In-situ measuring device and measuring method for flow rate of throttle of pneumatic transmission system

Abstract

The application discloses a kind of in-situ measuring device and measuring method of air pressure transmission system throttler flow, it is a kind of indirect measuring type flow measuring device and measuring method, including high-pressure small gas cylinder, check valve, electromagnetic switch, pressure relief valve, timer and battery pack.Pressure gauge, pressure relief valve and check valve are connected with high-pressure small gas cylinder respectively;One end of electromagnetic switch gas circuit is connected with the check valve, the other end is connected with gas inlet interface;The circuit of electromagnetic switch is connected with timer and battery pack respectively.The application can measure the total flow of throttler in unit time, so as to reflect the throttling effect of throttler in instantaneous flow or variable flow control process, solve the problem that direct measurement type flowmeter is not convenient for measuring instantaneous flow and variable flow process, can measure instantaneous flow control process or variable flow control process, and the measurement result can reflect whether the flow of throttler deviates from normal state.

Description

Technical Field

[0001] This invention relates to the field of mechanical engineering technology, specifically to an in-situ measuring device and method for measuring the flow rate of a throttle in a pneumatic transmission system. Background Technology

[0002] In pneumatic transmission systems, the flow rate of compressed gas is typically throttled using a throttle valve, thereby enabling control over the movement speed of actuators and the delay time of delaying elements within the pneumatic transmission system.

[0003] Generally, pneumatic transmission systems have specific requirements for the throttling capacity of the throttling device. If the throttling element in the throttling device becomes worn, stuck, or blocked, it will cause a change in the throttling capacity, thereby affecting the gas intake of subsequent actuators or delay elements, leading to changes in the control plan of the entire pneumatic transmission system, and causing malfunctions or accidents.

[0004] Therefore, during the service life of pneumatic transmission systems, it is necessary to periodically check the flow rate of the throttle to prevent accidents. Especially in existing equipment, it is usually necessary to check the operation of the entire system in conjunction with other components and accessories in the pneumatic transmission system. In this case, in-situ testing is required.

[0005] Currently, common devices for gas flow measurement include orifice flow meters, electromagnetic flow meters, turbine flow meters, venturi flow meters, volumetric flow meters, rotor flow meters, vortex flow meters, rotary impeller flow meters, ultrasonic flow meters, and nozzle flow meters. While these flow measurement devices operate on different principles, they can generally be categorized as direct-measurement flow meters. These devices are connected to the gas path during operation, offering the advantage of directly measuring the stable flow rate within the gas path—a direct and convenient method. Furthermore, the system's operational status can be checked during flow measurement. However, they also have the following disadvantages: 1. For instantaneous flow control processes, where the gas flow time is short (e.g., a few milliseconds to tens of milliseconds), achieving flow rate recording is difficult; 2. For variable flow control processes, sometimes it is necessary to measure the average flow rate over the entire process, requiring integration over the entire flow measurement process, which is also difficult to achieve. Summary of the Invention

[0006] To overcome the shortcomings of existing technologies in recording instantaneous flow rates and measuring average flow rates throughout the entire process, this invention proposes an in-situ measurement device and method for measuring the flow rate of a throttle in a pneumatic transmission system.

[0007] The in-situ measurement device for the flow rate of the throttle in the pneumatic transmission system proposed in this invention includes a high-pressure small gas cylinder, a one-way valve, an electromagnetic switch, a pressure relief valve, a timer, and a battery pack. The pressure gauge, pressure relief valve, and one-way valve are each connected to the high-pressure small gas cylinder; one end of the electromagnetic switch's air circuit is connected to the one-way valve, and the other end is connected to the air inlet; the electromagnetic switch's circuitry is connected to the timer and the battery pack.

[0008] In the deceleration parachute section of the cold air duct, the cold air circulation time is 1 second.

[0009] The specific process for measuring the flow rate of the throttle valve in the air cooling system of a certain type of aircraft using the in-situ measuring device proposed in this invention is as follows:

[0010] Step 1, disconnect the connector at the deceleration chute test point:

[0011] Disconnect the connector at the test point in front of the umbrella hook actuator.

[0012] Step 2, connect the testing device:

[0013] The connection test device connects the air inlet of the in-situ measuring device to the pipeline at the disconnected test point, so that the two are connected and gas can flow between the two devices.

