Distributed electric duct component wind tunnel test force measurement system

Abstract

The application provides a distributed electric duct component wind tunnel test force measuring system and relates to the technical field of wind tunnel test.The system comprises a fairing, a wing, an electric duct, an electric duct connecting plate, a wing connecting plate and a force measuring balance.The force measuring balance comprises a balance outer ring, a balance inner core and a force measuring beam.The wing connecting plate is connected with the wing, the electric duct is fixed on the top of the electric duct connecting plate, and the force measuring balance is arranged between the wing connecting plate and the electric duct connecting plate.The application ingeniously integrates multiple force measuring balances into the wing by taking advantage of the small size and large rigidity of the force measuring balances, thereby solving the practical problem that the conventional balance is too large to be used for distributed measurement of the aerodynamic force of multiple electric ducts.Through reasonable design and arrangement of the electric duct, the force measuring balance and the electric duct connecting plate and other components, the space limitation of the model is greatly reduced, so that the force measuring system can solve the problem of wind tunnel model balance structure design caused by insufficient internal space of the wing and difficulty in overall arrangement of the electric duct component force measuring system.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of wind tunnel test, in particular to a distributed electric duct component wind tunnel test force measurement system. BACKGROUND

[0002] Wind tunnel test is an important aerodynamic testing method, which is used to study the interaction between gas flow and aircraft model, so as to master the aerodynamic characteristics of aircraft. Wind tunnel component force test is mainly used to measure the aerodynamic force and moment of aircraft components in airflow, including drag, lift, side force, pitch moment, etc. These data are of great significance for evaluating the aerodynamic performance of components, optimizing design and verifying computational fluid dynamics simulation results.

[0003] Electric duct component force test is an aerodynamic performance test for electrically driven ducted fans. Through electric duct component force test, the aerodynamic performance of electric ducted fans can be comprehensively evaluated, providing scientific basis for related applications. It is mainly used to evaluate its thrust, drag, torque and other parameters, as well as the influence of different design parameters on its performance. Electric duct force test content includes: measuring the thrust, drag and torque of ducted fans under different working conditions, evaluating the influence of different inlet lip configurations on aerodynamic performance, and verifying numerical simulation results to optimize the design of ducted fans. Electric duct component force test not only provides data support for the design and optimization of ducted fans, but also promotes the development of green aviation technology.

[0004] Electric duct component force test system is mainly composed of force balance and electric duct model. As the most core equipment of force test, force balance is used to measure the aerodynamic force and moment of the model. Commonly used is six-component strain balance, which can measure drag, lift, side force, yaw moment, torsional moment and pitch moment, etc. Electric duct model is generally composed of wings, several electric ducts, fans, motors and fairing. As a research object of new propulsion system, electric duct is not a single one, but a distributed arrangement of multiple groups. Since electric duct is generally a ring-shaped thin shell with fan structure, in order to measure the six-component aerodynamic force of single electric duct, component force balance cannot be placed in the electric duct, but can only be embedded in the wing. However, due to the requirement of distributed measurement test, multiple force balances need to be distributed in a small space to realize distributed electric duct component force measurement. The length and height of conventional rod balance and box balance cannot meet the extremely narrow space requirement of the model, so it is difficult to arrange and design the test model and balance, affecting the development of wind tunnel test.

[0005] Therefore, it is necessary to design a distributed electric duct component wind tunnel test force measurement system to solve the above technical problems. SUMMARY

[0006] The present application is developed to solve the problem of insufficient model space and difficulty in arranging component force measuring balance caused by the requirement of force measuring test of distributed components of electric duct. Hereinafter, a brief summary of the present application is given to provide a basic understanding of some aspects of the present application. It should be understood that this summary is not an exhaustive overview of the present application. It is not intended to identify key or important parts of the present application nor to limit the scope of the present application.

