High-frequency erosive wear test device and method for reversing valve of aviation hydraulic system

Abstract

The invention discloses a high-frequency erosive wear test device and method for a reversing valve of an aviation hydraulic system. The device is composed of a control unit, a stirring unit, an erosion unit, a cooling unit and a circulating pipeline unit. The stirring unit mixes medium particles and aviation hydraulic oil and then conveys the mixture into the circulating pipeline unit; the control unit drives the hydraulic pump through the motor to enable mixed oil liquid to reach a set pressure value and then washes the reversing valve in the washout unit, and meanwhile the control unit can adjust the reversing frequency of the reversing valve to simulate the working state of the reversing valve of the aviation hydraulic system in the actual working condition. The cooling unit is used for cooling the eroded high-temperature oil liquid, so that the whole test is carried out at a specific temperature. According to the invention, high-frequency reversing of the aviation aircraft landing gear hydraulic system reversing valve and erosive wear behaviors under different pressure and temperature working conditions can be accurately simulated, and reliable test support is provided for material selection, structure optimization and service life prediction of the aviation system reversing valve.

Description

Technical Field

[0001] The present invention relates to the technical field of hydraulic component reliability testing, and in particular to a high-frequency erosion and wear test device and method for a directional valve in an aviation hydraulic system, which is an erosion and wear test device and method for simulating the high-frequency switching working conditions of a directional valve in an aviation hydraulic system. Background Art

[0002] Directional valves in aviation hydraulic systems (particularly three-position, four-way valves) are core actuating components of flight control systems. They switch oil circuits through high-frequency spool reversal (typically 30-50 Hz) to drive landing gear extension and retraction and wheel braking. Under high pressure (≥21 MPa) and high flow rates (>100 L / min), hydraulic fluid carries hard contaminants (such as metal debris and seal wear particles with a hardness ≥1500 HV) through the micron-level clearance (5-15 μm) between the spool and sleeve at velocities ≥50 m / s, causing continuous erosive wear. According to statistics, 70% of aviation hydraulic system failures are caused by valve wear, which directly leads to increased internal leakage (>0.5 L / min), reduced control accuracy (>20 ms response delay), and seal failure, seriously threatening flight safety.

[0003] To characterize the degree of high-frequency erosion wear of directional valves in aviation hydraulic systems, erosion wear test devices are typically used to conduct tests under specific environmental conditions, and the erosion wear resistance of directional valves in aviation hydraulic systems is evaluated based on the test results. Existing erosion wear test devices have the following five problems: 1. Existing erosion wear test devices lack erosion wear tests tailored to the actual operating conditions of directional valves in aviation landing gear hydraulic systems; 2. Existing erosion wear test devices typically only perform erosion tests on one-way valves, lacking erosion wear tests that examine the dynamic erosion of the valve core and sleeve under high-frequency reversing conditions; 3. Existing erosion wear test devices typically fail to monitor changes in test parameters such as pressure and temperature during the erosion test in real time; 4. Existing erosion wear test devices typically lack efficient and precise cooling and temperature regulation systems, and cannot guarantee that the test is conducted under specific temperature conditions; 5. Existing erosion wear test devices cannot perform pressure regulation and cannot accurately evaluate the erosion wear resistance of the sample under multiple erosion pressure parameters, resulting in inaccurate evaluation results.

[0004] Based on the above defects, the existing technology cannot solve the following core problems: ① How to accurately simulate the high-frequency dynamic erosion environment of aviation reversing valves? It is necessary to overcome the difficulty of reproducing the synergistic mechanism of the valve core's high-speed reversing (frequency ≥ 30Hz) and fluid impact; ② How to achieve high-precision coupled control of multiple parameters (pressure / temperature / frequency)? Requires erosion pressure stability ≤ ±1 MPa and temperature fluctuation ≤ ±2°C; ③ How to build a comprehensive monitoring system for the wear process? It is necessary to track the erosion pressure difference, particle concentration, and temperature gradient in real time to establish a wear quantification model.

