A vertical flow bidirectional adjustable gust generating system

Abstract

The present invention provides a vertical flow bidirectional adjustable gust generating system, which relates to the technical field of low-speed wind tunnel test. The present invention comprises a support device, which is located outside the wind tunnel, the support device and the wind tunnel are independently arranged, and a first gap is arranged between the support device and the wind tunnel; a blade, which is located in the wind duct, and the blade comprises a body and a rotating rod, the rotating rod passes through the side wall of the wind tunnel and is rotatably connected to the support device; and a motor, which is arranged on the support device and is used to drive the blade to rotate. Compared with the prior art, the present invention has the advantages of being able to flexibly control the swing amplitude, frequency and phase of the blade, and being able to generate various types of gusts to meet more complex and diverse experimental needs.

Description

Technical Field

[0001] The present invention relates to the technical field of low-speed wind tunnel testing, and in particular to a vertical flow bidirectionally adjustable gust generating system. Background Art

[0002] Gusts are a critical factor affecting aircraft flight. Gusts are sudden changes in wind speed in a specific direction. The transient loads they generate can affect the aircraft's motion, significantly impacting flight quality and safety. Therefore, studying and reproducing gust effects is crucial for aircraft design and flight safety testing.

[0003] Existing wind tunnel gust generators typically use oscillating blades to simulate gusts. These devices use a mechanical transmission mechanism to drive the synchronous oscillation of multiple blades, adjusting the uniform airflow within the wind tunnel to a desired gust. However, traditional mechanical transmission methods, relying on transmission structures such as connecting rods, limit the blade's oscillation amplitude, frequency, and phase. This limitation limits conventional gust generators to generating only a limited number of gust types, making them difficult to meet the needs of more complex and diverse experiments. Summary of the Invention

[0004] In order to solve the above problems, the present application provides a vertical flow bidirectional adjustable gust generating system.

[0005] The present application provides a vertical flow bidirectional adjustable gust generating system, which adopts the following technical solutions:

[0006] A vertical flow bidirectional adjustable gust generating system is applied to a wind tunnel, wherein the wind tunnel has an air duct, comprising:

[0007] a supporting device, located outside the wind tunnel, the supporting device and the wind tunnel being independently provided with a first gap between the supporting device and the wind tunnel;

[0008] a blade located in the wind tunnel, the blade comprising a body and a rotating rod, the rotating rod passing through the side wall of the wind tunnel and being rotatably connected to the supporting device;

[0009] The motor is arranged on the supporting device and is used for driving the blades to rotate.

[0010] Preferably, the output shaft of the motor is coaxially connected to the rotating rod;

[0011] And / or, the motor is one of a servo motor and a stepper motor.

[0012] Preferably, the side wall of the wind tunnel is provided with a connecting hole, and the rotating rod passes through the connecting hole and is rotatably connected to the supporting device, wherein:

[0013] A second gap is provided between the rotating rod and the connecting hole;

[0014] And / or, in the axial direction of the rotating rod, a third gap is provided between the two ends of the body and the side wall of the wind tunnel.

[0015] Preferably, the connecting hole is located within the projection area of ​​the blade along the axial direction of the rotating rod.

[0016] Preferably, the body is detachably connected to the rotating rod, and the rotating rod includes a first end and a second end.

[0017] Preferably, the support device includes a main body and a first support part and a second support part arranged relative to the main body, the first support part is located on one side of the wind tunnel, the second support part is located on the other side of the wind tunnel, the first end is rotatably connected to the first support part, the second end is rotatably connected to the second support part, the first support part is detachably connected to the main body, and the first support part is detachably connected to the rotating rod.

[0018] Preferably, the side wall of the wind tunnel includes a first cover plate, the first cover plate is detachably mounted on the wind tunnel, the first cover plate is provided with the connecting hole, and the first cover plate is located close to the first end side.

[0019] Preferably, the main body is provided with a through hole, the rotating rod is slidably passed through the through hole, the first end can be passed from one end of the through hole to the other end, and the rotating rod is provided with a stopper, and the stopper and the main body are rotated and limited in the circumferential direction of the rotating rod.

[0020] Preferably, the gust generating system includes a first state and a second state;

[0021] When the gust generating system is in the first state, the number of the blades is two;

[0022] When the gust generating system is in the second state, the number of the blade is one;

[0023] The number of the motors is set in one-to-one correspondence with the number of the blades.

[0024] Preferably, the supporting device includes a first fixing position, a second fixing position and a third fixing position for fixing the motor, the second fixing position is located between the first fixing position and the third fixing position, the first fixing position is provided with a first bolt, and the third fixing position is provided with a second bolt;

[0025] When the gust generating system is in the first state, there are two motors, one of which is fixed to the first fixing position by a first bolt, and the other of which is fixed to the third fixing position by a second bolt;

[0026] When the gust generating system is in the second state, the motor is fixed in the second fixing position, and at least part of the first bolts and at least part of the second bolts fix the motor in the second fixing position.

