Comprehensive test bed for pressure relief valve of airplane

Abstract

The invention discloses a comprehensive test bed for an aircraft pressure relief valve. The comprehensive test bed comprises a test oil tank, a fuel oil temperature adjusting system, a high and low temperature environment box, a test pipeline system and a measurement and control system, various test tasks are accurately carried out according to test contents through the measurement and control system, performance parameters of the to-be-tested pressure relief valve are meticulously obtained, it is ensured that the to-be-tested pressure relief valve can stably and effectively operate in actual use, and system risks caused by faults of the pressure relief valve are greatly reduced; the test pipeline system is provided with a double-flow pipeline and can test two pressure relief valves with different flows at the same time, so that the test time is greatly shortened, the detection efficiency is improved, and the development cycle of the pressure relief valves is shortened. Furthermore, the pressure relief valve test system has good universality and expandability, can adapt to test requirements of pressure relief valves of different types and specifications, and can perform corresponding modification and upgrading on a test pipeline system and a measurement and control system according to new standard requirements.

Description

Technical Field

[0001] The invention belongs to the technical field of aerospace testing, and in particular relates to a comprehensive test bench for aircraft pressure relief valves. Background Art

[0002] Aircraft valves are the terminal valves of the aircraft fuel system. They are used in an environment with an altitude of 0 to 15,000 meters and are installed close to the aircraft engine. Therefore, such valves must meet the requirements of high temperature resistance, low temperature resistance, oil pressure resistance, self-pressure relief, and good internal and external sealing. After the development of such valves is completed, internal sealing, external sealing, pressure relief valve, pressure resistance, high temperature durability, low temperature durability, and normal temperature durability tests need to be carried out. Previously, after the development of such valves was completed, they needed to be tested in the environmental test room, strength test room, and performance test room respectively. There were no conditions for performance tests during environmental tests, and the environmental conditions could not be met during performance tests. There are problems such as cumbersome test work, high test cost, and incomplete test content. Therefore, it is necessary to develop a comprehensive test bench that can meet the above conditions at the same time. The test bench can complete the internal sealing test, external sealing test, pressure relief valve test, pressure resistance test, low temperature durability test, high temperature durability test, and normal temperature durability test of a certain type of aircraft valve.

[0003] Most existing testing technologies rely on various laboratories and coordinate many departments to conduct tests. Environmental simulation requires the use of environmental laboratories, and performance tests require the cooperation of electrical and mechanical groups in performance laboratories. Existing testing technologies have the following disadvantages:

[0004] Single function: Only limited types of tests can be performed, which cannot fully cover the performance of aircraft pressure relief valves under various working conditions, such as extreme temperature, pressure, flow, etc.

[0005] Low degree of automation: The operation process still requires a lot of manual intervention, which not only increases labor costs, but also easily leads to errors and instability in test results due to human factors.

[0006] Limited data collection and processing capabilities: Unable to quickly and accurately collect large amounts of test data, and lack of clarity and visibility in data analysis and processing.

[0007] Poor compatibility: Different test contents need to be tested with the help of different test benches, which increases the test time and labor costs.

[0008] Insufficient reliability: The equipment itself is prone to failure, with high repair and maintenance costs, and may affect the test progress and accuracy of the results.

[0009] Lack of remote monitoring and diagnosis capabilities: Remote operation and monitoring cannot be achieved, which is not conducive to timely detection of problems and multi-location collaborative work. Summary of the invention

[0010] In order to solve the above problems existing in the prior art, the present invention provides an aircraft pressure relief valve comprehensive test bench. The technical problem to be solved by the present invention is achieved through the following technical solutions:

[0011] The present invention provides an aircraft pressure relief valve comprehensive test bench, comprising:

[0012] Test fuel tank, fuel temperature control system, high and low temperature environment box, test pipeline system and measurement and control system; among them,

[0013] The test fuel tank is used to store aviation kerosene;

[0014] The fuel temperature regulating system is used to automatically control and regulate the temperature of the aviation kerosene in the test pipeline system;

[0015] The high and low temperature environment box is used to provide a test environment with a corresponding temperature for the pressure relief valve to be tested;

[0016] The test pipeline system is used to transmit aviation kerosene to the pressure relief valve to be tested using its own dual flow pipeline according to the specifications of the pressure relief valve to be tested, and control the flow and pressure in the test pipeline system based on a preset PID system;

[0017] The measurement and control system is used to control the test temperature, pressure and flow in the high and low temperature environment box and the test pipeline system, test the pressure relief valve to be tested according to the test content, and obtain the test results.

[0018] In one embodiment of the present invention, a test oil tank comprises:

[0019] High temperature oil tank and low temperature oil tank; among them,

[0020] According to the requirements of high and low temperature tests, high temperature oil tanks are used to store the aviation kerosene needed for high temperature tests, and low temperature oil tanks are used to store the aviation kerosene needed for low temperature tests.

[0021] In one embodiment of the present invention, the fuel temperature regulating system comprises:

[0022] Fuel heating temperature control device, fuel cooling temperature control device, circulation system and control system.

