CN111157180B - A measuring system and testing method for airship ground leakage - Google Patents
A measuring system and testing method for airship ground leakage Download PDFInfo
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Abstract
本发明涉及气密性测试技术领域，公开了一种飞艇地面泄漏量的测量系统及测试方法，该测量系统包括压差装置、第一阀门、第二阀门、充气装置和三通连接器；三通连接器的第一端与压差装置连接，三通连接器的第二端通过第一阀门与充气装置连接，三通连接器的第三端通过第二阀门与飞艇的充气端连接。本发明提供的飞艇地面泄漏量的测量系统及测试方法，通过设置压差装置，并通过三通连接器连接压差装置、充气装置和飞艇，消除了飞艇在测试过程中不同压差下体积的变化影响，准确测量飞艇的实际泄漏量，可得到飞艇在不同压差条件下的泄漏量情况，对飞艇的加工制造质量评估具有指导意义，可以提高飞艇飞行时间的预测精度，降低飞艇飞行安全风险。
The invention relates to the technical field of air tightness testing, and discloses a measurement system and a testing method for airship ground leakage. The measurement system includes a differential pressure device, a first valve, a second valve, an inflation device and a three-way connector; three The first end of the through connector is connected to the differential pressure device, the second end of the three-way connector is connected to the inflatable device through the first valve, and the third end of the three-way connector is connected to the inflatable end of the airship through the second valve. The measuring system and testing method for airship ground leakage provided by the present invention, by setting the differential pressure device and connecting the differential pressure device, the inflation device and the airship through a tee connector, eliminates the volume difference of the airship under different pressure differences during the testing process. The actual leakage of the airship can be accurately measured, and the leakage of the airship under different pressure differential conditions can be obtained, which has guiding significance for the evaluation of the processing and manufacturing quality of the airship, which can improve the prediction accuracy of the airship flight time and reduce the flight safety risk of the airship. .
Description
Technical Field
The invention relates to the technical field of air tightness testing, in particular to a system and a method for measuring the ground leakage of an airship.
Background
The stratospheric airship is an aircraft which provides buoyancy by buoyancy gas such as helium or hydrogen. The stratosphere has low atmospheric density, so the stratosphere airship has huge volume and high manufacturing cost. The leakage rate of the airship capsule is an important index, and the standing-in-air time of the airship is directly determined. The airship has many leakage sources, mainly including the capsule material itself (including the air tightness of the material body and the leakage caused by the air tightness change caused by kneading in the processes of processing, transporting, inflating and the like), the interconnecting parts of the capsule material, and the equipment such as valves, fans and the like installed on the capsule material. The leakage condition of the airship capsule can be quantitatively measured through ground test, whether the airship is qualified or not is judged according to the leakage condition, and the air staying time of the airship is further evaluated.
The traditional pressure vessel airtightness test has large working pressure difference which is usually dozens of times of atmospheric pressure, the influence of atmospheric pressure change and temperature change on the test pressure is not large, in addition, the size of the pressure vessel is generally small and regular, and the volume change caused by the pressure is easy to measure.
The leakage amount is actually closely related to the pressure difference of the container, and the small pressure difference has small leakage and the large pressure difference has large leakage. The working pressure difference of the stratospheric airship is smaller than the atmospheric pressure, is one hundredth magnitude of the atmospheric pressure, is greatly influenced by the atmospheric pressure change, and in addition, the actual pressure difference of the airship fluctuates in a large range in the test process due to the temperature change, so that the actual leakage condition of the airship cannot be truly reflected by the test result.
Disclosure of Invention
In view of the technical defects and application requirements, the embodiment of the invention provides a system and a method for measuring the ground leakage amount of an airship, so as to overcome the influence of pressure difference change in the process of testing the leakage amount of the airship and more accurately test the actual leakage amount of the airship.
In order to solve the above problems, the present invention provides a system for measuring the ground leakage of an airship, comprising: the system comprises a pressure difference device, a first valve, a second valve, an air charging device and a three-way connector; the first end of the three-way connector is connected with the pressure difference device, the second end of the three-way connector is connected with the inflation device through the first valve, and the third end of the three-way connector is connected with the inflation end of the airship through the second valve.
