A three-dimensional aerodynamic detection device and system for a micro air vehicle

Abstract

The present invention discloses a three-dimensional aerodynamic detection device and system for a micro air vehicle. The device includes a three-dimensional force detector and an air vehicle fixture. The three-dimensional force detector is composed of three three-dimensional open orthogonal cantilever beams, namely the first, second, and third cantilever beams. The middle part of each cantilever beam is rectangularly hollowed out to form an elastic section for installing strain gauges to detect deformation, and the force detector mode can be switched through corresponding positioning holes. The air vehicle fixture consists of five parts, namely an air vehicle fixture base, a horizontal plane fixing rod, a horizontal plane positioning stud, a vertical plane fixing rod, and a vertical plane positioning stud. Through the cooperation of the horizontal plane fixing rod and the vertical plane fixing rod, the fuselage of different micro air vehicles can be fixed, and the versatility is strong. The detection device of the present invention makes full use of the characteristics of simple decoupling of the three-dimensional open orthogonal structure, small redundant space and strong adaptability of the air vehicle fixture, and has the advantages of low cost, simple installation, high precision, and strong versatility.

Description

Technical Field

[0001] The present invention relates to a three-dimensional aerodynamic detection device and system for a micro air vehicle, belonging to the technical field of aerodynamic measurement of air vehicles. Background Art

[0002] Compared with traditional fixed-wing and rotary-wing aircraft, micro air vehicles have many advantages, including low aerodynamic noise, flexible movement, strong bionic concealment, etc. In recent years, this field has received extensive attention from researchers at home and abroad. Currently, there are various micro air vehicles in the world, and they can achieve normal flight functions. However, due to the lack of a systematic design theory, the design and manufacture of micro air vehicles are still mainly based on intuitive experience and repeated trial and error.

[0003] The wings of micro air vehicles need to have a suitable shape and sufficient stiffness to support various loads during flight. At the same time, in order to reduce the weight of the aircraft, it is necessary to minimize the weight of the wings as much as possible. Therefore, the design and optimization of the wing structure are one of the important issues in the design of micro air vehicles. Since the design and manufacture theory of micro air vehicle prototypes is far from mature, the direct outdoor flight test is inefficient, and it is particularly important to measure the aerodynamic force of micro air vehicles in the laboratory. However, there are still the following problems in the existing aerodynamic force measurement of micro air vehicles:

[0004] 1) Traditional methods for aerodynamic force measurement at home and abroad usually use wind tunnel equipment for experiments. However, the use of wind tunnel equipment is complex and the system is expensive, which is not conducive to the extensive research of micro air vehicles.

[0005] 2) The aircraft measurement device composed of a static balance used in conjunction with wind tunnel equipment cannot reproduce the deformation and bending of the wing during the actual flight process, and the aerodynamic force under the actual flight of the aircraft cannot be obtained.

[0006] 3) The measurement range of traditional aerodynamic force measurement devices is too large, resulting in rough measurement accuracy and unable to meet the accuracy requirements for aerodynamic force measurement of micro air vehicles.

[0007] 4) Traditional aerodynamic force measurement devices need to customize special aircraft fixtures for different aircraft, with high time costs and poor versatility.

[0008] Therefore, it is necessary to design a new type of three-dimensional aerodynamic detection device with low cost, easy installation and high precision to solve the problem of aerodynamic force measurement of micro air vehicles. Summary of the Invention

[0009] The technical problem to be solved by the present invention is: to provide a three-dimensional aerodynamic detection device and system for a micro air vehicle, which overcomes the problems of complex and expensive existing aerodynamic force measurement device systems, low force measurement accuracy, poor versatility, etc., and has the advantages of strong clamping versatility and high measurement accuracy.