[0023] In one embodiment of the present invention, the fuel temperature regulating system automatically controls and regulates the temperature of the aviation kerosene in the test pipeline system, including:

[0024] When the fuel temperature regulating system regulates the temperature of the aviation kerosene in the test pipeline system, the circulation system is used as the power source, and the fuel heating temperature control device is used to repeatedly circulate and heat the high and low temperature medium, and the temperature of the aviation kerosene reaches the preset temperature requirement through heat exchange between the high and low temperature medium and the aviation kerosene;

[0025] When the fuel temperature regulating system cools down the temperature of the aviation kerosene in the test pipeline system, the circulation system is used as a power source, and the high and low temperature medium is repeatedly circulated and cooled through the fuel refrigeration temperature control device, so that the temperature of the aviation kerosene reaches the preset temperature requirement;

[0026] The control system uses the current temperature of the aviation kerosene as a feedback value, and based on the temperature PID control of the PLC, self-adjusts the power of the fuel heating temperature control device and the fuel cooling temperature control device according to the preset temperature requirements to achieve automatic control and adjustment of the aviation kerosene temperature.

[0027] In one embodiment of the present invention, the high and low temperature medium includes Dow Corning thermal oil.

[0028] In one embodiment of the present invention, the test pipeline system includes a small flow pipeline system and a large flow pipeline system.

[0029] In one embodiment of the present invention, the measurement and control system controls the test temperature, pressure and flow in the high and low temperature environment box and the test pipeline system, tests the pressure relief valve to be tested according to the test content, and obtains the test results, including:

[0030] The measurement and control system controls the test temperature, pressure and flow in the high and low temperature environment box and the test pipeline system, and controls the aircraft pressure relief valve comprehensive test bench to perform internal sealing and pressure resistance, external sealing and pressure relief, and durability tests according to the test content to obtain corresponding test results.

[0031] Beneficial effects of the present invention:

[0032] In the solution provided by the present invention, various test tasks are accurately performed according to the test content through the measurement and control system, and the performance parameters of the pressure relief valve to be tested are carefully obtained, ensuring that the pressure relief valve to be tested can operate stably and effectively in actual use, which greatly reduces the system risk caused by pressure relief valve failure; the test pipeline system has a dual flow pipeline, which can test two pressure relief valves with different flow rates at the same time, greatly reducing the time required for testing, improving detection efficiency, and shortening the development cycle of the pressure relief valve; further, the present invention has good versatility and scalability, can adapt to the testing requirements of pressure relief valves of different types and specifications, and can carry out corresponding transformation and upgrading of the test pipeline system and the measurement and control system according to the new standard requirements. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 A schematic diagram of an aircraft pressure relief valve integrated test bench provided by an embodiment of the present invention;

[0034] Figure 2 A schematic structural diagram of an aircraft pressure relief valve comprehensive test bench provided by an embodiment of the present invention;

[0035] Figure 3 A principle block diagram of a temperature control part in a comprehensive test bench for an aircraft pressure relief valve provided by an embodiment of the present invention;

[0036] Figure 4 A schematic diagram of a small flow rate pipeline system for conducting internal sealing and pressure resistance tests in an aircraft pressure relief valve comprehensive test bench provided by an embodiment of the present invention;

[0037] Figure 5 A schematic diagram of a small flow rate pipeline system for conducting external sealing and pressure relief tests on an aircraft pressure relief valve comprehensive test bench provided by an embodiment of the present invention;

[0038] Figure 6 A schematic diagram of a durability test of a small flow rate pipeline system in an aircraft pressure relief valve comprehensive test bench provided by an embodiment of the present invention;

[0039] Figure 7 A schematic diagram of the internal sealing and pressure resistance test of a large flow piping system in a comprehensive test bench for an aircraft pressure relief valve provided by an embodiment of the present invention;

[0040] Figure 8 A schematic diagram of a large flow rate pipeline system for conducting external sealing and pressure relief tests in a comprehensive test bench for an aircraft pressure relief valve provided by an embodiment of the present invention;

[0041] Fig. 9 A schematic diagram of a durability test of a large flow rate pipeline system in a comprehensive test bench for an aircraft pressure relief valve provided by an embodiment of the present invention;

[0042] Fig.10 A principle block diagram of a pressure control part in a comprehensive test bench for an aircraft pressure relief valve provided by an embodiment of the present invention;

[0043] Fig.11 The present invention provides a block diagram of the flow control part of an aircraft pressure relief valve comprehensive test bench. DETAILED DESCRIPTION

[0044] The present invention is further described in detail below with reference to specific embodiments, but the embodiments of the present invention are not limited thereto.

[0045] The embodiment of the present invention provides an aircraft pressure relief valve comprehensive test bench, such as Figure 1 As shown, it may include:

[0046] Test fuel tank, fuel temperature control system, high and low temperature environment box, test pipeline system and measurement and control system; among them,

[0047] Test fuel tanks, used to store aviation kerosene;

[0048] Fuel temperature regulation system, used to automatically control and regulate the temperature of aviation kerosene in the test pipeline system;

[0049] High and low temperature environment box, used to provide a test environment with corresponding temperature for the pressure relief valve to be tested;

[0050] The test pipeline system is used to transfer the aviation kerosene to the pressure relief valve to be tested by using its own dual flow pipeline according to the specifications of the pressure relief valve to be tested, and control the flow and pressure in the test pipeline system based on a preset PID system;

[0051] The measurement and control system is used to control the test temperature, pressure and flow in the high and low temperature environment box and the test pipeline system, test the pressure relief valve to be tested according to the test content, and obtain the test results.