[0007] To achieve the above-mentioned purpose, the present application is implemented by the following technical solutions:

[0008] A distributed electric duct component wind tunnel test force measuring system, comprising a fairing, a wing, a plurality of electric ducts, a plurality of electric duct connecting plates, a plurality of wing connecting plates and a plurality of force measuring balances, the plurality of electric ducts are distributed on the wing, the fairing is arranged above the plurality of electric ducts and connected with the wing.

[0009] The force measuring balance comprises a balance outer ring, a balance inner core arranged inside the balance outer ring and three force measuring beams connected between the balance outer ring and the balance inner core, the three force measuring beams are uniformly arranged along the circumference of the balance inner core, the force measuring beams can produce elastic deformation under the action of external force, and are pasted with sensitive elements for sensing six-component force from the outside; the wing connecting plate is fixedly connected with the wing, the electric duct connecting plate is arranged above the wing connecting plate, the electric duct is fixed on the top of the electric duct connecting plate, the force measuring balance is arranged between the wing connecting plate and the electric duct connecting plate, the lower surface of the balance inner core is fixedly connected with the upper surface of the wing connecting plate, and the upper surface of the balance outer ring is fixedly connected with the lower surface of the electric duct connecting plate.

[0010] Preferably, the three force beams are respectively a first force beam, a second force beam and a third force beam, wherein the first force beam is pasted with strain gauges 14-17, which are symmetrically pasted on two side surfaces of the first force beam to form an electric bridge M1; the first force beam is also pasted with strain gauges 26-29, which are symmetrically pasted on upper and lower end surfaces of the first force beam to form an electric bridge M4; the second force beam is pasted with strain gauges 18-21, which are symmetrically pasted on two side surfaces of the second force beam to form an electric bridge M2; the second force beam is also pasted with strain gauges 30-33, which are symmetrically pasted on upper and lower end surfaces of the second force beam to form an electric bridge M5; the third force beam is pasted with strain gauges 22-25, which are symmetrically pasted on two side surfaces of the third force beam to form an electric bridge M3; the third force beam is also pasted with strain gauges 34-37, which are symmetrically pasted on upper and lower end surfaces of the first force beam to form an electric bridge M6; the electric bridges M1, M2 and M3 can measure the yawing moment, tension or resistance and side force of the electric duct through addition and subtraction operation; the electric bridges M4, M5 and M6 can measure the lift, torque and pitching moment of the electric duct through addition and subtraction operation.

[0011] Preferably, the balance outer ring, the balance inner core and the force beam are integrally formed.

[0012] Preferably, the balance inner core is provided with a positioning protrusion, and the wing connecting plate is provided with a positioning opening matched with the positioning protrusion; the balance inner core is fixedly connected with the wing connecting plate through screws.

[0013] Preferably, the balance outer ring and the electric duct connecting plate are positioned through a positioning pin; the balance outer ring and the electric duct connecting plate are fixedly connected through screws.

[0014] Preferably, the electric duct connecting plate and the wing connecting plate are both provided with wiring holes, and the electric duct and the wing are both provided with wiring channels.

[0015] Preferably, the distributed electric duct component wind tunnel test force measuring system further comprises a balance calibration structure, the balance calibration structure comprises a calibration support, a calibration fixing part, a calibration measuring part and a calibration transition part, one end of the calibration support is connected with a support of a balance calibration device, the other end is detachably connected with the calibration fixing part, the calibration fixing part is detachably connected with the balance inner core, the calibration measuring part is detachably connected with the balance outer ring, one end of the calibration transition part is detachably connected with the calibration measuring part, and the other end is provided with a tapered part matched with a tapered hole in a loading sleeve of the balance calibration device.

[0016] Preferably, the calibration struts are connected to the support of the balance calibration device, the calibration struts are connected to the calibration fixing members, the calibration fixing members are connected to the inner core of the balance, the calibration measuring members are connected to the outer ring of the balance, and the calibration transition members are connected to the calibration measuring members by screws.

