CN110920929B - Wing lift force measurement experiment device and measurement method thereof - Google Patents

Wing lift force measurement experiment device and measurement method thereof Download PDF

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CN110920929B
CN110920929B CN201911222630.2A CN201911222630A CN110920929B CN 110920929 B CN110920929 B CN 110920929B CN 201911222630 A CN201911222630 A CN 201911222630A CN 110920929 B CN110920929 B CN 110920929B
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wing
connecting rod
strain gauges
arm
cantilever beam
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CN110920929A (en
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陈伟
梁栋
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Sichuan University
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Sichuan University
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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
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation

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  • Engineering & Computer Science (AREA)
  • Fluid Mechanics (AREA)
  • General Physics & Mathematics (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)

Abstract

The invention discloses an experimental device and a method for measuring wing lift force, and belongs to the field of mechanical measurement. The wing lift force measurement experiment device comprises a measurement circuit and a wind tunnel with an airflow channel, wherein a bracket is arranged on the outer side wall of the airflow channel, a horizontal cantilever arm is arranged on the bracket, the other end of the cantilever arm extends into the airflow channel, a detachable connecting rod is arranged at one end of the cantilever arm extending into the airflow channel, and a wing is arranged at the other end of the connecting rod; the measuring circuit comprises a power supply and 4 strain gauges arranged at one end of the cantilever beam arm, which is close to the bracket, wherein the 4 strain gauges are connected end to form a full bridge, 2 strain gauges are positioned on a first surface of the cantilever beam arm, the other 2 strain gauges are positioned on a second surface opposite to the first surface, and two ends of the power supply are respectively connected with a node between the two strain gauges positioned on the same surface; the other two nodes on the full bridge form an output end, and the output end is connected with the voltage measuring device after sequentially passing through the signal amplifying module and the filtering module.