Further, the pressure difference device includes: the tank body, the piston and the balance weight; the tank body is of a hollow structure with an opening at the top end, and the piston is movably arranged at the opening along the vertical direction; the counterweight is arranged on the piston; the tank body is provided with an inflation inlet, an air outlet and a pressure release valve, and the air outlet of the tank body is connected with the first end of the three-way connector.
Further, the measurement system further includes: a temperature sensor; the temperature sensor is disposed within the airship.
In order to solve the above problems, the present invention provides a method for testing an airship ground leakage, wherein the method for testing the airship ground leakage is used for controlling the above measurement system, and comprises the following steps:
step S1: opening the first valve and the second valve, opening the inflation device, inflating the airship and the pressure difference device until the pressure difference device is full, and closing the first valve;
step S2: after the temperature field in the airship is stabilized, opening a first valve, and slowly discharging part of gas until the gas in the pressure difference device reaches a preset amount;
step S3: and starting and recording the test, and calculating the leakage amount of the airship according to the starting point data and the ending point data when the time interval from the starting point to the ending point is greater than the specified test.
Further, the specific step of step S3 includes:
calculating the leakage of the airship according to the starting point data and the ending point data, wherein the formula is as follows:
wherein l is the leakage amount per unit area of the airship every day, and Delta V is the target pressure difference and temperature T0Corresponding leaked gas volume under conditions, T1Average temperature, V, of the airship at a selected starting point1The volume of gas in the airship and the pressure difference device is taken as the starting point, T2Average temperature, V, of the airship at a selected end point2For the end point of the gas volume in the airship and the pressure difference device, Δ t is the time interval between the start point and the end point, AaIs the airship surface area.
Further, step S1 is preceded by:
step S11: closing the first valve and the second valve, and filling test helium into the differential pressure device and the test pipeline;
step S12: detecting the leakage of the differential pressure device, the test pipeline, the first valve and the second valve by a helium mass spectrometer;
step S13: if there is no leak or the magnitude of the leak is within an acceptable range, the first valve and the inflation port of the pressure differential device are opened to release the test helium gas.
Further, step S1 is preceded by:
step S14: adjusting the mass of the counterweight, wherein the test pressure has the following relation with the mass of the counterweight;
pt＝(m1+m2)g/A
wherein p istFor measuring pressure, m1Is the piston mass, m2The counterweight mass, A is the cross-sectional area of the pressure differential device.
Further, the pressure difference of the helium gas tested in the step S11 is an order of magnitude greater than the pressure difference of the helium gas tested by the airship.
Further, the specific step of step S3 includes:
selecting the starting point data and the end point data to select the time when the internal temperatures of the airship are consistent, if the internal temperature consistent data cannot be found, prolonging the testing time, selecting the starting point data and the end point data which are consistent, wherein the leakage calculation formula is as follows:
wherein, V1The volume of gas in the airship and the pressure difference device is the starting point, V2For the end point of the gas volume in the airship and the pressure difference device, Δ t is the time interval between the start point and the end point, AaIs the airship surface area.
Further, the time when the test is started in step S3 is the middle time of the temperature change during the day.
According to the system and the method for measuring the ground leakage amount of the airship, the differential pressure device is arranged, and the three-way connector is connected with the differential pressure device, the inflation device and the airship, so that the influence of volume change of the airship under different differential pressures in the test process is eliminated, the actual leakage amount of the airship is accurately measured, the leakage amount condition of the airship under different differential pressures can be obtained, the system and the method have guiding significance for the processing and manufacturing quality evaluation of the airship, the prediction precision of the flight time of the airship can be improved, and the flight safety risk of the airship is reduced.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and those skilled in the art can also obtain other drawings according to the drawings without creative efforts.