[0005] It should be noted that the information disclosed in this background technology section is only intended to deepen the understanding of the overall background technology of the present invention, and should not be regarded as an admission or any form of implication that the information constitutes the prior art known to those skilled in the art. Summary of the Invention

[0006] To address the inability of existing testing devices to simulate high-frequency dynamic erosion, low parameter control accuracy, and a lack of process monitoring, this invention provides a high-frequency erosion wear test device and method for reversing valves in aviation hydraulic systems. Through the coordinated control of five units, precise adjustment of erosion pressure (10-35 MPa), temperature (40-120°C), and reversing frequency (1-100 Hz) is achieved, and a global data monitoring system is established.

[0007] To achieve the above object, the present invention adopts the following technical solutions: In a first aspect, the present invention provides a high-frequency erosion and wear test device for a directional valve in an aviation hydraulic system, comprising the following core units: Control unit: integrated with PLC and HMI interface, uses PID algorithm to close the loop to adjust the motor speed, pump flow and reversing frequency of the reversing valve; Mixing unit: A double mixing device is installed in the square mixing box. Ten pairs of fan-shaped blades rotate in opposite directions at 200 rpm to form turbulent flow (Reynolds number Re>5000), ensuring that the particle suspension uniformity is ≥95%; Erosion unit: The reversing valve clamping mechanism uses a damping silicone cushion layer, with a vibration suppression rate of >60%; the reversing valve working pipeline is connected to the valve body A / B port through a quick-change interface, supporting high-frequency oil circuit switching 100 times per second; Cooling unit: Plate heat exchanger (heat transfer coefficient ≥ 3500 W / (m²·K)) coupled with a variable frequency water pump, dynamically adjusting the cooling water flow based on temperature feedback, with a temperature control accuracy of ±1.5°C; Circulation line unit: A 10 μm metal impurity filter and a colloidal adsorption filter are connected in series to maintain oil cleanliness in accordance with NAS 1638 Class 6.

[0008] Preferably, the knob pre-tightening force of the reversing valve clamping mechanism is adjustable in a range of 50-200 N·m.

[0009] Preferably, the pressure sensor sampling frequency is 1 kHz, and the control unit calculates the pressure difference ΔP in real time and fits the wear curve: ΔP=KQ² / ρ, where K is the valve port coefficient and ρ is the oil density.

[0010] Preferably, the safety valve triggers an emergency stop within 0.5 s when the pressure exceeds the limit (> 120% of the set value).

[0011] In a second aspect, the present invention provides a high-frequency erosion wear test method for a reversing valve in an aviation hydraulic system, comprising the following steps: 1. Parameter setting: Input pressure P, temperature T, frequency f, and particle concentration η on the HMI interface of the control unit; 2. Medium mixing: The medium pump delivers WC particles (particle size 5-50 μm) to the mixing tank according to the η value (1-5 wt%); 3. Dynamic erosion: The hydraulic pump is pressurized to P ± 0.3 MPa; the electromagnetic driver drives the valve core to reverse with an accuracy of ± 0.5 Hz; 3. Closed loop temperature control: The water pump is based on the outlet oil temperature T out Adjust the flow rate so that T out =T set ±1.5℃; 4. Data collection: real-time recording of ΔP, Q, T and other parameters, and generation of wear rate reports; 6. Result evaluation: After the test, the valve body is laser scanned (accuracy 0.1 μm) to quantify the material loss volume ΔV.

[0012] Compared with the prior art, the advantages and positive effects of the present invention are: (1) The present invention provides a rationally designed erosion wear test device for reversing valves in aviation hydraulic systems. Compared with existing erosion wear test devices, the present invention simultaneously adjusts the control unit, stirring unit, erosion unit, cooling unit and circulation pipeline unit, and can realize multi-pressure, multi-temperature, high-frequency erosion wear tests for reversing valves in aviation hydraulic systems and collect process data in real time, which is convenient for performing erosion wear tests on valve parts under different working conditions on the same equipment and realizing real-time recording and monitoring of experimental data.

