Wing lift force simulation device

Abstract

The utility model provides a wing lift force simulation device. The wing lift force simulation device comprises a wing structure, a balancing device, a fan device and a base, the balancing device is a parallelogram connecting rod mechanism and is provided with a fixed supporting piece and a movable vertical connecting rod, and the vertical connecting rod is installed on the opposite sides of a quadrangle of the supporting piece. Wherein the top end of the vertical connecting rod is detachably connected with the upper convex surface or the lower plane of the wing structure, and a fixed included angle is formed between the chord line of the wing structure and the vertical connecting rod; the fan device and the balancing device are detachably installed on the base, and an air outlet of the fan device right faces the wing structure. By using the wing lift force simulation device, a user can visually observe the positive / negative lift force action condition of the wing at a specific attack angle and the influence of the change of the external flow field parameters of the wing boundary layer on the wing lift force.

Description

Technical Field

[0001] The utility model relates to the technical field of fluid mechanics simulation, in particular to a wing lift simulation device. Background Art

[0002] The reason why modern fixed-wing aircraft can take to the sky is mainly due to the lift generated by the wings of the "upper convex and lower flat airfoil structure". This lift comes from the air pressure difference above and below the wing. Specifically, when the aircraft moves forward relative to the air flow field, the airflow bypasses the lower plane or the upper convex surface from the leading edge of the wing to the trailing edge of the wing. At this time, because the distance the airflow takes around the lower plane is shorter than the distance around the upper convex surface, the overall air flow rate of the lower plane of the wing is lower than the overall air flow rate of the upper convex surface during the same period of time. Based on Bernoulli's principle, when the fluid density remains unchanged and the changes in gravitational acceleration and altitude are negligible, the pressure at the location with lower air flow rate is greater. At this time, the overall air pressure on the lower plane of the wing is greater than the overall air pressure on the upper convex surface, thereby generating lift.

[0003] However, for beginners, the theory of Bernoulli's principle is difficult to learn, which can easily undermine their confidence in exploring the field of aviation. Utility Model Content

[0004] The present invention addresses the above-mentioned deficiencies and shortcomings by providing a wing lift simulation device. By using the wing lift simulation device, users can visually observe the forward and reverse lift effects of a wing at a specific angle of attack, as well as the effects of changes in flow field parameters outside the wing boundary layer on wing lift.

[0005] According to a first aspect, the present application provides a wing lift simulation device, comprising a wing structure, a balancing device, a fan device, and a base;

[0006] The balancing device is a parallelogram linkage mechanism, provided with a fixed support member and a movable vertical link. The vertical link is mounted on opposite sides of the support member. The top end of the vertical link is detachably connected to the upper convex surface or the lower flat surface of the wing structure. The chord line of the wing structure forms a fixed angle with the vertical link.

[0007] The fan device and the balancing device are detachably mounted on the base, and the air outlet of the fan device faces the wing structure to simulate the positive / negative lift effect of the wing at a specific angle of attack.

[0008] In some embodiments, the wing lift simulation device further comprises a force and tilt sensor, and the balancing device further comprises a long arm lever and a lower short rod;

[0009] The upper end point of the support is rotatably connected to the middle fulcrum of the long arm lever, and the lower end point is rotatably connected to the first end point of the lower short rod. The support is detachably mounted on the base, and the support is also equipped with an angle plate.

[0010] The first end point of the long arm lever and the second end point of the lower short rod are rotatably connected to the upper end point and the lower end point of the vertical connecting rod respectively;

[0011] The force and tilt sensor is installed at the upper end of the support and is used to measure the angle between the pointer in the angle disk and the vertical direction to reflect the current lift of the wing structure.

[0012] In some embodiments, the line connecting the upper and lower endpoints of the support member is set to a vertical state, and the support member serves as a vertical fixed rod in the parallelogram linkage mechanism, so that the vertical connecting rod is always in a vertical state;

[0013] The chord line of the wing structure is set to a state perpendicular to the vertical connecting rod, so that the chord line of the wing structure is always in a horizontal state;

[0014] The air outlet of the fan device is installed horizontally on the base, so that the angle of attack of the wing structure is always zero degrees;

[0015] If the lower plane of the wing structure is detachably connected to the top end of the vertical connecting rod, the lift direction generated by the wing structure is vertically upward; if the upper convex surface of the wing structure is detachably connected to the top end of the vertical connecting rod, the lift direction generated by the wing structure is vertically downward, which is used to simulate the positive / negative lift effect of the wing at zero degree angle of attack.