[0017] Compared with the prior art, the present application has the following advantages:

[0018] 1. The distributed electric duct component wind tunnel test force measurement system of the present application ingeniously integrates multiple force balance units into the wing due to their small size and large stiffness, thereby solving the problem of conventional balance units that are too large to be used for distributed measurement of multiple electric duct aerodynamic forces. Through rational design and arrangement of the wing, fairing, electric duct, force balance unit, electric duct connecting plate, and wing connecting plate, the spatial limitations of the model are greatly reduced, and the problem of wind tunnel model balance structure design caused by insufficient internal space of the wing and difficulty in overall arrangement of the electric duct component force measurement system is solved.

[0019] 2. The distributed electric duct component wind tunnel test force measurement system of the present application is simple and practical, and its structure has sufficient strength and stiffness to meet the requirements of wind tunnel tests. It can assist in the design and integration of distributed electric propulsion systems and accurately obtain aerodynamic force data of electric ducts under different operating conditions, providing reliable basis for aerodynamic design and optimization. It plays an important role in improving the applicability and reliability of electric duct component test experiments and has a very broad application prospect.

[0020] 3. In the distributed electric duct component wind tunnel test force measurement system of the present application, the three force beams of the force balance unit are wrapped by the outer ring to form a shielding space, which can avoid electromagnetic interference of the electric duct motor and properly solve the problem of electromagnetic interference of the electric duct motor.

[0021] 4. The present application ingeniously obtains six-component aerodynamic forces of the electric duct by adding and subtracting six groups of full-bridge circuits, and the patch form is simple. By setting the balance calibration structure, the calibration connection of the force balance unit in the present application is converted into the cone connection form used by the conventional balance calibration device, so that the conventional balance calibration device can be applied to the calibration of the force balance unit in the present application, facilitating subsequent balance calibration work, forming a closed loop of balance design and calibration, and solving the problem that the conventional balance pasting calibration device is not suitable for the force balance unit in the present application. BRIEF DESCRIPTION OF DRAWINGS

[0022] Figure 1 FIG. 1 is a front view of a distributed electric duct component wind tunnel test force measurement system according to the present application;

[0023] Figure 2 FIG. 1 is a front view of a distributed electric duct component wind tunnel test force measurement system according to the present application;

[0024] Figure 3 is a front view of the force balance in the present application;

[0025] Figure 4 is a top view of the force balance in the present application;

[0026] Figure 5 is a bottom view of the force balance in the present application;

[0027] Figure 6 is a top view of the strain element arrangement of the force balance in the present application;

[0028] Figure 7 is a bottom view of the strain element arrangement of the force balance in the present application;

[0029] Figure 8 is a bridge circuit diagram of the force balance in the present application;

[0030] Figure 9 is a structural schematic diagram of the balance calibration structure in the present application.

[0031] BRIEF DESCRIPTION OF DRAWINGS

[0032] 1 - fairing, 2 - electric duct, 3 - wing, 4 - electric duct connecting plate, 5 - force balance, 6 - wing connecting plate, 7 - calibration support rod, 8 - calibration fixing piece, 9 - calibration measuring piece, 10 - calibration transition piece, 11 - balance outer ring, 12 - force beam, 13 - balance inner core. DETAILED DESCRIPTION

[0033] In order to make the objects, technical solutions and advantages of the present application clearer and more comprehensible, the present application will be described below through specific embodiments shown in the drawings. However, it should be understood that these descriptions are only exemplary and are not intended to limit the scope of the present application. In addition, in the following description, the description of known structures and technologies is omitted to avoid unnecessary confusion of the concept of the present application.

[0034] The connection mentioned in the present application is divided into fixed connection and detachable connection. The fixed connection (i.e. non-detachable connection) includes but is not limited to conventional fixed connection modes such as flange connection, rivet connection, adhesive connection and welding connection, and the detachable connection includes but is not limited to conventional detachable modes such as threaded connection, buckle connection, pin connection and hinge connection. When the specific connection mode is not specifically limited, at least one connection mode can be found in the existing connection mode to realize the function, and the person skilled in the art can select it according to the needs. For example: the fixed connection selects welding connection, and the detachable connection selects hinge connection.

