CN112067247A - Labview-based pressure measurement system and measurement method - Google Patents
Labview-based pressure measurement system and measurement method Download PDFInfo
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- CN112067247A CN112067247A CN202011114543.8A CN202011114543A CN112067247A CN 112067247 A CN112067247 A CN 112067247A CN 202011114543 A CN202011114543 A CN 202011114543A CN 112067247 A CN112067247 A CN 112067247A
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L11/00—Measuring steady or quasi-steady pressure of a fluid or a fluent solid material by means not provided for in group G01L7/00 or G01L9/00
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L67/00—Network arrangements or protocols for supporting network services or applications
- H04L67/01—Protocols
- H04L67/12—Protocols specially adapted for proprietary or special-purpose networking environments, e.g. medical networks, sensor networks, networks in vehicles or remote metering networks
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- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04L—TRANSMISSION OF DIGITAL INFORMATION, e.g. TELEGRAPHIC COMMUNICATION
- H04L69/00—Network arrangements, protocols or services independent of the application payload and not provided for in the other groups of this subclass
- H04L69/16—Implementation or adaptation of Internet protocol [IP], of transmission control protocol [TCP] or of user datagram protocol [UDP]
- H04L69/163—In-band adaptation of TCP data exchange; In-band control procedures
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Abstract
The invention discloses a pressure measurement system based on Labview, which comprises a pressure sensor, an exchanger and an upper computer, wherein the pressure sensor is connected with the exchanger, the exchanger is connected with the upper computer, the upper computer comprises a central processing unit, a connecting module, an acquisition module, a calibration module, a continuous acquisition module and a quit module, and the central processing unit is respectively connected with the connecting module, the acquisition module, the calibration module, the continuous acquisition module and the quit module; the number of the sensors can be selected at will according to the requirements of users, so that the flexibility and the expandability of the measuring system are improved; the software of the measuring system is simple to operate, stable in operation and high in reliability. The invention is applied to a wind tunnel test system at present, and has good application effect.
Description
Technical Field
The invention relates to the technical field of aerodynamic wind tunnel tests, in particular to a pressure measurement system and a pressure measurement method based on Labview.
Background
The model surface pressure distribution test is generally called as a pressure measurement test, and aims to measure the pressure distribution on the surface of each part of the aircraft, provide original data of pneumatic load distribution for the calculation of the structural strength of the aircraft and each part, and provide test basis for researching the performance of the aircraft and each part and the streaming characteristic of the model. 9116 intelligence pressure sensor is that present wind-tunnel pressure measurement test uses more pressure measurement equipment, but it only has 16 collection passageways, can't satisfy the test demand more than 16 points, and adopts the angle to target in place after stable, the mode of gathering pressure data again.
Disclosure of Invention
The purpose of the invention is as follows: a Labview-based pressure measurement system and a Labview-based pressure measurement method are provided, and a network communication mode and a synchronization technology of Labview are utilized to realize the merging and expansion of measurement functions of a plurality of 9116 intelligent pressure sensors.
The technical scheme of the invention is as follows:
a pressure measurement system based on Labview comprises a pressure sensor, a switch and an upper computer, wherein the pressure sensor is connected with the switch, the switch is connected with the upper computer, the upper computer comprises a central processing unit, a connecting module, an acquisition module, a calibration module, a continuous acquisition module and a quitting module, and the central processing unit is respectively connected with the connecting module, the acquisition module, the calibration module, the continuous acquisition module and the quitting module.
Further, the pressure sensor is a 9116 intelligent pressure sensor;
furthermore, the quantity of the 9116 intelligent pressure sensors is at least 1.
Further, the 9116 intelligent pressure sensor establishes communication connection with an upper computer through a switch by using different port numbers and IP addresses.
Further, the 9116 intelligent pressure sensor establishes communication connection with an upper computer through a TCP protocol.
Furthermore, 9116 intelligence pressure sensor pass through the net twine and link to each other with the switch, the host computer passes through the net twine and links to each other with the switch.
A measurement method of a Labview-based pressure measurement system comprises the following steps:
step 1: connecting all the pressure sensors with the switch, and connecting the upper computer with the switch;
step 2: inputting the port numbers and IP addresses of all the pressure sensors into an upper computer, starting a connecting module of the upper computer to enable all the pressure sensors to be connected with the upper computer through a switch, enabling a connecting indicator lamp on the upper computer to turn green after the connection is successful, and checking the reason and reconnecting if the connection is unsuccessful;
and step 3: a central processing unit of the upper computer sets a file storage position and acquisition times;
and 4, step 4: a calibration module of the upper computer sends a calibration instruction to the pressure sensor, so that zero drift of the pressure sensor is eliminated, and early preparation of measurement is completed;
and 5: an acquisition module of the upper computer sends acquisition instructions to all pressure sensors, the pressure sensors acquire the pressure of the surfaces of all parts of the aircraft according to set acquisition times and transmit the acquired pressure data to a central processing unit of the pressure sensors, and the central processing unit stores the pressure data into a set file storage position;
step 6: a continuous acquisition module of the upper computer continuously sends acquisition instructions to all pressure sensors, the pressure sensors continuously acquire the pressure on the surfaces of all parts of the aircraft according to set acquisition times and transmit the acquired pressure data to a central processing unit of the pressure sensors, the central processing unit stores the pressure data into a specified file storage position, and the central processing unit controls the rate of continuous acquisition and cyclic execution through a timing VI and a cyclic function;
and 7: after the pressure data acquisition of each part surface of the aircraft is finished, the quitting module of the upper computer is started to send an acquisition stopping instruction to the pressure sensor, and the pressure sensor stops acquiring.
