Aerodynamic lift demonstration device

Abstract

The invention relates to the field of teaching experiment instruments, in particular to an aerodynamic lift demonstration device which comprises an annular transparent mounting plate, a transparent top cover arranged on the upper end face of the transparent mounting plate and a model plane, a bottom plate is arranged at the bottom of the transparent mounting plate, and air channels with opposite openings are formed in the two sides of the transparent mounting plate. An air blowing assembly is arranged at an inlet of the air channel, the transparent top cover, the bottom plate and the transparent mounting plate are separated to form an inner cavity, the air channel is communicated with the inner cavity, the model plane is placed in the center of the upper end face of the bottom plate, and a positioning line set is detachably fixed to the upper end face of the model plane. The upper end face and the lower end face of the model airplane are positioned at the same time through the arranged positioning line set, the takeoff principle of the airplane can be stably displayed, and flight control between the whole transparent top cover and the transparent mounting plate can be achieved only by selecting the model airplane with a power structure.

Description

Technical Field

[0001] The invention relates to the field of teaching experimental equipment, in particular to a pneumatic lift demonstration device. Background Art

[0002] With the continuous development of technology, airplane travel has become a common way of travel in residents' daily lives. However, if the understanding of the flight principle of an airplane is only analyzed through theoretical knowledge, it is easy to lead to an incomplete understanding of the flight principle and the corresponding control method. Therefore, in order to facilitate the relevant personnel to learn about the principles and control of airplanes, a series of auxiliary experimental equipment are designed. Conventional auxiliary learning equipment usually includes a simple aircraft lift demonstration device, whose structure is realized by placing a suspended airplane in a transparent ventilation duct. When the airflow intensity in the ventilation duct is large enough, the structural design of the wing can be pushed up by the upper and lower pressure difference of the airflow. This design can only demonstrate the principle that the airplane can fly, but cannot control the flight attitude of the airplane. When performing the demonstration, it cannot fully show the flight attitude of the airplane under different conditions during the flight process for the relevant personnel. In addition, since this demonstration device is usually only designed to be suspended at the top, the airplane is prone to unstable pressure on the wing due to the imbalance of the airflow, which in turn causes the airplane to flip, tilt, and other abnormal take-off states. It is necessary to ensure the accuracy of the position of the airplane before take-off in order to complete the normal flight demonstration. Summary of the invention

[0003] The present invention aims at the deficiencies in the prior art and provides the following technical solutions:

[0004] The aerodynamic lift demonstration device comprises: a transparent mounting plate arranged in a ring shape, a transparent top cover arranged on the upper end surface of the transparent mounting plate, and a model airplane.

[0005] Specifically, a base plate is provided at the bottom of the transparent mounting plate, air ducts with openings facing each other are provided on both sides of the transparent mounting plate, an air blowing assembly is provided at the inlet of the air duct, the transparent top cover is separated from the base plate and the transparent mounting plate to form an inner cavity, the air duct is communicated with the inner cavity, the model aircraft is placed at the center position of the upper end surface of the base plate, a positioning wire group is detachably fixed to the upper end surface of the model aircraft, the other end of the positioning wire group passes through the transparent top cover and is detachably fixed to the lower end surface of the model aircraft, and when the air blowing assembly blows air, the model aircraft rises along the positioning wire group.

[0006] As an improvement of the above technical solution, the surface of the model aircraft is provided with threaded holes, the number of which is twice that of the positioning wire group, and each two threaded holes form a group and are respectively arranged on the upper end face and the lower end face of the model aircraft. A tension sensor is threadedly connected to the threaded hole, and the other end of the tension sensor is fixed to one end of the positioning wire group.

[0007] As an improvement of the above technical solution, the tension sensor is a double-headed columnar external thread tension sensor, the two threaded ends of which respectively pass through the upper end face and the lower end face of the model aircraft, and the two ends of the positioning wire group are respectively fixed to the two threaded ends.