[0014] Step 3, test the pressure relief valve:

[0015] Adjust the pressure relief valve by loosening the valve knob to make the pressure inside the high-pressure cylinder equal to the atmospheric pressure; then tighten the knob to close the pressure relief valve, thus cutting off the connection between the high-pressure cylinder and the atmosphere; the change in pressure inside the high-pressure cylinder is the change in pressure inside the measuring device.

[0016] Step 4, inflate the aircraft with air conditioning:

[0017] The aircraft's air conditioning system was filled with cool air to 120 kgf / cm². 2 This allows gas to flow inside the pipeline, enabling the measurement of the gas flow rate.

[0018] Adjust the timer to pass-through mode. In pass-through mode, the gas entering through the inlet port passes sequentially through the electromagnetic switch and the one-way valve into the high-pressure gas cylinder.

[0019] Step 6: Measure the change in gas flow rate in the pipeline:

[0020] Turn on the aircraft's main power switch and activate the parachute deployment switch to measure the change in gas flow rate in the pipeline during parachute deployment. Measure the change in gas flow rate in the pipeline using a measuring device.

[0021] Step 7: Obtain the change in gas flow rate within the pipeline:

[0022] The change in gas flow rate in the pipeline can be obtained by measuring the pressure value displayed on the pressure gauge.

[0023] The gas in the pipeline enters the measuring device through the inlet at the measuring point. The gas then passes through an electromagnetic switch and a one-way valve before entering a high-pressure gas cylinder. The gas's entry into the high-pressure gas cylinder alters the pressure within it, which is then measured by a pressure gauge inside the cylinder, thus determining the gas pressure within the pipeline.

[0024] Step 8, restore the aircraft air intake interface:

[0025] Turn off the aircraft power switch and timer in sequence, disconnect the air intake interface from the test point in step 2, separate the pipeline from the test point, and remove the measuring device.

[0026] Reconnect the disconnected connector at the test point before the umbrella hook actuator, that is, reconnect the disconnected pipes to complete the measurement.

[0027] The indirect flow measurement device and method proposed in this invention can measure the total flow rate passing through a flow throttling device per unit time, thereby reflecting the throttling effect of the flow throttling device in instantaneous flow or variable flow control processes. This solves the problem that direct flow meters are not convenient for measuring instantaneous flow and variable flow processes.

[0028] In this invention, the air circuit of the electromagnetic switch used should be closed when not energized, open when energized, and closed again when de-energized. The timer used can control the switch of the circuit and can be set to count down a certain amount. It is in the open circuit state by default. When the countdown of the timer ends, the circuit is connected and the electromagnetic switch is energized.

[0029] Before starting work, disconnect the air path after the throttle of the system under test and connect it to the air inlet of this equipment; adjust the pressure relief valve, first adjust it to the pressure relief state, confirm that the pressure in the high-pressure small gas cylinder is consistent with the atmospheric pressure, and then adjust it to the closed state.

[0030] During operation, the timer's working mode or countdown time is set according to different measurement needs; the gas path of the system under test is opened, and the timer or the timing mechanism of the system under test controls the time for gas to flow into the high-pressure small gas cylinder. This time is determined according to the gas cylinder volume and the gas flow rate in the pipeline; within the controlled time, the incoming gas from the system under test enters the high-pressure small gas cylinder, and then the gas path is blocked by the timing mechanism of the system under test or the electromagnetic switch of this device; the pressure gauge reading is read.

[0031] Test different parallel systems under the same setting parameters, or test the same system at different service stages under the same setting parameters to obtain multiple test data; through reliability analysis, determine whether there is abnormal data in the analyzed data, thereby judging whether the tested system has a fault.

[0032] In this invention, the reading of the pressure gauge connected to the high-pressure small gas cylinder reflects the amount of gas flowing into the high-pressure small gas cylinder within the controlled time, which is related to the gas flow rate and thus reflects the quality of the throttle.

[0033] This invention uses the gas flow rate of the throttle device to be measured indirectly based on the gas pressure in the high-pressure small gas cylinder. Compared with the direct measurement type flow meter, the beneficial effect of this invention is that it can measure the instantaneous flow control process or the variable flow control process, and the measurement result can reflect whether the flow rate of the throttle device deviates from the normal state. Attached Figure Description

[0034] Figure 1 This is a schematic diagram of an in-situ measurement device for the flow rate of a throttle in a pneumatic transmission system.

