A flow field simulation system and method for an aircraft

Abstract

This invention belongs to the field of flow field simulation for aircraft, specifically relating to a flow field simulation system and method for aircraft, including a wind tunnel, an aircraft mounting device, and an aircraft to be tested. The aircraft mounting device includes a mounting rod and an operating rod. The mounting rod is disposed inside the wind tunnel, and the operating rod is slidably mounted on the mounting rod, with one end of the operating rod located inside the wind tunnel and the other end extending outside the wind tunnel. A hinge seat is provided at the end of the mounting rod facing inside the wind tunnel, and the aircraft is hinged to the hinge seat. The aircraft is also provided with an arc-shaped external tooth coaxial with the hinge axis. A limit tooth is provided at the end of the operating rod located inside the wind tunnel. The operating rod slides along the mounting rod, and the limit tooth engages or disengages with the arc-shaped external tooth. In this invention, the entire aircraft mounting device combines the fixed control part with the hinge part, resulting in a simple and reliable structure, convenient and flexible control, and the ability to switch between two fixing methods, thus improving the simulation effect.

Description

Technical Field

[0001] This invention belongs to the field of flow field simulation for aircraft, specifically relating to a flow field simulation system and method for aircraft. Background Technology

[0002] An aircraft's control system controls its attitude by manipulating servos to deflect control plates, thereby generating aerodynamic forces. Attitude includes yaw, roll, and pitch. Because aircraft fly at high speeds, experimental observation is not only costly and difficult but also usually very short. Learners and enthusiasts find it difficult to intuitively perceive the control system's impact on attitude; therefore, simulation systems are typically used for assessment.

[0003] Currently, ground-based micro wind tunnels and micro aircraft are used for simulation, which can intuitively and cost-effectively observe the impact of the control system on a single attitude over a long period of time. However, the current installation equipment for installing aircraft in wind tunnels is highly targeted, requiring specific installation devices to be designed for specific aircraft. Moreover, they are generally complex in structure or simple in function. For example, Chinese patent "CN202110569916.9 - A small wind tunnel experimental system for the research of micro flapping-wing aircraft" cannot be adjusted or fixed after installation, and its functions are limited. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide a flow field simulation system and method for an aircraft that provides two aircraft fixing methods, and the switching between fixing methods is convenient and quick, and the overall structure is simple and reliable.

[0005] The present invention provides a flow field simulation system for an aircraft, comprising a wind tunnel, an aircraft mounting device, and an aircraft to be tested;

[0006] The aircraft mounting device includes a mounting rod and an operating rod. The mounting rod is disposed inside the wind tunnel, and the operating rod is slidably disposed on the mounting rod, with one end of the operating rod located inside the wind tunnel and the other end extending outside the wind tunnel.

[0007] The mounting rod is provided with a hinge seat at one end facing the wind tunnel, and the aircraft is hinged to the hinge seat;

[0008] The aircraft is also equipped with an arc-shaped external tooth coaxial with the hinge axis. The end of the operating lever located in the wind tunnel is equipped with a limiting tooth. The operating lever slides along the mounting rod, and the limiting tooth engages or disengages with the arc-shaped external tooth.

[0009] Furthermore, the hinge base includes two hinge plates arranged opposite each other and a hinge shaft that can be detachably connected to the two hinge plates. The aircraft is provided with a connecting plate, which is disposed between the two hinge plates, and the connecting plate is provided with a hinge hole that rotatably engages with the hinge shaft.

[0010] Furthermore, the arc-shaped external teeth are located on the outer side of the connecting plate.

[0011] Furthermore, the mounting rod is provided with a sliding groove along its axis, and the operating rod is slidably disposed within the sliding groove.

[0012] Furthermore, the other end of the mounting rod extends out of the wind tunnel, and the mounting rod is provided with a strip groove connecting the sliding groove on the outside of the wind tunnel. The operating rod is provided with a pressure rod extending out of the strip groove, and the operating rod is controlled to move along the sliding groove by operating the pressure rod.