[0008] As an improvement of the above technical solution, the blower assembly includes a fan assembly and a motor. The number of the fan assemblies is several and they are evenly arranged at the entrance of the air duct. The upper end face and the lower end face of the fan assembly are provided with protrusions, and the protrusions penetrate into the inner wall of the air duct. The number of the fan assemblies is the same as that of the motors. The motor is arranged on the upper end face of the air duct, and the power end of the motor penetrates into the interior of the air duct and is detachably fixedly connected to the protrusions.

[0009] As an improvement of the above technical solution, a wire groove and a displacement detection module are opened on the surface of the transparent top cover, the bottom of the wire groove is connected to the accommodating cavity of the positioning wire group, and the displacement detection module is arranged above the wire groove opening.

[0010] As an improvement of the above technical solution, the positioning line group includes a first positioning line and a second positioning line, the number of the first positioning line and the second positioning line is at least two groups, the two groups of the first positioning lines are respectively arranged on the two side wings of the model aircraft, and the two groups of the second positioning lines are respectively arranged on the upper end surface and the lower end surface of the model aircraft.

[0011] As an improvement of the above technical solution, a spherical bottom cover is detachably fixed to the lower end surface of the transparent mounting plate, and the two groups of the first positioning lines are D-shaped, and the arc-shaped parts of the first positioning lines are inserted into the inner walls of the spherical bottom cover, the transparent mounting plate and the transparent top cover in sequence.

[0012] As an improvement of the above technical solution, the lower end side of the spherical bottom cover is detachably fixed with supporting legs, the number of the supporting legs is at least three, the supporting legs are evenly distributed in a ring shape on the lower end side of the spherical bottom cover, and the lower end surface of the model aircraft is provided with supporting wheels.

[0013] As an improvement of the above technical solution, one end of the second positioning line located at the top is connected to the head of the upper end surface of the model aircraft, and the other end is connected to the tail of the upper end surface of the model aircraft. One end of the second positioning line located at the bottom is connected to the head of the lower end surface of the model aircraft, and the other end is connected to the tail of the lower end surface of the model aircraft.

[0014] As an improvement of the above technical solution, the two side wings of the model aircraft are provided with a plurality of jet assemblies of the same number, the two side wings of the model aircraft are provided with rotatable side wing panels, the tail of the model aircraft is provided with a rotatable tail wing panel, and the upper end surface of the tail of the model aircraft is provided with a rotatable rudder plate.

[0015] Beneficial effects of the present invention:

[0016] By setting up a positioning line group, the upper and lower end surfaces of the model aircraft are positioned simultaneously, so that the aircraft will not have excessive position deviation during flight, and the demonstration of the aircraft's take-off principle can be stably realized. In addition, only a model aircraft with a power structure needs to be selected to achieve flight control between the entire transparent top cover and the transparent mounting plate. Although the control difficulty is relatively high, it is still possible to achieve a certain control function of the aircraft's aerial attitude, and combined with the aircraft's aerodynamic lift principle demonstration, the integration of the two demonstration equipment of flight attitude and aerodynamic lift is realized. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a three-dimensional structural diagram of the present invention;

[0018] Figure 2 for Figure 1 The enlarged structure diagram at A in the middle;

[0019] Figure 3 It is the exploded structure diagram of the present invention;

[0020] Figure 4 for Figure 3 The enlarged structure diagram at B in the middle;

[0021] Figure 5 It is a top view of the structure of the present invention;

[0022] Figure 6 for Figure 5 Isometric section view at mid-CC;

[0023] Figure 7 It is the main structural diagram of the present invention;

[0024] Figure 8 for Figure 7 Plane section view at DD in the middle;

[0025] Fig. 9 for Figure 7 Isometric section view at mid DD;

[0026] Fig.10 The figure is a schematic diagram of the airflow direction after the deflection adjustment of the model aircraft according to the present invention.

