High-altitude pressurization equivalent test system for fuel system
By building a high-altitude boosting equivalent test system for components such as gas cylinders, oil tanks, and boosting oil pumps, the problems of high-cost and long cycles of traditional methods are solved, and low-cost and fast high-altitude boosting equivalent tests are achieved to ensure the simulation accuracy of engine oil inlet pressure requirements.
Patent Information
- Application Number
- CN202422646432.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-10-31
- Publication Date
- 2025-08-26
- Estimated Expiration
- 2034-10-31
AI Technical Summary
The traditional high-altitude boost verification method of fuel drones has high cost and long cycles, high requirements for testing equipment, and it is difficult to effectively simulate the engine oil inlet pressure requirements in high altitude environments.
The high-altitude boosting equivalent test system consisting of components such as gas cylinders, oil tanks, booster oil pumps, pumps, and air pressure adjustment pipes. The high-altitude boosting gas is provided through the gas cylinder, combined with the oil pumps and air pressure adjustment parts to simulate the high-altitude environment, dynamically adjust the pressure in the oil tank to ensure equivalence.
It realizes low-cost and fast high-altitude boosting equivalent tests, simplifies test operations, can effectively simulate the engine oil inlet pressure requirements in high altitude environments, and is easy to obtain appropriate return valve opening to meet engine requirements.
Smart Images
Figure CN223272178U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of aviation unmanned aerial vehicles, in particular to a high-altitude pressurization equivalent test system for a fuel system. Background Art
[0002] Drones are currently used in a wide range of fields. Fuel-powered drones offer significant advantages in terms of range, flight time, and flight speed. The engines of fuel-powered drones have specific fuel supply pressure requirements. As the drone's flight altitude increases, atmospheric pressure decreases, requiring pressure boosting to maintain this pressure. The effectiveness of this pressure boosting method requires testing. Traditionally, the effectiveness of this pressure boosting method has been verified through vacuum tank testing. This involves placing the fuel supply system in a vacuum tank and evacuating it to simulate a high-altitude environment. This method then simulates the amount of pressure boost required to meet the engine's fuel inlet pressure under these conditions. This method is costly, time-consuming, and requires high-quality test equipment. Utility Model Content
[0003] Based on the above, the purpose of the present invention is to provide a high-altitude pressurization equivalent test system for a fuel system, which has low cost, short test cycle and good equivalence.
[0004] In order to achieve the above purpose, the utility model adopts the following technical solutions:
[0005] A high altitude pressurization equivalent test system for a fuel system, comprising a gas cylinder, a fuel tank, a pressurized oil pump, an oil pump, an oil drum, an air pressure regulating tube, an air pressure regulating member, a return valve and a first pressure gauge;
[0006] The gas cylinder is connected to the fuel tank via a gas delivery pipe, and the gas cylinder is used to provide pressurized gas to the fuel tank. One end of the gas pressure regulating tube is connected to the fuel tank, and the other end is connected to the external atmosphere. The gas pressure regulating member is provided on the gas pressure regulating tube and is used to adjust the ventilation flow of the gas pressure regulating tube.
[0007] The oil barrel, the booster oil pump, the oil pump and the oil barrel are sequentially connected through a fuel delivery pipeline. The first pressure gauge is provided on the fuel delivery pipeline and is located between the booster oil pump and the oil pump. The oil pumping rate of the oil pump is adjustable.
[0008] The return valve is connected between the boosting oil pump and the oil tank through a fuel return pipeline, and the opening of the return valve is adjustable.
[0009] As a preferred solution for a high-altitude pressurization equivalent test system for a fuel system, the air pressure regulating component includes a flow regulating bolt, which is threadedly connected to the air pressure regulating tube, and the length of the flow regulating bolt inside the air pressure regulating tube is adjustable.
[0010] As a preferred solution for a high-altitude boost pressure equivalent test system for a fuel system, the air pressure regulating component includes a throttle valve, which is arranged on the air pressure regulating pipe and has an adjustable opening.
[0011] As a preferred solution for a high-altitude pressurization equivalent test system for a fuel system, the fuel tank has a fuel space and a gas space located above the fuel space, the fuel space contains fuel, and the fuel tank is provided with a vent hole connected to the gas space, the vent hole is connected to a vent pipe, and the gas delivery pipeline and the air pressure regulating pipe are connected to the vent pipe through a three-way valve.