[0013] Furthermore, the aircraft mounting device also includes an elastic element, one end of which is fixed to the mounting rod, and the other end is fixed to the operating rod or the limiting tooth. The elastic element drives the limiting tooth to mesh with the arc-shaped external tooth.

[0014] Furthermore, the aircraft mounting device also includes a base, one end of the mounting rod located outside the wind tunnel is fixed to the base, an electromagnet is provided at the bottom of the sliding groove on the base, and an electromagnet mating block is provided at the one end of the operating rod located outside the wind tunnel.

[0015] Furthermore, the aircraft is equipped with a smoke canister, and the side wall of the aircraft is provided with a vent that connects to the smoke canister.

[0016] Furthermore, the wind tunnel includes a diffusion section, a stabilization section, a contraction section, a test section, and a diffuser section arranged in sequence, with the aircraft mounting device and the aircraft located in the test section.

[0017] The present invention also provides a flow field simulation method for an aircraft, which uses the above-mentioned flow field simulation system for an aircraft and includes the following steps:

[0018] S1, the aircraft under test is hinged to the end of the mounting rod via the hinge seat. After adjusting the angle of the aircraft, the operating rod is driven to move toward the aircraft until the limit tooth meshes with the arc-shaped external tooth, thus completing the installation of the aircraft and fixing the initial angle.

[0019] S2, open the wind tunnel, and after the airflow speed in the wind tunnel has stabilized, control the aircraft to enter flight mode;

[0020] S3, drive the control stick away from the aircraft, and the limit tooth disengages from the arc-shaped external tooth;

[0021] S4, observe or record the pitch control status of the aircraft.

[0022] The beneficial effects of the present invention are that the aircraft installation device provided by the present invention can install the aircraft inside the wind tunnel and can provide omnidirectional fixation and local directional fixation with pitch direction rotational freedom. The fixation method can be selected according to different simulation requirements, and the switching of the fixation method is carried out outside the wind tunnel. Only the movement of the control stick needs to be controlled, which is convenient and quick.

[0023] The specific fixing method utilizes a combination of hinges, arc-shaped external teeth, and limiting teeth. The limiting teeth can only move linearly along the direction of movement of the control lever. After the limiting teeth mesh with the arc-shaped external teeth, the positions of the arc-shaped external teeth and the aircraft are defined. At this point, even if the wind in the wind tunnel causes the aircraft to pitch, meaning the arc-shaped external teeth have an external force driving their rotation, this external force also drives the limiting teeth to rotate, not to move linearly. Therefore, the aircraft's own weight and the external forces generated by the wind in various directions will not affect the meshing stability of the limiting teeth and the arc-shaped external teeth. Without manual or external force control of the control lever, the aircraft is fixed stably and reliably. For fixing the contact pitch angle rotation degree of freedom, only manual or external force control of the control lever to move it away from the aircraft is required. In this case, the aircraft is fixed to the end of the mounting rod through a hinge structure and can rotate the pitch angle along the hinge axis.

[0024] The entire aircraft mounting system combines the fixed control section with the articulated section, resulting in a simple, reliable structure with convenient and flexible control. It allows switching between two fixing modes, improving simulation effectiveness. The simulation process allows observation of the control system's influence on a single attitude, thereby deepening the understanding of relevant control principles and parameter settings. For example, control parameters can be modified within a certain deviation range, and the impact of different parameters on the attitude can be compared. This system can also be used for teaching, greatly aiding students and enthusiasts in understanding control principles. It is particularly significant for beginners in deepening their understanding of control principles and enhancing their learning interest. Attached Figure Description

[0025] Appendix Figure 1 This is a schematic diagram of the wind tunnel structure in this invention;

[0026] Appendix Figure 2 This is a front view of the wind tunnel in this invention;

[0027] Appendix Figure 3 This is a front sectional view of the present invention;

[0028] Appendix Figure 4 This is a perspective view of the present invention;

[0029] Appendix Figure 5 for Figure 4 A magnified view of a section at point A in the middle;

[0030] Appendix Figure 6 for Figure 5 A magnified view of a section at point B in the middle;

[0031] Appendix Figure 7 for Figure 6 A half-section view;

[0032] Appendix Figure 8 for Figure 5 A magnified view of a section at point C;

[0033] Appendix Figure 9 for Figure 8 A half-section view.