[0010] The present invention adopts the following technical solutions to solve the above technical problems:

[0011] A three-dimensional aerodynamic detection device for a micro-aerial vehicle, the device comprising a three-dimensional force sensor and an aerial vehicle fixture; the three-dimensional force sensor includes a first, a second, and a third cantilever beam, the first cantilever beam and the second cantilever beam are arranged at 90 degrees in the horizontal plane, and the second cantilever beam and the third cantilever beam are arranged at 90 degrees in the vertical plane, that is, one end of the first cantilever beam and one end of the second cantilever beam are fixed at 90 degrees in the horizontal plane, and the other end of the second cantilever beam and one end of the third cantilever beam are fixed at 90 degrees in the vertical plane; each cantilever beam includes an elastic section and two rigid sections, the elastic section is fixed between the two rigid sections, the elastic section includes two identical thin-walled sheets, the two thin-walled sheets are fixed between the two rigid sections, a rectangular hollow is formed between the two thin-walled sheets and the two rigid sections, at least one strain gauge is installed on the outer side of each thin-walled sheet, and the strain gauges installed on the two thin-walled sheets are symmetric with each other, and the distance between the two thin-walled sheets is less than the height of the rigid section;

[0012] The aerial vehicle fixture is fixed to the other end of the third cantilever beam, and the aerial vehicle fixture includes an aerial vehicle fixture base, a horizontal plane fixing rod, a horizontal plane positioning stud, a vertical plane fixing rod, and a vertical plane positioning stud; the aerial vehicle fixture base is fixed to the other end of the third cantilever beam, the horizontal plane fixing rod and the vertical plane fixing rod are respectively fixed on both sides of the upper surface of the aerial vehicle fixture base, the horizontal plane positioning stud is arranged at the top of the horizontal plane fixing rod, the vertical plane positioning stud is arranged at the top of the vertical plane fixing rod, and the horizontal plane positioning stud and the vertical plane positioning stud are used to clamp the fuselage of the aerial vehicle to be measured in the radial direction, and by changing the locking conditions of the horizontal plane positioning stud and the vertical plane positioning stud, the deflection angle and the pitch angle of the fuselage of the aerial vehicle to be measured are changed.

[0013] As a preferred solution of the device of the present invention, an axial threaded blind hole is provided at one end of the first cantilever beam, a threaded through hole perpendicular to the axial direction and an axial threaded blind hole are respectively provided at one end and the other end of the second cantilever beam, and a threaded through hole perpendicular to the axial direction is provided at one end of the third cantilever beam; the axial threaded blind hole at one end of the first cantilever beam and the threaded through hole perpendicular to the axial direction at one end of the second cantilever beam are fixedly connected by screws, and the axial threaded blind hole at the other end of the second cantilever beam and the threaded through hole perpendicular to the axial direction at one end of the third cantilever beam are fixedly connected by screws.

[0014] As a preferred solution of the device of the present invention, a force sensor fixture mounting hole is provided at the other end of the third cantilever beam, an aerial vehicle fixture mounting hole is provided on the aerial vehicle fixture base, and the aerial vehicle fixture mounting hole and the force sensor fixture mounting hole are fixedly connected by bolts.

[0015] As a preferred embodiment of the device of the present invention, positioning holes are provided on both rigid segments of the first cantilever beam and the second cantilever beam. When only the positioning hole at the other end of the first cantilever beam is fixed, the device is in a three-bar force measurement mode; when the positioning holes at both ends of the first cantilever beam are fixed, the device is in a two-bar force measurement mode; when the positioning holes at both ends of the first cantilever beam and the second cantilever beam are fixed, the device is in a single-bar force measurement mode.

[0016] As a preferred embodiment of the device of the present invention, the first cantilever beam, the second cantilever beam, and the third cantilever beam are all made of low-modulus lightweight metal materials, and the low-modulus lightweight metal materials include, but are not limited to, aluminum alloy, aluminum-magnesium alloy, and titanium alloy.

[0017] As a preferred embodiment of the device of the present invention, the aircraft fixture is made of high-strength plastic, and the high-strength plastic includes, but is not limited to, polymethyl methacrylate and polycarbonate.

[0018] A detection system based on the micro-aircraft aerodynamic three-dimensional detection device described above. The system includes an aerodynamic three-dimensional detection device, a signal amplification circuit, a data acquisition card, and a PC. The aerodynamic three-dimensional detection device is used to clamp the fuselage of the aircraft to be measured. The strain gauges in the aerodynamic three-dimensional detection device generate deformations and output voltages to the signal amplification circuit when the wings of the aircraft to be measured freely deform. The signal amplification circuit amplifies the voltage output by the strain gauges and then transmits it to the data acquisition card. The data acquisition card transmits the collected voltage to the PC in a serial communication manner. The PC processes the voltage and compares it with the pre-calibrated results to calculate the final aerodynamic force.

