In-situ measurement device and measurement method for flow volume of throttler of pneumatic transmission system

Abstract

The invention relates to an in-situ measurement device and a measurement method for the flow volume of a throttle of a pneumatic transmission system, in particular to an indirect measurement type flow measurement device and a measurement method, which comprises a small high-pressure gas cylinder, a one-way valve, an electromagnetic switch, a pressure release valve, a timer and a battery pack. The pressure gauge, the pressure release valve and the one-way valve are respectively connected with the small high-pressure gas cylinder; one end of the electromagnetic switch gas circuit is connected with the one-way valve, and the other end is connected with the gas inlet interface; and a circuit of the electromagnetic switch is respectively connected with the timer and the battery pack. According to the invention, the total flow quantity flowing through the throttler in unit time can be measured, so that the throttling effect of the throttler in the instantaneous flow or variable flow control process is reflected, and the problem that the instantaneous flow and variable flow process is inconvenient to measure by a direct measurement type flowmeter is solved; the instantaneous flow control process or the variable flow control process can be measured, and the measurement result can reflect whether the flow volume of the throttler deviates from the normal state or not.

Description

Technical Field

[0001] The invention relates to the technical field of mechanical engineering, in particular to an in-situ measuring device and a measuring method for the flow rate of a throttle of a pneumatic transmission system. Background Art

[0002] In a pneumatic transmission system, a throttle is generally used to throttle the flow of compressed gas, thereby achieving control of the movement speed of the actuator, the delay time of the delay element, etc. in the pneumatic transmission system.

[0003] Generally speaking, the pneumatic transmission system has clear requirements for the throttling amount of the throttle. If the throttling element in the throttle is worn, stuck or blocked, the throttling amount of the throttle will change, thereby affecting the gas intake of the subsequent actuator or delay element, resulting in changes in the control plan of the entire pneumatic transmission system, causing failures or accidents.

[0004] Therefore, during the service period of the pneumatic transmission system, it is necessary to regularly test the flow rate of the throttle to prevent accidents. Especially on active equipment, it is usually necessary to cooperate with other parts and accessories in the pneumatic transmission system to test the working condition of the entire system. At this time, in-situ testing is required.

[0005] At present, the common devices for measuring gas flow rate mainly include orifice flowmeter, electromagnetic flowmeter, turbine flowmeter, venturi flowmeter, volumetric flowmeter, rotor flowmeter, vortex flowmeter, impeller flowmeter, ultrasonic flowmeter, nozzle flowmeter, etc. The measurement principles of these flow measurement devices are different, but they can be roughly classified as direct measurement flowmeters. For these flow measurement devices, they are connected to the gas circuit during operation. The advantage is that the stable flow value in the gas circuit can be directly measured during measurement, which is direct and convenient, and the system working condition can also be checked when measuring the flow. However, they also have the following disadvantages: 1. For the instantaneous flow control process, the gas circulation time is short (such as a few milliseconds to tens of milliseconds), and the flow value recording function needs to be realized, which is difficult to achieve; 2. For the variable flow control process, sometimes it is necessary to measure the average flow value of the whole process, and the entire flow measurement process needs to be integrated, which is also difficult to achieve. Summary of the invention

[0006] In order to overcome the deficiency in the prior art that it is difficult to record the instantaneous flow value and measure the average flow value of the whole process, the present invention proposes an in-situ measurement device and method for the flow rate of a throttle of a pneumatic transmission system.

[0007] The in-situ measuring device for the flow rate of the throttle of the pneumatic transmission system proposed by the present invention comprises a small high-pressure gas cylinder, a one-way valve, an electromagnetic switch, a pressure relief valve, a timer and a battery pack. The pressure gauge, the pressure relief valve and the one-way valve are respectively connected to the small high-pressure gas cylinder; one end of the electromagnetic switch gas circuit is connected to the one-way valve, and the other end is connected to the air inlet interface; the circuit of the electromagnetic switch is respectively connected to the timer and the battery pack.

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

[0009] The specific process of using the in-situ measurement device to measure the flow rate of the throttle of the cooling system of a certain type of aircraft parachute is as follows:

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

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

[0012] Step 2, connect the test device:

[0013] The connection test device is to connect the air inlet interface in the in-situ measurement device with the pipeline at the disconnected test point so that the two are connected and the gas can flow in the two devices.

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

[0015] Adjust the pressure relief valve and loosen the pressure relief valve knob to make the pressure in the high-pressure small gas cylinder consistent with the atmospheric pressure; then tighten the knob to close the pressure relief valve, and the high-pressure small gas cylinder is no longer connected to the atmosphere; the change in the air pressure in the high-pressure small gas cylinder is the change in the air pressure in the measuring device.