[0052] An aircraft pressure relief valve comprehensive test bench provided by an embodiment of the present invention accurately performs various test tasks according to the test content through a measurement and control system, and meticulously obtains the performance parameters of the pressure relief valve to be tested, ensuring that the pressure relief valve to be tested can operate stably and effectively in actual use, greatly reducing the system risk caused by pressure relief valve failure; the test pipeline system has a dual flow pipeline, which can test two pressure relief valves with different flow rates at the same time, greatly reducing the time required for testing, improving detection efficiency, and shortening the development cycle of the pressure relief valve; further, the present invention has good versatility and scalability, can adapt to the testing requirements of pressure relief valves of different types and specifications, and can carry out corresponding modifications and upgrades to the test pipeline system and the measurement and control system according to new standard requirements.

[0053] See the schematic diagram of the structure of an aircraft pressure relief valve comprehensive test bench provided by the embodiment of the present invention. Figure 2 As shown, for ease of understanding, the following will be combined Figure 2 Each module of the aircraft pressure relief valve comprehensive test bench proposed in the embodiment of the present invention is introduced respectively.

[0054] Test fuel tank

[0055] Test fuel tank, such as Figure 2 As shown, it may include:

[0056] High temperature oil tank and low temperature oil tank; among them,

[0057] According to the requirements of high and low temperature tests, high temperature oil tanks are used to store the aviation kerosene needed for high temperature tests, and low temperature oil tanks are used to store the aviation kerosene needed for low temperature tests.

[0058] Specifically, the high-temperature oil tank and the low-temperature oil tank are respectively composed of a tank body, a flame-retardant breathing valve, a liquid level gauge and a hose connector. The maximum flow rate of the test pipeline system is 667L / min, which is equivalent to a maximum circulation flow rate of 494kg per minute. The oil temperature needs to be accurately controlled during the high and low temperature test. Considering that the cycle time is too short and the pump and other equipment have a great impact on the oil temperature during the cycle, the circulation time of the fuel in the tank cannot be too short. The cycle time is determined to be two minutes. The minimum oil storage capacity of the tank is 1 ton, and the minimum volume is calculated to be 1290L. Considering factors such as the expansion space of the tank, the capacity of a single test tank can be 1.5m 3 .

[0059] The test fuel tank contains two tanks, which have a dual backup function. If a single tank fails during long-term use, the backup tank can be used in time to ensure the progress of the test; the interval between high-temperature and low-temperature tests may be very short. Considering the thermal inertia of the fuel, two tanks are selected to ensure that the high-temperature and low-temperature tests can be quickly switched. Users can flexibly set the temperature threshold according to their specific needs, use the high-temperature tank to store aviation kerosene above the temperature threshold for high-temperature tests, and use the low-temperature tank to store aviation kerosene below the temperature threshold for low-temperature tests.

[0060] Fuel temperature control system

[0061] Fuel temperature regulation system, such as Figure 2 As shown, it may include:

[0062] Fuel heating temperature control device, fuel cooling temperature control device, circulation system and control system.

[0063] The fuel temperature regulation system automatically controls and regulates the temperature of the aviation kerosene in the test pipeline system, which may include:

[0064] When the fuel temperature regulating system regulates the temperature of the aviation kerosene in the test pipeline system, the circulation system is used as the power source, and the fuel heating temperature control device is used to repeatedly circulate and heat the high and low temperature medium, and the temperature of the aviation kerosene reaches the preset temperature requirement through heat exchange between the high and low temperature medium and the aviation kerosene;

[0065] When the fuel temperature regulating system cools down the temperature of the aviation kerosene in the test pipeline system, the circulation system is used as the power source, and the high and low temperature media are repeatedly circulated and cooled through the fuel refrigeration temperature control device to make the temperature of the aviation kerosene reach the preset temperature requirement;

[0066] The control system uses the current temperature of the aviation kerosene as the feedback value, and based on the temperature PID control of the PLC, self-adjusts the power of the fuel heating temperature control device and the fuel cooling temperature control device according to the preset temperature requirements to achieve automatic control and regulation of the aviation kerosene temperature.

[0067] Understandably, the fuel temperature regulation system adopts cascade refrigeration and explosion-proof heating technology. Through precise temperature PID control, the fuel temperature can be accurately adjusted within the range of (-45±2)℃~(93±2)℃, ensuring the stable test under different temperature conditions and improving the test accuracy. The high and low temperature environment chamber uses a unique air duct system and cascade refrigeration and explosion-proof heating technology to simulate the ambient temperature of (-55±2)℃~(120±2)℃, and the temperature fluctuation rate, uniformity, deviation and other indicators are precisely controlled, providing a stable and reliable test environment for the pressure relief valve to be tested.

[0068] The high and low temperature medium may include Dow Corning thermal oil.

[0069] Specifically, the fuel refrigeration temperature control device is composed of a compressor, a condenser, an evaporator and various refrigeration pipe valves. The refrigeration cycle adopts a reverse Carroll cycle, which consists of two isothermal processes and two adiabatic processes. The process is as follows: the refrigerant is adiabatically compressed to a higher pressure by the compressor, consuming work to increase the exhaust temperature, and then the refrigerant isothermally exchanges heat with the surrounding medium through the condenser to transfer heat to the surrounding medium. The refrigerant then adiabatically expands through the throttle valve to do work, and the refrigerant temperature decreases at this time. Finally, the refrigerant isothermally absorbs heat from the object with a higher temperature through the evaporator, lowering the temperature of the cooled object. This cycle repeats itself to achieve the purpose of cooling.