[0013] (2) The present invention introduces a plate heat exchanger and a water pump by setting a cooling unit, and realizes the erosion wear test at a specific temperature by controlling the operation of the water pump through program setting. By setting a medium pump, the device can automatically feed the material. By setting a module, metal impurities and viscous oil can be effectively filtered, thereby achieving the purpose of recycling. By setting a motor and a hydraulic pump, the erosion wear tester can automatically set the erosion pressure, thereby realizing the erosion wear test under a specific erosion pressure. By coupling the external electromagnetic drive device with the reversing valve and control unit of the aviation hydraulic system to be tested, the reciprocating speed of the valve core is precisely controlled to achieve precise control of the reversing frequency, thereby realizing a high-frequency erosion wear test with adjustable reversing frequency. At the same time, the erosion wear test data is displayed in real time on the integrated large panel of the control unit, thereby realizing data monitoring and recording of the erosion wear test process, thereby obtaining an accurate erosion wear evaluation.

[0014] (3) The applicant has found that when conducting erosion wear tests, the existing erosion wear test equipment relies more on manual labor to adjust the erosion wear test parameters and collect and record the erosion wear test results. During the erosion wear test, manpower is limited, and it is difficult for the human eye to systematically and accurately collect test data during the erosion wear process, which makes it difficult to explore how the erosion pressure and erosion temperature change during the erosion wear test. The present invention can more accurately achieve stepless adjustment and real-time monitoring of erosion wear test parameters such as erosion pressure, erosion temperature, reversing frequency of the reversing valve, and impurity concentration during the erosion process through the control unit, which further develops the test device and method for high-frequency reversing valves in aviation hydraulic systems. It also provides reliable test support for the material selection, structural optimization and life prediction of reversing valves in aviation hydraulic systems. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Figure 1 : A schematic structural diagram showing a high-frequency erosion and wear test device for a directional valve in an aviation hydraulic system according to an embodiment of the present invention; Figure 2 : shows a schematic structural diagram of the erosion unit; Figure 3 : Shows a schematic diagram of the HMI interface of the control unit; In the figure: 1-control unit; 2-stirring unit; 3-erosion unit; 4-cooling unit; 5-pipeline circulation unit; 6-oil tank switch; 7-oil tank; 8-first temperature sensor; 9-stirring device; 10-medium pump switch; 11-medium pump; 12-medium storage box; 13-hydraulic pump; 14-motor; 15-flow sensor; 16-relief valve; 17-second temperature sensor; 18-first pressure sensor; 19-oil inlet and outlet pipelines; 20-test bench support structure Structure; 21-Reversing valve clamping mechanism; 22-Reversing working pipeline; 23-Third temperature sensor; 24-Second pressure sensor; 25-Filter 1 switch; 26-Filter 1; 27-Filter switch 2; 28-Filter 2; 29 Heat exchanger hot medium inlet; 30-Heat exchanger hot medium outlet; 31-Heat exchanger cold medium inlet; 32-Heat exchanger cold medium outlet; 33-Water pump; 34-Heat exchanger switch; 35-Water tank; 36-Fourth temperature sensor; 37-Safety valve. DETAILED DESCRIPTION

[0016] The following is combined with Figure 1-3 The preferred embodiments of the present invention are described in detail. This will make the advantages and features of the present invention more easily understood by those skilled in the art, thereby making a clearer and more precise definition of the scope of protection of the present invention. When specific technical conditions are not specified in the examples, they are all implemented according to conventional means in the art.