[0027] Figure numerals: 10, transparent mounting plate; 11, air duct; 12, blower assembly; 121, fan assembly; 122, motor; 13, bottom plate; 14, support leg; 20, transparent top cover; 21, wire trough; 22, displacement detection module; 30, model airplane; 31, jet assembly; 32, tail wing panel; 33, side wing panel; 34, rudder plate; 35, positioning line group; 351, first positioning line; 352, second positioning line; 36, tension sensor; 40, spherical bottom cover. DETAILED DESCRIPTION

[0028] The following describes the embodiments of the present invention through specific examples, and those skilled in the art can easily understand other advantages and effects of the present invention from the contents disclosed in this specification. The present invention can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present invention.

[0029] Conventional auxiliary learning equipment usually includes a simple aircraft lift demonstration device, whose structure is achieved by placing a suspended aircraft in a transparent ventilation duct. When the airflow intensity in the ventilation duct is large enough, the structural design of the wing can be pushed up by the upper and lower pressure differences of the airflow. This design can only demonstrate the principle that the aircraft can fly, but cannot control the flight attitude of the aircraft. When conducting a demonstration, it is not possible to fully show the flight attitude of the aircraft under different conditions during the flight process to relevant personnel. In addition, since this demonstration device is usually only designed to be suspended at the top, the aircraft is prone to unstable pressure on the wings due to unbalanced airflow, which in turn causes the aircraft to flip, tilt, and other abnormal take-off states. The aircraft position must be accurate before take-off to complete a normal flight demonstration.

[0030] To solve the above problems, see Figures 1 to 9 , provides an aerodynamic lift demonstration device, including: a transparent mounting plate 10 arranged in a ring shape, a transparent top cover 20 arranged on the upper end surface of the transparent mounting plate 10, and a model aircraft 30.

[0031] Specifically, a bottom plate 13 is provided at the bottom of the transparent mounting plate 10, and air ducts 11 with openings opposite to each other are provided on both sides of the transparent mounting plate 10. A blower assembly 12 is provided at the inlet of the air duct 11. The transparent top cover 20 is separated from the bottom plate 13 and the transparent mounting plate 10 to form an inner cavity. The air duct 11 is connected to the inner cavity. The model aircraft 30 is placed at the center position of the upper end surface of the bottom plate 13. A positioning wire group 35 is detachably fixed to the upper end surface of the model aircraft 30. The other end of the positioning wire group 35 passes through the transparent top cover 20 and is detachably fixed to the lower end surface of the model aircraft 30. When the blower assembly 12 blows air, the model aircraft 30 rises along the positioning wire group 35.

[0032] When working, the air blowing assembly 12 is controlled to blow air from the air duct 11 on one side, and air is blown outward through the air blowing assembly 12 at the entrance of the air duct 11 on the other side, thereby forming a complete airflow channel, and the model aircraft 30 is in the middle position of the airflow channel and faces the air intake side. In this case, since the model aircraft 30 is positioned by the positioning line group 35, it is possible to ensure that the wings of the model aircraft 30 form a pressure difference under the action of the airflow, thereby forming a state in which the model aircraft 30 is lifted. This form demonstrates the posture of the aerodynamic lift of the model aircraft 30.

[0033] When the model aircraft 30 stops flying due to the pressure difference, the gravity and aerodynamic lift of the model aircraft 30 form a balanced state. In order to ensure the controllability of the model aircraft 30 during flight, it is necessary to ensure that the model aircraft 30 has a power structure. For details, please refer to Figures 1 to 4 The two side wings of the model aircraft 30 are provided with a plurality of jet assemblies 31 of the same number, the two side wings of the model aircraft 30 are provided with rotatable side wing panels 33, the tail wing of the model aircraft 30 is provided with a rotatable tail wing panel 32, and the upper end surface of the tail of the model aircraft 30 is provided with a rotatable rudder plate 34.