[0034] In the diagram, 1-wind tunnel; 11-diffuser section; 12-stabilizing section; 121-rectifier grid; 13-contraction section; 14-test section; 15-diffuser section; 16-axial flow fan; 2-aircraft mounting device; 21-mounting rod; 211-hinge seat; 2111-hinge plate; 2112-hinge shaft; 212-sliding groove; 213-strip groove; 22-operating lever; 221-limiting tooth; 222-pressure rod; 23-base; 24-electromagnet; 25-electromagnet mating block; 26-elastic element; 27-electromagnet controller; 3-aircraft; 31-arc-shaped external tooth; 32-connecting plate; 33-hinge hole; 34-smoke canister; 35-vent; 36-rudder control device. Detailed Implementation

[0035] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0036] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indication will also change accordingly.

[0037] Furthermore, in this invention, descriptions involving "first," "second," etc., are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0038] In this invention, unless otherwise explicitly specified and limited, the terms "connection," "fixed," etc., should be interpreted broadly. For example, "fixed" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection, an electrical connection, a physical connection, or a wireless communication connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal communication of two elements or the interaction between two elements, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0039] Furthermore, the technical solutions of the various embodiments of the present invention can be combined with each other, but only if they are feasible for those skilled in the art. If the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such combination of technical solutions does not exist and is not within the scope of protection claimed by the present invention.

[0040] As attached Figure 1-9 As shown, the present invention provides a flow field simulation system for an aircraft, including a wind tunnel 1, an aircraft mounting device 2, and an aircraft 3 to be tested, wherein the aircraft 3 can be a powered aircraft or an unpowered aircraft, or a rocket or munition.

[0041] The aircraft mounting device 2 includes a mounting rod 21 and an operating rod 22. The mounting rod 21 is disposed inside the wind tunnel 1. That is, the mounting rod 21 can be entirely located inside the wind tunnel 1, or a portion of the mounting rod 21 can be located inside the wind tunnel 1. In a preferred embodiment, a portion of the mounting rod 21 is located inside the wind tunnel 1, and the other portion extends out of the wind tunnel 1, which facilitates the fixing of the aircraft mounting device 2. Preferably, the mounting rod 21 is perpendicular to the air duct of the wind tunnel 1. The operating rod 22 is slidably disposed on the mounting rod 21, with one end of the operating rod 22 located inside the wind tunnel 1 and the other end extending out of the wind tunnel 1. The other end of the operating rod 22 extends out of the wind tunnel 1, which facilitates the control of the operating rod 22.

[0042] The mounting rod 21 is provided with a hinge seat 211 at one end inside the wind tunnel 1. The aircraft 3 is hinged on the hinge seat 211, that is, the aircraft 3 can rotate along the hinge axis and has the degree of freedom of pitch rotation.

[0043] The aircraft 3 is also equipped with an arc-shaped external tooth 31 coaxial with the hinge axis. The end of the operating lever 22 located in the wind tunnel 1 is equipped with a limiting tooth 221. The operating lever 22 slides along the mounting rod 21, and the limiting tooth 221 engages or disengages with the arc-shaped external tooth 31. By setting the arc-shaped external tooth 31 and the limiting tooth 221, the pitch angle rotation of the aircraft 3 can be fixed and released. Before and after the specific simulation test, the pitch angle of the aircraft 3 can be fixed by the engagement of the arc-shaped external tooth 31 and the limiting tooth 221 during installation, so as to achieve omnidirectional fixation of the aircraft 3 in the wind tunnel 1. During the simulation test, the arc-shaped external tooth 31 and the limiting tooth 221 can be disengaged by the operating lever 22 to release the limitation on the pitch direction rotation of the aircraft 3, which is used to observe the pitch capability of the aircraft 3 and the pitch adjustment capability of the servo system.