Further, the port number and the IP address of the pressure sensor in step 2 are stored in the upper computer in an array form.
The invention has the beneficial effects that:
compared with the prior art, the invention realizes the combination and extension of the measurement capability of a plurality of pressure sensors in the wind tunnel, enriches the pressure measurement test means and improves the test efficiency; the number of the sensors can be selected at will according to the requirements of users, so that the flexibility and the expandability of the measuring system are improved; the software of the measuring system is simple to operate, stable in operation and high in reliability. The invention is applied to a wind tunnel test system at present, and has good application effect.
Drawings
FIG. 1 is a schematic diagram of the system architecture of the present invention;
fig. 2 is a flow chart of the method of the present invention.
Detailed Description
The following detailed description of the embodiments of the present invention, such as the shapes, configurations, mutual positions and connection relationships of the components, the functions and operating principles of the components, the manufacturing processes and the operation and use methods thereof, will be further described in detail with reference to the accompanying drawings, so as to help those skilled in the art to more completely, accurately and deeply understand the concept and technical solutions of the present invention:
as shown in fig. 1, a Labview-based pressure measurement system comprises 1 or more 9116 intelligent pressure sensors, which are connected with an upper computer through a TCP protocol by different port numbers and IP addresses. Each device sends acquired data to a network in the form of data packets, an upper computer processes the received data into byte streams through a TCP protocol, the byte streams are combined into segments, and then the TCP transfers segment numbering and sequencing. And finally, displaying the data on the upper computer according to requirements, and storing the data in an appointed path.
In the technical scheme of the invention, the central processing unit, the connection module, the acquisition module, the calibration module, the continuous acquisition module and the exit module are added in the event branch through the event structure, the corresponding conditional branch is executed when the event occurs, and data communication is carried out among different parts of the same program diagram through the queue operation function, so that ordered data transmission is ensured and conflict is avoided.
A central processing unit: storing and processing signals output by the 9116 intelligent pressure sensor, and setting a file storage position and acquisition times;
a connecting module: sending a connection instruction to the 9116 intelligent pressure sensor to enable all the pressure sensors to be connected with an upper computer through a switch, wherein after the connection is successful, a connection indicator lamp on the upper computer turns green, and if the connection is unsuccessful, checking the reason and reconnecting;
an acquisition module: sending an acquisition instruction to the 9116 intelligent pressure sensor to enable the 9116 intelligent pressure sensor to start to acquire the pressure of the surfaces of all parts of the aircraft;
a calibration module: sending a calibration instruction to the pressure sensor, eliminating zero drift of the pressure sensor and completing preparation in the early stage of measurement;
a continuous acquisition module: sending a continuous acquisition instruction to the 9116 intelligent pressure sensor to enable the 9116 intelligent pressure sensor to start continuously acquiring the pressure of the surfaces of all parts of the aircraft;
an exit module: sending an acquisition stopping instruction to the 9116 intelligent pressure sensor to enable the 9116 intelligent pressure sensor to stop acquiring the pressure of the surfaces of all parts of the aircraft;
in the technical scheme of the invention, information such as the port number and the IP address of the 9116 intelligent pressure sensor is put into a cluster and exists in an array form, so that the number of the 9116 intelligent pressure sensors can be infinitely expanded.
In the technical scheme of the invention, the rate of cycle execution is controlled by timing VI and a cycle function, so that continuous acquisition is realized.
As shown in fig. 2, a measurement method of a Labview-based pressure measurement system includes the following steps:
step 1: connecting all the pressure sensors with the switch, and connecting the upper computer with the switch;
step 2: information such as a port number and an IP address of the 9116 intelligent pressure sensor is put into a cluster and exists in an array form, the number of the 9116 intelligent pressure sensors can be infinitely increased, a connecting module of an upper computer is started, all the pressure sensors are connected with the upper computer through a switch, after connection is successful, a connecting indicator lamp on the upper computer turns green, and if connection is unsuccessful, reasons are checked and reconnection is carried out;
and step 3: a central processing unit of the upper computer sets a file storage position and acquisition times;
and 4, step 4: a calibration module of the upper computer sends a calibration instruction to the pressure sensor, so that zero drift of the pressure sensor is eliminated, and early preparation of measurement is completed;
and 5: an acquisition module of the upper computer sends acquisition instructions to all pressure sensors, the pressure sensors acquire the pressure of the surfaces of all parts of the aircraft according to set acquisition times and transmit the acquired pressure data to a central processing unit of the pressure sensors, and the central processing unit stores the pressure data into a set file storage position;
step 6: a continuous acquisition module of the upper computer continuously sends acquisition instructions to all pressure sensors, the pressure sensors continuously acquire the pressure on the surfaces of all parts of the aircraft according to set acquisition times and transmit the acquired pressure data to a central processing unit of the pressure sensors, the central processing unit stores the pressure data into a specified file storage position, and the central processing unit controls the rate of continuous acquisition and cyclic execution through a timing VI and a cyclic function;
and 7: after the pressure data acquisition of each part surface of the aircraft is finished, the quitting module of the upper computer is started to send an acquisition stopping instruction to the pressure sensor, and the pressure sensor stops acquiring.
