Aircraft type measuring method for high-speed water flow model test in low-pressure environment

Abstract

The invention provides a measuring device and method for a high-speed water flow model test in a low-air-pressure environment, and relates to the technical field of high-speed water flow model tests in hydraulic engineering, and the measuring device comprises a control assembly arranged on an aircraft, a wireless transceiver arranged at the top of the control assembly, and the control assembly is arranged in a protection frame. A group of wings are arranged on the periphery of the protection frame respectively, and are connected with the control assembly through supporting members; the protection frame is rotationally connected with a telescopic rod through a knob; an integrated measuring instrument is arranged at the bottom end of the telescopic rod; the control assembly is electrically connected with the data controller, the data controller comprises a data control host, a navigation control unit and a data analysis processing unit are arranged in the data control host, and a touch display screen, operation buttons and a communication interface are arranged on the data control host. The invention aims to provide a new measurement method for the high-speed water flow model test, avoid the complexity of the original measurement process and solve the problem that the parameters of the water vapor two-phase flow model are difficult to comprehensively detect.

Description

Technical Field

[0001] This invention relates to the field of high-speed water flow model testing technology in hydraulic engineering, and in particular to a measuring device and method for high-speed water flow model testing in low-pressure environments. Background Technology

[0002] With the vigorous development of water conservancy projects in my country, high-altitude, high-head, large-discharge, and long flood discharge structures have been built. However, cavitation erosion and excessive negative pressure due to wind speed in these structures can affect the safety of the projects to some extent. Water conservancy projects often employ measures such as aeration to reduce erosion and ventilation to replenish air to mitigate the safety hazards caused by these problems. High-speed water flow model tests, to cope with the low air pressure at high altitudes, need to be conducted in a decompression chamber. On the one hand, operators cannot enter the decompression chamber; on the other hand, various physical quantities need to be collected separately, making the process complex. Furthermore, the sensors need to be fixed in place, which is not flexible enough, and the buried wires are prone to damage, making it difficult to objectively and comprehensively detect parameters such as wind speed, pressure, aeration concentration, water depth, and flow velocity in the water-vapor two-phase flow model. Summary of the Invention

[0003] This invention provides a measuring device and method for high-speed water flow model tests in low-pressure environments, aiming to solve at least one of the technical problems of the prior art mentioned in the background section.

[0004] The present invention provides the following technical solution to achieve the above objectives: A measuring device and method for high-speed water flow model testing in low-pressure environments includes an aircraft, a control component on the aircraft, a wireless transceiver on the top of the control component, the control component being housed within a protective frame, a set of wings on each of the four sides of the protective frame, the wings being connected to the control component via support members; the protective frame is connected to a telescopic rod via a knob, and an integrated measuring instrument is located at the bottom of the telescopic rod. The control component is electrically connected to the data controller, which includes a data control host, a navigation control unit and a data analysis and processing unit, and a touch screen, operation buttons and a communication interface.

[0005] Furthermore, the integrated measuring instrument includes a high-speed camera, a wind speed sensor, a pressure sensor, a probe sensor, a depth measuring instrument, and a flow velocity sensor.

[0006] A measurement method for high-speed water flow model tests in low-pressure environments, performed using the measuring device described in claim 1, includes the following steps: Step 1: Turn on the data controller and input the 3D test model into the data controller; Step 2: Plan the aircraft's flight path, measurement point locations, preset measurement point parameters, and measurement content through the navigation control unit; Step 3: Issue commands through the control components to instruct the aircraft to complete the measurement operation.

[0007] Furthermore, the preset measurement parameters and measurement content in step two include a measurement time of more than 90 seconds for each measurement point, and the measurement includes water flow pattern, wind speed, air concentration, water depth, flow velocity and time-averaged pressure.

[0008] Compared with the prior art, the present invention has the following beneficial effects: This invention provides a measurement device for high-speed water flow model tests in low-pressure environments, aiming to provide a new measurement method for high-speed water flow model tests, avoid the complexity of the original measurement process, and solve the problem of the difficulty in comprehensively detecting the parameters of water vapor two-phase flow models. Attached Figure Description

[0009] Figure 1 This is a schematic diagram of the aircraft structure of the present invention; Figure 2 This is a schematic diagram of the data controller of the present invention; Reference numerals: 1-Wing; 2-Power supply line; 3-Protective frame; 4-Wind speed sensor; 5-Telescopic rod; 6-Aircraft support component; 7-Pressure sensor; 8-Depth detector; 9-Knob; 10-Flow velocity sensor; 11-High-speed camera; 12-Gas concentration sensor; 13-Aircraft control components; 14-Wireless transceiver; 15-Motor; 16-Button; 17-Communication interface; 18-Power cord; 19-Power supply; 20-Remote data control host; 21-Touch screen. Detailed Implementation

[0010] To facilitate understanding of the present invention, a more complete description of this application will be given below with reference to the accompanying drawings, which illustrate preferred embodiments of the invention. However, the invention can be implemented in many different forms and is not limited to the embodiments described herein. Rather, these embodiments are provided to enable a more thorough and complete understanding of the disclosure of the present invention.

[0011] It should be noted that the terms "vertical," "horizontal," "up," "down," "left," "right," and similar expressions used in this article are for illustrative purposes only and do not represent the only possible implementation.

[0012] Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains; the terminology used herein in the description of the invention is for the purpose of describing particular embodiments only and is not intended to limit the invention; the term "and / or" as used herein includes any and all combinations of one or more of the associated listed items.