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

[0017] Fill the air conditioning system on the aircraft to 120kgf / cm 2 , so that gas can flow inside the pipeline, and then the gas flow rate can be measured.

[0018] The timer is adjusted to a passage mode. In the passage mode, the gas entering the air inlet interface passes through the electromagnetic switch and the one-way valve in sequence and enters the high-pressure small gas cylinder.

[0019] Step 6, measure the change of pipeline gas flow:

[0020] Turn on the aircraft main power switch and toggle the parachute release switch on the aircraft to measure the change in gas flow in the pipeline during the parachute release process. The change in gas flow in the pipeline is measured by a measuring device.

[0021] Step 7, obtain the change of gas flow in the pipeline:

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

[0023] The gas in the pipeline enters the measuring device through the gas inlet interface at the measuring point. The gas passes through the electromagnetic switch and the one-way valve in turn and enters the high-pressure small gas cylinder. After the gas enters the high-pressure small gas cylinder, the pressure in the high-pressure small gas cylinder will change. The pressure of the gas in the high-pressure small gas cylinder, that is, the gas pressure in the pipeline, is obtained through the pressure gauge in the high-pressure small gas cylinder.

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

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

[0026] Reconnect the disconnected joint at the test point in front of the umbrella hook actuator, that is, reconnect the disconnected pipeline together to complete the measurement.

[0027] The indirect measurement flow measurement device and the use method proposed in the present invention can realize the measurement of the total flow rate flowing through the throttle per unit time, thereby reflecting the throttling effect of the throttle during the instantaneous flow or variable flow control process, and solves the problem that the direct measurement flow meter is not convenient for measuring the instantaneous flow and the variable flow process.

[0028] In the present invention, the gas circuit of the electromagnetic switch used should be in a closed state when no power is supplied, the gas circuit should be connected when power is supplied, and the gas circuit should be closed again when power is cut off; the timer used can control the switch of the circuit, and a certain timing amount can be set for countdown. In the default state, it is in an open circuit state. When the countdown of the timing amount ends, the circuit is connected to power the electromagnetic switch.

[0029] Before work, disconnect the gas path behind the throttle of the system under test and connect it to the above-mentioned air inlet interface 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 working mode or countdown time of the timer is set according to different measurement needs; the gas circuit of the system under test is opened, and the timer or the timing mechanism of the system under test controls the time for the gas to flow into the high-pressure small gas cylinder, and this time is determined according to the volume of the gas cylinder and the gas flow in the pipeline; within the controlled time, the incoming gas of the system under test enters the high-pressure small gas cylinder, and then the gas circuit is blocked by the timing mechanism of the system under test or the electromagnetic switch of this device; read the reading of the pressure gauge.

[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 are abnormal data in the analyzed data, so as to judge whether there is a fault in the tested system.

[0032] In the present 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 during the controlled time, which is related to the gas flow rate and thus reflects the quality of the throttle.

[0033] The present invention uses the gas flow rate of the measured throttle to indirectly reflect the gas pressure in the high-pressure small gas cylinder. Compared with the direct measurement flow meter, the present invention has the beneficial effects of being able to 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 deviates from the normal state. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0035] Figure 2 This is a diagram of the cooling air pipeline of a certain type of aircraft parachute.

[0036] In the figure: 1. Air inlet interface; 2. Solenoid 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 from the cooling system; 10. One-way valve; 11. Cooling air bottle for deceleration parachute; 12. Solenoid valve for parachute release; 13. Solenoid valve for parachute ejection; 14. Throttle; 15. Test point; 16. Parachute structure actuator. DETAILED DESCRIPTION

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

[0038] The cooling air pipeline of a certain type of aircraft parachute is shown in the figure below. Figure 2 As shown, the flow rate of the throttle 14 affects the success rate of parachute deployment of the aircraft. If the flow rate of cold air passing through the throttle changes from the normal level, the parachute deployment of the aircraft will fail during landing, threatening flight safety. Therefore, the flow rate of cold air in the throttle needs to be tested regularly to prevent the throttle failure from getting worse, so that it can be replaced in advance.

[0039] exist Figure 2 In the cooling air pipeline of the deceleration parachute shown, the cooling air circulation time is determined by the aircraft's timing mechanism controlling the parachute release electromagnetic valve; the cooling air circulation time is 1 second.

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

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

[0042] The joint at the test point 15 in front of the umbrella hook actuator 16 is disconnected in a conventional manner, that is, the pipeline is divided into two parts at the test point.