[0016] In some embodiments, the wing lift simulation device further includes a wind speed sensor, which is mounted on the base and disposed between the wing structure and the fan device;

[0017] The wind speed sensor is used to measure the gas flow rate generated by the fan device.

[0018] In some embodiments, a pressure differential sensor is installed inside the wing structure. The pressure differential sensor is provided with a first measuring port and a second measuring port. The first measuring port and the second measuring port are respectively installed at specific positions on the upper convex surface and the lower plane of the wing structure. The pressure differential sensor is used to measure the pressure difference between the upper surface and the lower surface of the wing structure.

[0019] In some embodiments, the wing lift simulation device further includes a wireless transmission module;

[0020] The wireless transmitter module is installed at the upper end of the support and is connected to the force and tilt sensor, wind speed sensor and pressure difference sensor respectively;

[0021] The wireless transmission module is used to send the measurement data from each sensor to the user terminal.

[0022] In some embodiments, the support member is further installed with an angle dial, which is used to display the current horizontal tilt angle of the long arm lever.

[0023] In some embodiments, the force and tilt sensor includes a force sensor and a tilt sensor, and a counterweight is provided at the second end of the long arm lever, the counterweight being used to balance the vertical link at the first end of the long arm lever, the entire weight of the wing structure, and part of the weight of the lower short rod;

[0024] When the force sensor is turned on, the force and tilt sensor is used to measure the component of the weight of the counterweight along the direction of the pointer, or when the tilt sensor is turned on, the force and tilt sensor is used to measure the angle between the pointer in the angle disk and the vertical direction to reflect the current lift of the wing structure.

[0025] Among them, if the force sensor and the inclination sensor are started separately, the force and inclination sensor is a sensor that can only measure the component of the gravity of the counterweight along the pointer direction, or can only measure the angle between the pointer in the angle disk and the vertical direction.

[0026] In some embodiments, the wing structure is a plastic skin-frame airfoil structure.

[0027] In some embodiments, the wing structure is an integral foamed polypropylene airfoil structure, or an integral rubber-plastic foamed airfoil structure.

[0028] In some embodiments of the present disclosure, a user first secures a balancing device of a wing lift simulator to a base. The balancing device is a parallelogram linkage mechanism, and the user secures a support member to the base, serving as the sole fixed rod in the parallelogram linkage mechanism. At this point, the line connecting the upper and lower endpoints of the support member forms a fixed first angle with the horizontal line, which can be a 90-degree vertical angle. Furthermore, in the parallelogram linkage mechanism, the vertical connecting rods located on opposite sides of the support member also form a fixed first angle with the horizontal line. Furthermore, because the wing structure is mounted at the top of the vertical connecting rods, the chord line of the wing structure forms a fixed second angle with the vertical connecting rods, which can be a 90-degree vertical angle. Therefore, if both the first and second angles are set to 90 degrees, the chord line of the wing structure is constantly parallel to the horizontal line. The user then secures the fan device to the base, with the air outlet of the fan device facing the wing structure. When the user turns on the fan device, the above-mentioned wing structure will move along a specific circular trajectory under the action of the wind, and eventually the wing structure will stop at a certain position at a specific angle of attack, and the angle of attack remains constant. The angle of attack of the wing refers to the angle between the chord line and the relative wind direction. When the wing produces a displacement perpendicular to the wind direction of the external flow field (for example, when the wing moves up / down), the relative wind direction of the wing is generally unstable, and the angle of attack is also constant. Assuming that the outlet gas flow direction of the fan device is always parallel to the horizontal line, the first angle and the second angle are both set to 90 degrees. When the user turns on the fan device, the wing structure will move along a specific circular trajectory and eventually stop at a certain position at an angle of attack of 0 degrees. In this way, it is possible to visually observe the positive / negative lift effect of the wing at a specific angle of attack. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 This is a schematic diagram of the installation of a wing lift simulation device when the wing is installed in a forward direction in one or more embodiments of the present invention;