[0034] That is, when the model aircraft 30 is in a relatively balanced state, the side wing panels 33 on both sides of the aircraft can be controlled to rotate to a certain arc. The "rotatable" here means that it is in a stored state under normal conditions, and when adjustment is required, it can be transformed from the stored state to an unfolded form. Usually, the side wing panels 33, the tail wing panels 32 and the rudder panels 34 can form a certain angle with their installation positions, thereby ensuring that the angle adjustment function of the model aircraft 30 is realized when rotating out.

[0035] When the model aircraft 30 needs to make a horizontal turn, the rudder plate 34 can be turned to make the tail produce a certain arc, thereby realizing the turning demonstration function. Due to the turning, the change of the fuselage will cause the change of the wind direction, that is, the direction of the wind blowing and the direction of the wing are no longer a straight line, but a certain inclination angle is generated. This inclination angle will cause the model aircraft 30 to be unevenly stressed, so that it cannot continue to fly. Therefore, it is also necessary to ensure the adjustability of the blower assembly 12. Based on this, please refer to Figure 1 and Figure 2 Specifically, the blower assembly 12 includes a fan assembly 121 and a motor 122. The number of fan assemblies 121 is several and is evenly arranged at the entrance of the air duct 11. The upper end surface and the lower end surface of the fan assembly 121 are provided with protrusions, and the protrusions penetrate into the inner wall of the air duct 11. The number of fan assemblies 121 is the same as that of motors 122. The motor 122 is arranged on the upper end surface of the air duct 11, and the power end of the motor 122 penetrates into the interior of the air duct 11 and is detachably fixedly connected to the protrusions.

[0036] That is, the motor 122 can automatically adjust the direction, so as to adjust the fan assembly 121, and then adjust the wind direction of the internal structure. Due to the change in direction, the flow direction of the internal airflow is no longer a straight line, but has a certain curvature. However, the part of the airflow contacting the wing of the model aircraft 30 is still in a straight line state, and since only the blower assembly 12 on one side is adjusted, the airflow tends to be in a straight line state when the air is discharged at the tail. In addition, in order to reduce the disturbance of the internal airflow as much as possible, the fan assembly 121 on the air outlet side and the air inlet side is closed according to the steering angle of the model aircraft 30, such as Fig.10 As shown, the side of the model aircraft 30 facing is the air intake side, and the part of the fan assembly 121 facing the nose of the model aircraft 30 is open, while the part not facing the nose of the model aircraft 30 is directly closed, and the air flow inside it flows as shown in FIG. Fig.10 Therefore, although the model aircraft 30 has achieved a turn, the pressure difference generated by the airflow can still keep the model aircraft 30 in a flying state.

[0037] When the above scheme is adjusted, the steering angle of the model aircraft 30 is the same as the blade blowing angle of the fan assembly 121, but the steering direction is opposite, and the fan assembly 121 is closed according to the part covering the nose of the model aircraft 30. In addition, in order to ensure the normal flight of the model aircraft 30, the steering angle shall not be higher than the angle between the edge fan and the central axis of the model aircraft 30 in the initial state, so as to avoid the wind force being unable to ensure the flight state of the model aircraft 30.

[0038] In order to further strengthen the detection of relevant data during the model flight, please refer to Figure 3 and Figure 4 Specifically, the surface of the model aircraft 30 is provided with threaded holes, the number of which is twice that of the positioning wire group 35. Each group of two threaded holes is respectively arranged on the upper end surface and the lower end surface of the model aircraft 30. A tension sensor 36 is threadedly connected to the threaded hole, and the other end of the tension sensor 36 is fixed to one end of the positioning wire group 35.

[0039] The tension sensor 36 is used to detect the tension during the take-off process and the deflection force when the side wings and tail wing produce angle changes during angle adjustment, so as to more intuitively feel the force changes of the model aircraft 30 during the flight.