Fig. 1 is a schematic structural diagram of a system for measuring an amount of ground leakage of an airship according to an embodiment of the present invention;
fig. 2 is a schematic flow chart of a method for testing the ground leakage of an airship according to an embodiment of the present invention;
description of reference numerals: 1. an airship; 2. a differential pressure device; 3. a three-way connector; 4. an inflator; 5. a first valve; 6. a second valve; 11. an airship inflation tube; 21. a piston; 22. an inflation inlet; 23. and (4) balancing weight.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The embodiment of the invention provides a system for measuring the ground leakage of an airship, as shown in figure 1, the system is mainly used for testing the airship on a stratosphere, and comprises: a differential pressure device 2, a first valve 5, a second valve 6, an inflator 4 and a three-way connector 3. The first end of the three-way connector 3 is connected with the pressure difference device 2, the second end of the three-way connector 3 is connected with the inflation device 4 through the first valve 5, and the third end of the three-way connector 3 is connected with the inflation end of the airship 1 through the second valve 6. Wherein, an airship inflation tube 11 is arranged between the airship 1 and the second valve 6.
In this embodiment, the pressure difference device 2 is a pressure difference stabilization tank, including: a canister, a piston 21 and a counterweight 23. The tank body is a hollow structure with an opening at the top end, and the piston 21 is movably arranged at the opening along the vertical direction. A weight 23 is provided on the piston 21. The tank body is provided with an inflation inlet 22, an air outlet and a pressure release valve, and the air outlet of the tank body is connected with the first end of the three-way connector 3. Different counterweights 23 are selected for testing, and the leakage rate of the airship under different pressure difference conditions can be obtained.
To facilitate measuring the temperature, the measurement system includes a temperature sensor. The temperature sensor is disposed within the airship 1.
Before the test process, a measuring system for the ground leakage of the airship is assembled. In the test process, the first valve 5 and the second valve 6 are opened, the inflating device 4 is opened to inflate the airship 1 and the pressure difference device 2 until the pressure difference device 2 is full, and then the first valve 5 is closed. After the temperature field inside the airship is stabilized, the first valve 5 is opened for several times, and part of the gas is slowly released until the gas in the pressure difference device 2 reaches a preset amount, wherein the preset amount is about half of the full amount of the pressure difference device 2. And starting and recording the test, and calculating the leakage amount of the airship according to the starting point data and the ending point data when the time interval from the starting point to the ending point is greater than the specified test.
It should be noted that the system for measuring the ground leakage of the airship provided by the embodiment can also be used for testing the leakage of the captive balloon on the ground.
According to the system for measuring the ground leakage of the airship, which is provided by the embodiment of the invention, the differential pressure device is arranged, and the three-way connector is connected with the differential pressure device, the inflation device and the airship, so that the influence of the volume change of the airship under different differential pressures in the test process is eliminated, the actual leakage of the airship is accurately measured, the leakage condition of the airship under different differential pressures can be obtained, the system has guiding significance for the processing and manufacturing quality evaluation of the airship, the prediction precision of the flight time of the airship can be improved, and the flight safety risk of the airship is reduced.
The embodiment of the invention provides a method for testing the ground leakage of an airship, which is used for controlling a measuring system shown in fig. 1 and testing the stratospheric airship.
As shown in fig. 2, the test method includes the steps of:
step S1: and opening the first valve and the second valve, opening the inflation device, inflating the airship and the pressure difference device until the pressure difference device is full, and closing the first valve.
Step S2: and after the temperature field in the airship is stabilized, opening the first valve, and slowly discharging part of gas until the gas in the pressure difference device reaches a preset amount.
Step S3: and starting and recording the test, and calculating the leakage amount of the airship according to the starting point data and the ending point data when the time interval from the starting point to the ending point is greater than the specified test.
To reduce measurement error, the time to start the test is the middle of the day when the temperature changes.
The specific steps of step S3 include:
calculating the leakage of the airship according to the starting point data and the ending point data, wherein the formula is as follows:
wherein l is the leakage amount per unit area of the airship every day, and Delta V is the target pressure difference and temperature T0Corresponding leaked gas volume under conditions, T1Average temperature, V, of the airship at a selected starting point1The volume of gas in the airship and the pressure difference device is taken as the starting point, T2Average temperature, V, of the airship at a selected end point2To end the point the gas volume, delta, in the airship and the pressure differential devicet is the time interval between the start and end points, AaIs the airship surface area. The average helium temperature in the airship is obtained by comparing and analyzing multipoint temperature data measured by the distributed temperature sensors and the distribution condition of the temperature in the airship calculated through simulation.