The invention realizes the combination and extension of the measurement capability of a plurality of 9116 intelligent pressure sensors in the wind tunnel, enriches the pressure measurement test means and improves the test efficiency. The software of the measuring system is simple to operate, the number of the sensors can be selected according to the requirements of users, and the flexibility and the expandability of the measuring system are improved.
The invention has been described above with reference to the accompanying drawings, it is obvious that the invention is not limited to the specific implementation in the above-described manner, and it is within the scope of the invention to apply the inventive concept and solution to other applications without substantial modification.
Claims (8)
1. A Labview-based pressure measurement system, comprising: including pressure sensor, switch and host computer, pressure sensor be connected with the switch, the switch is connected with the host computer, the host computer include central processing unit, linking module, collection module, calibration module, continuous collection module and withdraw from the module, central processing unit respectively with linking module, collection module, calibration module, continuous collection module and withdraw from the module and be connected.
2. The Labview-based pressure measurement system of claim 1, wherein: the pressure sensor is a 9116 intelligent pressure sensor.
3. The Labview-based pressure measurement system of claim 2, wherein: the quantity of the 9116 intelligent pressure sensors is at least 1.
4. The Labview-based pressure measurement system of claim 2, wherein: the 9116 intelligent pressure sensor establishes communication connection with an upper computer through a switch by using different port numbers and IP addresses.
5. A Labview-based pressure measurement system according to claim 3, wherein: the 9116 intelligent pressure sensor establishes communication connection with an upper computer through a TCP protocol.
6. A Labview-based pressure measurement system according to claim 3, wherein: 9116 intelligence pressure sensor pass through the net twine and link to each other with the switch, the host computer passes through the net twine and links to each other with the switch.
7. A measurement method of a Labview-based pressure measurement system according to any one of claims 1 to 5, wherein: the method comprises the following steps:
step 1: connecting all the pressure sensors with the switch, and connecting the upper computer with the switch;
step 2: inputting the port numbers and IP addresses of all the pressure sensors into an upper computer, starting a connecting module of the upper computer to enable all the pressure sensors to be connected with the upper computer through a switch, enabling a connecting indicator lamp on the upper computer to turn green after the connection is successful, and checking the reason and reconnecting if the connection is unsuccessful;
and step 3: a central processing unit of the upper computer sets a file storage position and acquisition times;
and 4, step 4: a calibration module of the upper computer sends a calibration instruction to the pressure sensor, so that zero drift of the pressure sensor is eliminated, and early preparation of measurement is completed;
and 5: an acquisition module of the upper computer sends acquisition instructions to all pressure sensors, the pressure sensors acquire the pressure of the surfaces of all parts of the aircraft according to set acquisition times and transmit the acquired pressure data to a central processing unit of the pressure sensors, and the central processing unit stores the pressure data into a set file storage position;
step 6: a continuous acquisition module of the upper computer continuously sends acquisition instructions to all pressure sensors, the pressure sensors continuously acquire the pressure on the surfaces of all parts of the aircraft according to set acquisition times and transmit the acquired pressure data to a central processing unit of the pressure sensors, the central processing unit stores the pressure data into a specified file storage position, and the central processing unit controls the rate of continuous acquisition and cyclic execution through a timing VI and a cyclic function;
and 7: after the pressure data acquisition of each part surface of the aircraft is finished, the quitting module of the upper computer is started to send an acquisition stopping instruction to the pressure sensor, and the pressure sensor stops acquiring.
8. The Labview-based pressure measurement system measurement method of claim 7, wherein: and 2, storing the port number and the IP address of the pressure sensor in the upper computer in an array form.
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| CN202011114543.8A CN112067247A (en) | 2020-10-16 | 2020-10-16 | Labview-based pressure measurement system and measurement method |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113848805A (en) * | 2021-09-22 | 2021-12-28 | 成都飞机工业（集团）有限责任公司 | Numerical control system machining state monitoring system and method |
| CN116842983A (en) * | 2023-08-29 | 2023-10-03 | 西安法拉第电子科技有限公司 | Data processing method and system |
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2020
- 2020-10-16 CN CN202011114543.8A patent/CN112067247A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113848805A (en) * | 2021-09-22 | 2021-12-28 | 成都飞机工业（集团）有限责任公司 | Numerical control system machining state monitoring system and method |
| CN116842983A (en) * | 2023-08-29 | 2023-10-03 | 西安法拉第电子科技有限公司 | Data processing method and system |
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