[0040] Specifically, the tension sensor 36 is a double-ended columnar external thread tension sensor, the two threaded ends of which respectively pass through the upper end surface and the lower end surface of the model aircraft 30, and the two ends of the positioning wire group 35 are respectively fixed to the two threaded ends.

[0041] A double-ended column type external thread tension sensor usually refers to a connector with threaded columns at both ends and a detection component in the middle. The detection component is connected from the side when wiring. When the threaded column generates tension, the detection component will generate an electrical signal. The tension situation is identified based on the strength of the electrical signal. The double-ended column type external thread tension sensor is used to detect tension. This sensor not only has a stable detection effect, but also its structural design makes it easier to install on the model aircraft 30, and is more convenient in disassembly, maintenance and other operations.

[0042] To further read the direction of the force that produces the angle change of the model aircraft 30, please refer to Figure 1 and Figure 2 Specifically, a wire groove 21 and a displacement detection module 22 are opened on the surface of the transparent top cover 20 , the bottom of the wire groove 21 is connected to the accommodating cavity of the positioning wire group 35 , and the displacement detection module 22 is arranged above the opening of the wire groove 21 .

[0043] The displacement detection module 22 is provided to detect the moving direction of the internal positioning line group 35, and the direction of the pulling force is inferred reversely through the moving direction of the positioning line group 35. The pulling force is usually in the same direction as the moving direction. For example, the line on the upper end surface of the model aircraft 30 moves up, and the state formed is that this part of the model aircraft 30 moves up, and the pressure difference is that the pressure at the bottom is large and the pressure at the top is small. The pulling force generated here is the pulling force on the top of the model aircraft 30.

[0044] In order to ensure the stability of the model aircraft 30 and ensure that the model aircraft 30 can accurately and completely turn, adjust the nose and tail, etc., please refer to FIG. Figure 4 Specifically, the positioning line group 35 includes a first positioning line 351 and a second positioning line 352. The number of the first positioning line 351 and the second positioning line 352 is at least two groups. The two groups of first positioning lines 351 are respectively arranged on the two side wings of the model aircraft 30, and the two groups of second positioning lines 352 are respectively arranged on the upper end surface and the lower end surface of the model aircraft 30.

[0045] The two side wings and the front and rear end setting lines of the model aircraft 30 are positioned in a symmetrical manner, and the first positioning line 351 controls the two sides of the aircraft. When the aircraft needs to be flipped, it can be flipped by unfolding the side wing panels 33. The straight wind will hit the unfolded side wing panels 33. When the side wing panels 33 are flipped up at the same time, the nose of the entire model aircraft 30 tilts downward, and when the two side wing panels 33 are flipped down, the nose of the entire model aircraft 30 tilts upward, and when the flipping directions of the two side wing panels 33 are opposite, the entire model aircraft 30 flips over. In this embodiment, the model aircraft 30 cannot be completely flipped. This is because Due to the limitation of the first positioning line 351 and the second positioning line 352, the model aircraft 30 can only flip at a certain angle, and its flipping angle is affected by the length and material of the first positioning line 351 and the second positioning line 352. The longer the length of the first positioning line 351 and the second positioning line 352, the greater the angle at which the model aircraft 30 can flip. The softer the material of the first positioning line 351 and the second positioning line 352, the greater the angle at which the model aircraft 30 can flip. In order to ensure the normal operation of the model aircraft 30, it is necessary to avoid the deflection angle of the model aircraft 30 exceeding 45°. If it exceeds 45°, it may cause the aircraft to become unbalanced and fall onto the base plate 13.

[0046] In the above scheme, the first positioning line 351 and the second positioning line 352 will generate a certain friction force during the movement, and this friction force will affect the force required for the model aircraft 30 to take off. In order to reduce the influence of the friction force of the first positioning line 351 and the second positioning line 352 during the movement on the take-off, please refer to the figure. For details, please refer to Figures 1 to 6 The lower end surface of the transparent mounting plate 10 is detachably fixed with a spherical bottom cover 40, and the two sets of first positioning lines 351 are D-shaped, and the arc-shaped parts of the first positioning lines 351 penetrate into the inner walls of the spherical bottom cover 40, the transparent mounting plate 10 and the transparent top cover 20 in sequence.