[0013] Example. A measurement device and method for high-speed water flow model tests in low-pressure environments, with structural reference... Figure 1 and 2 The system includes an aircraft, on which a control component 13 is installed. A wireless transceiver 14 is installed on the top of the control component 13. The control component 13 is installed inside a protective frame 3. A set of wings 1 are installed around the protective frame 3. The wings 1 are connected to the control component 13 through a support member 6. The protective frame 3 is connected to a telescopic rod 5 by rotating a knob 9. An integrated measuring instrument is installed at the bottom of the telescopic rod 5. The aircraft selected is a high-performance aircraft (multi-rotor UAV). The telescopic rod 5 is telescopically extended by the knob 9. The flexibility of the measuring point is achieved by controlling the rotation of the knob 9 and the extension and retraction of the telescopic rod 5. The control component 13 is electrically connected to the data controller, which includes a data control host 20. The data control host 20 is equipped with a navigation control unit and a data analysis and processing unit. The data control host 20 is equipped with a touch screen 21, operation buttons 16 and a communication interface 17. The protective frame 3 is made of a high-strength, low-density material and is fixedly installed on the aircraft support component 6 by bolts, which facilitates good stability of the aircraft in the air. The control component 13 is used to control the operation of the entire device and has a built-in rechargeable battery for power supply; a wireless transceiver 14 is fixedly installed on the top of the aircraft control board, which can be a ping1090i ADS-B transceiver or a TR-1W ADS-B transceiver, etc., for transmitting and receiving remote signals; a waterproof motor 15 is fixedly installed under the wing 1, which can be a 1104 brushless motor or a SURPASS-HOBBY waterproof brushless motor; the integrated measuring instrument is connected to the battery in the control component 13 through the power supply line 2; The navigation control unit is pre-installed with 3D model recognition software and trajectory layout software, which are used for importing and viewing 3D models, as well as for accurately planning flight trajectories and measurement point positions. The 3D model recognition software can be eDrawings or Unigraphics, and the trajectory layout software can be Mission Planner or Maya. The data analysis and processing unit is pre-installed with numerical calculation software and video playback software for data preprocessing, realizing compensation algorithms and visualization of results; and for viewing and storing videos captured by high-speed cameras; the numerical calculation software is selected from MATLAB or Simulink, etc.; the video playback software is selected from VLC or PotPlayer, etc. The integrated measuring instrument includes a high-speed camera 11 for recording and observing the flow state of water, a high-precision ultrasonic wind speed sensor 4 for measuring wind speed, a pressure sensor 7 for measuring pressure, a probe sensor 12 for measuring air concentration, an ultrasonic depth gauge 8 for measuring water depth, and a flow velocity sensor 10 for measuring flow velocity.

[0014] A measurement method for high-speed water flow model tests in low-pressure environments includes the following steps: Step 1: Turn on the data controller and input the 3D test model into the data controller; Step 2: Plan the aircraft's flight path, measurement point locations, preset measurement point parameters, and measurement content through the navigation control unit; the preset measurement point parameters and measurement content include a measurement time of more than 90 seconds for each measurement point, and the measurement includes parameters such as water flow pattern, wind speed (m / s), air concentration, water depth (m), flow velocity (m / s), and hourly average pressure (kPa).

[0015] Step 3: Issue commands through control component 13 to instruct the aircraft to complete the measurement operation.

[0016] Obviously, the above description is only a part of the embodiments of the present invention, and not all of the embodiments. The above embodiments are not intended to limit the present invention, and various modifications and variations can be made to the present invention by those skilled in the art. Any combination, modification, equivalent substitution, improvement, and all other embodiments that can be made by those skilled in the art within the spirit and principles of the present invention should be within the protection scope of the present invention.

Claims

1. A measuring device for high-speed water flow model testing in low-pressure environments, comprising an aircraft, characterized in that: The aircraft is equipped with a control component (13), and a wireless transceiver (14) is installed on the top of the control component (13). The control component (13) is installed inside the protective frame (3). A set of wings (1) is installed around the protective frame (3). The wings (1) are connected to the control component (13) through the support member (6). The protective frame (3) is connected to the telescopic rod (5) by rotating the knob (9). An integrated measuring instrument is installed at the bottom of the telescopic rod (5). The control component (13) is electrically connected to the data controller. The data controller includes a data control host (20). The data control host (20) is equipped with a navigation control unit and a data analysis and processing unit. The data control host (20) is equipped with a touch screen (21), operation buttons (16) and a communication interface (17).

2. The measuring device according to claim 1, characterized in that: The integrated measuring instrument includes a high-speed camera (11), a wind speed sensor (4), a pressure sensor (7), a probe sensor (12), a water depth measuring instrument (8), and a flow velocity sensor (10).

3. A measurement method for a high-speed water flow model test in a low-pressure environment, performed using the measuring device described in claim 1, characterized in that... Includes the following steps: Step 1: Turn on the data controller and input the 3D test model into the data controller; Step 2: Plan the aircraft's flight path, measurement point locations, preset measurement point parameters, and measurement content through the navigation control unit; Step 3: Issue commands through the control component (13) to instruct the aircraft to complete the measurement operation.

4. The measurement method according to claim 3, characterized in that: The preset measurement parameters and measurement content in step two include a measurement time of more than 90 seconds for each measurement point, and the measurement includes water flow pattern, wind speed, air concentration, water depth, flow velocity and time-averaged pressure.

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