CN107796591B - Wind-resistant laboratory for small rotorcraft and experimental method - Google Patents
Wind-resistant laboratory for small rotorcraft and experimental method Download PDFInfo
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Abstract
The invention discloses a wind-resistant laboratory for a small rotorcraft and an experimental method, which comprise the following steps: the laboratory body is internally provided with an experimental area; a fan set wind surface consisting of a plurality of fans is arranged on a first wall body of the laboratory body at a position corresponding to the experimental area, and the fan set wind surface is controlled by a frequency converter to generate a wind field with adjustable wind speed; an air inlet is formed in the first wall, and an air outlet is formed in the second wall opposite to the first wall; wind speed sensors are respectively arranged at the positions away from the set positions of the wind inlet and the wind outlet; the invention has the beneficial effects that: the wind resistance performance of the small rotorcraft can be detected in an indoor environment, and the wind resistance performance is small due to external interference factors. The frequency converter is adopted to control the fan unit to operate, so that the wind field is adjustable in wind speed and small in wind speed fluctuation.
Description
Technical Field
The invention relates to the technical field of performance detection of small rotorcraft, in particular to a wind-resistant laboratory and an experimental method of the small rotorcraft.
Background
Small rotorcraft have evolved rapidly in recent years and have found practical application in many industries. Small rotorcraft flying outdoors are susceptible to weather conditions, or sometimes they are required to operate in adverse weather conditions, such as rainy or windy weather. The development of detection devices for performance indicators such as wind resistance and rain resistance of small rotorcraft is delayed.
The wind resistance of the small rotorcraft is taken as one of important indexes of the small rotorcraft, the detection of the wind resistance of the small rotorcraft generally stays in a simulation stage, and the method has important significance on the research of a wind resistance experiment device of the small rotorcraft. The experiment of wind resistance performance is carried out to small-size gyroplane, must have stable controllable wind field at first. Artificial wind refers to wind generated by flowing air using a machine. From the experimental site, the method can be divided into an outdoor method and an indoor method. Outdoor environments are susceptible to weather elements. In an indoor environment, a wind tunnel model may be considered. The wind tunnel mainly comprises a tunnel body, a driving system and a measurement control system. The wind tunnel is divided into a continuous wind tunnel and a temporary impact wind tunnel according to the driving system. Continuous wind tunnels are generally constituted by fans or axial compressors. The temporary-flushing wind tunnel has air tank in the inlet of tunnel body and vacuum tank in the outlet of tunnel body. The wind tunnel model is not used for testing the wind resistance of the small rotorcraft in the flight state.
At present, aiming at the flying state of a small rotorcraft, the ground surface is about 5 meters high, and a device for testing the wind resistance performance of the small rotorcraft is mainly outdoors and has no indoor testing device. However, the artificial wind field in the outdoor environment is influenced by a plurality of factors, and the measurement result is easy to be inaccurate.
Disclosure of Invention
The invention aims to solve the problems and provides a small rotorcraft wind resistance laboratory and an experimental method.
In order to achieve the purpose, the invention adopts the following specific scheme:
the invention discloses a wind-resistant laboratory for a small rotorcraft, comprising:
the laboratory body is internally provided with an experimental area; a fan set wind surface consisting of a plurality of fans is arranged on a first wall body of the laboratory body at a position corresponding to the experimental area, and the fan set wind surface is controlled by a frequency converter to generate a wind field with adjustable wind speed;
an air inlet is formed in the first wall, and an air outlet is formed in a second wall opposite to the first wall; wind speed sensors are respectively arranged at the positions away from the set positions of the wind inlet and the wind outlet;
the method includes the steps that a test area site is divided into areas, corresponding wind speeds of all the areas under different fan set rotating speeds are tested in advance, and the actual wind speeds of the small rotorcraft at the positions are estimated according to the actual wind speeds of the wind speed sensors.
Further, still include: the control system is used for realizing wind speed control and data acquisition, and the frequency converter and the wind speed sensor are respectively connected with corresponding serial ports of the control system in a bus form; the control system realizes the simultaneous work of a plurality of serial ports through the PCI-to-serial port expansion card, and each serial port is responsible for the equipment of the same type. The invention adopts a multithreading multi-serial port bus type communication mode, so that each serial port bus has unique responsibility and does not interfere with each other.
Further, still include: a small-size gyroplane flight path real-time tracking system for obtaining small-size gyroplane flight path and three-dimensional coordinate information.