[0019] Compared with the prior art, the present invention adopts the above technical solutions and has the following technical effects:

[0020] 1. The device of the present invention has a low manufacturing cost, strong processability, and a simple system structure, which is convenient for installation and measurement in the laboratory.

[0021] 2. The device of the present invention enables the wings of the micro-aircraft to freely deform during the measurement process, and the aerodynamic force measurement results are close to the actual windless environment, which is real and effective.

[0022] 3. The present invention uses low-modulus lightweight metal materials to manufacture the three-dimensional force sensor and uses an elastic layer hollow structure, with stable measurement and high precision.

[0023] 4. The aircraft fixture of the present invention can realize the fixation of different micro-aircraft through the cooperation of the horizontal fixing rod and the vertical fixing rod, with strong versatility. Description of the Drawings

[0024] Figure 1 is a schematic structural diagram of the micro-aircraft aerodynamic three-dimensional detection device of the present invention;

[0025] Figure 2 It is a schematic diagram of the three - dimensional force sensor structure in the device of the present invention;

[0026] Figure 3 It is a schematic diagram of the aircraft fixture structure in the device of the present invention;

[0027] Figure 4 It is a schematic diagram before and after the deformation of the cantilever beam in the device of the present invention;

[0028] Figure 5 It is a schematic diagram of the structure of the three - dimensional aerodynamic detection system for the micro - mini aircraft of the present invention.

[0029] Among them, 1 - three - dimensional force sensor, 2 - aircraft fixture, 3 - strain gauge, 11 - the first cantilever beam, 12 - the second cantilever beam, 13 - the third cantilever beam, 14 - axial blind threaded hole or threaded through - hole perpendicular to the axial direction, 111 - the first cantilever beam positioning hole, 121 - the second cantilever beam positioning hole, 131 - the force sensor fixture mounting hole, 21 - aircraft fixture base, 22 - horizontal plane fixing rod, 23 - vertical plane fixing rod, 211 - aircraft fixture mounting hole, 221 - horizontal plane positioning stud, 231 - vertical plane positioning stud. Specific embodiments

[0030] The following details the embodiments of the present invention. The examples of the embodiments are shown in the drawings, where the same or similar reference numerals represent the same or similar elements or elements with the same or similar functions throughout. The embodiments described below with reference to the drawings are exemplary and are only used to explain the present invention and should not be construed as limiting the present invention.

[0031] As Figure 1 shown, the present invention provides a three - dimensional aerodynamic detection device for a micro - mini aircraft, including a three - dimensional force sensor 1 and an aircraft fixture 2. As Figure 2 shown, the three - dimensional force sensor 1 is composed of three cantilever beams, namely the first, the second and the third. The three cantilever beams are orthogonally distributed in a three - dimensional open form; the middle part of each cantilever beam is rectangularly hollowed out, and rounded grooves are provided on both sides for installing the strain gauge 3; the first cantilever beam 11 and the second cantilever beam 12 are respectively provided with the first cantilever beam positioning hole 111 and the second cantilever beam positioning hole 121, and the third cantilever beam 13 is provided with the force sensor fixture mounting hole 131; the three - dimensional force sensor 1 is made of low - modulus lightweight metal materials such as aluminum alloy, aluminum - magnesium alloy, titanium alloy, etc. It has a low stiffness, and under the action of a small force, the strain is large, which can improve the accuracy of the force sensor.

[0032] As Figure 3As shown in the figure, the aircraft fixture 2 consists of five parts: the aircraft fixture base 21, the horizontal plane fixing rod 22, the horizontal plane positioning stud 221, the vertical plane fixing rod 23, and the vertical plane positioning stud 231. The distance between the horizontal plane fixing rod 22 and the vertical plane fixing rod 23 is set to be compact, and the clamping method uses positioning studs. There is no redundant space during the clamping process, which will not affect the movement of the aircraft under test. The aircraft fixture 2 is made of high-strength plastics such as polymethyl methacrylate and polycarbonate. The material has low hardness and good elasticity, and will not cause damage to the fuselage when positioning the aircraft.

[0033] The third cantilever beam 13 is provided with four force sensor fixture mounting holes 131. The four force sensor fixture mounting holes 131 are symmetrically distributed in a rectangular vertex model, which can restrict the relative position of the aircraft fixture and the three-dimensional force sensor in multiple directions. All four force sensor fixture mounting holes are threaded through holes, and are connected to the aircraft fixture mounting holes 211 on the aircraft fixture 2 by bolts to realize the fixation of the aircraft fixture.