[0035] Figure 2 This is a diagram of the cooling air piping for the drag chute of a certain type of aircraft.

[0036] In the diagram: 1. Air inlet; 2. Electromagnetic switch; 3. One-way valve; 4. Pressure gauge; 5. High-pressure small gas cylinder; 6. Pressure relief valve; 7. Timer; 8. Battery pack; 9. Air supply to the air conditioning system; 10. One-way valve; 11. Deceleration parachute air cylinder; 12. Parachute deployment electromagnetic valve; 13. Parachute throwing electromagnetic valve; 14. Throttling device; 15. Test point; 16. Parachute mechanism actuator. Detailed Implementation

[0037] This embodiment is an in-situ measurement device for the flow rate of a throttle in a pneumatic transmission system, including a high-pressure small gas cylinder 5, a one-way valve 3, an electromagnetic switch 2, a timer 7, and a battery pack 8. The pressure gauge 4, pressure relief valve 6, and one-way valve 3 are connected to the high-pressure small gas cylinder 5; one end of the air path of the electromagnetic switch 2 is connected to the one-way valve, and the other end is connected to the air inlet 1; the circuit of the electromagnetic switch 2 is connected to the timer 7 and the battery pack 8. Figure 1 As shown.

[0038] The diagram shows the cooling ductwork of a certain type of aircraft's drag chute. Figure 2 As shown, the airflow through the throttle 14 affects the success rate of parachute deployment. If the amount of cold air flowing through the throttle changes from the normal level, it can cause the parachute to fail during landing, threatening flight safety. Therefore, the amount of cold air flowing through the throttle needs to be tested regularly to prevent the throttle malfunction from worsening and to allow for timely replacement.

[0039] exist Figure 2 In the deceleration parachute section of the air conditioning duct shown, the air conditioning flow time is determined by the aircraft's timing mechanism controlling the parachute deployment electromagnetic valve; the air conditioning flow time is 1 second.

[0040] This embodiment also proposes a method for measuring the flow rate of the throttle valve in the cooling system of a certain type of aircraft using the aforementioned in-situ measuring device. The specific process is as follows:

[0041] Step 1, disconnect the connector at the deceleration chute test point:

[0042] Disconnect the connector at test point 15 before the umbrella hook actuator cylinder 16 using the conventional method, that is, separate the pipeline into two parts at the test point.

[0043] Step 2, Connect the testing device

[0044] Connect the air inlet 1 in the in-situ measuring device to the pipeline at the disconnected test point 15 using conventional methods, so that the two are connected and gas can flow between the two devices.

[0045] Step 3, test the pressure relief valve:

[0046] Adjust the pressure relief valve by loosening the pressure relief valve knob to allow... Figure 1 The pressure inside the high-pressure small gas cylinder 5 is the same as the atmospheric pressure; then tighten the knob to close the pressure relief valve, and the high-pressure small gas cylinder 5 is no longer connected to the atmosphere; the change in gas pressure in the high-pressure small gas cylinder is the change in gas pressure in the measuring device.

[0047] Step 4, inflate the aircraft with air conditioning:

[0048] The aircraft's air conditioning system was filled with cool air to 120 kgf / cm². 2 The cooling duct is ventilated to allow gas to flow inside, thereby enabling the measurement of the gas flow rate.

[0049] Step 5, adjust the timer:

[0050] Adjust the timer 7 to its closed-circuit mode. This is done by turning the knob on the timer to switch it to closed-circuit mode. In closed-circuit mode, the gas entering through the air inlet 1 passes sequentially through the electromagnetic switch and the one-way valve before entering the high-pressure gas cylinder.

[0051] Step 6, activate the umbrella release switch:

[0052] Turn on the aircraft's main power switch and activate the parachute deployment switch to measure the change in gas flow rate in the pipeline during parachute deployment. Measure the change in gas flow rate in the pipeline using a measuring device.

[0053] Step 7, obtain the gas pressure in the pipeline:

[0054] The change in gas flow rate in the pipeline can be obtained by measuring the pressure value displayed on the pressure gauge.

[0055] The gas in the pipeline enters the measuring device through the air inlet at measuring point 15. The gas then passes through the electromagnetic switch 2 and the one-way valve 3 before entering the high-pressure small gas cylinder 5. The gas changes the pressure inside the high-pressure small gas cylinder, and the pressure inside the cylinder, i.e., the gas pressure in the pipeline, is obtained through the pressure gauge 4 inside the high-pressure small gas cylinder.