Furthermore, wind-proof devices are arranged on the air inlet and the air outlet, so that indoor interference caused by external wind can be prevented.
Furthermore, the wind surface of the fan set is provided with a wind shaping device which is a hollow cuboid, one surface of the wind shaping device, which is opposite to the wind surface, is formed by a plurality of lattice structures, and the wind surface quality can be improved after the wind shaping is carried out through the small lattices.
Furthermore, the top of the laboratory body is designed into an arc shape, and a membrane structure is adopted, so that GPS signal receiving can be enhanced.
In order to further enhance GPS signal reception, the laboratory main body is made of a steel structure, and a glass curtain wall is arranged outside the laboratory main body.
The invention also discloses a wind resistance experiment method of the small rotorcraft, which comprises the following steps:
(1) placing the small rotorcraft to be tested in the center of the experimental area, and controlling the small rotorcraft to fly to a set high place away from the ground to hover;
(2) estimating the wind speed of the position of the small rotorcraft, increasing the wind speed of the position of the small rotorcraft from zero to a set wind speed, acquiring the flight path and three-dimensional information of the small rotorcraft, and observing the moving distance of the small rotorcraft;
(3) controlling the wind speed to be reduced to zero, enabling the small rotorcraft to change angles, and repeating the steps; and the wind resistance test of each angle of the small rotorcraft is completed.
Further, the specific method for estimating the wind speed at the position of the small rotorcraft is as follows:
(2-1) dividing a test area site into areas, testing the corresponding wind speed of each area at different fan set rotating speeds, and pre-making a calibration table corresponding to the wind speed of each area at different fan set rotating speeds;
(2-2) respectively arranging wind speed sensors at the set positions away from the air inlet and the air outlet;
and (2-3) setting the rotating speed of the fan set in the experiment, observing wind speed data obtained by the wind speed sensors at the two positions in the experiment, and estimating the real-time wind speed at the position of the small rotorcraft according to the calibration table obtained in the step (2-1) by a calibration method.
Further, the wind speed at the position of the small and medium sized rotorcraft in the step (2-3) is specifically as follows:
obtaining a wind speed error rate at the wind inlet according to the wind speed at the position corresponding to the wind speed sensor at the wind inlet in the calibration table and the wind speed at the position corresponding to the wind speed sensor at the wind inlet measured in the experiment;
obtaining a wind speed error rate at the air outlet according to the wind speed at the position corresponding to the wind speed sensor at the air outlet in the calibration table and the wind speed at the position corresponding to the wind speed sensor at the air outlet measured in the experiment;
calculating the average value of the wind speed error rate at the wind inlet and the wind speed error rate at the wind gap;
and obtaining the wind speed of the position of the small rotorcraft in the experiment according to the wind speed of the position of the small rotorcraft in the calibration table and the obtained average value.
The invention has the beneficial effects that:
1. the wind resistance performance of the small rotorcraft can be detected in an indoor environment, and the wind resistance performance is small due to external interference factors.
2. The invention adopts the frequency converter to control the operation of the fan unit, realizes the adjustable wind speed of the wind field and small fluctuation of the wind speed.
3. According to the invention, the wind speed measurement of the small rotorcraft in the hovering state can be realized through the wind speed estimation method at the position of the small rotorcraft, so that the wind resistance of the small rotorcraft in the hovering state can be detected, and the problem that the wind speed of the small rotorcraft in the flying state in a wind field with attenuated wind speed cannot be measured in the past is solved.
4. The wind field experimental equipment is designed according to industrial standards, and has the advantages of good stability and durability, high digitization degree, convenient operation and easy maintenance.
Drawings
FIG. 1 is a top view of the overall layout of the present invention;
FIG. 2 is a schematic external view of the present invention;
FIG. 3 is a design effect diagram of the present invention;
FIG. 4 is a schematic view of the wind surface equipment of the present invention;
FIG. 5 is a schematic view of the present invention;
FIG. 6 is a control system architecture diagram of the present invention;
fig. 7 is a schematic view of an estimated wind speed calibration point at the location of a small rotorcraft according to the present invention.