[0035] In the present application, unless otherwise explicitly specified and limited, the terms "mounting", "connecting", "connecting", "fixing" and the like should be understood in a broad sense, for example, it can be fixedly connected, or it can be detachably connected, or it can be integrated; it can be mechanically connected, or it can be electrically connected; it can be directly connected, or it can be indirectly connected through an intermediate medium; it can be the internal communication of two elements or the interaction relationship between two elements. For those skilled in the art, the specific meaning of the above terms in the present application can be understood according to the specific circumstances.

[0036] Please refer to Figure 1 and Figure 2 A distributed electric duct component wind tunnel test force measurement system, comprising a fairing 1, a wing 3, a plurality of electric ducts 2, a plurality of electric duct connecting plates 4, a plurality of wing connecting plates 6 and a plurality of force measuring balances 5, the plurality of electric ducts 2 are distributed on the wing 3, the fairing 1 is arranged above the plurality of electric ducts 2 and connected with the wing 3. Among them, the number of electric ducts 2, electric duct connecting plates 4, wing connecting plates 6 and force measuring balances 5 is the same, in this embodiment, the number of the above components is set to five as an example, one electric duct 2 corresponds to one electric duct connecting plate 4, one wing connecting plate 6 and one force measuring balance 5. The fairing 1 is only connected with the wing 3, and has no contact with each electric duct 2, and each electric duct 2 also has no contact with each other.

[0037] It should be noted that the electric duct 2 described in this embodiment includes motor, propeller, propeller hoop, propeller cap, rear fairing and other components. The electric duct 2 in this embodiment is only connected with the corresponding electric duct connecting plate 4, and has no contact with the wing 3, the fairing 1 and other components.

[0038] Please refer to Figure 3 , Figure 4 and Figure 5, the force measuring platform 5 comprises a platform outer ring 11, a platform inner core 13 arranged inside the platform outer ring 11, and three force measuring beams 12 connected between the platform outer ring 11 and the platform inner core 13, the platform outer ring 11, the platform inner core 13 and the force measuring beams 12 are preferably integrally formed. The structure of the force measuring platform 5 in this embodiment has the characteristics of small size and large rigidity, and the three force measuring beams 12 are wrapped by the platform outer ring 11 to form a shielding space, which can avoid electromagnetic interference of the electric duct motor. The force measuring beam 12 in this embodiment has a T-shaped horizontal cross section, the three force measuring beams 12 are evenly arranged along the circumference of the platform inner core 13, the force measuring beam 12 can produce elastic deformation under the action of external force, and a sensitive element is pasted for sensing six-component force from the outside; the wing connecting plate 6 is fixedly connected with the wing 3, the electric duct connecting plate 4 is arranged above the wing connecting plate 6, the electric duct 2 is fixed on the top of the electric duct connecting plate 4, the wing connecting plate 6 and the wing 3, and the electric duct 2 and the electric duct connecting plate 4 can be connected by screws or bolts, the force measuring platform 5 is arranged between the wing connecting plate 6 and the electric duct connecting plate 4, the platform inner core 13 is a fixed part, and its lower surface is fixedly connected with the upper surface of the wing connecting plate 6, the platform outer ring 11 is a measuring part, and its upper surface is fixedly connected with the lower surface of the electric duct connecting plate 4.

[0039] The distributed electric duct component wind tunnel test force measuring system of this embodiment ingeniously integrates multiple force measuring platforms 5 into the wing 3 by using the characteristics of small size and large rigidity, solving the practical problem that the size of the conventional platform is too large to measure the aerodynamic force of multiple electric ducts in a distributed manner. Through the reasonable design and arrangement of the wing 3, the fairing 1, the electric duct 2, the force measuring platform 5, the electric duct connecting plate 4 and the wing connecting plate 6, the space limitation of the model is greatly reduced, so that the force measuring system can solve the problem of wind tunnel model platform structure design caused by the difficulty of overall arrangement of the electric duct component force measuring system due to insufficient internal space of the wing.