[0030] Figure 2 This is a schematic diagram of the installation of a wing lift simulation device when the wing is reversely installed in one or more embodiments of the present invention;

[0031] Figure 3 A schematic diagram of the installation of a differential pressure sensor for a wing structure in one or more embodiments of the present invention;

[0032] Figure 4 A schematic structural diagram of a balancing device and its supporting member in one or more embodiments of the present invention;

[0033] Figure 5 A schematic diagram of an upper convex surface structure of a wing in one or more embodiments of the present invention;

[0034] Figure 6 The figure is a schematic diagram of the lower plane structure of a wing in one or more embodiments of the present invention. DETAILED DESCRIPTION

[0035] In order to make the purpose, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0036] It should be noted that when a part or component is considered to be "connected to," "located on," or "assembled on" another part or component, it can be directly disposed on the other part or component or there may be a central part or component. The terms "left," "right," "upper," "lower," and similar expressions used herein are for illustrative purposes only.

[0037] According to a first aspect, the present application provides a wing lift simulation device, such as Figure 1-4 As shown, it includes a wing structure 1, a balancing device 2, a fan device 3 and a base 4;

[0038] The balancing device 2 is a parallelogram linkage mechanism, provided with a fixed support member 24 and a movable vertical link 22. The vertical link 22 is mounted on the opposite side of the quadrilateral of the support member 24. The top end of the vertical link 22 is detachably connected to the upper convex surface or the lower flat surface of the wing structure 1. The chord line of the wing structure 1 forms a fixed angle with the vertical link 22.

[0039] The fan device 3 and the balancing device 2 are detachably mounted on the base 4. The air outlet of the fan device 3 faces the wing structure 1 to simulate the positive and negative lift effects of the wing at a specific angle of attack. The angle of attack refers to the angle between the chord line of the wing and the direction of the wind.

[0040] Specifically, the balancing device 2 is a parallelogram linkage mechanism with the support member 24 as a fixed link and the vertical link 22 as the opposite side of the quadrilateral of the support member 24. In this linkage mechanism, the vertical link 22 is always parallel to the line connecting the upper end point 2411 and the lower end point 2416 of the support member 24. The bottom of the support member 24 can be detachably mounted on the base 4 through the fixing holes 2417 and 2418. Figure 3 As shown, the actual motion trajectory of the upper endpoint 222 of the vertical link 22 is trace b, while the motion trajectory of the top point 223 of the vertical link is trace a. Between trace a and trace b, no matter where the vertical link 22 moves, the line connecting the upper endpoint 222 and the top point 223 is always parallel to the line connecting the upper endpoint 2411 and the lower endpoint 2416 of the support member 24.

[0041] Among them, such as Figure 1-2 As shown, if the top end of the vertical link 22 is detachably connected to the upper convex surface or the lower plane of the wing structure 1. Figure 1-2 The x direction and the y direction are marked in FIG, wherein the x direction indicates the direction of the chord line, and the y direction indicates the direction of the vertical connecting rod 22. Under normal circumstances, the chord line of the wing structure 1 is horizontal, such as Figure 2 As shown. Under normal conditions, the y-direction is vertical, i.e., perpendicular to the horizontal. Therefore, the fixed angle formed by the chord line and the vertical connecting rod 22 is specifically the angle between the x-direction and the y-direction. Furthermore, assuming the z-direction is the outlet wind direction of the fan device 3, the angle of attack of the wing structure 1 is the angle between the x-direction and the opposite z-direction, where this angle of attack is generally acute.

