating pump is connected to the oil tank via a replenishment pipeline. When the hydraulic medium in the pipeline is insufficient, it can be replenished directly from the oil tank through the replenishment pipeline.

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

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

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

[0013] Furthermore, a third check valve is installed on the pipeline between the circulating pump and the heater, and pressure sensors are located on the pipeline between the heater and the three-way valve, and between the circulating pump and the heater.

[0014] Furthermore, the oil tank, heating and pressurizing pipelines, and cooling pipelines are all housed inside the test housing, which is made of carbon fiber and has casters at the bottom.

[0015] Compared to existing technologies, the aviation environment simulator provided by this invention has at least the following features:

[0016] Beneficial effects:

[0017] 1. It uses components such as heaters, circulating pumps, and cooling pipes to dynamically adjust the temperature and pressure of the entire pipeline, ensuring that the pressure and stability within the sealed simulation chamber are constant. This allows the hydraulic medium entering the sealed simulation chamber to meet the set requirements. The bearings and other components to be tested are then placed in the sealed simulation chamber to simulate the high temperature and high pressure environment in aviation, facilitating the verification of the lifespan and degradation of bearings and other components under high temperature and high pressure conditions.

[0018] 2. The second outlet of the three-way valve is equipped with a second check valve. The second check valve is used to divert 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 not too high, avoiding excessive pressure at the three-way valve and causing damage to the three-way valve. At the same time, after the hydraulic medium in the sealed simulation chamber is full, the hydraulic medium can be allowed to flow directly out from the second check valve, so that the pressure of the hydraulic medium entering the sealed simulation chamber is close to 0.

[0019] 3. A relief valve and a first valve are connected in parallel between the sealed simulation chamber and the second valve. The relief 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 check valve, and the relief valve, the temperature and pressure of the entire aviation environment simulator can reach above 200℃ without affecting stability, avoiding the failure of existing electronic components in high-temperature environments. Attached Figure Description

[0020] To more clearly illustrate the technical solutions of the embodiments of the present invention, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of the present invention and should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0021] Figure 1 This is a schematic diagram of the external structure of the present invention;

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

[0023] Figure 3 This is a schematic diagram of the heating and pressurizing pipeline in this invention;

[0024] Figure 4 This is a schematic diagram of the cooling pipe structure in this invention;

[0025] Icons: 1. Oil tank; 11. Oil inlet; 12. Overflow port; 13. Liquid level controller; 14. One-way throttle valve; 15. Oil outlet; 16. Oil replenishment line; 2. Oil-gas separator; 3. Circulating pump; 4. Heater; 5. Sealed simulation chamber; 6. Filter; 7. Liquid cooling device; 701. Cooling water channel; 702. First circulating cooling pipe; 703. Heat exchanger; 704. Second circulating cooling pipe; 705. Cooling solenoid valve; 8. Thermostat; 9. Overflow valve; 10. Housing; 1001. Caster wheel; 101. Three-way valve; 102. First valve; 103. Second valve; 201. First check valve; 202. Second check valve; 203. Third check valve; 204. Fourth check valve; 301. First temperature sensor; 302. Second temperature sensor. Detailed Implementation

[0026] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. The components of the embodiments of the present invention described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0027] Therefore, the following detailed description of the embodiments of the invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the invention without inventive effort are within the scope of protection of the invention.

[0028] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0029] Furthermore, terms such as "horizontal" and "vertical" do not imply that components must be absolutely horizontal or suspended, but rather that they can be slightly tilted. For example, "horizontal" simply 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 this invention, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0031] Example 1: As 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. 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 the inlet of a three-way valve 101 connected sequentially from end to end through the pipeline. The first outlet of the three-way valve 101 is connected sequentially from the pipeline to a sealed simulation chamber 5, a first valve 102, a second valve 103, and a filter 6. The filter 6 is connected to the oil-gas separator 2. The second outlet of the three-way valve 101 is connected sequentially from the pipeline to a second check valve 202 and the oil-gas separator 2. The fuel tank 1 is connected sequentially from the pipeline to the first check valve 201 and the oil-gas separator 2. The cooling pipeline includes a liquid cooling device 7. A cooling water channel 701 is provided on the sealed simulation chamber 5. The liquid cooling device 7 is connected to the cooling water channel 701 from end to end through a first circulating cooling pipeline 702, and is used to cool the sealed simulation chamber 5 and control the temperature inside the sealed simulation chamber 5.