[0012] As a preferred solution for a high-altitude pressurization equivalent test system for a fuel system, a pressure relief valve is provided on the gas delivery pipeline. The pressure relief valve is used to adjust the ventilation flow of the gas delivery pipeline, and the opening of the pressure relief valve is adjustable.
[0013] As a preferred solution for a high-altitude pressurization equivalent test system for a fuel system, a second pressure gauge is provided on the gas delivery pipeline, and the second pressure gauge is located between the pressure relief valve and the fuel tank.
[0014] As a preferred solution for the high-altitude pressurization equivalent test system for the fuel system, it also includes an electronic scale, and the oil barrel is placed on the electronic scale.
[0015] As a preferred solution for a high-altitude boost pressure equivalent test system for a fuel system, a third pressure gauge is provided on the fuel delivery pipeline, and the third pressure gauge is located between the fuel tank and the boost oil pump.
[0016] The beneficial effects of the utility model are:
[0017] The utility model provides a high-altitude pressurization equivalent test system for a fuel system, which provides pressurized gas to the fuel tank through a gas cylinder to simulate the high-altitude pressurization effect of a drone, and extracts fuel in the fuel tank through a pump to simulate the actual fuel consumption process of the drone. During the oil pumping process, the pressure in the fuel tank will gradually decrease, and by adjusting the ventilation flow of the air pressure regulating tube, the pressure in the fuel tank can be dynamically balanced at a pressure equivalent to the high-altitude environmental pressure to ensure the simulation equivalence, that is, the joint work of the gas cylinder, the pump and the air pressure regulating component makes the state of the fuel tank equivalent to the actual state at high altitude, that is, the construction of a high-altitude equivalent environment is realized, the structure is simple, easy to assemble, and the cost is low, and the test operation is simple. After the high-altitude equivalent environment is established, the fuel delivered to the fuel delivery pipeline is pressurized by the booster pump to simulate the actual boosted oil pumping effect in the high-altitude environment. The hydraulic pressure in the fuel delivery pipeline after the booster pump is pressurized by the booster pump is obtained in real time by reading the pressure value of the first pressure gauge. The opening of the return valve is adjusted according to the value of the first pressure gauge to control the boost amount of the booster pump until the pressure value of the first pressure gauge is within a preset range, that is, at this time, the hydraulic pressure of the pressurized fuel meets the engine's fuel inlet pressure requirement. This high-altitude boost equivalent test system for the fuel system realizes a low-cost equivalent simulation of the pressure state in the fuel tank of a drone in a high-altitude environment. It can also verify whether the preset boost amount meets the engine's fuel inlet pressure in the high-altitude environment through a simple test process. The appropriate opening of the return valve can also be obtained through the test operation to obtain the boost amount that meets the engine's fuel inlet pressure requirement. The test operation is convenient and fast, which shortens the test cycle. The overall high-altitude boost equivalent test system is easy to obtain and build, and is low in cost. BRIEF DESCRIPTION OF THE DRAWINGS
[0018] In order to more clearly illustrate the technical solutions in the embodiments of the present invention, the following is a brief introduction to the drawings required for use in the description of the embodiments of the present invention. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on the contents of the embodiments of the present invention and these drawings without paying any creative work.
[0019] Figure 1 It is a structural schematic diagram of a high altitude pressurization equivalent test system for a fuel system provided by an embodiment of the present utility model.
[0020] In the picture:
[0021] 1. Gas cylinder; 2. Fuel tank; 3. Booster pump; 4. Oil pump; 5. Oil drum; 6. Air pressure regulating tube; 7. Air pressure regulating element; 8. Return valve; 9. First pressure gauge; 10. Pressure relief valve; 11. Second pressure gauge; 12. Electronic scale; 13. Third pressure gauge;
[0022] 100. Gas delivery pipeline; 200. Fuel delivery pipeline; 300. Fuel return pipeline; 400. Ventilation pipe. DETAILED DESCRIPTION
[0023] The present invention will be further described in detail below with reference to the accompanying drawings and examples. It should be understood that the specific embodiments described herein are intended only to illustrate the present invention and are not intended to limit the present invention. It should also be noted that, for ease of description, the accompanying drawings only illustrate portions relevant to the present invention, not all of its components.