[0042] For example, the user sequentially installs the balancing device 2 and the fan device 3 onto the base 4. At this point, the line connecting the upper endpoint 2411 and the lower endpoint 2416 of the support member 24 forms a fixed first angle with the horizontal line. In the parallelogram linkage mechanism, the vertical connecting rod 22 located on the opposite side of the quadrilateral of the support member 24 also forms a constant first angle with the horizontal line, that is, the y-direction forms a constant first angle with the horizontal line. Furthermore, because the wing structure 1 is mounted on the top of the vertical connecting rod 22, the angle between the x-direction and the y-direction forms a fixed second angle. When the user turns on the fan device 3, it generates wind in the z-direction. Under the influence of the wind, the wing structure 1 moves along a specific circular trajectory, ultimately coming to rest at a specific angle of attack. The angle of attack of the wing structure 1 refers to the angle between the x-direction and the opposite z-direction. In this way, the forward and reverse lift effects of the wing at a specific angle of attack can be visually observed.

[0043] In some embodiments, as Figure 1-4 As shown, the wing lift simulation device further includes a force and tilt sensor 7, and the balancing device 2 further includes a long arm lever 21 and a lower short rod 23;

[0044] The upper end point 2411 of the support member 24 is rotatably connected to the middle fulcrum of the long arm lever 21, and the lower end point 2416 is rotatably connected to the first end point of the lower short rod 23. The support member 24 is detachably mounted on the base 4. The support member 24 is also equipped with an angle plate 6.

[0045] The first end point of the long arm lever 21 and the second end point of the lower short rod 23 are rotatably connected to the upper end point and the lower end point of the vertical connecting rod 22 respectively;

[0046] The force and tilt sensor 7 is installed at the upper end of the support 24 and is used to measure the angle between the pointer 61 in the angle plate 6 and the vertical direction (ie, the direction of gravity) to reflect the current lift of the wing structure 1.

[0047] Specifically, the long arm lever 21 and the lower short rod 23 are respectively used as connecting rods connected to the two ends of the support member 24. In the parallelogram linkage mechanism, the long arm lever 21 and the lower short rod 23 are always parallel, and the line connecting the upper end point 2411 and the lower end point 2416 of the support member 24 is always parallel to the vertical connecting rod 22. Figure 4 As shown, the actual motion trajectory of the upper endpoint 222 of the vertical connecting rod 22 is trace b, while the motion trajectory of the lower endpoint 221 of the vertical connecting rod is trace c. Trajectory b is a circular arc trace drawn with the upper endpoint 2411 of the support member 24 as the center and the distance from the upper endpoint 2411 to the upper endpoint 222 as the radius. Trajectory c is a circular arc trace drawn with the lower endpoint 2416 of the support member 24 as the center and the distance from the lower endpoint 2416 to the lower endpoint 221 as the radius. Furthermore, since the distance from the upper endpoint 2411 to the upper endpoint 222 is the same as the distance from the lower endpoint 2416 to the lower endpoint 221, the radii of the two circles are equal and the length of the radii remains constant. Based on the above known conditions, it can be inferred that the line connecting the upper endpoint 2411 to the lower endpoint 2416 is always parallel to the line connecting the upper endpoint 222 to the lower endpoint 221.

[0048] For example, when the fan device 3 is turned on and generates wind in the z direction, the above-mentioned wing structure 1 will generate a lift perpendicular to the x direction under the action of the wind. However, since the displacement freedom of the wing structure 1 is limited by the above-mentioned parallelogram linkage mechanism, under the action of the lift, the wing structure 1 can only translate along the positive / negative direction of the above-mentioned trace a, and eventually the wing structure 1 will stop at a certain position of the trace a at a specific angle of attack. Moreover, at this time, the long-arm lever 21 will form a specific inclination angle with the horizontal line, that is, the line connecting the upper end point 2411 to the upper end point 222 will form a specific inclination angle with the horizontal line. The force and inclination sensor 7 allows the user to visually view the inclination angle of the long-arm lever 21, thereby reflecting the positive / negative lift action of the wing at a specific angle of attack.