[0040] Please refer to Figure 6 、 Figure 7 and Figure 8The three force beams 12 in the embodiment are respectively a first force beam, a second force beam and a third force beam. The first force beam is pasted with strain gauges 14-17, which are symmetrically pasted on two side surfaces of the first force beam to form an electric bridge M1. The first force beam is also pasted with strain gauges 26-29, which are symmetrically pasted on upper and lower end surfaces of the first force beam to form an electric bridge M4. The second force beam is pasted with strain gauges 18-21, which are symmetrically pasted on two side surfaces of the second force beam to form an electric bridge M2. The second force beam is also pasted with strain gauges 30-33, which are symmetrically pasted on upper and lower end surfaces of the second force beam to form an electric bridge M5. The third force beam is pasted with strain gauges 22-25, which are symmetrically pasted on two side surfaces of the third force beam to form an electric bridge M3. The third force beam is also pasted with strain gauges 34-37, which are symmetrically pasted on upper and lower end surfaces of the first force beam to form an electric bridge M6. The electric bridges M1, M2 and M3 can measure the yaw moment, tension or resistance and side force of the electric duct 2 through addition and subtraction operation. The electric bridges M4, M5 and M6 can measure the lift, torque and pitching moment of the electric duct 2 through addition and subtraction operation.

[0041] In the embodiment, the force balance 5 uses 24 strain gauges to form six Wheatstone bridges for signal measurement, and the strain gauges are simply pasted. The strain gauge 14 and the strain gauge 15 form a pair of bridge arms, the strain gauge 16 and the strain gauge 17 form a pair of bridge arms, the strain gauge 14 and the strain gauge 16 form a connected bridge arm, and the strain gauge 15 and the strain gauge 17 form a connected bridge arm. Each bridge arm is connected into a first full-bridge circuit through an enameled wire. Similarly, the strain gauges 18-21 form a second full-bridge circuit, and the strain gauges 22-25 form a third full-bridge circuit. The strain gauge 26 and the strain gauge 27 form a pair of bridge arms, the strain gauge 28 and the strain gauge 29 form a pair of bridge arms, the strain gauge 26 and the strain gauge 28 form a connected bridge arm, and the strain gauge 27 and the strain gauge 29 form a connected bridge arm. Each bridge arm is connected into a fourth full-bridge circuit through an enameled wire. Similarly, the strain gauges 30-33 form a second full-bridge circuit, and the strain gauges 34-37 form a third full-bridge circuit. The electric bridges M1, M2 and M3 can measure the yaw moment, tension or resistance and side force of the electric duct 2 through addition and subtraction operation. The electric bridges M4, M5 and M6 can measure the lift, torque and pitching moment of the electric duct 2 through addition and subtraction operation.

[0042] Please refer to Figure 3 , Figure 4 and Figure 5In some optional embodiments, the bottom of the inner core 13 of the balance is provided with a positioning protrusion, and the wing connecting plate 6 is provided with a positioning opening matched with the positioning protrusion; the inner core 13 of the balance is fixedly connected with the wing connecting plate 6 through screws. Specifically, the positioning buckle and the positioning protrusion can both be square. During installation, the positioning protrusion at the bottom of the inner core 13 of the balance is inserted into the positioning opening on the wing connecting plate 6. After positioning is completed, the inner core 13 of the balance and the wing connecting plate 6 are fixed through six screws.