[0056] In this embodiment, the pressure gauge displays a value of 25.1 kgf.

[0057] Step 11, restore the aircraft air intake interface:

[0058] Turn off the aircraft power switch and timer 7 in sequence, and disconnect the connector 1 from test point 15 in step 2 to separate the pipeline from the test point and remove the measuring device.

[0059] Reconnect the disconnected connector at the test point before the umbrella hook actuator, that is, reconnect the disconnected pipes to complete the measurement.

Claims

1. An in-situ measuring device for the flow rate of a throttle in a pneumatic transmission system, characterized in that, It includes a high-pressure small gas cylinder (5), a one-way valve (3), an electromagnetic switch (2), a pressure relief valve (6), a timer (7), and a battery pack (8); wherein, the pressure gauge (4), the pressure relief valve, and the one-way valve are respectively connected to the high-pressure small gas cylinder; one end of the electromagnetic switch's air circuit is connected to the one-way valve, and the other end is connected to the air inlet (1); the electromagnetic switch's circuit is respectively connected to the timer and the battery pack.

2. A method for measuring the flow rate of a throttle in the air conditioning system of a certain type of aircraft using the in-situ measuring device described in claim 1, characterized in that, The specific process is as follows: Step 1, disconnect the connector at the deceleration chute test point: Disconnect the connector at the test point (15) in front of the umbrella hook actuator cylinder (16); Step 2, connect the testing device: Step 3, test the pressure relief valve: Step 4, inflate the aircraft with air conditioning: The aircraft's air conditioning system was filled with cool air to 120 kgf / cm². 2 This allows gas to flow inside the pipeline, thereby enabling the measurement of the gas flow rate. Adjust the timer (7) to the pass mode; in the pass mode, the gas entering through the air inlet (1) passes through the electromagnetic switch and the one-way valve in sequence and enters the high-pressure small gas cylinder; Step 6: Measure the change in gas flow rate in the pipeline: Turn on the aircraft's main power switch and toggle the parachute deployment switch to measure the change in gas flow rate in the pipeline during parachute deployment; measure the change in gas flow rate in the pipeline using a measuring device. Step 7: Obtain the change in gas flow rate within the pipeline: The change in gas flow rate in the pipeline can be obtained by measuring the pressure value displayed on the pressure gauge. Step 8, restore the aircraft air intake interface: Turn off the aircraft power switch and timer (7) in sequence, and remove the air intake interface from the test point (15) in step 2 to separate the pipeline from the test point and remove the measuring device; Reconnect the disconnected connector at the test point before the umbrella hook actuator, that is, reconnect the disconnected pipeline to complete the measurement.

3. The method for measuring the flow rate of the throttle in the air conditioning system of a certain type of aircraft drag chute as described in claim 2, characterized in that, In the deceleration parachute section of the cooling air duct, the cooling air circulation time is 1 second.

4. The method for measuring the flow rate of the throttle in the air conditioning system of a certain type of aircraft drag chute as described in claim 2, characterized in that, The connection test device connects the air inlet (1) in the in-situ measuring device to the pipeline at the disconnected test point (15), so that the two are connected and the gas can flow in the two devices.

5. The method for measuring the flow rate of the throttle in the air conditioning system of a certain type of aircraft drag chute as described in claim 2, characterized in that, Adjust the pressure relief valve by loosening the valve knob to make the pressure inside the high-pressure small gas cylinder match the atmospheric pressure; then tighten the knob to close the pressure relief valve, and the high-pressure small gas cylinder (5) is no longer connected to the atmosphere; the change in gas pressure in the high-pressure small gas cylinder is the change in gas pressure inside the measuring device.

6. The method for measuring the flow rate of the throttle in the air conditioning system of a certain type of aircraft drag chute as described in claim 2, characterized in that, The gas in the pipeline enters the measuring device through the air inlet at the test point (15); the gas passes through the electromagnetic switch (2) and the one-way valve (3) in sequence and enters the high-pressure small gas cylinder (5); after the gas enters the high-pressure small gas cylinder, it will change the pressure inside the high-pressure small gas cylinder. The pressure of the gas in the high-pressure small gas cylinder is obtained through the pressure gauge (4) in the high-pressure small gas cylinder, that is, the gas pressure in the pipeline.

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