[0032] It uses components such as heater 4, circulating pump 3, and cooling pipes to dynamically adjust the temperature and pressure of the entire pipeline, ensuring that the pressure and stability within the sealed simulation chamber 5 are constant. This ensures that the hydraulic medium entering the sealed simulation chamber 5 meets the set requirements. Components such as bearings to be tested are placed in the sealed simulation chamber 5 to simulate the high-temperature and high-pressure environment in aviation, facilitating the verification of the lifespan and degradation of components under high-temperature and high-pressure conditions. The second outlet of the three-way valve 101 is equipped with a second check valve 202. The second check valve 202 is used to divert the pressure of the hydraulic medium after it exits from the heater 4, ensuring that the pressure of the hydraulic medium entering the sealed simulation chamber 5 is not too high. This avoids excessive pressure at the three-way valve 101, which could damage the valve. At the same time, after the hydraulic medium in the sealed simulation chamber 5 is full, the hydraulic medium can flow directly out from the second check valve 202, making the pressure of the hydraulic medium entering the sealed simulation chamber 5 close to 0. The oil tank 1 is higher than the heating and pressurizing pipelines and the cooling pipelines, 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] The hydraulic medium in tank 1 flows into oil-gas separator 2 through the first one-way valve 201. The hydraulic medium then sequentially passes through oil-gas separator 2, circulating pump 3, heater 4, three-way valve 101, sealed simulation chamber 5, first valve 102, second valve 103, and filter 6 before returning to oil-gas separator 2, creating a circulating flow. During this flow, the hydraulic medium is pressurized by circulating pump 3, heated by heater 4, depressurized by three-way valve 101, and cooled by cooling pipes, maintaining a constant temperature and pressure within the sealed simulation chamber 5 to achieve the set temperature and pressure required for the test. The sealed simulation chamber 5 contains the bearings and other components to be tested, placing them under the set temperature and pressure to simulate the lifespan and degradation process of these components under high-temperature, high-pressure aerospace conditions. This solves the problem of existing equipment where the medium generates heat under high pressure, causing the temperature to rise continuously and making it impossible to maintain a constant high-temperature, high-pressure environment simultaneously. Both tank 1 and the pipelines contain aviation hydraulic oil, meaning aviation hydraulic oil is used as the hydraulic medium.

[0034] The oil tank 1 is equipped with an oil inlet 11 and an overflow outlet 12. A level controller 13 is installed inside the oil tank 1, and a one-way throttle valve 14 is installed on the pipeline between the oil tank 1 and the first one-way valve 201. Hydraulic media, such as hydraulic oil, is added to the oil tank 1 through the oil inlet 11. If too much is added, it can be discharged through the overflow outlet 12. At the same time, the level controller 13 can also sense the liquid level in the oil tank 1 in real time, which facilitates the addition or discharge of hydraulic media.

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

[0036] An overflow valve 9 is also installed on the pipeline between the sealed simulation chamber 5 and the second valve 103. The overflow valve 9 is arranged in parallel with the first valve 102. The overflow valve 9 acts as a safety valve to control the pressure of the hydraulic medium at the outlet of the sealed simulation chamber 5. Through the installation of mechanical valves such as the three-way valve 101, the second one-way valve 202, and the overflow valve 9, the temperature and pressure of the entire aviation environment simulator can be maintained at a stability of over 200°C without being affected, avoiding the failure of existing electronic components in high-temperature environments.

[0037] Through the design of heater 4 and cooling pipelines, the sealed simulation chamber 5 can reach and maintain a stable temperature of 0-200℃ under flowing hydraulic medium. Simultaneously, through the design of circulating pump 3, three-way valve 101, second check valve 202, and relief valve 9, the sealed simulation chamber 5 can reach and maintain a stable pressure of 0-10MPa under flowing hydraulic medium. In other words, constant temperature and pressure can be achieved within the sealed simulation chamber 5 under flowing hydraulic medium, meeting the experimental requirements.

[0038] The oil-gas separator 2 separates the hydraulic medium from the gas generated after pressurization, ensuring that only the hydraulic medium can enter the next cycle. The circulating pump 3 provides pressure to the hydraulic medium. The heater 4 is an electric heater that heats the hydraulic medium. The cooling pipeline is used to cool the hydraulic medium. Temperature and pressure sensors are installed inside the sealed simulation chamber, which can, according to actual requirements, enable the first circulation cooling pipeline and heat exchanger of the liquid cooling device to cool down, the circulating pump to pressurize, the heater to heat, and the three-way valve to depressurize, ensuring constant temperature and pressure within the sealed simulation chamber.