[0024] In the description of this utility model, unless otherwise specified or limited, the terms "connected," "connect," and "fixed" should be understood in a broad sense. For example, they can refer to fixed connection, detachable connection, or integration; mechanical connection or electrical connection; direct connection or indirect connection through an intermediate medium; internal communication between two components or interaction between two components. Those skilled in the art will understand the specific meanings of the above terms in this utility model based on the specific circumstances.
[0025] In the present invention, unless otherwise expressly specified or limited, a first feature being "above" or "below" a second feature may include the first and second features being in direct contact, or may include the first and second features being in contact not directly but through another feature between them. Moreover, a first feature being "above," "above," and "above" a second feature may include the first feature being directly above or obliquely above the second feature, or may simply mean that the first feature is higher in level than the second feature. A first feature being "below," "below," and "below" a second feature may include the first feature being directly below or obliquely below the second feature, or may simply mean that the first feature is lower in level than the second feature.
[0026] In the description of this embodiment, terms such as "upper," "lower," "left," and "right" are based on the orientations or positional relationships shown in the accompanying drawings and are intended solely for ease of description and simplified operation. They are not intended to indicate or imply that the devices or components referred to must have, be constructed, or operate in a specific orientation. Therefore, they should not be construed as limitations on the present invention. In the description of this utility model, unless otherwise specified, "plurality" means two or more. Furthermore, the terms "first" and "second" are used solely for descriptive purposes and do not have any special meaning.
[0027] like Figure 1As shown, this embodiment provides a high-altitude pressurization equivalent test system for a fuel system, the high-altitude pressurization equivalent test system for a fuel system includes a gas cylinder, a fuel tank, a pressurized oil pump, an oil pump, an oil barrel, an air pressure regulating pipe, an air pressure regulating member, a return valve and a first pressure gauge. Specifically, the fuel tank has a fuel space and a gas space above the fuel space, the fuel space contains fuel, the gas cylinder is connected to the fuel tank through a gas delivery pipe, specifically, the gas cylinder is connected to the gas space through a gas delivery pipe, the gas cylinder is used to provide pressurized gas to the fuel tank, the air pressure regulating member One end of the joint pipe is connected to the fuel tank, specifically to the gas space, and the other end is connected to the external atmosphere. The air pressure regulating part is arranged on the air pressure regulating pipe, which is used to adjust the ventilation flow of the air pressure regulating pipe; the oil barrel, the booster pump, the oil pump and the oil barrel are connected in sequence through the fuel delivery pipe, specifically the fuel delivery pipe is connected to the fuel space, the first pressure gauge is arranged on the fuel delivery pipe and is located between the booster pump and the oil pump, and the oil pumping rate of the oil pump is adjustable; the return valve is connected between the booster pump and the fuel tank through the fuel return pipe, and the opening of the return valve is adjustable. The fuel tank is supplied with pressurized gas through a gas cylinder to simulate the high-altitude pressurization effect of the UAV. The fuel in the fuel tank is extracted through a pump to simulate the actual fuel consumption process of the UAV. During the pumping process of the pump, the pressure in the fuel tank will gradually decrease. By adjusting the ventilation flow of the air pressure regulating tube, the pressure in the fuel tank can be dynamically balanced at the same level as the high-altitude environmental pressure, ensuring the equivalence of the simulation. That is, the joint work of the gas cylinder, the pump and the air pressure regulating component makes the state of the fuel tank equivalent to the actual state at high altitude, that is, the construction of a high-altitude equivalent environment is achieved. The structure is simple, easy to assemble, low in cost, and easy to operate. Among them, by adjusting the pumping rate of the pump, the different actual fuel consumption rates of the UAV can be simulated. For example, adjusting the pumping rate of the pump to be equivalent to the maximum or minimum value of the actual fuel consumption of the UAV ensures the reliability and practicality of the test results of the equivalent test. After the high-altitude equivalent environment is established, the fuel delivered to the fuel delivery pipeline is pressurized by the booster pump to simulate the actual boosted oil pumping effect in the high-altitude environment. The hydraulic pressure in the fuel delivery pipeline after the booster pump is pressurized by the booster pump is obtained in real time by reading the pressure value of the first pressure gauge. The opening of the return valve is adjusted according to the value of the first pressure gauge to control the boost amount of the booster pump until the pressure value of the first pressure gauge is within a preset range, that is, at this time, the hydraulic pressure of the pressurized fuel meets the engine's fuel inlet pressure requirement. This high-altitude boost equivalent test system for the fuel system realizes a low-cost equivalent simulation of the pressure state in the fuel tank of a drone in a high-altitude environment. It can also verify whether the preset boost amount meets the engine's fuel inlet pressure in the high-altitude environment through a simple test process. The appropriate opening of the return valve can also be obtained through the test operation to obtain the boost amount that meets the engine's fuel inlet pressure requirement. The test operation is convenient and fast, which shortens the test cycle. The overall high-altitude boost equivalent test system is easy to obtain and build, and is low in cost.