[0043] Step 2: Connect the test device

[0044] The air inlet interface 1 in the in-situ measurement device is connected to the pipeline at the disconnected test point 15 in a conventional manner so that the two are connected and the gas can flow in the two devices.

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

[0046] Adjust the pressure relief valve and loosen the pressure relief valve knob to Figure 1 The pressure in the middle 5-high-pressure gas cylinder is consistent with the atmospheric pressure; then tighten the knob to close the pressure relief valve, and the high-pressure gas cylinder 5 is no longer connected to the atmosphere; the change in the air pressure in the high-pressure gas cylinder is the change in the air pressure in the measuring device.

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

[0048] Fill the air conditioning system on the aircraft to 120kgf / cm 2 The cold air pipeline is ventilated so that gas can flow inside the pipeline, thereby measuring the gas flow rate.

[0049] Step 5, adjust the timer:

[0050] The timer 7 is adjusted to be in the passage mode. During the adjustment, the knob on the timer is turned to change the working mode of the timer to the passage mode. In the passage mode, the gas entering the air inlet interface 1 passes through the electromagnetic switch and the one-way valve in sequence and enters the high-pressure small gas cylinder.

[0051] Step 6, toggle the umbrella switch:

[0052] Turn on the aircraft main power switch and toggle the parachute release switch on the aircraft to measure the change in gas flow in the pipeline during the parachute release process. The change in gas flow in the pipeline is measured by a measuring device.

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

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

[0055] The gas in the pipeline enters the measuring device through the gas inlet interface at the measuring point 15. The gas passes through the electromagnetic switch 2 and the one-way valve 3 in sequence and enters the high-pressure gas cylinder 5. After the gas enters the high-pressure gas cylinder, the pressure in the high-pressure gas cylinder will change. The pressure of the gas in the high-pressure gas cylinder, that is, the gas pressure in the pipeline, is obtained through the pressure gauge 4 in the high-pressure gas cylinder.

[0056] The value displayed by the pressure gauge in this embodiment is 25.1 kgf.

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

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

[0059] Reconnect the disconnected joint at the test point in front of the umbrella hook actuator, that is, reconnect the disconnected pipeline together 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: The invention comprises a small high-pressure 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 small high-pressure gas cylinder; one end of the electromagnetic switch gas circuit is connected to the one-way valve, and the other end is connected to the air inlet interface (1); and the circuit of the electromagnetic switch is respectively connected to the timer and the battery pack.

2. The in-situ measuring device for the flow rate of the throttle of the pneumatic transmission system according to claim 1, characterized in that: In the cold air pipeline of the deceleration parachute part, the cold air circulation time is 1 second.

3. A method for measuring the flow rate of the throttle of the cooling system of a certain type of aircraft parachute using the in-situ measurement device, characterized in that: The specific process is: Step 1, disconnect the connector at the parachute test point: Disconnect the connector at the test point (15) in front of the umbrella hook actuator (16); Step 2, connect the test device: Step 3, test the pressure relief valve: Step 4, charge the aircraft with air conditioning: Fill the air conditioning system on the aircraft to 120kgf / cm 2 , so that gas can flow inside the pipeline, and then measure the gas flow rate; The timer (7) is adjusted to a passage mode; in the passage mode, the gas entering the gas inlet interface (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 of pipeline gas flow: Turn on the aircraft main power switch and toggle the parachute release switch on the aircraft to measure the change in gas flow in the pipeline during the parachute release process; measure the change in gas flow in the pipeline through a measuring device; Step 7, obtain the change of gas flow in the pipeline: The change of gas flow in the pipeline can be obtained by the pressure value displayed on the pressure gauge; Step 8, restore the aircraft air intake interface: Turn off the aircraft switch and the timer (7) in sequence, remove the air intake interface in step 2 from the test point (15), separate the pipeline from the test point, and remove the measuring device; Reconnect the disconnected joint at the test point in front of the umbrella hook actuator, that is, reconnect the disconnected pipeline together to complete the measurement.

4. The method for measuring the flow rate of the throttle of the cooling system of a certain type of aircraft parachute as claimed in claim 3, characterized in that: The connection test device is to connect the air inlet interface (1) in the in-situ measurement device with 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 of the cooling system of a certain type of aircraft parachute as claimed in claim 3, characterized in that: Adjust the pressure relief valve and loosen the pressure relief valve knob to make the pressure in the high-pressure small gas cylinder consistent with the atmospheric pressure; Then, the knob is tightened to close the pressure relief valve, so that the high-pressure gas cylinder (5) is no longer connected to the atmosphere; The change in the air pressure in the small high-pressure gas cylinder is the change in the air pressure in the measuring device.

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

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