[0017] An embodiment of the present invention provides a high-frequency erosion and wear test device for a reversing valve in an aviation hydraulic system, the core of which includes: a control unit 1, a stirring unit 2, an erosion unit 3, a cooling unit 4, and a circulation pipeline unit 5; the control unit 1 controls the motor 14, the medium pump 11, the water pump 33, the safety valve 37, and the sensor network through electrical connections to achieve closed-loop control of the erosion pressure, temperature, and reversing frequency. Specifically, the control unit 1 is connected to the motor 14, and the motor 14 drives the hydraulic pump 13 to adjust the pressure of the mixed oil to achieve the setting of the erosion pressure; the control unit 1 is connected to the switch 10 of the medium pump 11 to control the medium pump 11 to suck the medium from the medium storage box 12, and the medium storage box 12 has a built-in balance, so as to achieve the purpose of setting the medium concentration; the control unit 1 is connected to the switch 34 of the heat exchanger to control the flow rate of water sucked from the water tank by the water pump 33 to achieve the regulation of the oil temperature; the control unit 1 is connected to the first filter 26 and the second filter 28 to achieve the filtration of metal impurities and viscous oil in the oil; the control unit Element 1 is connected to the aviation three-position four-way reversing valve to be eroded to realize the setting of the reversing frequency of the reversing valve; the control unit 1 is connected to the first temperature sensor 8, the second temperature sensor 17, the third temperature sensor 23 and the fourth temperature sensor 36, which are respectively used to display the mixing box temperature, the erosion temperature, the temperature after erosion and the temperature after cooling; the control unit 1 is connected to the flow sensor 15, which is used to display the erosion oil flow; the erosion unit 1 is connected to the first pressure sensor 18 and the second pressure sensor 24, which are respectively used to display the erosion pressure and the pressure after erosion; the control unit 1 is connected to the safety valve 37 to form an emergency stop control.

[0018] 1. Control Unit 1 Implementation Details like Figure 1 、 Figure 3 As shown, the control unit 1 uses Siemens S7-1200 PLC as the core and integrates a 10-inch HMI touch screen. The control unit 1 collects in real time the changes in the test parameters of "oil flow", "erosion pressure", "pressure after erosion", "erosion temperature", "temperature after erosion", "mixing box temperature", "temperature after cooling", and "mixing box temperature" during the erosion wear test of the aviation hydraulic system reversing valve sample. The first temperature sensor 8 can monitor the temperature in the square oil mixing box in real time, the second temperature sensor 17 and the third temperature sensor 23 are used to monitor the temperature data before and after erosion in real time, the fourth temperature sensor 36 can monitor the temperature after cooling in real time, the first pressure sensor 18 and the second pressure sensor 24 can monitor the pressure before and after erosion in real time, and the flow sensor 15 can monitor the oil flow before erosion in real time. The above test data are all transmitted to the control unit 1, so as to adjust the mixed oil for transportation and erosion. The control logic of the control unit 1 includes: (1) Pressure closed-loop control: The signal from the first pressure sensor 18 is collected and the speed of the motor 14 is adjusted by the PID algorithm (proportional coefficient Kp = 0.8, integral time Ti = 0.1s) to stabilize the erosion pressure within the range of ±0.3 MPa of the set value; (2) Precise temperature regulation: Based on the feedback from the third temperature sensor 23, the flow rate of the water pump 33 is controlled by fuzzy PID (regulation resolution 0.1 L / min) to maintain the oil temperature within a deviation of ±1.5°C; (3) Commutation frequency drive: Output PWM signal to an external electromagnetic driver (not shown in the figure), driving the valve core displacement amplitude to ±10 mm, and the frequency control accuracy to ±0.5 Hz (test data see the table below); (4) Safety interlock: When the value of the first pressure sensor 18 exceeds 120% of the set value, the power supply of the motor 14 is cut off within 0.5s and the safety valve 37 is opened.

[0019] 2. Implementation details of the stirring unit The outside of the stirring unit 2 is a square stirring box (size 600×400×500 mm), inside which are installed two stirring devices 9 and a first temperature sensor 8. The two stirring devices 9 are installed above the square stirring box, and there are fan-shaped stirring blades arranged at intervals below them. The first temperature sensor 8 is installed on the right side of the left stirring device. The aviation hydraulic oil coming in from the circulation pipeline unit 5 and the metal medium input from the medium storage box 12 by the medium pump 11 are fully stirred and mixed in the square stirring box and then enter the circulation pipeline unit 5.

[0020] The key technical parameters of the mixing unit 2 are designed as follows: Structural parameters: Each set of stirring shafts is equipped with 10 304 stainless steel blades, with a blade inclination angle of 30° and a diameter of 150 mm; Dynamic design: The two agitators rotate counterclockwise / clockwise at 200 rpm, generating a turbulent flow field with a Reynolds number of Re = 5200; Medium mixing: The medium pump 11 uses a gear metering pump to pump WC particles (average particle size 25 μm) from the medium storage box 12 according to the concentration (1-5 wt%) set by the control unit. The mixing uniformity reaches 96.7% (detected by laser particle size analyzer).