[0070] The fuel heating temperature control device heats high and low temperature media and assists in constant temperature at low temperatures. The fuel heating temperature control device can adopt an explosion-proof structure. The heater used is an explosion-proof heater, which is customized by a professional manufacturer with explosion-proof qualifications and meets explosion-proof requirements. The heating power is calculated according to the first formula and a certain margin is left. Among them, the first formula is as follows:

[0071]

[0072] The fuel heating temperature control device has three heating protections. When the control protection of the controller body fails, the temperature exceeds the temperature value set by the deviation protector in the fuel heating temperature control device, and the power supply of the solid-state relay will be cut off; the independent temperature limiter prevents the temperature from exceeding the limit value after the deviation protector fails, preventing high temperature overshoot.

[0073] The high and low temperature medium exchanges heat with the aviation kerosene through heat transfer to reach the required temperature of the aviation kerosene.

[0074] The circulation system consists of a stainless steel expansion tank, a cold storage tank, a magnetic circulation pump, pipelines, valves, flanges, etc., and is equipped with good insulation measures when it leaves the factory. The insulation is made of high-density rubber and plastic insulation materials, which has good insulation and heat insulation effects. The detachable design is very convenient for subsequent maintenance and repair. The design of the circulation system fully considers the prevention of leakage of the refrigerant or its vapor. An expansion tank is provided. When the equipment is working normally, the expansion tank is closed and does not come into contact with the outside air. Only when it is running for the first time, it is necessary to open the exhaust valve to discharge the air in the system. The expansion tank can ensure that the system is full of liquid at low temperatures, and the liquid level of the expansion tank rises but does not overflow when the system is high temperature. The circulation system accelerates the convection speed of high and low temperature media through the circulation pump, and makes it exchange heat with the fuel in the high and low temperature fuel tank through the heat exchanger to achieve a better heat exchange effect. The entire system is equipped with a separate annular circulation pipeline. The high and low temperature media flow through the heat exchanger to exchange heat with the aviation kerosene in the high and low temperature fuel tank, and circulate repeatedly. By controlling the circulation flow and temperature of the high and low temperature media, the temperature of the fuel in the high and low temperature tank can be accurately controlled.

[0075] The control system controls and adjusts the temperature and flow of high and low temperature media, thereby accurately controlling the temperature of the fuel in the high and low temperature fuel tanks. The system control principle is based on PLC temperature PID control. For the principle block diagram of the temperature control part, please refer to Figure 3 .from Figure 3 It can be seen that when the fuel is heated, the explosion-proof heater starts to work, the fuel temperature is detected by the temperature sensor, and the temperature value signal is sent to the PLC or temperature instrument. The PLC compares the temperature feedback signal with the input reference value to obtain the deviation value. This deviation value is corrected according to the PID algorithm to adjust the heating power of the explosion-proof heater, thereby realizing automatic control of the fuel temperature. When the fuel is cooled, the compressor starts to work, the fuel temperature is detected by the temperature sensor, and the temperature value signal is sent to the PLC or temperature instrument. The PLC compares the temperature feedback signal with the input reference value to obtain the deviation. This deviation is corrected according to the PID algorithm to adjust the cooling capacity of the compressor, thereby realizing automatic control of the fuel temperature. The method of changing the control set value can respond to the system lag in the process as quickly as possible and obtain the minimum system overshoot. The control consists of two groups of PID (each PID is variable) control loops, which are called: the main loop and the slave loop. The control output of the main loop is used as the set value of the slave loop. The system uses a feedforward PV. The output of the PID operation result of the main control loop is combined with the feedforward PV signal as the set value of the slave control loop. By controlling the temperature change gradient in this way, the temperature control accuracy of the system is guaranteed.

[0076] High and low temperature environment box

[0077] The high and low temperature environmental chamber provides a test environment with corresponding temperature for the pressure relief valve to be tested. The high and low temperature environmental chamber is mainly composed of a working box, a heating system, a refrigeration system, an air duct system and a temperature control system. During the high temperature test, the air duct system draws the air of the working room from the bottom into the air duct through a multi-wing fan, and blows it out from the top of the air duct after being heated by the heating coil of the heating system. The air that has exchanged heat with the test piece in the working room is then blown into the air duct again, and the cycle is repeated to meet the high temperature setting requirements; during the low temperature test, the air duct system draws the air of the working room from the bottom into the air duct through a multi-wing fan, and blows it out from the top of the air duct after being cooled by the refrigeration system. The air that has exchanged heat with the test piece in the working room is then blown into the air duct again, and the cycle is repeated to meet the low temperature setting requirements; the control system automatically adjusts the cooling capacity and the power of the heating coil according to the feedback value of the temperature sensor in the working room and compares it with the temperature value to achieve automatic control of the temperature of the test chamber.

[0078] Test pipeline system

[0079] The test piping system uses its own dual flow pipeline to transfer aviation kerosene to the pressure relief valve to be tested according to the specifications of the pressure relief valve to be tested, and controls the flow and pressure in the test piping system based on the preset PID system.