[0044] The aircraft mounting device 2 provided by the present invention can install the aircraft 3 inside the wind tunnel 1, and can provide omnidirectional fixation and local directional fixation with pitch direction rotational freedom. The fixation method can be selected according to different simulation requirements, and the switching of the fixation method is carried out outside the wind tunnel 1, and only the movement of the control stick 22 needs to be controlled, which is convenient and quick.

[0045] The specific fixing method involves a combination of hinge, arc-shaped external teeth 31, and limiting teeth 221. The limiting teeth 221 can only move linearly along the direction of movement of the operating lever 22. After the limiting teeth 221 and the arc-shaped external teeth 31 are engaged, the position of the arc-shaped external teeth 31 and the aircraft 3 is limited. At this time, even if the wind in the wind tunnel 1 pushes the aircraft 3 to pitch and rotate, that is, the arc-shaped external teeth 31 has an external force that drives its rotation, this external force also drives the limiting teeth 221 to rotate rather than drive the limiting teeth 221 to move linearly. Therefore, the aircraft 3's own weight and the external forces generated by the wind in various directions will not affect the meshing stability of the limiting teeth 221 and the arc-shaped external teeth 31. Without manual or external force control of the operating lever 22, the fixing of the aircraft 3 is stable and reliable. As for fixing the pitch angle rotation degree of freedom, it is only necessary to manually or by external force control the control stick 22 to move away from the aircraft 3. At this time, the aircraft 3 is fixed to the end of the mounting rod 21 through the hinge structure and can rotate the pitch angle along the hinge axis.

[0046] The entire aircraft mounting device 2 combines the fixed control section with the articulated section, resulting in a simple and reliable structure with convenient and flexible control. It allows switching between two fixing modes, improving simulation effectiveness. The simulation process allows observation of the control system's influence on a single attitude, thereby deepening the understanding of relevant control principles and parameter settings. For example, control parameters can be modified within a certain deviation range, and the impact of different parameters on the attitude can be compared. This system can also be used for teaching, greatly aiding students and enthusiasts in understanding control principles. It is particularly significant for beginners in deepening their understanding of control principles and enhancing their learning interest.

[0047] In one embodiment, the hinge base 211 includes two opposing hinge plates 2111 and a hinge shaft 2112 that detachably connects the two hinge plates 2111. That is, the hinge base 211 can be detachably connected to the aircraft 3, which facilitates the replacement of the aircraft 3 for testing. The aircraft 3 is provided with a connecting plate 32, which is located between the two hinge plates 2111. The connecting plate 32 is provided with a hinge hole 33 that rotatably engages with the hinge shaft 2112. With this hinge method, the modification of the aircraft 3 only requires the addition of a connecting plate 32 with a hinge hole 33 and an arc-shaped external tooth 31, which facilitates the addition of a connection structure to the existing aircraft 3. In addition, the connection relationship between the connecting plate 32 and the two hinge plates 2111 can also restrict the lateral movement of the aircraft 3 along the hinge axis, thereby improving the fixation reliability of the aircraft 3.

[0048] When disassembling and assembling the aircraft 3, simply inserting or pulling out the hinge shaft 2112 is sufficient to complete the docking and separation of the aircraft 3.