[0021] 3. Erosion unit implementation details Inside the erosion unit 3, there are installed oil inlet and outlet pipelines 19, a test bench support structure 20, a reversing valve clamping mechanism 21, and a reversing valve working pipeline 22. The oil inlet and outlet pipelines 19 are located below the reversing valve clamping mechanism 21. The test bench support structure 20 is manually installed on the test bench protective cover. The base of the reversing valve clamping mechanism 21 is connected and fixed to the test bench support structure. The reversing valve working pipeline 22 is installed above the protective cover and secured by a snap-fit ​​device. The reversing valve working pipeline 22 is located 20 cm above the reversing valve clamping mechanism 21. The end of the reversing valve working pipeline 22 has a dedicated interface that can be connected to ports A and B of the three-position, four-way reversing valve. The reversing valve clamping mechanism 21 is fixed to the test bench support structure 20. It is a manual, two-way clamping mechanism. Knobs on both sides control the tightness of the reversing valve clamp. When clamped, it reduces the severe vibration generated by the reversing valve during operation. The oil inlet and outlet pipelines 19 are located below the reversing valve clamping mechanism 21 , and the ends of the oil inlet and outlet pipelines 19 have dedicated connectors that can be connected to the P port and T port of the reversing valve.

[0022] The key technical parameters of erosion unit 3 are as follows: Directional valve clamping mechanism 21: The base is embedded with an 8 mm thick damping silicone layer (Shore hardness HA 50), which can attenuate vibration energy by 60%, as verified by ANSYS simulation. The bidirectional knob has a preload range of 50-200 N·m and is suitable for valve bodies with a diameter of 20-50 mm.

[0023] Pipeline connection design: The reversing valve working pipeline 22 is located 20 cm above the reversing valve clamping mechanism 21. The end of the reversing valve working pipeline 22 has a dedicated interface for connecting to ports A and B of the three-position four-way reversing valve. The reversing valve working pipeline 22 uses a ferrule-type quick-change connector (ISO 16050 standard) to ensure no leakage at ports A / B at 100 Hz. The inner wall of the P / T port pipeline 19 is sprayed with an Al2O3 coating (80 μm thick) to resist particle erosion.

[0024] 4. Cooling unit implementation details Cooling unit 4 includes a plate heat exchanger, a water pump 33, and a water tank 35. The plate heat exchanger includes a hot medium inlet 29, a hot medium outlet 30, a cold medium inlet 31, a cold medium outlet 32, and a heat exchanger switch 34. When heat exchanger switch 34 is turned on, water pump 33 dynamically adjusts the flow rate of water pumped from water tank 35 based on the temperature set by control unit 1. Hot oil, which has been eroded, enters the plate heat exchanger through hot medium inlet 29 and returns to the circulation piping unit 5 through hot medium outlet 30. Water enters the plate heat exchanger through cold medium inlet 31 and returns to water tank 35 through cold medium outlet 32. The water in water tank 35 is an external water source and its temperature is maintained constant. Water pump 33 dynamically adjusts the cooling water flow rate based on feedback from the temperature sensor to maintain the oil temperature within ±2°C of the set value.

[0025] The technical parameters of the plate heat exchanger (model GEA PHE35) are as follows: Heat transfer performance: effective heat exchange area 2.8 m², heat transfer coefficient 3650 W / (m²·K); Temperature control process: 1. Hot oil (initial temperature 85°C) enters the heat exchanger from inlet 29; 2. Water pump 33 adjusts the water flow rate according to the formula $Q_w = k \cdot (T_{set} - T_{out}) $ (k=0.5L / min·℃); 3. Cooling water (constant temperature 20°C) flows from the water tank 35 through the inlet 31, and the water temperature at the outlet 32 ​​rises to 28°C; 4. The temperature of the oil outlet 30 is stable at 83.5±1.2℃ (data from continuous testing for 2 hours).