[0043] The outer ring 11 of the balance is positioned with the electric duct connecting plate 4 through a positioning pin, and the outer ring 11 of the balance is fixedly connected with the electric duct connecting plate 4 through screws. Specifically, the upper end surface of the outer ring 11 of the balance and the electric duct connecting plate 4 are both provided with a positioning pin hole. During installation, the outer ring 11 of the balance and the electric duct connecting plate 4 are positioned through a positioning pin, and then the outer ring 11 of the balance and the electric duct connecting plate 4 are fixed through six screws.

[0044] In some optional embodiments, the electric duct connecting plate 4 and the wing connecting plate 6 are both provided with a wiring hole, and the electric duct 2 and the wing 3 are both provided with a wiring channel, so as to facilitate wiring. Five groups of cables of the electric duct 2 are respectively led out from the wiring hole reserved in the corresponding electric duct connecting plate 4, and the load cell 5 is led out from the side surface of the outer ring 11 of the balance. In order to ensure the electromagnetic shielding effect, the cable of the load cell 5 and the cable of the electric duct 2 are respectively led into different areas of the wing 3 through different wiring channels.

[0045] The load cell 5 needs to complete balance calibration before being applied to wind tunnel test. Since the conventional balance calibration device cannot be applied to the load cell 5 in the embodiment, the distributed electric duct component wind tunnel test load measuring system in the embodiment further includes a balance calibration structure. The structure converts the calibration connection of the load cell 5 in the embodiment into a taper connection form adopted by the conventional balance calibration device, so that the conventional balance calibration device can be applied to the calibration of the load cell 5 in the embodiment, and the subsequent balance calibration work is facilitated.

[0046] Please refer to Figure 9The balance calibration structure comprises a calibration support 7, a calibration fixing part 8, a calibration measuring part 9 and a calibration transition part 10. One end of the calibration support 7 is connected with a support of a balance calibration device, and the other end is detachably connected with the calibration fixing part 8. The calibration fixing part 8 is detachably connected with the inner core 13 of the balance. The calibration measuring part 9 is detachably connected with the outer ring 11 of the balance. One end of the calibration transition part 10 is detachably connected with the calibration measuring part 9, and the other end is provided with a taper part matched with a taper hole of a loading sleeve of the balance calibration device. The calibration support 7, the calibration support 7 and the calibration fixing part 8, the calibration fixing part 8 and the inner core 13 of the balance, the calibration measuring part 9 and the outer ring 11 of the balance, and the calibration transition part 10 and the calibration measuring part 9 are all connected by screws or bolts. It should be noted that those skilled in the art can completely obtain the specific arrangement of the above-mentioned connection by screws or bolts according to the need, and therefore the embodiment will not be described again.

[0047] In use, the calibration fixing part 8 is connected with the inner core 13 of the balance, the calibration measuring part 9 is connected with the outer ring 11 of the balance, and the calibration fixing part 8 and the calibration measuring part 9 are respectively located at two ends of the axial direction of the force balance 5. Then one end of the calibration support 7 is connected with the support of the conventional balance calibration device, the other end is connected with the calibration fixing part 8, the calibration transition part 10 is connected with the calibration measuring part 9, and finally the taper hole of the loading sleeve of the conventional balance calibration device is connected with the taper part of the calibration transition part 10. After locking by the locking part, the calibration work can be started.

Claims

1. A distributed electric duct component wind tunnel test force measurement system, characterized by, The electric duct (2) is distributedly arranged on the wing (3), the fairing (1) is arranged above the electric duct (2) and is connected with the wing (3); The force balance (5) comprises an outer ring (11), an inner core (13) arranged inside the outer ring (11), and three force beams (12) connected between the outer ring (11) and the inner core (13), the three force beams (12) are uniformly arranged along the circumference of the inner core (13), the force beam (12) can be elastically deformed under the action of an external force, and a sensitive element is pasted for sensing six-component force; the wing connecting plate (6) is fixedly connected with the wing (3), the electric duct connecting plate (4) is arranged above the wing connecting plate (6), the electric duct (2) is fixed on the top of the electric duct connecting plate (4), the force balance (5) is arranged between the wing connecting plate (6) and the electric duct connecting plate (4), the lower surface of the inner core (13) is fixedly connected with the upper surface of the wing connecting plate (6), and the upper surface of the outer ring (11) is fixedly connected with the lower surface of the electric duct connecting plate (4).