[0049] In one embodiment, the arc-shaped external tooth 31 is disposed on the outer side of the connecting plate 32. In this embodiment, the outer side of the connecting plate 32 adopts an arc-shaped structure, and the arc-shaped external tooth 31 is directly disposed on the outer side of the connecting plate 32, making the improvement of the aircraft 3 simpler. Only a connecting plate 32 with a hinge hole 33 and an arc-shaped external tooth 31 needs to be added. In this embodiment, the connecting plate 32 can be fixed to the aircraft 3 by adhesive bonding without causing any destructive modifications to the aircraft 3. In addition, at this time, the limiting tooth 221 also moves linearly within the range between the two hinge plates 2111. The two hinge plates 2111 can guide and limit the movement of the limiting tooth 221, improving the movement stability of the operating lever 22 and the limiting tooth 221.

[0050] In one embodiment, the mounting rod 21 is provided with a sliding groove 212 along its axis, and the operating rod 22 is slidably disposed within the sliding groove 212. In this embodiment, the operating rod 22 is disposed inside the mounting rod 21, which can reduce the area of ​​the aircraft mounting device 2 in the wind tunnel 1, reduce drag, and at the same time make the linear movement guidance of the operating rod 22 the best, so that the operating rod 22 can move and rotate linearly along the sliding groove 212. Combined with the limiting teeth 221 and the limiting of the hinge plate 2111, the operating rod 22 can only move linearly along the sliding groove 212.

[0051] In one embodiment, the other end of the mounting rod 21 extends out of the wind tunnel 1, and the mounting rod 21 is provided with a strip groove 213 that connects to the sliding groove 212 outside the wind tunnel 1. The operating rod 22 is provided with a pressure rod 222 that extends out of the strip groove 213. The operating rod 22 is controlled to move along the sliding groove 212 by operating the pressure rod 222. In this embodiment, the operator can move the operating rod 22 by operating the pressure rod 222, which can simplify the difficulty of moving the operating rod 22. Moreover, the two ends of the strip groove 213 can limit the movement stroke of the pressure rod 222, so as to avoid the operating rod 22 from moving too much.

[0052] In one embodiment, the aircraft mounting device 2 further includes an elastic element 26. One end of the elastic element 26 is fixed to the mounting rod 21, and the other end is fixed to the operating rod 22 or the limiting tooth 221. The elastic element 26 drives the limiting tooth 221 to engage with the arc-shaped external tooth 31. The elastic element 26 is preferably a spring. The spring causes the limiting tooth 221 to move closer to and engage with the arc-shaped external tooth 31. That is, in the default state, the limiting tooth 221 and the arc-shaped external tooth 31 are engaged. The aircraft mounting device 2 fixes the aircraft 3 in all directions. Only when the restoring force of the elastic element 26 is overcome by manual or external force to control the operating rod 22 will the aircraft 3 be converted into a state that can rotate in the pitch direction, which can greatly improve the safety of the simulation.

[0053] In one embodiment, the limiting teeth 221 are arranged in an arc-shaped array, that is, the limiting teeth 221 are also arranged in an arc shape, which can improve the meshing power and meshing strength between the limiting teeth 221 and the arc-shaped external teeth 31.

[0054] In one embodiment, the aircraft mounting device 2 further includes a base 23. One end of the mounting rod 21 located outside the wind tunnel 1 is fixed to the base 23. An electromagnet 24 is provided at the bottom of the sliding groove 212 on the base 23. An electromagnet mating block 25 is provided at the end of the operating rod 22 located outside the wind tunnel 1. In this embodiment, the on / off state of the electromagnet 24 can be controlled by the electromagnet controller 27, thereby controlling the attraction and engagement of the electromagnet 24 and the electromagnet mating block 25. The electromagnet 24 can continuously overcome the restoring force of the elastic element 26, maintaining the separation state of the limiting tooth 221 and the arc-shaped external tooth 31, simplifying the installation of the aircraft 3 and allowing state control for pitch direction rotation.