[0026] 5. Implementation details of the circulation piping unit The circulation piping unit 5 includes a hydraulic pump 13, a motor 14, a flow sensor 15, a relief valve 16, a second temperature sensor 17, a first pressure sensor 18, a third temperature sensor 23, a second pressure sensor 24, a fourth temperature sensor 36, and a filter module. The hydraulic pump 13 and the motor 14 are located to the right of the agitator unit 2 and are connected to the agitator unit 2 via the circulation piping unit 5. The key features of the circulation piping unit 5 are as follows: The filter module includes a first filter 26 and a second filter 28 arranged in parallel: The first filter 26: uses a sintered stainless steel filter element (pore size 10 μm) to intercept metal debris; The second filter 28: uses an activated carbon fiber filter element to adsorb oxidized colloid; The dual-filter parallel design achieves a pressure drop of less than 0.1 MPa and an oil cleanliness level that meets NAS 1638 Class 5.

[0027] Sensor layout: The flow sensor 15 is of turbine type (accuracy ±0.5% FS) and is installed in a 300 mm straight pipe section upstream of the erosion valve; The sampling frequency of the first pressure sensor 18 and the second pressure sensor 24 is 1 kHz, and the pressure difference ΔP (ΔP=P 18 -P 24 ) is transmitted to the control unit 1 in real time.

[0028] A high-frequency erosion and wear test device for a reversing valve in an aviation hydraulic system according to an embodiment of the present invention has the following specific working process: the aviation hydraulic oil in the oil tank 7 enters the square mixing tank and is fully mixed with the medium input by the medium pump 11, and then is transported to the hydraulic pump 13. After the control unit 1 sets the target erosion pressure value, the motor 14 drives the hydraulic pump 13 to establish the system pressure, pressurizes the mixed oil to the set value and pumps it to the erosion unit 3. The eroded oil passes through the circulation pipeline unit 5 and then enters the cooling unit 4. Finally, it returns to the oil tank through the circulation pipeline unit to undergo the next erosion and wear test cycle.

[0029] The method for using the erosion wear testing device of the present invention includes the following steps: When conducting an erosion wear test on a reversing valve in an aviation hydraulic system, determining a relevant experimental plan, such as common test plan types such as "comparative test under different pressures" and "test under different temperatures." During the use of the erosion wear testing machine, the oil-to-medium mixing ratio can be adjusted. Test parameters within the test plan include "medium type," "medium concentration," "medium particle size," "switching frequency," "test unit flow rate," "test duration," "mixed oil erosion pressure," and "erosion temperature." The test parameters should be set based on a comprehensive consideration of the test requirements and the limitations of the test equipment.

[0030] According to the test plan, parameters such as erosion pressure, erosion temperature, and switching frequency are set. The required metal medium weight, medium type, or medium particle size are manually stored in the medium storage tank 12. Simultaneously, the aircraft hydraulic system reversing valve specimen to be tested is placed on the test support 20 and clamped by the reversing valve clamping mechanism 21. The control unit 1 activates the medium pump switch 10 and the heat exchanger switch 34, and then sets the erosion pressure, temperature, and switching frequency. The medium pump 11 transfers the medium from the medium storage tank 12 to the mixing tank, where it is evenly mixed with the aviation hydraulic oil. The mixed oil enters the hydraulic pump 13, where a drive motor pressurizes the mixed oil to the set pressure and then transfers it to the erosion unit 3. The eroded oil passes through the cooling unit 4 and then returns to the oil tank 7 for a cycle test. Finally, a manually set erosion time is set. This erosion cycle is repeated until the erosion wear test of the aircraft hydraulic system reversing valve is completed. After a manual shutdown, the reversing valve clamping mechanism 21 is released and the specimen is removed. After the test, the removed directional control valves were evaluated in the following steps: 1. Surface contamination removal: Ultrasonic cleaning was used to remove oil residue and attached particles; 2. 3D topography reconstruction: Laser focused microscopy was used to scan the sealing and throttling edges to quantify the erosion pit depth and material loss volume. This concluded the erosion wear test.

[0031] The present invention constructs a digital monitoring system for the erosion and wear test of the reversing valve in the aviation hydraulic system, and realizes the full-domain perception of the erosion process through the coordinated control of multiple parameters such as erosion pressure, oil temperature and reversing frequency.