[0028] Specifically, a pressure relief valve is installed on the gas delivery pipeline to regulate the ventilation flow rate. When the pressure relief valve is opened, the high-pressure gas in the gas cylinder is delivered through the gas delivery pipeline into the gas space within the fuel tank, pressurizing the gas space. Closing the pressure relief valve stops the gas cylinder from delivering high-pressure gas to the gas space. By adjusting the opening of the pressure relief valve, the ventilation flow rate in the gas delivery pipeline, and thus the pressurization level of the gas space, is regulated, providing high flexibility.
[0029] Preferably, a second pressure gauge is provided on the gas delivery pipeline, located between the pressure relief valve and the fuel tank. By reading the pressure value on the second pressure gauge, the pressure value of the high-pressure gas in the gas delivery pipeline relative to the external environment can be obtained, facilitating the determination of whether the fuel tank pressurization meets the test requirements, i.e., verifying the pressurization effect.
[0030] In this embodiment, the high-altitude pressurization equivalent test system for the fuel system also includes an electronic scale. The oil barrel is placed on the electronic scale. The electronic scale can display the weight of the oil barrel in real time, that is, the weight of the fuel extracted into the oil barrel. By observing the changes in the weight of the fuel in the oil barrel over a period of time, the oil pumping rate can be known in real time, so that it can be intuitively compared with the actual fuel consumption rate of the drone in a high-altitude environment, so that the oil pumping rate of the oil pump can be adjusted in time to make the actual oil pumping rate of the test equivalent to the actual fuel consumption rate of the drone in a high-altitude environment, thereby ensuring the effectiveness and accuracy of the high-altitude equivalent environment, thereby ensuring the test effect.
[0031] Preferably, a third pressure gauge is provided on the fuel delivery pipeline, and the third pressure gauge is located between the fuel tank and the booster pump. The value of the third pressure gauge can be used to obtain in real time the hydraulic pressure of the fuel in the fuel delivery pipeline before it is pressurized by the booster pump in an equivalent environment at high altitude, which is convenient for judging whether the hydraulic pressure before pressurization meets the test requirements; it is also convenient for comparing with the hydraulic pressure of the fuel in the fuel delivery pipeline after it is pressurized by the booster pump, thereby obtaining the hydraulic pressure difference before and after the fuel is pressurized in the fuel delivery pipeline, that is, the pressure increase amount can be intuitively known.
[0032] In one embodiment, the air pressure regulating member includes a flow regulating bolt, which is threadedly connected to the air pressure regulating tube. The length of the flow regulating bolt within the air pressure regulating tube is adjustable. By adjusting the length of the flow regulating bolt within the air pressure regulating tube, the diameter of the aperture corresponding to the flow regulating bolt within the air pressure regulating tube is changed, thereby adjusting the ventilation flow of the air pressure regulating tube, thereby achieving fine adjustment of the air pressure within the fuel tank, thereby simulating the pressurization effect of a drone at different flight altitudes, and preventing the air pressure within the fuel tank from dropping too much during oil pumping, resulting in a large difference between the air pressure within the fuel tank and the actual high-altitude ambient pressure, thereby ensuring the effectiveness of the equivalent pressure of the air pressure within the fuel tank.