[0034] The three-dimensional force sensor 1 is composed of three independent cantilever beams. Each cantilever beam has a component connection hole, that is, an axial threaded blind hole or a threaded through hole 14 perpendicular to the axial direction. The connection hole on the first cantilever beam 11 is an axial threaded blind hole 14, and the second cantilever beam 12 has an axial threaded blind hole 14 and a threaded through hole 14 perpendicular to the axial direction respectively. The connection hole on the third cantilever beam 13 is a threaded through hole 14 perpendicular to the axial direction. Screws can be used to fix the relative positions of one threaded through hole end and one threaded blind hole end, so as to realize the mutual fixation of the first cantilever beam 11 and the second cantilever beam 12, and the second cantilever beam 12 and the third cantilever beam 13. The split structure can not only ensure the repeated usability of the measuring device, but also reduce the manufacturing cost of the measuring device, making it more economical.

[0035] As Figure 4 shown, the middle part of each cantilever beam of the three-dimensional force sensor 1 is rectangularly hollowed out, and grooves are designed on both sides to form a thin-walled sheet layer, thereby forming an elastic section. The strain gauge 3 is pasted on the outer surface of the elastic section. The middle of the cantilever beam is rectangularly hollowed out and the grooves on both sides are rounded off, so that the strain on the elastic section is evenly distributed. The designed grooves can reduce the thickness of the elastic section, thereby increasing the sensitivity of the elastic section to strain and improving the accuracy of the device.

[0036] The three-dimensional force detector 1 can divide the use of the detection device into three force measurement modes: single-rod force measurement, double-rod force measurement, and triple-rod force measurement according to the usage of the first cantilever beam positioning hole 111 and the second cantilever beam positioning hole 121. When only the first beam positioning hole at the left end of the first cantilever beam 11 is fixed, the first cantilever beam 11, the second cantilever beam 12, and the third cantilever beam 13 are all in a bendable state. At this time, all three cantilever beams have the function of measuring force, and the device is in the triple-rod force measurement mode; when all the first beam positioning holes are fixed, the first cantilever beam 11 is in a locked state and cannot be bent, and the second cantilever beam 12 and the third cantilever beam 13 are in a bendable state. At this time, the first cantilever beam 11 loses the function of measuring force, and the second cantilever beam 12 and the third cantilever beam 13 have the function of measuring force. The measuring device is in the double-rod force measurement mode; when the first beam positioning hole and the second beam positioning hole are completely fixed, the first cantilever beam 11 and the second cantilever beam 12 are in a locked state and cannot be bent, and only the third cantilever beam 13 is in a bendable state. At this time, the first cantilever beam 11 and the second cantilever beam 12 lose the function of measuring force, and the third cantilever beam 13 has the function of measuring force. The device is in the single-rod force measurement mode. Different force measurement modes can correspond to different actual usage scenarios, expanding the applicable range of the measuring device.

[0037] The strain gauges pasted on the outer surface of the elastic section adopt fancy strain gauges, and are symmetrically glued to the grooves on both sides of the thin wall in the middle of each beam. The number on each side should be no less than one (when there are multiple ones, they are distributed along the axial direction of the beam), and the symmetrical distribution forms a full-bridge connection of opposite arms. When there are multiple ones on each side, the strain gauges on that side are connected in series. It can eliminate the bending stress caused by the manufacturing accuracy and installation error of the cantilever beam itself and improve the measurement accuracy; when the number of strain gauges on each side is multiple, the strain gauges on that side are connected in series, and the measurement accuracy is improved by calculating the average strain.