Description

Wing lift force measurement experiment device and measurement method thereof
Technical Field
The invention relates to the field of mechanical measurement, in particular to an experimental device and a method for measuring wing lift force.
Background
Wing lift measurement is a typical experimental item in hydrodynamics. The common measuring device consists of a wind tunnel and a three-component force measuring balance, and the functional relation between the balance reading and aerodynamic force is obtained by static force calibration in advance, so that the calibration process is complicated, and the equipment cost is high.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide an experimental device for measuring the wing lift force, which is simple in calibration process and low in manufacturing cost, and a measuring method thereof.
In order to achieve the aim of the invention, the invention adopts the following technical scheme:
the wing lift force measurement experimental device comprises a measurement circuit and a wind tunnel with an airflow channel, wherein a bracket is arranged on the outer side wall of the airflow channel, a horizontal cantilever arm is arranged on the bracket, the other end of the cantilever arm extends into the airflow channel, a detachable connecting rod is arranged at one end of the cantilever arm extending into the airflow channel, and a wing is arranged at the other end of the connecting rod;
the measuring circuit comprises a power supply and 4 strain gauges arranged at one end of the cantilever beam arm, which is close to the bracket, wherein the 4 strain gauges are connected end to form a full bridge, 2 strain gauges are positioned on a first surface of the cantilever beam arm, the other 2 strain gauges are positioned on a second surface opposite to the first surface, and two ends of the power supply are respectively connected with a node between the two strain gauges positioned on the same surface; the other two nodes on the full bridge form an output end, and the output end is connected with the voltage measuring device after sequentially passing through the signal amplifying module and the filtering module.
Further, the strain gauge is a resistive strain gauge and is adhered to the cantilever arm.
Further, the connecting line between the strain gages positioned on the same surface is perpendicular to the central line of the cantilever arm, the 4 strain gages are positioned at 4 vertex angles of a rectangle, and the plane of the rectangle is perpendicular to the plane of the cantilever arm.
Further, the distance between the center point of the two strain gauges on the same plane and the fixed end of the cantilever beam arm is 50-70mm.
Further, the cantilever beam arm is a steel sheet.
Further, the cantilever arms have dimensions of 260mm by 30mm by 2mm.
Further, the wing and the connecting rod are formed by 3D printing, and the material is ABS.
Further, the cross section of the connecting rod is in an inverted T shape, and the part for realizing detachable connection of the connecting rod comprises two mounting holes formed in the cantilever beam arm, a threaded hole formed in the bottom of the connecting rod and a bolt and a nut matched with the threaded hole.
Further, the cantilever beam arm is detachably connected with the bracket.
On the other hand, a measurement method of the wing lift force measurement experimental device designed based on the scheme is provided, which comprises the following steps:
before the connecting rod is installed, a weights with the mass of m are loaded one by one at the center of the pre-connecting position of the connecting rod and the cantilever beam arm;
recording the voltage value on the voltage measuring device after the weights are loaded each time, and obtaining the corresponding relation between the change delta mg and the voltage value variation delta U;
installing a connecting rod and recording the voltage value U on the current voltage measuring device o ；
Starting the airflow generating device, and recording the voltage value U on the current voltage measuring device after the airflow in the airflow channel reaches the set condition c The lift experienced by the wing is then calculated:
Figure BDA0002301286090000021
wherein F is the lift force exerted by the wing.
The beneficial effects of the invention are as follows:
based on the principle of cantilever beam arm stress deformation, the lift force change is converted into output end voltage change by utilizing 4 strain gauges, and the voltage is amplified and filtered by a signal amplification module and a filtering module, so that more stable, accurate and obvious voltage change is obtained, and further the measurement of the lift force of the wing is completed. Meanwhile, the wing lift force measurement experimental device has low total cost of other devices or elements besides the original wind tunnel, and further lower manufacturing cost is realized.
Before the connecting rod is installed, a weights with the mass of m are loaded one by one at the center of the pre-connecting position of the connecting rod and the cantilever beam arm, the voltage value on the voltage measuring device after the weights are loaded each time is recorded, the corresponding relation between the change delta mg and the voltage value change delta U is obtained, and the calibration is completed.
Drawings
FIG. 1 is a partial front view of an embodiment of the present wing lift measurement experiment device in use;
FIG. 2 is an elevation view of the cantilever beam of FIG. 1;
FIG. 3 is top and bottom views of the cantilever beam of FIG. 1;
FIG. 4 is a front view of the wing and connecting rod of FIG. 1;
FIG. 5 is a left side view of the wing and connecting rod of FIG. 1;
FIG. 6 is a rear view of the wing and connecting rod of FIG. 1;
FIG. 7 is a schematic perspective view of the wing and connecting rod of FIG. 1;
fig. 8 is a schematic diagram of a measurement circuit in an embodiment.
Wherein, 1, an airflow channel; 2. a wing; 3. a connecting rod; 4. a bracket; 5. a cantilever beam arm; 6. a strain gage; 7. and (5) mounting holes.
Detailed Description
The following detailed description of the invention is presented in conjunction with the drawings to facilitate understanding of the invention by those skilled in the art. It should be apparent that the embodiments described below are only some, but not all embodiments of the invention. All other embodiments, which come within the spirit and scope of the invention as defined and defined by the following claims, may be made by one skilled in the art without any inventive faculty.
As shown in fig. 1 and 2, the experimental device for measuring the lift force of the wing comprises a measuring circuit and a wind tunnel with an airflow channel 1, wherein a bracket 4 is arranged on the outer side wall of the airflow channel 1, a horizontal cantilever arm 5 is arranged on the bracket 4, the other end of the cantilever arm 5 extends into the airflow channel 1, a detachable connecting rod 3 is arranged at one end of the cantilever arm 5 extending into the airflow channel 1, and the wing 2 is arranged at the other end of the connecting rod 3.
The measuring circuit comprises a power supply and 4 strain gauges 6 arranged on one end of the cantilever beam arm 5, which is close to the bracket 4, wherein the 4 strain gauges 6 are connected end to form a full bridge, 2 strain gauges 6 are positioned on a first surface of the cantilever beam arm 5, the other 2 strain gauges 6 are positioned on a second surface opposite to the first surface, and two ends of the power supply are respectively connected with a node between the two strain gauges 6 positioned on the same surface; the other two nodes on the full bridge form an output end, and the output end is connected with the voltage measuring device after sequentially passing through the signal amplifying module and the filtering module.
The extension of the other end of the cantilever arm 5 into the airflow channel 1 herein includes that the other end of the cantilever arm 5 is located within the cross-sectional inner contour of the airflow channel 1, while also including that the other end of the airflow channel 1 is located at the mouth of the airflow channel 1 and not within the cross-sectional inner contour of the airflow channel 1.
In practice, as shown in fig. 1, the cantilever arm 5 is preferably a steel sheet with a size of 260mm by 30mm by 2mm. The other end of the cantilever arm 5 is located at the mouth of the airflow channel 1 and is not located within the cross-sectional internal profile of the airflow channel 1. The strain gage 6 is a resistance strain gage, and is bonded to the cantilever arm 5. As shown in fig. 3, the connecting line between the strain gauges 6 on the same surface is perpendicular to the center line of the cantilever arm 5, and the 4 strain gauges 6 are positioned at 4 vertex angles of a rectangle, and the plane of the rectangle is perpendicular to the plane of the cantilever arm 5. And, the distance between the center point of the two strain gauges 6 located on the same plane and the fixed end of the cantilever arm 5 is 50-70mm.
As shown in fig. 4-7, the wing 2 and the connecting rod 3 are formed by 3D printing (i.e. the wing 2 and the connecting rod 3 are integrally formed), and the materials are ABS. The cross section of connecting rod 3 is the shape of falling T, realizes that connecting rod 3 can dismantle the part of connection and includes two mounting holes 7 of seting up on the cantilever beam arm 5, the screw hole of seting up of connecting rod 3 bottom and with screw hole complex bolt and nut.
Wherein, the voltage measuring device is a voltmeter. As shown in fig. 8, four resistance strain gauges R 1 -R 4 Is of the same model and is 350 omega, power supply E m Is a 10V direct current power supply, resistor R 5 1KΩ, resistance R 6 1KΩ, resistance R 7 47KΩ, resistance R 8 47KΩ, resistance R 9 1.8KΩ, resistance R 10 10KΩ, capacitance C of 0.33uF, V OUT And connecting with a voltmeter. R is R 1 And R is 4 On the same plane as the cantilever arm 5, R 2 And R is 3 On the other side of the cantilever arm 5.
Wherein, the cantilever beam arm 5 is detachably connected with the bracket 4, and the detachable connection between the cantilever beam arm 5 and the bracket 4 is realized through pliers.
On the other hand, this scheme still provides a wing lift force measurement experimental apparatus's measurement method based on this scheme design, and it includes:
before the connecting rod 3 is installed, a weights with the mass of m are loaded one by one at the center of the pre-connecting position of the connecting rod 3 and the cantilever beam arm 5;
recording the voltage value on the voltage measuring device after the weights are loaded each time, and obtaining the corresponding relation between the change delta mg and the voltage value variation delta U, namely finishing the calibration process;
installing the connecting rod 3 and recording the voltage value U on the current voltage measuring device o ；
Starting the airflow generating device, and recording the voltage value U on the current voltage measuring device after the airflow in the airflow channel reaches the set condition c The lift experienced by the wing 2 is then calculated:
Figure BDA0002301286090000051
where F is the lift experienced by the wing 2.
In the whole process, the external force effect can lead to the deformation of the cantilever surface, thereby leading to the change of the parameters of the strain gauge 6, and finally reflecting the change of the output end voltage.
In a specific embodiment, a is 5, the weight has a mass of 20g, and the calibration process is recorded as follows:
Figure BDA0002301286090000061
/>
thus, Δmg=196, Δu=53.2 (averaged).