In order to eliminate the influence of water vapor pressure and simplify the calculation of the leakage amount, the specific steps in step S3 include:
selecting the starting point data and the end point data to select the time when the internal temperatures of the airship are consistent, if the internal temperature consistent data cannot be found, prolonging the testing time, selecting the starting point data and the end point data which are consistent, wherein the leakage calculation formula is as follows:
wherein, V1The volume of gas in the airship and the pressure difference device is the starting point, V2For the end point of the gas volume in the airship and the pressure difference device, Δ t is the time interval between the start point and the end point, AaIs the airship surface area.
Before step S1, leak detection needs to be performed on the entire measurement system, which includes the following steps:
step S11: and closing the first valve and the second valve, and filling test helium into the differential pressure device and the test pipeline.
The pressure difference of the tested helium is one order of magnitude larger than that of the helium for airship testing, so that the airtightness of the pressure difference device and the testing pipeline is normal.
Step S12: and detecting the leakage of the differential pressure device, the test pipeline, the first valve and the second valve by a helium mass spectrometer.
Step S13: if there is no leak or the magnitude of the leak is within an acceptable range, the first valve and the inflation port of the pressure differential device are opened to release the test helium gas.
In order to obtain the leakage rate of the airship under different pressure difference conditions, before the step S1, the method further includes:
step S14: adjusting the mass of the balance weight, selecting different balance weights for testing, wherein the test pressure has the following relation with the mass of the balance weight;
pt＝(m1+m2)g/A
wherein p istFor measuring pressure, m1Is the piston mass, m2The counterweight mass, A is the cross-sectional area of the pressure differential device.
In a specific embodiment, as shown in fig. 1, before the testing process, a distributed temperature sensor is placed inside the airship 1, a three-way connector is connected to the airship inflation tube 11, the inflation device 4 and the pressure difference device 2 are respectively connected, a first valve 5 is connected between the inflation device 4 and the three-way connector 3, and a second valve 6 is connected between the three-way connector 3 and the airship inflation tube 11.
After the measurement system is assembled, the whole measurement system needs to be subjected to leak detection, the first valve 5 and the second valve 6 are closed, and the pressure difference device 2 and the test pipeline are filled with high-pressure helium gas through the gas filling port 22. The pressure differential device 2, test lines and valves were leak tested using a helium mass spectrometer, demonstrating no leakage or an order of magnitude of leakage within acceptable limits. In the test process, the first valve 5 and the second valve 6 are opened, the inflating device 4 is opened to inflate the airship 1 and the pressure difference device 2 until the pressure difference device 2 is full, and then the first valve 5 is closed. After the temperature field inside the airship is stabilized, the first valve 5 is opened for several times, and part of the gas is slowly released until the gas in the pressure difference device 2 reaches a preset amount, wherein the preset amount is about half of the full amount of the pressure difference device 2.
When the test starts, the computer records the test data of the test system in real time, and the test data comprises: atmospheric pressure, atmospheric temperature, airship internal temperature sensor temperature, airship differential pressure, piston position, counterweight weight, and the like. And when the test time is longer than the specified test time, selecting the processing data, wherein the time interval from the starting point to the ending point is longer than the specified test, and calculating the leakage amount of the airship according to the starting point data and the ending point data.
According to the method for testing the ground leakage amount of the airship, the pressure difference device is arranged, and the three-way connector is connected with the pressure difference device, the air charging device and the airship, so that the influence of volume change of the airship under different pressure differences in the testing process is eliminated, the actual leakage amount of the airship is accurately measured, the leakage amount condition of the airship under different pressure differences can be obtained, the method has guiding significance for the processing and manufacturing quality evaluation of the airship, the prediction precision of the flight time of the airship can be improved, and the flight safety risk of the airship is reduced.