[0080] The test piping system may include a small flow piping system and a large flow piping system.

[0081] The small flow piping system consists of a small oil pump, oil filter, small flow meter, electric valve, ball valve, pressure sensor, etc. It is mainly used to test the internal sealing and pressure resistance, external sealing and pressure relief, and durability of the pressure relief valve Z / KJ-4 to be tested. For the schematic diagram of the internal sealing and pressure resistance test of the small flow piping system, please refer to Figure 4 As shown, it can be seen that when conducting the test, first close ball valve 3 and ball valve 7, then connect the hand pump interface at the valve inlet to the hand pump, pressurize the fuel pressure in the pipeline to the pressure value required by the test through the hand pump, measure the leakage through a measuring cup at the hand pump interface at the valve outlet, and measure the leakage through a stopwatch; when conducting the reverse test, connect the hand pump to the hand pump interface at the valve outlet, and measure the reverse leakage of the valve through a measuring cup. The tested valve is set at the high point of the test pipeline, and the hand pump interface is set at the low point of the test pipeline, so that the pipeline can be quickly drained before the test and the leaked fuel at the outlet can be quickly collected during the test.

[0082] For the schematic diagram of the external sealing and pressure relief test of the small flow piping system, please refer to Figure 5As shown in the figure, the pressure in the pipeline is 0.5MPa during the external sealing test of the pressure relief valve to be tested, and the pressure in the pipeline is 0.4-0.6MPa during the pressure relief test. The fuel flow rate is 0.15L / min. The fuel pressure required by the test is relatively high. The oil pump model is KCB18.3-304 stainless steel gear pump, and the working flow rate of the flow pump is 0.6m 3 / h, working pressure 1.2MPa, meet the test requirements. During the external sealing test, close the hand pump interface at the valve inlet and outlet. The fuel is powered by the fuel pump and is delivered to the valve inlet through a stainless steel pipeline after being pressurized. A pressure sensor is set on the pipeline to collect and feedback the pressure in the pipeline in real time. The control system controls the opening size of the electric valve 1 according to the feedback value of the pressure sensor, and then controls the medium pressure in the pipeline to reach the test set value. Visually check whether there is fuel leakage outside the shell. During the pressure relief test, close the hand pump interface and ball valve 7 of the Z / KJ-4 inlet, and open the hand pump interface of the Z / KJ-4 outlet; the pressure relief valve opening pressure is 0.4~0.6MPa. In order to prevent the pressure relief valve from opening failure or excessive pressure in the pipeline after opening, an electric valve 2 is set in the bypass of the small oil pump to control the pressure in the pipeline and prevent the fuel in the pipeline from overpressure and damaging the equipment. When the pressure relief valve is opened, the flow rate is 0.15L / min. The flow rate in the pipeline is too small to be accurately measured by the flow meter. It is necessary to open the hand pump interface at the outlet of the test piece and measure the flow rate with a measuring cup.

[0083] For the schematic diagram of durability test of small flow piping system, please refer to Figure 6 As shown, the durability test pipeline system schematic diagram shows the durability test under normal temperature, the durability test under high temperature, and the durability test under low temperature. Close the hand pump interface and open hand valve 3 and hand valve 7; the medium flow rate in the Z / KJ-4 durability test pipeline is 3.6L / min, and the working flow rate of the small flow pump can meet the test requirements. The small flow meter collects the flow rate in the pipeline in real time and feeds it back to the control system. The control system controls the electric regulating valve 1 according to the flow feedback value so that the flow rate in the pipeline meets the test set value; in order to prevent the fuel pressure in the pipeline from being too high after the Z / KJ-4 valve is closed, the small oil pump bypass is set with an electric valve 2 to adjust the pressure in the pipeline. A bellows is set at the valve inlet to suppress the water hammer effect caused by the sudden closure of the valve.

[0084] The small flow piping system is used to test the pressure relief valve Z / KJ-4 to be tested. According to the test requirements of the pressure relief valve Z / KJ-4 to be tested, the maximum flow required for the test is 3.6L / min. The flow capacity of the small flow piping system should cover the flow requirements of the pressure relief valve Z / KJ-4 to be tested, and have a certain margin; the calculation formula for the inner diameter of the pipeline is as follows:

[0085]

[0086] Among them, d represents the inner diameter of the pipeline, Q represents the maximum flow rate through the pipeline, and V represents the allowable flow rate of fuel in the pipeline.

[0087] The large flow piping system consists of a large flow pump, stainless steel pipes, manual ball valves, check valves, hand pumps and other finished products.

[0088] For the schematic diagram of the internal tightness and pressure resistance test of the large flow piping system, please refer to Figure 7 As shown, when testing the pressure relief valve Z / KJ-3 (Z / KJ-2) to be tested, first close valve 4 and valve 6, then connect the hand pump interface of the valve inlet to the hand pump, pressurize to the pressure value required by the test through the hand pump, measure the leakage through the measuring cup at the hand pump interface of the valve outlet, and measure the leakage through the stopwatch; when testing in reverse, connect the hand pump to the hand pump interface of the valve outlet, and measure the leakage of the valve inlet with the measuring cup. The pressure relief valve to be tested is set at the high point of the test pipeline, and the hand pump interface is set at the low point of the test pipeline, so that the pipeline can be quickly drained before the test and the fuel leaked from the outlet can be quickly collected during the test.