[0038] The aircraft fixture 2 can change the pose of the main rod of the aircraft to be measured according to the locking conditions of the horizontal positioning studs and the vertical positioning studs, thereby changing the magnitudes of the deflection angle and the pitch angle of the aircraft fuselage. When the fixed positions of the two vertical positioning studs 231 of the vertical fixing rod 23 are at the U-shaped center line, the pitch angle is zero; when the fixed positions of the two vertical positioning studs 231 of the vertical fixing rod 23 deviate from the center upwards, the pitch angle is negative; when the fixed positions of the two vertical positioning studs 231 of the vertical fixing rod 23 deviate from the center downwards, the pitch angle is positive; by controlling the degree of deviation of the fixed positions of the two vertical positioning studs 231 from the center, the pitch angle of the aircraft to be measured can be controlled. Similarly, when the fixed positions of the two horizontal positioning studs 221 of the horizontal fixing rod 22 are at the U-shaped center line, the deflection angle is zero; when the fixed positions of the two horizontal positioning studs 221 of the horizontal fixing rod 22 deviate from the center to the left, the deflection is negative; when the fixed positions of the two horizontal positioning studs 221 of the horizontal fixing rod 22 deviate from the center to the right, the deflection angle is positive; by controlling the degree of deviation of the fixed positions of the two horizontal positioning studs 221 from the center, the deflection angle of the aircraft to be measured can be controlled. Furthermore, the force conditions of the aircraft to be measured in different postures can be measured, improving the universality of the measuring device.

[0039] The present invention also proposes a three-dimensional aerodynamic detection system for a micro-aircraft, including an aerodynamic three-dimensional detection device, a signal amplification circuit, a data acquisition card, and a PC terminal. As Figure 5 shown, the working principle of the system is as follows: First, the micro-aircraft is reasonably clamped; during measurement, the wings of the aircraft are controlled to freely deform and interact with the air, and the reaction force acts on the three-dimensional force sensor, causing the strain gauges on the beam to deform, and the resistance of the strain gauges changes accordingly; the output voltage of the balanced bridge circuit is obtained through the signal amplification circuit to obtain a real-time and effective output voltage, and the output voltage is transmitted to the data acquisition card at a sampling frequency of 10 kHz, where the sampling frequency is much higher than the natural frequency of the three-dimensional force sensor and will not affect the real-time performance of signal processing due to too high a sampling frequency; then, the signals collected by the data acquisition card are transmitted to the PC terminal in the form of serial communication, and the PC terminal analyzes and processes the collected signals through corresponding software (such as mean filtering, Fourier wavelet transform, etc.) to reduce data noise, and obtains the final aerodynamic force and image after corresponding processing with the calibration results.

[0040] The calibration process is as follows: A static load is applied to the prototype of the three-dimensional force sensor using a vibration isolation table and a loading unit; the loading unit consists of high-precision standard weights, soft thin ropes, and a micro pulley group, and realizes step-by-step loading from 0 to 100 g (each 5 g is one level); the standard force is applied to the top of the sensor along a specific direction through the pulley group; a static calibration experiment is carried out to determine the actual input-output relationship of the sensor and establish the corresponding mapping relationship between the load and the output voltage of each branch, as shown in the following formula:

[0041] V = QF

[0042] In the formula, V is the output voltage of the sensor, and F is the external force vector applied to the other end of the third cantilever beam;

[0043] Based on Figure 4 the kinematic model of the elastic segment micro-variation shown, determine the linear matrix coefficient of the force and output voltage of the sensor; use the calibration matrix Q to eliminate the inter-dimensional interference of the multi-dimensional sensor, reduce the measurement coupling error, and ensure that the sensor obtains accurate measurement results.

[0044] The expression of Q is as follows:

[0045]

[0046] In the formula, c is the strain sensitivity coefficient of the metal strain gauge, V0 is the full-bridge excitation voltage, L is half of the length of each cantilever beam, μ is the strain coefficient of the cantilever beam, θ1 is the deflection angle of the third cantilever beam, θ2 is the deflection angle of the second cantilever beam, and θ3 is the deflection angle of the first cantilever beam.

[0047] The above embodiments are only used to illustrate the technical idea of the present invention, and the protection scope of the present invention cannot be limited thereby. Any modification made on the basis of the technical solution according to the technical idea proposed by the present invention falls within the protection scope of the present invention.