It should be noted that the method for testing the ground leakage of the airship provided by the embodiment can also be used for testing the leakage of the captive balloon on the ground.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (8)
1. A method for testing the ground leakage of an airship, wherein the method is used for controlling a measurement system, and the measurement system comprises: the system comprises a pressure difference device, a first valve, a second valve, an air charging device and a three-way connector; the first end of the three-way connector is connected with the pressure difference device, the second end of the three-way connector is connected with the inflation device through the first valve, and the third end of the three-way connector is connected with the inflation end of the airship through the second valve;
the test method comprises the following steps:
step S1: opening the first valve and the second valve, opening the inflation device, inflating the airship and the differential pressure device until the differential pressure device is full, and closing the first valve;
step S2: after the temperature field in the airship is stable, opening the first valve, and slowly discharging part of gas until the gas in the pressure difference device reaches a preset amount;
step S3: starting testing and recording, and calculating the leakage of the airship according to the starting point data and the ending point data when the time interval from the starting point to the ending point is greater than the specified test; selecting the time when the internal temperature of the airship is consistent by selecting the starting point data and the end point data, if the internal temperature consistent data cannot be found, prolonging the testing time, selecting the starting point data and the end point data which are consistent in internal temperature, wherein the leakage calculation formula is as follows:
wherein, V1As a starting point the volume of gas in the airship and the pressure differential device, V2For ending the gas volume in the airship and the pressure differential device, Δ t being the time interval between the starting point and the ending point, AaIs the surface area of the airship.
2. The testing method according to claim 1, wherein the step S3 includes the following steps:
calculating the leakage of the airship according to the starting point data and the ending point data, wherein the formula is as follows:
wherein l is the leakage amount per unit area of the airship every day, and Delta V is the target pressure difference and temperature T0Corresponding leaked gas volume under conditions, T1Average temperature, V, of said airship for a selected starting point1As a starting point the volume of gas in the airship and the pressure differential device, T2Average temperature, V, of the airship for a selected end point2For ending the gas volume in the airship and the pressure differential device, Δ t being the time interval between the starting point and the ending point, AaIs the surface area of the airship.
3. The testing method according to claim 1, wherein the step S1 is preceded by:
step S11: closing the first valve and the second valve, and filling test helium into the differential pressure device and the test pipeline;
step S12: leak testing the pressure differential device, the test line, the first valve, and the second valve with a helium mass spectrometer;
step S13: and if no leakage exists or the magnitude of the leakage is within an acceptable range, opening the first valve and a charging port of the differential pressure device, and discharging the test helium gas.
4. The testing method according to claim 1, wherein the step S1 is preceded by:
step S14: adjusting the mass of the counterweight, wherein the test pressure has the following relation with the mass of the counterweight;
pt＝(m1+m2)g/A
wherein p istFor measuring pressure, m1Is the piston mass, m2The mass of the counterweight, A, is the cross-sectional area of the pressure differential device.
5. The method of claim 3, wherein the pressure differential of the helium tested in step S11 is an order of magnitude greater than the pressure differential of the helium tested for the airship.
6. The test method according to claim 1, wherein the time at which the test is started in step S3 is an intermediate time of a temperature change during a day.
7. The test method of claim 1, wherein the differential pressure device comprises: the tank body, the piston and the balance weight; the tank body is of a hollow structure with an opening at the top end, and the piston is movably arranged at the opening along the vertical direction; the counterweight is arranged on the piston; the tank body is provided with an inflation inlet, an air outlet and a pressure release valve, and the air outlet of the tank body is connected with the first end of the three-way connector.
8. The testing method of claim 1, wherein the measurement system further comprises: a temperature sensor; the temperature sensor is disposed within the airship.
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| CN114348295A (en) * | 2022-01-05 | 2022-04-15 | 北京临近空间飞艇技术开发有限公司 | Test system and method for measuring aerodynamic performance of helium gas compressor |
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| CN104568347B (en) * | 2014-12-22 | 2017-05-03 | 浙江中烟工业有限责任公司 | Testing device and testing method for testing leakage of small cigarette case |
| CN106802220A (en) * | 2017-03-10 | 2017-06-06 | 中国电子科技集团公司第三十八研究所 | A kind of measurement apparatus for flexible container entirety leak rate detection |
| CN108896250A (en) * | 2018-05-08 | 2018-11-27 | 中国航发湖南动力机械研究所 | Air-tightness detection device and air-tightness detection method |
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