[0033] In another embodiment, the air pressure regulating member includes a throttle valve, which is disposed on the air pressure regulating tube and has an adjustable opening. The throttle valve is readily available, relatively low in cost, and convenient to adjust. By adjusting the opening of the throttle valve, the ventilation flow of the air pressure regulating tube is adjusted, thereby achieving fine adjustments to the air pressure within the fuel tank, thereby simulating the pressurization effect of a drone at different flight altitudes, and preventing the air pressure within the fuel tank from dropping too much when the oil pump is pumping oil, resulting in a large difference between the air pressure within the fuel tank and the actual high-altitude ambient pressure, thereby ensuring the effectiveness of the equivalent pressure of the air pressure within the fuel tank.
[0034] To simplify piping layout, the fuel tank has a vent hole connected to the gas space. This vent hole is connected to a vent pipe. The gas delivery pipeline and the air pressure regulating pipe are connected to the vent pipe via a three-way valve. In other words, the gas delivery pipeline and the air pressure regulating pipe are connected to the gas space of the fuel tank through the three-way valve, eliminating the need for additional holes in the fuel tank.
[0035] Note that the above are merely preferred embodiments of the present invention and the technical principles employed. Those skilled in the art will appreciate that the present invention is not limited to the specific embodiments described herein, and that various obvious changes, readjustments, and substitutions are possible for those skilled in the art without departing from the scope of protection of the present invention. Therefore, while the present invention has been described in detail through the above embodiments, the present invention is not limited to the above embodiments and may include many other equivalent embodiments without departing from the scope of the present invention. The scope of the present invention is determined by the scope of the appended claims.
Claims
1. A high altitude pressurization equivalent test system for a fuel system, characterized in that: It includes a gas cylinder, a fuel tank, a booster oil pump, a pump, an oil barrel, an air pressure regulating pipe, an air pressure regulating member, a return valve and a first pressure gauge; The gas cylinder is connected to the fuel tank via a gas delivery pipe, and the gas cylinder is used to provide pressurized gas to the fuel tank. One end of the gas pressure regulating tube is connected to the fuel tank, and the other end is connected to the external atmosphere. The gas pressure regulating member is provided on the gas pressure regulating tube and is used to adjust the ventilation flow of the gas pressure regulating tube. The oil barrel, the booster oil pump, the oil pump and the oil barrel are sequentially connected through a fuel delivery pipeline. The first pressure gauge is provided on the fuel delivery pipeline and is located between the booster oil pump and the oil pump. The oil pumping rate of the oil pump is adjustable. The return valve is connected between the boosting oil pump and the oil tank through a fuel return pipeline, and the opening of the return valve is adjustable.
2. The high altitude pressurization equivalent test system for fuel system according to claim 1, characterized in that: The air pressure regulating member includes a flow regulating bolt, which is threadedly connected to the air pressure regulating pipe. The length of the flow regulating bolt inside the air pressure regulating pipe is adjustable.
3. The high altitude pressurization equivalent test system for fuel system according to claim 1, characterized in that: The air pressure regulating component includes a throttle valve, which is arranged on the air pressure regulating pipe and has an adjustable opening.
4. The high altitude pressurization equivalent test system for fuel system according to claim 3, characterized in that: The fuel tank has a fuel space and a gas space above the fuel space. The fuel space contains fuel. The fuel tank is provided with a vent hole connected to the gas space. The vent hole is connected to a vent pipe. The gas delivery pipeline and the air pressure regulating pipe are connected to the vent pipe through a three-way valve.
5. The high altitude pressurization equivalent test system for fuel system according to claim 1, characterized in that: The gas delivery pipeline is provided with a pressure relief valve, which is used to adjust the ventilation flow of the gas delivery pipeline, and the opening of the pressure relief valve is adjustable.
6. The high altitude pressurization equivalent test system for fuel system according to claim 5, characterized in that: A second pressure gauge is provided on the gas delivery pipeline, and the second pressure gauge is located between the pressure relief valve and the oil tank.
7. The high altitude pressurization equivalent test system for fuel system according to claim 1, characterized in that: Also included is an electronic scale, on which the oil barrel is placed.
8. The high altitude pressurization equivalent test system for fuel system according to claim 1, characterized in that: The fuel delivery pipeline is provided with a third pressure gauge, and the third pressure gauge is located between the fuel tank and the boosting oil pump.