[0039] Example 2: Figure 4 As shown, based on Embodiment 1, a heat exchanger 703 is installed on the pipeline between the heater 4 and the three-way valve 101. The heat exchanger 703 is connected to the liquid cooling device 7 through the second circulating cooling pipeline 704 to cool the hydraulic medium.

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

[0041] The thermostat 8 controls the operation of the heater 4 and the cooling solenoid valve 705, thereby controlling the temperature of the hydraulic medium heated by the heater. It also controls the operation of the cooling solenoid valve 705, controlling the flow rate of cooling water into the heat exchanger 703, thus controlling the temperature of the hydraulic medium entering the sealed simulation chamber 5 to reach the set temperature, further ensuring the temperature conditions within the sealed simulation chamber 5. The liquid cooling device 7 is a water chiller. Cooling water exits from the water chiller's outlet, passes through the cooling solenoid valve 705 to regulate its opening, closing, and flow rate, and enters the heat exchanger to exchange heat with the hydraulic medium exiting the heater 4. The water then flows back into the water chiller through the fourth one-way valve 204. The arrows in the diagram indicate the direction of cooling water flow.

[0042] Example 3: Figure 2-3As shown, based on Embodiment 1 or 2, a third one-way valve 203 is installed on the pipeline between the circulating pump 3 and the heater 4, and pressure sensors are located on the pipelines between the heater 4 and the three-way valve 101, and between the circulating pump 3 and the heater 4. This ensures the unidirectional flow of the hydraulic medium and allows for clear monitoring of the pressure at various points in the pipeline.

[0043] Example 4: Figure 1 As shown, based on embodiments one to three, the oil tank 1, heating and pressurizing pipelines, and cooling pipelines are all housed within the test housing 10. The test housing 10 is made of carbon fiber, and a caster wheel 1001 is provided at the bottom of the test housing 10. The carbon fiber housing 10 is lightweight, which can greatly reduce the weight of the aviation environment simulator. At the same time, the combination with the caster wheel 1001 improves its flexibility and facilitates its movement.

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

[0045] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. An aviation environment simulator, characterized in that: It includes an oil tank (1), heating and pressurizing pipelines and cooling pipelines, wherein the oil tank (1) is higher than the heating and pressurizing pipelines and cooling pipelines; The heating and pressurizing pipeline includes an oil-gas separator (2), a circulating pump (3), a heater (4), and the inlet of a three-way valve (101) connected sequentially from end to end. The first outlet of the three-way valve (101) is connected sequentially through a pipeline to a sealed simulation chamber (5), a first valve (102), a second valve (103), and a filter (6). The filter (6) is connected to the oil-gas separator (2). The second outlet of the three-way valve (101) is connected sequentially through a pipeline to a second check valve (202) and the oil-gas separator (2). The oil tank (1) is sequentially connected to a first check valve (201) and an oil-gas separator (2) via pipelines; The cooling pipeline includes a liquid cooling device (7), and a cooling water channel (701) is provided on the sealed simulation cavity (5). The liquid cooling device (7) is connected to the cooling water channel (701) through a first circulating cooling pipe (702) to cool the sealed simulation cavity (5). A heat exchanger (703) is installed on the pipe between the heater (4) and the three-way valve (101). The heat exchanger (703) is connected to the liquid cooling device (7) through the second circulating cooling pipe (704) to cool the hydraulic medium. An overflow valve (9) is also provided on the pipeline between the sealed simulation chamber (5) and the second valve (103), and the overflow valve (9) is arranged in parallel with the first valve (102).

2. The aviation environment simulator according to claim 1, characterized in that: The oil tank (1) is provided with an oil inlet (11) and an oil overflow outlet (12). The oil tank (1) is provided with a liquid level controller (13). 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 drain port (15) is provided on the pipeline between the oil-gas separator (2) and the circulating pump (3).

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

5. The aviation environment simulator according to claim 1, characterized in that: A first temperature sensor (301) is installed on the pipe between the heater (4) and the heat exchanger (703), a second temperature sensor (302) is installed on the heater (4), a cooling solenoid valve (705) is installed at the cooling water inlet of the heat exchanger (703), and a temperature controller (8) is also installed on the heating and pressurizing pipeline. The temperature controller (8) is used to control the operation of the heater (4) and the cooling solenoid valve (705).

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

7. The aviation environment simulator according to claim 1, characterized in that: The oil tank (1), heating and pressurizing pipelines and cooling pipelines are all located inside the test shell (10). The test shell (10) is made of carbon fiber and has casters (1001) at the bottom.

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