[0047] The first positioning line 351 and the second positioning line 352 are inserted in an arc-shaped manner. Compared with the friction force of the rectangular structure at the corner point, this design receives more uniform and lower friction, which can ensure the stability of the model aircraft 30 during operation and avoid jamming the flight posture of the model aircraft 30.

[0048] Specifically, one end of the second positioning line 352 located at the top is connected to the head of the upper end surface of the model aircraft 30, and the other end is connected to the tail of the upper end surface of the model aircraft 30. One end of the second positioning line 352 located at the bottom is connected to the head of the lower end surface of the model aircraft 30, and the other end is connected to the tail of the lower end surface of the model aircraft 30.

[0049] This connection method requires that the wires are first inserted and then the ends of the two wires are wrapped around the threaded column of the double-headed column external threaded tension sensor. After the threaded column is wrapped, the entire double-headed column external threaded tension sensor can be fixed on the model aircraft 30 by tightening the two ends with nuts. The first positioning line 351 and the second positioning line 352 are also respectively connected to different threaded columns at both ends, and the tension of the double-headed column external threaded tension sensor is tested at both ends.

[0050] In order to facilitate the adjustment of the entire transparent mounting plate 10, please refer to Figure 1 and Figure 2 The lower end side of the spherical bottom cover 40 is detachably fixed with a support leg 14, the number of the support legs 14 is at least three, and the support legs 14 are evenly distributed in a ring shape on the lower end side of the spherical bottom cover 40, and the lower end surface of the model aircraft 30 is provided with a supporting wheel.

[0051] The supporting function provided on the base plate 13 by the supporting wheels of the model aircraft 30 ensures that the model aircraft 30 can be stably parked on the upper end surface of the base plate 13, and the support legs 14 are fixed on the spherical bottom cover 40 to facilitate the adjustment of the transparent mounting plate 10, that is, the transparent mounting plate 10 can be directly mounted on the spherical bottom cover 40. Since the position of the transparent mounting plate 10 is usually not adjusted during use, and the force generated during the whole process is not enough to push the entire transparent mounting plate 10 to deflect, the entire transparent mounting plate 10 can be buckled on the spherical bottom cover 40. It only needs to be sealed between the spherical bottom cover 40 and the transparent mounting plate 10 to avoid airflow leakage, which causes internal airflow disturbance and affects the normal operation of the model aircraft 30.

[0052] The above embodiments are only used to illustrate the technical solutions of the present invention, but not to limit them. Anyone familiar with the technology can modify or change the above embodiments without violating the spirit and scope of the present invention. Therefore, all equivalent modifications or changes made by those with ordinary knowledge in the technical field without departing from the spirit and technical ideas disclosed by the present invention should still be covered by the claims of the present invention.

Claims

1. An aerodynamic lift demonstration device, characterized in that: include: A transparent mounting plate (10) arranged in an annular shape, a bottom plate (13) being arranged at the bottom of the transparent mounting plate (10), air ducts (11) with openings facing each other being arranged on both sides of the transparent mounting plate (10), and an air blowing assembly (12) being arranged at the inlet of the air duct (11); A transparent top cover (20) is arranged on the upper end surface of the transparent mounting plate (10), wherein the transparent top cover (20) is separated from the bottom plate (13) and the transparent mounting plate (10) to form an inner cavity, and the air duct (11) is connected to the inner cavity; A model airplane (30) is placed at the center of the upper end surface of the bottom plate (13), a positioning wire group (35) being detachably fixed to the upper end surface of the model airplane (30), and the other end of the positioning wire group (35) passes through the transparent top cover (20) and is detachably fixed to the lower end surface of the model airplane (30); When the air blowing assembly (12) blows air, the model airplane (30) rises along the positioning line group (35).