[0032] The technical effects of the present invention are verified through several specific embodiments below.

[0033] Example 1: Standard erosion test process Follow these steps: 1. Clamp the valve body: Place the aviation 3 / 4-way valve (model MOOG D633) on the support structure 20 and tighten the clamping mechanism 21 to 80 N·m. 2. Parameter setting: Enter P=25 MPa, T=80℃, f=40 Hz, η=3 wt% on the HMI; 3. Start the system: The medium pump 11 delivers WC particles (particle size 20-40 μm) to the mixing tank, mixes for 10 minutes, and then starts the hydraulic pump; 4. Data recording: After 50 h of continuous operation, the control unit recorded an increase in ΔP from an initial 1.2 MPa to 3.8 MPa; 5. Result analysis: Laser scanning shows that the material loss of the valve sleeve throttling edge is ΔV = 0.82 mm³, and the wear rate is consistent with the formula Eᵣ = α·(ΔP)¹· 5 ·η, prediction error <7%.

[0034] Example 2: Comparative test with traditional device The performance parameters of the present invention and the conventional erosion test device are compared under the same test conditions (pressure fluctuation, see the paper "Design and Performance Testing of Erosion Test Platform for Drilling and Completion Tools"; wear dispersion, see patent publication number CN115200976A; valve core vibration acceleration and temperature fluctuation, see patent publication number CN 109100127 A). The comparison is shown in the table below: Performance indicators This embodiment Traditional devices Temperature fluctuation (℃) ±1.5 The temperature is single and uncontrollable Pressure fluctuation (%) ±0.5 ±2 Wear dispersion (%) 6.3 ≥20 Valve core vibration acceleration (g) 0.4 Uncontrollable and without buffer device Conclusion: The present invention can significantly improve the test consistency and the authenticity of working condition simulation.

[0035] In the description of the embodiments of the present invention, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "center", "top", "bottom", "top", "bottom", "inside", "outside", "inner side", "outer side" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the purpose of facilitating the description of the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention. Among them, "inside" refers to an internal or enclosed area or space. "Periphery" refers to the area surrounding a specific component or specific area.

[0036] In the description of the embodiments of the present invention, the terms "first," "second," "third," and "fourth" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly specifying the number of the technical features indicated. Therefore, a feature specified as "first," "second," "third," or "fourth" may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "plurality" means two or more.

[0037] In the description of the embodiments of the present invention, it should be noted that, unless otherwise expressly specified or limited, the terms "installed," "connected," "connected," and "assembled" should be understood in a broad sense. For example, they may refer to fixed connections, detachable connections, or integral connections; they may refer to direct connections, indirect connections through an intermediate medium, or internal connections between two components. Those skilled in the art will understand the specific meanings of the above terms in the present invention in specific circumstances.

[0038] In the description of the embodiments of the present invention, specific features, structures, materials or characteristics may be combined in an appropriate manner in any one or more embodiments or examples.

[0039] In describing the embodiments of the present invention, it should be understood that "-" and "~" represent a range between two values, and the range includes the endpoints. For example, "AB" represents a range greater than or equal to A and less than or equal to B. "A~B" represents a range greater than or equal to A and less than or equal to B.

[0040] In describing the embodiments of the present invention, the term "and / or" is used herein to describe a relationship between associated objects, indicating that three possible relationships exist. For example, "A and / or B" can represent three situations: A exists alone, A and B exist simultaneously, and B exists alone. Furthermore, the character " / " is generally used herein to indicate that the associated objects are in an "or" relationship.

[0041] While embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions, and variations may be made to these embodiments without departing from the principles and spirit of the invention, and that the scope of the invention is defined by the appended claims and their equivalents.