The specific implementation mode is as follows:
the invention is described in detail below with reference to the accompanying drawings:
the invention discloses a wind-resistant laboratory for a small rotorcraft, as shown in fig. 1, comprising: the laboratory body is internally provided with an experimental area; a fan set wind surface consisting of a plurality of fans is arranged on a first wall body of the laboratory body and at a position corresponding to the experimental area, and the fan set wind surface is controlled by a frequency converter to generate a wind field with adjustable wind speed; the frequency converter cabinets are respectively arranged on two sides of the wind surface of the fan unit.
Air inlets are respectively arranged at two sides of the first wall body, and air outlets are respectively arranged at two sides of a second wall body opposite to the first wall body; the design that the air inlet and the air outlet are opposite can ensure the balance of indoor and outdoor pressure and ensure the smooth and stable indoor airflow.
And wind speed sensors are respectively arranged at the set positions away from the wind inlet and the wind outlet.
And wind-proof devices are arranged on the air inlet and the air outlet to prevent the indoor interference caused by external wind. The wind-proof device includes: the air buffer area or the airflow buffer area is arranged at the air inlet, the rolling door is arranged at the air inlet, the air buffer area or the airflow buffer area is arranged at the air outlet, and the rolling door is arranged at the air outlet.
In this embodiment, a buffer area 2 meters wide is arranged at the air inlet, and a rolling door is added, and a buffer area 4 meters wide is added at the air outlet, as shown in the top view of fig. 1.
The dimensions of a laboratory house given with reference to fig. 1 are 17m × 12m × 12m (length, width and height). The house is designed with an air inlet (side air inlet) and an air outlet (side air outlet). A4 m wide fan unit wind surface is arranged in the middle of the wind inlet and is controlled by a frequency converter to generate speed-adjustable wind, and the frequency converter cabinets are respectively arranged on two sides of the fan unit wind surface. The side air outlet is composed of 4 rolling doors, and the air generated by the fan can be discharged outdoors through the rolling doors, so that the indoor pressure is ensured to be unchanged. People can be located in the control room to operate wind field equipment to complete the anti-wind experiment of the small rotorcraft.
As shown in figure 2, the appearance of the house is schematically shown, the wind surface formed by the fans is arranged at the wind inlet of the house, and the height of the center of the wind surface from the ground is 5 meters. The roof of the house is designed into an arc shape, and a membrane structure is adopted, so that GPS signal receiving can be enhanced.
As shown in figure 3, the design effect diagram is provided, the laboratory main body is made of steel structure, and the exterior of the laboratory main body is a glass curtain wall. GPS signal reception may be enhanced.
As shown in fig. 4, which is a schematic view of the design of the wind surface, a large wind surface is required for the small rotorcraft to perform the wind resistance test in the flight state. From the wind tunnel model, we need a continuous wind tunnel, the driving system of which generally consists of a fan, and through comparing a centrifugal fan, an axial flow fan and a mixed flow fan, the mixed flow fan is found to have the advantages of more fan blades, stable air outlet, high wind speed and wind pressure, strong anti-attenuation capability and the like, so the mixed flow fan is selected as the wind surface. The single mixed-flow fan cannot meet the requirement of the test on the wind surface, so that the mode of combining a plurality of fans is adopted, and the influence of the mixed-flow fans combined by the plurality of fans on the wind quality is found to be small through simulation.
As shown in fig. 5, the wind shaping device is schematically shown, and the wind can be slightly diffused when wind exits from the wind surface formed by the fans, so that the wind shaping device is added. The wind-rectifying device is a hollow cuboid made of iron sheet, the length and the width of the hollow cuboid are consistent with the size of a wind surface, the thickness of the hollow cuboid is 1 meter, wind generated by the wind surface passes through the cuboid with the thickness of 1 meter, one surface of the cuboid, corresponding to the wind surface of the fan unit, is formed by a plurality of small lattices, the wind passes through the small lattices, the wind-rectifying device performs wind-rectifying, and the quality of the wind surface can be improved.
The control system is arranged in the control room and used for realizing wind speed control and data acquisition; as shown in fig. 6, the frequency converter and the wind speed sensor are respectively connected with corresponding serial ports of the control system in a bus form; the upper computer of the control system is realized by VC + +, a plurality of serial ports can work simultaneously by a PCI-to-serial port expansion card, and each serial port is responsible for equipment of the same type, and the duties are unique and do not interfere with each other. Each serial port adopts a 485 half-duplex communication mode, and the mounted equipment is controlled in a bus mode.