2. The aerodynamic lift demonstration device according to claim 1, characterized in that: The surface of the model aircraft (30) is provided with threaded holes, the number of which is twice that of the positioning wire group (35), and each group of two threaded holes is respectively arranged on the upper end surface and the lower end surface of the model aircraft (30), and the threaded holes are internally threadedly connected with a tension sensor (36), and the other end of the tension sensor (36) is fixed to one end of the positioning wire group (35).

3. The aerodynamic lift demonstration device according to claim 2, characterized in that: The tension sensor (36) is a double-ended column type external thread tension sensor, the two threaded ends of which respectively pass through the upper end surface and the lower end surface of the model aircraft (30), and the two ends of the positioning wire group (35) are respectively fixed to the two threaded ends.

4. The aerodynamic lift demonstration device according to claim 1, characterized in that: The air blowing assembly (12) comprises a fan assembly (121) and a motor (122). The number of the fan assemblies (121) is several and they are evenly arranged at the entrance of the air duct (11). The upper end surface and the lower end surface of the fan assembly (121) are provided with protrusions, and the protrusions penetrate the inner wall of the air duct (11). The number of the fan assemblies (121) is the same as that of the motor (122). The motor (122) is arranged on the upper end surface of the air duct (11), and the power end of the motor (122) penetrates into the interior of the air duct (11) and is detachably fixedly connected to the protrusions.

5. The aerodynamic lift demonstration device according to claim 1, characterized in that: A wire groove (21) and a displacement detection module (22) are provided on the surface of the transparent top cover (20); the bottom of the wire groove (21) is connected to the accommodating cavity of the positioning wire group (35); and the displacement detection module (22) is arranged above the opening of the wire groove (21).

6. The aerodynamic lift demonstration device according to any one of claims 1 to 5, characterized in that: The positioning line group (35) comprises a first positioning line (351) and a second positioning line (352), the number of the first positioning line (351) and the second positioning line (352) being at least two groups, the two groups of the first positioning lines (351) being respectively arranged on the two side wings of the model aircraft (30), and the two groups of the second positioning lines (352) being respectively arranged on the upper end surface and the lower end surface of the model aircraft (30).

7. The aerodynamic lift demonstration device according to claim 6, characterized in that: A spherical bottom cover (40) is detachably fixed to the lower end surface of the transparent mounting plate (10), and the two groups of the first positioning lines (351) are D-shaped, and the arc-shaped parts of the first positioning lines (351) are sequentially penetrated into the inner walls of the spherical bottom cover (40), the transparent mounting plate (10) and the transparent top cover (20).

8. The aerodynamic lift demonstration device according to claim 7, characterized in that: The lower end side surface of the spherical bottom cover (40) is detachably fixed with supporting legs (14), the number of the supporting legs (14) is at least three, and the supporting legs (14) are evenly distributed in a ring shape on the lower end side surface of the spherical bottom cover (40), and the lower end surface of the model aircraft (30) is provided with supporting wheels.

9. The aerodynamic lift demonstration device according to claim 7, characterized in that: One end of the second positioning line (352) located at the top is connected to the head of the upper end surface of the model aircraft (30), and the other end is connected to the tail of the upper end surface of the model aircraft (30); one end of the second positioning line (352) located at the bottom is connected to the head of the lower end surface of the model aircraft (30), and the other end is connected to the tail of the lower end surface of the model aircraft (30).

10. The aerodynamic lift demonstration device according to claim 9, characterized in that: The two side wings of the model aircraft (30) are provided with a plurality of jet assemblies (31) of the same number, the two side wings of the model aircraft (30) are provided with rotatable side wing panels (33), the tail of the model aircraft (30) is provided with a rotatable tail panel (32), and the upper end surface of the tail of the model aircraft (30) is provided with a rotatable steering panel (34).

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