Claims

1. A high-frequency erosion and wear test device for reversing valves in aviation hydraulic systems, characterized in that: include: A control unit (1), a stirring unit (2), an erosion unit (3), a cooling unit (4) and a circulation pipeline unit (5); the stirring unit (2) mixes the medium particles and the aviation hydraulic oil and then transports the mixed oil to the circulation pipeline unit (5); the control unit (1) drives the hydraulic pump (13) through the motor (14) to make the mixed oil reach a set pressure value and then erodes the reversing valve in the erosion unit (3); at the same time, the control unit (1) can adjust the reversing frequency of the reversing valve to simulate the working state of the reversing valve of the aviation hydraulic system in actual working conditions; the cooling unit (4) cools the high-temperature oil after erosion, so that the entire test is carried out at a specific temperature; The control unit (1) controls the motor (14), the medium pump (11), the water pump (33), the safety valve (37) and the sensor network through electrical connections to achieve closed-loop control of erosion pressure, temperature and switching frequency.

2. The device according to claim 1, characterized in that The stirring unit (2) comprises: A stirring box, two symmetrically arranged stirring devices (9), a first temperature sensor (8) and a medium pump (11); The two stirring devices (9) are respectively provided with ten fan-shaped blades that rotate in opposite directions to form turbulence; the medium pump (11) quantitatively transports the hard particles in the medium storage box (12) to the stirring box, and mixes them with the aviation hydraulic oil through the stirring device (9) to form an erosion suspension; wherein, the medium storage box (12) has a built-in balance to make the medium concentration adjustable.

3. The device according to claim 1, characterized in that The erosion unit (3) comprises: a reversing valve clamping mechanism (21), a test bench support structure (20), oil inlet and oil outlet pipelines (19), and a reversing valve working pipeline (22); The control unit (1) is coupled to an external electromagnetic drive device to accurately adjust the switching frequency of the reversing valve.

4. The device according to claim 3, characterized in that The reversing valve clamping mechanism (21) is a manual bidirectional clamping structure, which locks the valve body by a knob to suppress vibration caused by high-frequency reversing; The end of the reversing valve working pipeline (22) is provided with a dedicated interface for connecting to the A / B port of the reversing valve body, and the ends of the oil inlet and oil outlet pipelines (19) are provided with dedicated connectors for connecting to the P / T port of the reversing valve body.

5. The device according to claim 1, characterized in that The cooling unit (4) comprises: Plate heat exchanger, water pump (33) and constant temperature water tank (35); The water pump (33) dynamically adjusts the flow rate of cooling water based on feedback from the temperature sensor to maintain the oil temperature within a set value of ±2°C.

6. The device according to claim 1, characterized in that The circulation pipeline unit (5) comprises: A hydraulic pump (13), a motor (14), a relief valve (16), a first filter (26) and a second filter (28) connected in parallel; The first filter (26) filters out metal impurities, and the second filter (28) separates viscous oil colloid.

7. The device according to claim 1, characterized in that The sensor network comprises: a first temperature sensor (8), a second temperature sensor (17), a third temperature sensor (23), and a fourth temperature sensor (36) distributed at the stirring box, the inlet / outlet of the erosion unit (3), and the outlet of the cooling unit (4); A first pressure sensor (18) and a second pressure sensor (24) are arranged at the inlet / outlet of the erosion unit (3); a flow sensor (15) is arranged at the inlet of the erosion unit (3); The data from each sensor is transmitted to the integrated panel of the control unit (1) in real time.

8. The method according to claim 1, wherein: The control unit (1) calculates and displays in real time: Erosion pressure difference (ΔP=P 18 -P 24 ), particle concentration deviation, temperature gradient and cumulative erosion time.

9. The device according to claim 7, characterized in that Further comprising a safety unit comprising: The overpressure linkage safety valve (37) triggers an emergency stop of the system when the detection value of the first pressure sensor (18) exceeds 120% of a set threshold value.

10. A high-frequency erosion wear test method for a reversing valve in an aviation hydraulic system, implemented based on the device according to any one of claims 1 to 9, characterized in that: Including steps: a. Set erosion pressure, temperature, switching frequency and particle concentration; b. The medium pump (11) quantitatively delivers hard particles to the mixing tank to form a uniform suspension; c. The hydraulic pump (13) pressurizes the oil to the set pressure, driving the reversing valve to operate at the set frequency; d. The plate heat exchanger adjusts the cooling water flow based on outlet oil temperature feedback; e. Real-time recording of erosion pressure difference, temperature and flow data; f. After the test, perform a 3D topography scan of the valve body to quantify the material loss volume.

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