2. The distributed electric duct component wind tunnel test force measurement system of claim 1, wherein, The three force beams (12) are respectively a first force beam, a second force beam and a third force beam, wherein: The first force beam is pasted with strain gauges 14-17, the strain gauges 14-17 are symmetrically pasted on the two side surfaces of the first force beam to form an electric bridge M1; the first force beam is also pasted with strain gauges 26-29, the strain gauges 26-29 are symmetrically pasted on the upper and lower end surfaces of the first force beam to form an electric bridge M4; The second force beam is pasted with strain gauges 18-21, the strain gauges 18-21 are symmetrically pasted on the two side surfaces of the second force beam to form an electric bridge M2; the second force beam is also pasted with strain gauges 30-33, the strain gauges 30-33 are symmetrically pasted on the upper and lower end surfaces of the second force beam to form an electric bridge M5; The third force beam is pasted with strain gauges 22-25, the strain gauges 22-25 are symmetrically pasted on the two side surfaces of the third force beam to form an electric bridge M3; the third force beam is also pasted with strain gauges 34-37, the strain gauges 34-37 are symmetrically pasted on the upper and lower end surfaces of the first force beam to form an electric bridge M6; The electric bridge M1, the electric bridge M2 and the electric bridge M3 can measure the yaw moment, the tension or the resistance and the side force of the electric duct (2) through addition and subtraction operation; the electric bridge M4, the electric bridge M5 and the electric bridge M6 can measure the lift, the torque and the pitch moment of the electric duct (2) through addition and subtraction operation.

3. The distributed electric duct component wind tunnel test force measurement system of claim 1, wherein: The outer ring (11), the inner core (13) and the force beam (12) are an integral whole and are integrally processed.

4. The distributed electric duct component wind tunnel test force measurement system of claim 1, wherein: The bottom of the balance inner core (13) is provided with a positioning protrusion, and the wing connecting plate (6) is provided with a positioning opening matched with the positioning protrusion; the balance inner core (13) is fixedly connected with the wing connecting plate (6) through screws.

5. The distributed electric duct component wind tunnel test force measurement system of claim 1, wherein: The balance outer ring (11) and the electric duct connecting plate (4) are positioned through positioning pins; the balance outer ring (11) and the electric duct connecting plate (4) are fixedly connected through screws.

6. The distributed electric duct component wind tunnel test force measurement system of claim 1, wherein: The electric duct connecting plate (4) and the wing connecting plate (6) are both provided with wiring holes, and the electric duct (2) and the wing (3) are both provided with wiring channels.

7. The distributed electric duct component wind tunnel test force measurement system of claim 1, wherein: The balance calibration structure comprises a calibration supporting rod (7), a calibration fixing piece (8), a calibration measuring piece (9) and a calibration transition piece (10), one end of the calibration supporting rod (7) is connected with a support of a balance calibration device, the other end is detachably connected with the calibration fixing piece (8), the calibration fixing piece (8) is detachably connected with the balance inner core (13), the calibration measuring piece (9) is detachably connected with the balance outer ring (11), and one end of the calibration transition piece (10) is detachably connected with the calibration measuring piece (9), and the other end is provided with a tapered portion matched with a tapered hole in a loading sleeve of the balance calibration device.

8. A distributed electric duct component wind tunnel test force measurement system according to claim 7, characterized in that: The calibration supporting rod (7) and the support of the balance calibration device, the calibration supporting rod (7) and the calibration fixing piece (8), the calibration fixing piece (8) and the balance inner core (13), the calibration measuring piece (9) and the balance outer ring (11), and the calibration transition piece (10) and the calibration measuring piece (9) are all connected through screws.

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