The invention discloses a wind resistance experiment method of a small rotorcraft, which comprises the following steps:
(1) placing the small rotorcraft to be tested in the center of the experimental area, and controlling the small rotorcraft to fly to a set high place away from the ground to hover;
(2) estimating the wind speed of the position of the small rotorcraft, increasing the wind speed of the position of the small rotorcraft from zero to a set wind speed, acquiring the flight path and three-dimensional information of the small rotorcraft, and observing the moving distance of the small rotorcraft;
(3) controlling the wind speed to be reduced to zero, enabling the small rotorcraft to change angles, and repeating the steps; and the wind resistance test of each angle of the small rotorcraft is completed.
When the test is started, firstly, observing outdoor natural wind, and if no wind exists outdoors, completely opening the roller shutters at the side air inlet and the side air outlet; if wind exists outdoors, the wind direction is observed, and the side wind inlet and the side wind outlet are only provided with the side rolling door, so that the natural wind is prevented from interfering the indoor environment.
Secondly, put the small-size gyroplane that awaits measuring in the test area center, control small-size gyroplane and fly to hovering 5 meters eminence from ground, the people is located control room control, observation, increases small-size gyroplane position department wind speed from zero to wind speed 10m/s, through the inside small-size gyroplane flight path real-time tracking system who is equipped with of laboratory, acquires small-size gyroplane flight path and three-dimensional information, and its measurement accuracy is centimetre level, observes the distance that small-size gyroplane removed.
And finally, controlling the wind speed to be reduced to zero, enabling the small rotorcraft to convert the angle to face the wind surface, and repeating the steps. And the wind resistance test of each angle of the small rotorcraft is completed.
The wind speed at the position of the small rotorcraft is obtained through estimation, the specific method is shown in fig. 7, the wind speed information at the position of the small rotorcraft can be known by testing the wind resistance performance of the small rotorcraft, and the wind field with the attenuated wind speed is not as easy to obtain the real-time wind speed at the target position of the test area as the wind tunnel.
First, the small rotorcraft itself cannot carry wind speed monitoring equipment because this affects its weight and thus its accuracy in wind resistance testing, and the small rotorcraft generally does not carry an anemometer during operation. Secondly, because the small-sized rotorcraft is subjected to a wind resistance test in a flying state, the wind speed at the small-sized rotorcraft needs to be monitored in real time in the process, and the installation of the wind speed sensor faces a difficult problem.
Aiming at the characteristics of the test of the wind field, the invention provides a method for monitoring the wind speed of the position of a small rotorcraft when the small rotorcraft is in a flight state in the wind field with attenuated wind speed. The method comprises the following specific steps:
(1) dividing a test site into areas, and testing the wind speed corresponding to different rotating speeds of a fan in each area;
(2) and air speed sensors are respectively arranged at positions 3 meters away from the air inlet and the air outlet.
(3) And during the test, the data of the two sensors are observed, and the real-time wind speed of the small rotorcraft is obtained by a calibration method. For example, dividing the test area into zones as shown in the table of fig. 7, the fan is installed in the middle position on the right side of the table, assuming that we have tested values corresponding to different fan speeds in each zone, the wind speed sensors are installed at positions D2 and D6, the small rotorcraft is at position D4, and the wind speed at position D4 is estimated.
At the wind speed V of the fan outletfanWhen the wind speed is 10m/s, the position D6 corresponding to V is obtained by a pre-made table of wind speeds of different wind speeds of the fan corresponding to the wind speed of each areaD6_tableD4 position corresponds to VD4_tableD2 corresponds to position VD2_table。
Setting the wind speed of a fan to be 10m/s through a computer after the test is started, and reading the wind speed V of a sensor at the position D2 at the momentD2_currentWind speed V of wind speed sensor at D6 positionD6_currentThen the wind speed V at D4 can be estimatedD4_currentAs shown in the following formula.
Although the embodiments of the present invention have been described with reference to the accompanying drawings, it is not intended to limit the scope of the present invention, and it should be understood by those skilled in the art that various modifications and variations can be made without inventive efforts by those skilled in the art based on the technical solution of the present invention.