[0089] For the schematic diagram of the external tightness and pressure relief test of large flow piping systems, please refer to Figure 8 As shown, when conducting the external sealing test, close the hand pump interface at the inlet and outlet of the valve, close valve 3 and open valve 5. The fuel is powered by the fuel pump and is delivered to the valve inlet through a stainless steel pipeline after being pressurized. A pressure sensor is set on the pipeline to collect and feedback the pressure in the pipeline in real time. The control system controls the opening size of the electric valve 1 according to the feedback value of the pressure sensor, and then controls the medium pressure in the pipeline to reach the test set value. Visually check whether there is fuel leakage outside the shell. When conducting the pressure relief test, close the hand pump interface and ball valve 7 at the inlet of Z / KJ-3 (Z / KJ-2), and open the hand pump interface at the outlet of Z / KJ-3 (Z / KJ-2); the pressure relief valve opening pressure is 0.4~0.6MPa. In order to prevent the pressure relief valve from opening failure or excessive pressure in the pipeline after opening, an electric valve 2 is set in the bypass of the small oil pump to control the pressure in the pipeline and prevent the fuel in the pipeline from overpressure and damaging the equipment. When the pressure relief valve is opened, the flow rate is 0.25L / min. The flow rate in the pipeline is too small to be accurately measured by the flow meter. It is necessary to open the hand pump interface at the outlet of the test piece and measure the flow rate with a measuring cup.

[0090] For the schematic diagram of durability test of large flow piping system, please refer to Fig. 9 As shown in the figure, the specific test principles of durability test under normal temperature environment, durability test under high temperature environment, and durability test under low temperature environment. During the Z / KJ-3 (Z / KJ-2) durability test, the test pipeline flow rate is 6.33×105ml / min, and the large oil pump model selected is ISW80-200A centrifugal pump with a flow rate of 47m3 / h, head 44m. Meet the test requirements. The fuel is powered by a large oil pump and is delivered to the inlet of Z / KJ-3 (Z / KJ-2) after being pressurized. The flow in the pipeline is collected in real time through a large flow meter and fed back to the control system. The control system controls the electronically controlled regulating valve according to the feedback value to control the flow in the pipeline. Considering that the sudden closure of the test piece during the durability test will cause a sharp increase in the pressure in the pipeline, in order to prevent overpressure in the pipeline, an electric regulating valve is set at the bypass of the large oil pump to adjust the pressure in the pipeline. A bellows is set at the valve inlet to suppress the water hammer effect caused by the sudden closure of the valve.

[0091] In the aircraft pressure relief valve comprehensive test bench provided by the embodiment of the present invention, the principle block diagram of the pressure control part can be found in Fig.10 As shown in the figure, the pressure control part adopts a pressure control simulation system. The pressure control is used to accurately simulate the pressure in the fuel pipeline and check the relevant working performance of the pressure relief valve to be tested. The control system mainly consists of a control system, an electric control valve, a pressure sensor and other main components to form a closed-loop control system for real-time control. The control system takes pressure as the target control quantity. After comparing it with the actual pressure sensor feedback signal, the control system outputs the electric valve opening control signal for the current deviation. Through the fast, stable and accurate control of the electric control valve, the stable control of pressure is finally achieved. When conducting the test, you only need to enter the pressure value on the measurement and control system. The system will monitor the pressure sensor data in real time, and compare the value with the given pressure value in real time by real-time feedback of the pressure sensor value. Then the measurement and control system will automatically control the electric control valve to make real-time adjustments until the pressure sensor value is equal to the given pressure value. The electric control valve maintains the current position, and the pipeline system reaches the required pressure value of the test.

[0092] In the aircraft pressure relief valve comprehensive test bench provided by the embodiment of the present invention, the principle block diagram of the flow control part can be found in Fig.11 As shown in the figure, the flow control part adopts a flow control simulation system. The flow control is used to accurately simulate the flow in the fuel pipeline and check the valve related working performance. The control system mainly consists of a control system, an electric control valve, a flow sensor and other main components to form a closed-loop control system for real-time control. The control system takes the flow as the target control quantity. After comparing with the actual flow sensor feedback signal, the control system outputs the electric valve opening control signal for the current deviation. Through the fast, stable and accurate control of the electric control valve, the stable control of the flow is finally achieved. When conducting the test, you only need to enter the flow value in the software, the system will monitor the flow sensor data in real time, and compare the value with the given flow value in real time by real-time feedback of the flow sensor. Then the software will automatically control the electric control valve to make real-time adjustments (open or close) until the flow sensor value is equal to the given flow value. The electric control valve maintains the current position, and the pipeline system reaches the flow value required by the test.

[0093] The aircraft pressure relief valve comprehensive test bench proposed in the embodiment of the present invention can quickly adjust the test pipeline system and test parameters according to the interface and performance requirements of different pressure relief valves to be tested, so as to realize comprehensive testing of pressure relief valves of various specifications to be tested, so as to expand the scope of test objects and improve the applicability of the test bench.

[0094] The test pipeline system proposed in the embodiment of the present invention has a dual-flow pipeline, which can test two pressure relief valves with different flow rates at the same time, greatly reducing the time required for testing, improving detection efficiency, and shortening the development cycle of the pressure relief valve.