[0055] In one embodiment, the aircraft 3 is provided with a smoke canister 34, and the side wall of the aircraft 3 is provided with a vent 35 communicating with the smoke canister 34. In this embodiment, when the aircraft 3 is conducting simulated flight, smoke can be released by opening the smoke canister 34, and the airflow can be displayed in the downstream part, thereby facilitating the observation of the aerodynamic performance of the aircraft 3 and the airflow guidance of the rudder or tail fin. Preferably, multiple vent 35s are evenly arranged along the circumference of the aircraft 3, and the vent 35s are micropores. The smoke canister 34 is connected to the micropores through a pipe.

[0056] In one embodiment, the wind tunnel 1 includes a diffuser section 11, a stabilizing section 12, a contraction section 13, a test section 14, and a diffuser section 15 arranged sequentially. A rectifier grid 121 is provided in the stabilizing section 12, and an axial flow fan 16 is provided upstream of the diffuser section 11 to provide airflow. The aircraft mounting device 2 and the aircraft 3 are located at the test section 14.

[0057] The present invention also provides a flow field simulation method for an aircraft, which uses the above-mentioned flow field simulation system for an aircraft and includes the following steps:

[0058] S1, the aircraft to be tested 3 is hinged to the end of the mounting rod 21 via the hinge seat 211. After adjusting the angle of the aircraft 3, the operating rod 22 is driven to move toward the aircraft 3 until the limiting tooth 221 meshes with the arc-shaped external tooth 31, thus completing the installation of the aircraft 3 and fixing the initial angle.

[0059] In the embodiment equipped with elastic element 26 and electromagnet 24, before the aircraft 3 is installed, electromagnet 24 is magnetically attracted to electromagnet mating block 25 at the end of operating lever 22, so that limiting tooth 221 is away from aircraft 3. After aircraft 3 is hinged to hinge seat 211 and the angle of aircraft 3 is adjusted, electromagnet controller 27 controls electromagnet 24 to release magnetic attraction from electromagnet mating block 25. The restoring force of elastic element 26 drives operating lever 22 and limiting tooth 221 to move linearly, so that limiting tooth 221 meshes with arc-shaped external tooth 31, and the initial angle of aircraft 3 is fixed.

[0060] S2, turn on the axial flow fan 16 in the wind tunnel 1. After the airflow speed in the wind tunnel 1 is stable, control the aircraft 3 to enter the flight mode. Specifically, the control device 36 of the aircraft 3 can be put into working state.

[0061] S3, drive the operating lever 22 away from the aircraft 3 to move, and the limiting tooth 221 disengages from the arc-shaped external tooth 31. In the embodiment equipped with the elastic element 26 and the electromagnet 24, after the operating lever 22 is moved close to the electromagnet 24, the electromagnet controller 27 controls the electromagnet 24 to magnetically attract with the electromagnet mating block 25, so that the limiting tooth 221 and the arc-shaped external tooth 31 remain separated.

[0062] S4, observe or record the pitch control status of aircraft 3;

[0063] During the observation process, the smoke canister 34 can be opened to facilitate the observation of airflow. After the observation is completed, the electromagnet controller 27 can be used to control the electromagnet 24 and the electromagnet mating block 25 to release the magnetic attraction. The restoring force of the elastic element 26 drives the operating rod 22 and the limiting tooth 221 to move linearly, so that the limiting tooth 221 meshes with the arc-shaped external tooth 31, thereby completing the angle fixation of the aircraft 3 and facilitating the disassembly and subsequent operation of the aircraft 3.

[0064] This method makes the installation, angle fixing, and fixing method adjustment of the aircraft 3 convenient and quick, which can simplify the difficulty and procedures of the test and improve the test efficiency.

[0065] The contents not described in detail in this specification are existing technologies known to those skilled in the art.