Claims (9)

1. The wing lift force measurement experiment device comprises a wind tunnel with an airflow channel and is characterized by comprising a measurement circuit, wherein a bracket (4) is arranged on the outer side wall of the airflow channel, a horizontal cantilever arm (5) is arranged on the bracket (4), the other end of the cantilever arm (5) extends into the airflow channel, a detachable connecting rod (3) is arranged at one end of the cantilever arm (5) extending into the airflow channel, and a wing (2) is arranged at the other end of the connecting rod (3);
the measuring circuit comprises a power supply and 4 strain gauges (6) arranged at one end, close to the bracket (4), of the cantilever beam arm (5), wherein the 4 strain gauges (6) are connected end to form a full bridge, 2 strain gauges (6) are positioned on a first surface of the cantilever beam arm (5), the other 2 strain gauges (6) are positioned on a second surface opposite to the first surface, and two ends of the power supply are respectively connected with nodes between the two strain gauges (6) positioned on the same surface; the other two nodes on the full bridge form an output end, and the output end is connected with a voltage measuring device after sequentially passing through a signal amplifying module and a filtering module;
the measuring method of the wing lift force measuring experimental device comprises the following steps:
before the connecting rod (3) is installed, a weights with the mass of m are loaded one by one at the center of the pre-connection position of the connecting rod (3) and the cantilever beam arm (5);
recording the voltage value on the voltage measuring device after the weights are loaded each time, and obtaining the corresponding relation between the change delta mg and the voltage value variation delta U;
installing a connecting rod (3) and recording the voltage value U on the current voltage measuring device o ；
Starting the airflow generating device, and recording the voltage value U on the current voltage measuring device after the airflow in the airflow channel reaches the set condition c Then calculating the lift force to which the wing (2) is subjected:
Figure FDA0004057222200000011
wherein F is the lift force exerted on the wing (2).
2. The wing lift measurement experiment device according to claim 1, characterized in that the strain gauge (6) is a resistive strain gauge, which is glued to the cantilever beam arm (5).
3. The wing lift force measurement experiment device according to claim 1, wherein the connecting line between the strain gauges (6) located on the same plane is perpendicular to the central line of the cantilever beam arm (5), the 4 strain gauges (6) are located at 4 vertex angles of a rectangle, and the plane of the rectangle is perpendicular to the plane of the cantilever beam arm (5).
4. A wing lift measurement experiment device according to claim 3, characterized in that the distance between the centre point of two strain gauges (6) located on the same side and the fixed end of the cantilever arm (5) is 50-70mm.
5. The wing lift measurement experiment device according to claim 1, characterized in that the cantilever beam arm (5) is a steel sheet.
6. The wing lift measurement experiment device according to claim 2, characterized in that the cantilever beam arm (5) has a size of 260mm x 30mm x 2mm.
7. The wing lift force measurement experiment device according to claim 1, wherein the wing (2) and the connecting rod (3) are formed by 3D printing, and the materials are ABS.
8. The wing lift force measurement experiment device according to claim 1, wherein the cross section of the connecting rod (3) is in an inverted T shape, and the parts for realizing the detachable connection of the connecting rod (3) comprise two mounting holes (7) formed in the cantilever beam arm (5), a threaded hole formed in the bottom of the connecting rod (3) and a bolt and a nut matched with the threaded hole.
9. The wing lift measurement experiment device according to any one of claims 1-8, characterized in that the cantilever arm (5) is detachably connected to the bracket (4).
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