[0049] In some embodiments, as Figure 1-4 As shown, in a normal state, the line between the upper end point 2411 and the lower end point 2416 of the support member 24 is set to a vertical state, and the vertical connecting rod 22 is in a vertical state;

[0050] The chord line of the wing structure 1 is set to be perpendicular to the vertical connecting rod 22, so that the chord line of the wing structure 1 is always in a horizontal state;

[0051] The air outlet of the fan device 3 is horizontally mounted on the base 4 so that the angle of attack of the wing structure 1 is always zero degrees;

[0052] If the lower plane of the wing structure 1 is detachably connected to the top end of the vertical connecting rod 22, the lift direction generated by the wing structure 1 is vertically upward; if the upper convex surface of the wing structure 1 is detachably connected to the top end of the vertical connecting rod 22, the lift direction generated by the wing structure 1 is vertically downward, which is used to simulate the positive / negative lift effect of the wing at a zero angle of attack.

[0053] For example, in the balancing device 2, it is known that the line connecting the upper endpoint 2411 and the lower endpoint 2416 of the support member 24 forms a fixed first angle with the horizontal line, the y direction is always at the first angle with the horizontal line, the x direction is at a fixed second angle with the y direction, and the wind direction generated by the fan device 3 is z. If the first angle and the second angle are both set to 90 degrees, and the z direction is parallel to the horizontal line, then the chord line of the wing structure 1 is always parallel to the horizontal line. At this time, when the user turns on the fan device 3, the above-mentioned wing structure 1 will translate along the positive / negative direction of the trajectory a under the action of the wind force, and during this period, the wing structure 1 does not produce rolling motion. Ultimately, the wing structure 1 will come to rest at a certain position with a zero angle of attack, that is, the angle between the x direction and the opposite direction of the z direction is zero degrees.

[0054] In some embodiments, as Figure 1-2 As shown, the wing lift simulation device also includes a wind speed sensor 5, which is installed on the base 4 and is arranged between the wing structure 1 and the fan device 3; the wind speed sensor 5 is used to measure the gas flow rate value generated by the fan device 3.

[0055] Specifically, since wind speed sensor 5 is installed away from the boundary layer of wing structure 1, which refers to an extremely thin layer of airflow on the surface of wing structure 1, this airflow layer will rotate along the chord line of wing structure 1 due to the viscosity of the gas itself. Furthermore, the gas velocity distribution within the boundary layer is extremely complex and significantly different from the flow field outside the boundary layer. Therefore, wind speed sensor 5 needs to be installed away from wing structure 1 to avoid measurement interference caused by the presence of the boundary layer of wing structure 1. In this way, the gas velocity outside the boundary layer of wing structure 1 can be measured intuitively and quickly, and feedback can be provided to the user in a timely manner.

[0056] In some embodiments, as Figure 3-6 As shown, a pressure differential sensor 9 is installed inside the wing structure 1. The pressure differential sensor 9 is provided with a first measuring port and a second measuring port. The first measuring port and the second measuring port are respectively installed at specific positions 91 and 92 of the upper convex surface and the lower plane of the wing structure 1, and can measure the pressure difference between the upper surface and the lower surface of the wing structure 1.

[0057] For example, specific position 91 is a measuring hole provided on the upper convex surface of wing structure 1. This upper convex surface of wing structure 1 is also provided with a fixing slot 11, which is used to removably fix the upper convex surface of wing structure 1 above apex point 223. Similarly, the lower surface is provided with a positioning step 12, which is used to removably fix the lower surface of wing structure 1 above apex point 223, allowing wing structure 1 to be flipped and installed interchangeably. Specifically, specific position 92 is a measuring hole provided on one side of positioning step 12.

[0058] In some embodiments, as Figure 1-3 As shown, the wing lift simulation device also includes a wireless transmitter module 8; the wireless transmitter module 8 is mounted on the upper end of the support member 24 and is connected to the force and tilt sensor 7, the wind speed sensor 5, and the pressure differential sensor 9. The wireless transmitter module 8 is used to transmit the measurement data from each sensor to a user terminal. This design allows the user to visually observe the tilt angle of the long-arm lever 21, thereby reflecting the positive and negative lift effects on the wing structure 1. Furthermore, the user can directly view various flow field parameters outside the boundary layer of the wing structure 1, including pressure and flow velocity, through the terminal device.