Claims

1. A three-dimensional aerodynamic detection device for a micro air vehicle, characterized in that The device includes a three-dimensional force sensor and an aircraft fixture; the three-dimensional force sensor includes a first, a second, and a third cantilever beam. The first cantilever beam and the second cantilever beam are arranged at 90 degrees in the horizontal plane, and the second cantilever beam and the third cantilever beam are arranged at 90 degrees in the vertical plane. That is, one end of the first cantilever beam and one end of the second cantilever beam are fixed at 90 degrees in the horizontal plane, and the other end of the second cantilever beam and one end of the third cantilever beam are fixed at 90 degrees in the vertical plane. Each cantilever beam includes an elastic section and two rigid sections. The elastic section is fixed between the two rigid sections. The elastic section includes two identical thin-walled sheets, and the two thin-walled sheets are fixed between the two rigid sections. A cuboid-shaped hollow is formed between the two thin-walled sheets and the two rigid sections. At least one strain gauge is installed on the outer side of each thin-walled sheet, and the strain gauges installed on the two thin-walled sheets are symmetric to each other. The distance between the two thin-walled sheets is less than the height of the rigid section. The aircraft fixture is fixed to the other end of the third cantilever beam. The aircraft fixture includes an aircraft fixture base, a horizontal plane fixing rod, a horizontal plane positioning stud, a vertical plane fixing rod, and a vertical plane positioning stud. The aircraft fixture base is fixed to the other end of the third cantilever beam. The horizontal plane fixing rod and the vertical plane fixing rod are respectively fixed on both sides of the upper surface of the aircraft fixture base. The horizontal plane positioning stud is arranged at the top of the horizontal plane fixing rod, and the vertical plane positioning stud is arranged at the top of the vertical plane fixing rod. The horizontal plane positioning stud and the vertical plane positioning stud are used to clamp the fuselage of the aircraft to be measured in the radial direction. By changing the locking conditions of the horizontal plane positioning stud and the vertical plane positioning stud, the deflection angle and the pitch angle of the fuselage of the aircraft to be measured can be changed.

2. The three-dimensional aerodynamic detection device for a micro-aerial vehicle according to claim 1, wherein An axial threaded blind hole is provided at one end of the first cantilever beam. A threaded through hole perpendicular to the axial direction and an axial threaded blind hole are respectively provided at one end and the other end of the second cantilever beam. A threaded through hole perpendicular to the axial direction is provided at one end of the third cantilever beam. The axial threaded blind hole at one end of the first cantilever beam and the threaded through hole perpendicular to the axial direction at one end of the second cantilever beam are fixedly connected by screws. The axial threaded blind hole at the other end of the second cantilever beam and the threaded through hole perpendicular to the axial direction at one end of the third cantilever beam are fixedly connected by screws.

3. The three-dimensional aerodynamic detection device for a micro air vehicle according to claim 1, characterized in that A force sensor fixture mounting hole is provided at the other end of the third cantilever beam. An aircraft fixture mounting hole is provided on the aircraft fixture base. The aircraft fixture mounting hole and the force sensor fixture mounting hole are fixedly connected by bolts.

4. The three-dimensional aerodynamic detection device for a micro air vehicle according to claim 1, wherein, Positioning holes are provided on the two rigid sections of the first cantilever beam and the second cantilever beam. When only the positioning hole at the other end of the first cantilever beam is fixed, the device is in a three-bar force measurement mode; when the positioning holes at both ends of the first cantilever beam are fixed, the device is in a two-bar force measurement mode; when the positioning holes at both ends of the first cantilever beam and the second cantilever beam are fixed, the device is in a single-bar force measurement mode.

5. The three-dimensional aerodynamic detection device for micro air vehicles according to claim 1, characterized in that The first cantilever beam, the second cantilever beam, and the third cantilever beam are all made of low-modulus lightweight metal materials. The low-modulus lightweight metal materials include aluminum alloy, aluminum-magnesium alloy, or titanium alloy.

6. The three-dimensional aerodynamic detection device for a micro air vehicle according to claim 1, characterized in that The aircraft fixture is made of high-strength plastic. The high-strength plastic includes polymethyl methacrylate or polycarbonate.

7. A detection system for the aerodynamic three-dimensional detection device of the micro air vehicle according to any one of claims 1-6, characterized in that, The system includes an aerodynamic three-dimensional detection device, a signal amplification circuit, a data acquisition card, and a PC. The aerodynamic three-dimensional detection device is used to clamp the fuselage of the aircraft to be tested. The strain gauges in the aerodynamic three-dimensional detection device generate deformations and output voltages to the signal amplification circuit when the wings of the aircraft to be tested freely deform. The signal amplification circuit amplifies the voltages output by the strain gauges and then transmits them to the data acquisition card. The data acquisition card transmits the collected voltages to the PC in the form of serial communication. The PC processes the voltages and compares them with the pre-calibrated results for calculation, so as to obtain the final aerodynamic force.

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