Claims (2)
1. A laboratory method for a wind-resistant laboratory for small rotorcraft, characterized in that it comprises the following steps:
(1) placing the small rotorcraft to be tested in the center of the experimental area, and controlling the small rotorcraft to fly to a set high place away from the ground to hover;
(2) estimating the wind speed of the position of the small rotorcraft, increasing the wind speed of the position of the small rotorcraft from zero to a set wind speed, acquiring the flight path and three-dimensional information of the small rotorcraft, and observing the moving distance of the small rotorcraft;
(3) controlling the wind speed to be reduced to zero, enabling the small rotorcraft to change angles, and repeating the steps; completing the wind resistance test of each angle of the small rotorcraft;
the specific method for estimating the wind speed of the small rotorcraft at the position comprises the following steps:
(2-1) dividing a test area site into areas, testing the corresponding wind speed of each area at different fan set rotating speeds, and pre-making a calibration table corresponding to the wind speed of each area at different fan set rotating speeds;
(2-2) respectively arranging wind speed sensors at the set positions away from the air inlet and the air outlet;
and (2-3) setting the rotating speed of the fan set in the experiment, observing wind speed data obtained by the wind speed sensors at the two positions in the experiment, and estimating the real-time wind speed at the position of the small rotorcraft according to the calibration table obtained in the step (2-1) by a calibration method.
2. The experimental method according to claim 1, wherein the wind speed at the location of the small-to-medium sized rotorcraft in step (2-3) is specifically:
obtaining a wind speed error rate at the wind inlet according to the wind speed at the position corresponding to the wind speed sensor at the wind inlet in the calibration table and the wind speed at the position corresponding to the wind speed sensor at the wind inlet measured in the experiment;
obtaining a wind speed error rate at the air outlet according to the wind speed at the position corresponding to the wind speed sensor at the air outlet in the calibration table and the wind speed at the position corresponding to the wind speed sensor at the air outlet measured in the experiment;
calculating the average value of the wind speed error rate at the wind inlet and the wind speed error rate at the wind gap;
and obtaining the wind speed of the position of the small rotorcraft in the experiment according to the wind speed of the position of the small rotorcraft in the calibration table and the obtained average value.
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| CN109502049A (en) * | 2018-11-30 | 2019-03-22 | 山东鲁能智能技术有限公司 | Unmanned plane wind resistance detection system and method |
| CN110671352A (en) * | 2018-12-05 | 2020-01-10 | 昆明北理工产业技术研究院有限公司 | Multi-fan cooperative wind field system based on wind speed estimation model |
| CN111289218B (en) * | 2018-12-07 | 2022-04-08 | 重庆交通大学 | Experimental system for researching collision avoidance in meeting of multiple ships under severe wind conditions |
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| CN103439531B (en) * | 2013-08-27 | 2015-02-18 | 中钢集团马鞍山矿山研究院有限公司 | Wind tunnel detection test device and method for calibrating multiple wind meters automatically |
| CN104406762B (en) * | 2014-11-28 | 2016-09-21 | 国家电网公司 | A kind of overhead transmission line depopulated helicopter cruising inspection system wind capability detection method |
| CN106096207B (en) * | 2016-06-29 | 2019-06-07 | 武汉中观自动化科技有限公司 | A kind of rotor wing unmanned aerial vehicle wind resistance appraisal procedure and system based on multi-vision visual |
| CN106525375B (en) * | 2016-10-21 | 2020-05-12 | 国网山东省电力公司电力科学研究院 | Self-adaptive system for detecting wind resistance of unmanned aerial vehicle |
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Address after: Ji'nan City, Shandong Province Wang Yue Road 250003 No. 2000 Applicant after: Electric Power Research Institute of State Grid Shandong Electric Power Company Applicant after: National Network Intelligent Technology Co., Ltd. Applicant after: State Grid Corporation of China Address before: Ji'nan City, Shandong Province Wang Yue Road 250003 No. 2000 Applicant before: Electric Power Research Institute of State Grid Shandong Electric Power Company Applicant before: Shandong Luneng Intelligent Technology Co., Ltd. Applicant before: State Grid Corporation of China |
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Effective date of registration: 20201029 Address after: 250101 Electric Power Intelligent Robot Production Project 101 in Jinan City, Shandong Province, South of Feiyue Avenue and East of No. 26 Road (ICT Industrial Park) Patentee after: National Network Intelligent Technology Co.,Ltd. Address before: Ji'nan City, Shandong Province Wang Yue Road 250003 No. 2000 Patentee before: ELECTRIC POWER RESEARCH INSTITUTE OF STATE GRID SHANDONG ELECTRIC POWER Co. Patentee before: National Network Intelligent Technology Co.,Ltd. Patentee before: STATE GRID CORPORATION OF CHINA |