[0095] Measurement and control system

[0096] The measurement and control system controls the test temperature, pressure and flow in the high and low temperature environment box and the test pipeline system, tests the pressure relief valve to be tested according to the test content, and obtains the test results, which may include:

[0097] The measurement and control system controls the test temperature, pressure and flow in the high and low temperature environmental chamber and the test pipeline system, and controls the aircraft pressure relief valve comprehensive test bench to perform internal sealing and pressure resistance, external sealing and pressure relief, and durability tests according to the test content to obtain the corresponding test results.

[0098] The aircraft pressure relief valve comprehensive test bench proposed in the embodiment of the present invention integrates multiple test functions, and can complete tests such as internal sealing, external sealing, pressure relief, pressure resistance, durability under different temperature environments, etc., covering multiple key aspects of valve performance testing. Compared with traditional single-function testing equipment, it greatly improves test efficiency and versatility and meets diversified testing needs.

[0099] The measurement and control system may include: a test subsystem and a control subsystem.

[0100] The lower computer of the test subsystem uses a professional data acquisition card to continuously collect various sensor signals (such as pressure signals, flow signals, switch signals). The sensor signals are conditioned and converted and transmitted to the upper computer, which processes and displays the sensor signals graphically. The lower computer of the control subsystem issues control instructions through a professional output control card according to the control instructions issued by the upper computer's measurement and control software, realizing on-site data collection and analysis, closed-loop control of the fuel pressure and flow in the pipeline, and cyclic on-off control of the electric control valve.

[0101] It is understandable that the measurement and control system proposed in the embodiment of the present invention adopts high-speed, high-precision data acquisition cards and high-precision sensors in hardware, which can collect a large amount of test data in real time, including: pressure, temperature, flow rate and number of cycles. The measurement and control system adopts an industrial computer, which is equipped with an advanced multi-core processor with a large number of cores and high frequency, and can process massive data tasks in parallel in an instant, whether it is complex algorithm calculations or large-scale data screening, it can handle it easily; it is equipped with large-capacity high-speed memory to provide a solid guarantee for efficient processing; it is equipped with high-speed solid-state hard disk storage, so that the industrial computer will not freeze when processing large amounts of data.

[0102] The measurement and control system uses LabVIEW software as the development platform for application software. The entire development environment is powerful and user-friendly, forming a fully integrated development environment. The measurement and control software mainly includes software function bars and function display interfaces. The test interface of the measurement and control software mainly includes: communication monitoring, alarm monitoring, test data monitoring, test data recording, test data playback, test data analysis, test data storage, test condition control and curve display. Communication monitoring is used to monitor the operation of various functions; alarm monitoring is used to monitor the medium temperature and environmental box temperature to prevent the temperature from being too high and causing danger; test data monitoring is mainly used to monitor the start-up characteristics, time, current, life and other data of valves with different pressures and flows; test data analysis is mainly reflected in the ability to display the monitoring data in real time in the form of curves, data storage means that the software has the ability to save test data so that the test data can be checked at any time, and data playback means that the software has the function of test data playback so that the test data can be checked at any time. Test condition control is mainly used to control the flow and pressure in the pipeline to meet the test requirements; curve display can display the collected test data in real time in the form of curves.

[0103] The aircraft pressure relief valve comprehensive test bench proposed in the embodiment of the present invention can conveniently install and fix various models and specifications of pressure relief valves to be tested through the installation interface and the adjustable test fixture. When testing the pressure relief valve to be tested, the pressure relief valve to be tested is first installed in a high and low temperature environmental chamber through the test fixture, and the interface of the pressure relief valve to be tested is connected to the test pipeline system. The aircraft pressure relief valve comprehensive test bench can select different test pipelines for testing according to different flow (pressure) sizes by setting dual flow pipelines; tooling fixtures of different sizes are set at the installation location of the pressure relief valve to be tested in the high and low temperature environmental chamber, so that performance detection tests of valves of different sizes and specifications can be carried out.

[0104] The embodiment of the present invention selects high-quality components and materials to improve the stability and durability of the equipment; the test bench adopts a modular design, which decomposes the complex system of the test bench into multiple relatively independent modules, each module has clear functions and boundaries, and is easy to design and optimize separately, which helps to ensure that each module reaches a high quality and reliability standard before being put into overall use; secondly, when a module of the test bench fails, the faulty module can be quickly located and replaced without large-scale inspection and debugging of the entire system, thereby reducing downtime and improving the availability of the test bench; furthermore, the modular design facilitates the upgrading and improvement of the modules. With the development of technology and changes in demand, a module can be updated separately without affecting the normal operation of other modules, so that the test bench can maintain performance and reliability that keep pace with the times; in addition, modular design is conducive to standardized production and quality control.

[0105] It is understandable that the aircraft pressure relief valve comprehensive test bench proposed in the embodiment of the present invention is highly unique. Its modular design concept designs the test oil tank, fuel temperature regulation system, high and low temperature environment box test pipeline system and measurement and control system into independent and coordinated modules, which is not only convenient for the replacement of faulty parts, but also can be flexibly combined and expanded according to different test requirements. For example, the test pipeline system designs large flow and small flow test pipelines for valves of different specifications, respectively using DN65 and DN25 stainless steel pipes, and equipped with oil pumps of different powers, which can meet the test requirements of various valves. The various modules in the aircraft pressure relief valve comprehensive test bench are closely coordinated, and are not independent technical patchworks; among them, the fuel temperature regulation system, the high and low temperature environment box and the test pipeline system cooperate with each other to accurately simulate complex working conditions. When conducting high temperature durability tests, the fuel temperature regulation system provides specific temperature fuel for the test pipeline, and the high and low temperature environment box creates the corresponding ambient temperature, so that the parameters of each module are accurately matched.