Claims

1. A flow field simulation system for an aircraft, characterized by, The wind tunnel (1), the aircraft mounting device (2) and the aircraft (3) to be tested are included. The aircraft mounting device (2) includes a mounting rod (21) and an operating rod (22), the mounting rod (21) is arranged in the wind tunnel (1), and the operating rod (22) is slidingly arranged on the mounting rod (21), one end of the operating rod (22) is located in the wind tunnel (1), and the other end extends out of the wind tunnel (1). One end of the mounting rod (21) located in the wind tunnel (1) is provided with a hinged seat (211), and the aircraft (3) is hingedly arranged on the hinged seat (211). An arc-shaped external gear (31) coaxial with the hinged axis is further arranged on the aircraft (3), one end of the operating rod (22) located in the wind tunnel (1) is provided with a limiting tooth (221), and the operating rod (22) slides along the mounting rod (21), the limiting tooth (221) is engaged with or separated from the arc-shaped external gear (31). The aircraft mounting device (2) further includes an elastic member (26), one end of the elastic member (26) is fixed with the mounting rod (21), the other end is fixed with the operating rod (22) or the limiting tooth (221), and the elastic member (26) drives the limiting tooth (221) to engage with the arc-shaped external gear (31). The aircraft mounting device (2) further includes a base (23), one end of the mounting rod (21) located outside the wind tunnel (1) is fixed on the base (23), the base (23) is provided with an electromagnet (24) at the bottom of the sliding groove (212), and one end of the operating rod (22) located outside the wind tunnel (1) is provided with an electromagnet matching block (25).

2. The flow field simulation system of claim 1, wherein, The hinged seat (211) includes two oppositely arranged hinged plates (2111) and a hinged shaft (2112) detachably connecting the two hinged plates (2111), and the aircraft (3) is provided with a connecting plate (32) arranged between the two hinged plates (2111), and the connecting plate (32) is provided with a hinged hole (33) rotatably matched with the hinged shaft (2112).

3. The flow field simulation system of claim 2, wherein, The arc-shaped external gear (31) is arranged outside the connecting plate (32).

4. The flow field simulation system of any of claims 1-3, wherein, The mounting rod (21) is provided with a sliding groove (212) along the axis, and the operating rod (22) is slidingly arranged in the sliding groove (212).

5. The flow field simulation system of claim 4, wherein, The other end of the mounting rod (21) extends outside the wind tunnel (1), and the mounting rod (21) located outside the wind tunnel (1) is provided with a strip-shaped groove (213) communicating with the sliding groove (212), the operating rod (22) is provided with a pressing rod (222) extending out of the strip-shaped groove (213), and the operating rod (22) is controlled to move along the sliding groove (212) by operating the pressing rod (222).

6. The flow field simulation system of claim 1-3, 5 any one of, characterized in that, The aircraft (3) is provided with a smoke tank (34), and the side wall of the aircraft (3) is provided with a gas permeable hole (35) communicating with the smoke tank (34).

7. The flow field simulation system of claim 1-3, 5 any one of, characterized in that, The wind tunnel (1) includes a diffusion section (11), a stable section (12), a contraction section (13), a test section (14) and an expansion section (15) arranged in sequence, and the aircraft mounting device (2) and the aircraft (3) are arranged at the test section (14).

8. A method of flow field simulation of an aircraft, characterized by, A flow field simulation system for an aircraft as claimed in any one of claims 1 to 7, comprising the steps of: S1, the aircraft (3) to be tested is hingedly arranged at the end of the mounting rod (21) through the hinged seat (211), after adjusting the angle of the aircraft (3), the operating rod (22) is driven to move towards the aircraft (3) until the limiting teeth (221) engage with the arc-shaped outer teeth (31), completing the installation and initial angle fixation of the aircraft (3); S2, open the wind tunnel (1), after the airflow speed of the wind tunnel (1) runs smoothly, control the aircraft (3) to enter the flight mode; S3, drive the operating rod (22) to move away from the aircraft (3), and the limiting teeth (221) are disengaged from the arc-shaped outer teeth (31); S4, observe or record the pitch control condition of the aircraft (3).

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