[0059] In some embodiments, as Figure 1-4 As shown, the pointer 61 in the angle disc 6 is fixedly connected to the long arm lever 21 , and the pointer 61 is perpendicular to the long arm lever 21 , and a counterweight block 611 is provided at the lower end of the pointer 61 .

[0060] Specifically, when the long arm lever 21 swings, the pointer 61 also swings and indicates the current tilt angle of the long arm lever 21 on the angle plate 6. And because of the action of the counterweight 611, the long arm lever 21 and the pointer 61 have a reset tendency.

[0061] Furthermore, the support member 24 is divided into a main member 241 and a sub-cover member 242. The aforementioned angle disc 6 is mounted on the front side of the main member 241. On the rear side of the main member 241, the main member 241 and the sub-cover member 242 are assembled together by inserting the plugs 2412, 2413, 2414, and 2415 of the main member 241 into the sockets 2422, 2423, 2424, and 2425 of the sub-cover member 242, respectively. This design allows users to visually observe the tilt angle of the long-arm lever 21, thereby reflecting the forward and reverse lift effects of the wing, without the need for a terminal device.

[0062] In some embodiments, as Figure 3-4As shown, the force and tilt sensor 9 includes a force sensor and a tilt sensor. A counterweight 211 is provided at the second end of the long arm lever 21. The counterweight 211 is used to balance the vertical connecting rod 22 located at the first end of the long arm lever 21, the entire weight of the wing structure 1, and part of the weight of the lower short rod 23.

[0063] When the mechanical sensor is turned on, the force and inclination sensor 9 is used to measure the component of the gravity of the counterweight 611 along the direction of the pointer 61, or, when the inclination sensor is turned on, the force and inclination sensor 9 is used to measure the angle between the pointer 61 in the angle plate 6 and the vertical direction to reflect the current lift size of the wing structure 1.

[0064] Specifically, if the force sensor and the tilt sensor are activated independently, the force and tilt sensor 9 can only measure the component of the weight of the counterweight 611 in the direction of the pointer 61, or can only measure the angle between the pointer 61 and the vertical direction within the angle dial 6. The fulcrum of the long-arm lever 21 is located at the upper end point 2411 of the support member 24, and the second end of the long-arm lever 21 bears the entire weight of the counterweight 211. The entire weight of the vertical connecting rod 22 and the wing structure 1 acts on the first end of the long-arm lever 21, while a portion of the weight of the lower short rod 23 acts on the lower end point 2416 of the support member 24.

[0065] For example, the user can change the length of the force arm on the long-arm lever 21 on which the counterweight 211 is located by twisting the counterweight 211, thereby achieving counterweight balance at both ends of the long-arm lever 21. The force and inclination sensor can measure the component force of the counterweight block 611 in the direction parallel to the support 24 and the angle relative to the vertical direction of the support 24. The current lift of the wing structure 1 at the first end of the long-arm lever 21 can be calculated based on the force and angle data. The force condition at the second end of the long-arm lever 21 is thus calculated. Through such a design, before the user turns on the fan device 3, the long-arm lever 21 is adjusted to a horizontal initial state by twisting the counterweight 21, and the force condition at the second end of the long-arm lever 21 can be quickly calculated by the mechanical sensor.

[0066] In some embodiments, the wing structure 1 is a plastic skin-frame airfoil structure. Alternatively, in some embodiments, the wing structure 1 is an integrated foamed polypropylene airfoil structure, or an integrated rubber-plastic foamed airfoil structure.

[0067] Specifically, the wing structure 1 can be a lightweight skin-and-frame structure or a one-piece lightweight plastic structure. This design reduces the overall average density of the wing structure 1, thereby reducing its own weight. This allows the wing structure 1 to more quickly translate to a stationary position under the influence of the wind from the fan device 3, thereby improving the efficiency of the wing lift simulation.

[0068] The technical features of the above embodiments can be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0069] The above embodiments merely illustrate several implementations of the present invention. While the descriptions are relatively specific and detailed, they should not be construed as limiting the scope of the utility model patent. It should be noted that a person skilled in the art would be able to make numerous variations and improvements without departing from the concept of the present invention, and these variations and improvements fall within the scope of protection of the present invention. Therefore, the scope of protection of the present utility model patent shall be determined by the appended claims.