[0106] The embodiment of the present invention accurately performs various test tasks according to the test content through the measurement and control system, and obtains the performance parameters of the pressure relief valve to be tested in detail, ensuring that the pressure relief valve to be tested can operate stably and effectively in actual use, greatly reducing the system risk caused by the failure of the pressure relief valve; the test pipeline system has a dual flow pipeline, which can test two pressure relief valves with different flow rates at the same time, greatly reducing the time required for testing, improving the detection efficiency, and shortening the development cycle of the pressure relief valve; further, the present invention has good versatility and scalability, can adapt to the testing requirements of pressure relief valves of different types and specifications, and can perform corresponding transformation and upgrading of the test pipeline system and the measurement and control system according to the new standard requirements. Through modular design, the entire aircraft pressure relief valve comprehensive test bench is divided into a test oil tank, a fuel temperature adjustment system, a high and low temperature environment box, a test pipeline system and a measurement and control system, so that the aircraft pressure relief valve comprehensive test bench improves maintainability, enhances flexibility, shortens the development cycle, improves the quality of the test bench, reduces the production cost of the test bench, and improves the scalability of the test bench.

[0107] It should be noted that in the description of the present invention, it should be understood that the terms "first" and "second" are only used for descriptive purposes and cannot be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.

[0108] The above description is only a preferred embodiment of the present invention and is not intended to limit the protection scope of the present invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention are included in the protection scope of the present invention.

Claims

1. An aircraft pressure relief valve comprehensive test bench, characterized in that: include: Test fuel tank, fuel temperature control system, high and low temperature environment box, test pipeline system and measurement and control system; among them, The test fuel tank is used to store aviation kerosene; The fuel temperature regulating system is used to automatically control and regulate the temperature of the aviation kerosene in the test pipeline system; The high and low temperature environment box is used to provide a test environment with a corresponding temperature for the pressure relief valve to be tested; The test pipeline system is used to transmit aviation kerosene to the pressure relief valve to be tested using its own dual flow pipeline according to the specifications of the pressure relief valve to be tested, and control the flow and pressure in the test pipeline system based on a preset PID system; The measurement and control system is used to control the test temperature, pressure and flow in the high and low temperature environment box and the test pipeline system, test the pressure relief valve to be tested according to the test content, and obtain the test results.

2. The aircraft pressure relief valve comprehensive test bench according to claim 1, characterized in that: The test oil tank comprises: High temperature oil tank and low temperature oil tank; among them, According to the requirements of high and low temperature tests, high temperature oil tanks are used to store the aviation kerosene needed for high temperature tests, and low temperature oil tanks are used to store the aviation kerosene needed for low temperature tests.

3. The aircraft pressure relief valve comprehensive test bench according to claim 1, characterized in that: The fuel temperature regulating system comprises: Fuel heating temperature control device, fuel cooling temperature control device, circulation system and control system.

4. The aircraft pressure relief valve comprehensive test bench according to claim 3, characterized in that: The fuel temperature regulating system automatically controls and regulates the temperature of the aviation kerosene in the test pipeline system, including: When the fuel temperature regulating system regulates the temperature of the aviation kerosene in the test pipeline system, the circulation system is used as the power source, and the fuel heating temperature control device is used to repeatedly circulate and heat the high and low temperature medium, and the temperature of the aviation kerosene reaches the preset temperature requirement through heat exchange between the high and low temperature medium and the aviation kerosene; When the fuel temperature regulating system cools down the temperature of the aviation kerosene in the test pipeline system, the circulation system is used as a power source, and the high and low temperature medium is repeatedly circulated and cooled through the fuel refrigeration temperature control device, so that the temperature of the aviation kerosene reaches the preset temperature requirement; The control system uses the current temperature of the aviation kerosene as a feedback value, and based on the temperature PID control of the PLC, self-adjusts the power of the fuel heating temperature control device and the fuel cooling temperature control device according to the preset temperature requirements to achieve automatic control and adjustment of the aviation kerosene temperature.

5. The aircraft pressure relief valve comprehensive test bench according to claim 4, characterized in that: The high and low temperature medium includes Dow Corning heat transfer oil.

6. The aircraft pressure relief valve comprehensive test bench according to claim 1, characterized in that: The test pipeline system includes a small flow pipeline system and a large flow pipeline system.

7. The aircraft pressure relief valve comprehensive test bench according to claim 1, characterized in that: The measurement and control system controls the test temperature, pressure and flow in the high and low temperature environment box and the test pipeline system, tests the pressure relief valve to be tested according to the test content, and obtains the test results, including: The measurement and control system controls the test temperature, pressure and flow in the high and low temperature environment box and the test pipeline system, and controls the aircraft pressure relief valve comprehensive test bench to perform internal sealing and pressure resistance, external sealing and pressure relief, and durability tests according to the test content to obtain corresponding test results.

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