Claims

1. A wing lift simulation device, characterized in that: It includes wing structure, balancing device, fan device and base; The balancing device is a parallelogram linkage mechanism, provided with a fixed support member and a movable vertical link, wherein the vertical link is mounted on opposite sides of the quadrilateral of the support member; wherein the top end of the vertical link is detachably connected to the upper convex surface or the lower flat surface of the wing structure, and the chord line of the wing structure forms a fixed angle with the vertical link; The fan device and the balancing device are detachably mounted on the base, and the air outlet of the fan device faces the wing structure.

2. The wing lift simulation device according to claim 1, characterized in that: It also includes a force and tilt sensor, and the balancing device also includes a long arm lever and a lower short rod; The upper end point of the support member is rotatably connected to the middle fulcrum of the long arm lever, and the lower end point is rotatably connected to the first end point of the lower short rod. The support member is detachably mounted on the base, and the support member is also equipped with an angle plate; The first end point of the long arm lever and the second end point of the lower short rod are rotatably connected to the upper end point and the lower end point of the vertical connecting rod respectively; The force and tilt sensor is installed at the upper end of the support member and is used to measure the angle between the pointer in the angle disk and the vertical direction.

3. The wing lift simulation device according to claim 2, characterized in that: The line connecting the upper end point and the lower end point of the support member is set to be in a vertical state, and the support member serves as a vertical fixed rod in the parallelogram linkage mechanism, so that the vertical connecting rod is always in a vertical state; The chord line of the wing structure is set to a state perpendicular to the vertical connecting rod, so that the chord line of the wing structure is always in a horizontal state; The air outlet of the fan device is horizontally mounted on the base so that the angle of attack of the wing structure is constantly zero degrees; If the lower plane of the wing structure is detachably connected to the top end of the vertical connecting rod, the direction of the lift generated by the wing structure is vertically upward; If the upper convex surface of the wing structure is detachably connected to the top end of the vertical connecting rod, the lift direction generated by the wing structure is vertically downward, which is used to simulate the positive / negative lift effect of the wing at zero angle of attack.

4. The wing lift simulation device according to claim 2, characterized in that: Also included is a wind speed sensor, which is mounted on the base and disposed between the wing structure and the fan device; The wind speed sensor is used to measure the gas flow rate value generated by the fan device.

5. The wing lift simulation device according to claim 4, characterized in that: A pressure differential sensor is installed inside the wing structure. The pressure differential sensor is provided with a first measuring port and a second measuring port. The first measuring port and the second measuring port are respectively installed on the upper convex surface and the lower plane of the wing structure.

6. The wing lift simulation device according to claim 5, characterized in that: Also includes a wireless transmitter module; The wireless transmission module is installed at the upper end of the support member and is respectively connected to the force and tilt sensor, the wind speed sensor and the pressure difference sensor; The wireless transmission module is used to send the measurement data from each sensor to the user terminal.

7. The wing lift simulation device according to claim 2, characterized in that: The pointer in the angle disk is fixedly connected to the long-arm lever, and the pointer is perpendicular to the long-arm lever. A counterweight is provided at the lower end of the pointer.

8. The wing lift simulation device according to claim 7, characterized in that: The force and inclination sensor includes a force sensor and an inclination sensor; a counterweight is provided at the second end of the long arm lever, and the counterweight is used to balance the vertical connecting rod located at the first end of the long arm lever, the total weight of the wing structure, and part of the weight of the lower short rod; When the mechanical sensor is turned on, the force and inclination sensor is used to measure the component force of the gravity of the counterweight block along the direction of the pointer, or when the inclination sensor is turned on, the force and inclination sensor is used to measure the angle between the pointer in the angle disk and the vertical direction.

9. The wing lift simulation device according to claim 1, characterized in that: The wing structure is a plastic skin-skeleton airfoil structure.

10. The wing lift simulation device according to claim 1, characterized in that: The wing structure is an integrated foamed polypropylene airfoil structure, or an integrated rubber-plastic foamed airfoil structure.

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