[0027] The present invention has the following advantages and beneficial effects:

[0028] This application uses a motor to directly drive the blades, enabling flexible control of the blade's swing amplitude, frequency, and phase. This control process is unrestricted, allowing these parameters to be set arbitrarily. This innovation effectively overcomes the control limitations of existing technologies, enabling the generation of a variety of wind gusts to meet more complex and diverse experimental needs.

[0029] Furthermore, the support device and wind tunnel are independently installed, with a first gap between them to prevent mutual interference. The motor is mounted on the support device, allowing its vibration to be transmitted to the support device. This reduces the impact of vibration generated by the motor directly driving the blades on the blades and the wind tunnel, ensuring the accuracy of the test data. The support device is directly fixed to the ground, effectively buffering the vibration generated by the motor and further reducing interference with the experiment. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for use in the embodiments or the description of the prior art. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying any creative work.

[0031] Figure 1 This is a first structural diagram of an embodiment of the present application.

[0032] Figure 2 This is a second structural diagram of an embodiment of the present application.

[0033] Figure 3 It is a structural diagram when the first supporting part is hidden.

[0034] Figure 4 It is a structural diagram when the first cover is hidden.

[0035] Figure 5 It is a structural diagram of the gust generating system in the first state.

[0036] Figure 6 It is a structural diagram of the gust generating system when it is in the second state.

[0037] Figure 7 Schematic diagram of the distribution structure of the first, second and third fixed positions.

[0038] The following are marked in the figure:

[0039] 10. Wind tunnel; 11. Connecting hole; 12. First cover plate; 13. Air duct; 100. Support device; 110. First gap; 120. First support part; 130. Second support part; 140. First fixing position; 150. Second fixing position; 160. Third fixing position; 170. First bolt; 180. Second bolt; 190. Main body; 200. Blade; 210. Rotating rod; 211. Second gap; 212. First end; 213. Second end; 214. Stop member; 214a. Protrusion; 220. Main body; 221. Through hole; 222. Third gap; 223. Groove; 300. Motor. DETAILED DESCRIPTION

[0040] To make the objectives, technical solutions, and advantages of the present invention more apparent, the technical solutions of the present invention will be described in detail below. Obviously, the embodiments described are only some of the embodiments of the present invention, not all of them. Based on the embodiments of the present invention, all other implementations obtained by those of ordinary skill in the art without inventive effort are within the scope of protection of the present invention.

[0041] The terms "first," "second," and the like in the specification and claims of this application are used to distinguish similar objects, and are not used to describe a specific order or precedence. It should be understood that the terms used in this manner are interchangeable where appropriate, so that the embodiments of this application can be implemented in an order other than that illustrated or described herein, and that the objects distinguished by "first," "second," and the like are generally of the same type, and do not limit the number of objects; for example, the first object can be one or more. In addition, the term "and / or" in the specification and claims refers to at least one of the connected objects, and the character " / " generally indicates that the objects connected are in an "or" relationship.

[0042] During aircraft flight, mitigation control is crucial for ensuring safety and stability. Especially at high speeds, the impact of gusts on aircraft performance cannot be ignored. Therefore, in-depth research on aircraft behavior and response to gusts during high-speed flight is crucial. To accurately simulate these flight conditions, high-speed wind tunnel experiments are typically conducted, typically with wind speeds exceeding Mach 0.4.

[0043] To study the effects of gusts on aircraft flight, high-speed wind tunnels have been used to simulate gusts by installing blades designed to generate gusts. However, due to the high wind speeds in high-speed wind tunnels, existing technologies typically use a mechanical transmission system to drive the blades. This design not only reduces the direct impact of the power unit on blade movement but also effectively prevents the reverse push of high-speed airflow on the blades, thereby preventing damage to the power system due to overload.

[0044] The core design of the transmission system is to achieve unidirectional transmission, ensuring that power is used only to drive the blades and control their swing amplitude, frequency, and phase. When the blades are subjected to high-speed airflow, the transmission system prevents the reaction force from being transmitted to the power system, thereby ensuring the stability and safety of the power system. Therefore, a mechanical transmission device must be used between the blades and the power system to ensure precise blade control and safe operation of the power system. This structural design not only enhances experimental safety, but also provides an effective experimental platform for studying the impact of gusts on aircraft.

[0045] However, the inventors discovered that in low-speed wind tunnels (wind tunnels with wind speeds less than Mach 0.3), when simulating the impact of gusts on aircraft during takeoff, mechanical transmission devices are still used to drive the blades. This traditional design becomes less flexible and accurate under low-speed conditions. Since the impact of gusts on aircraft is more significant at low speeds, experiments often need to simulate more complex gust patterns. However, existing mechanical transmission devices have limitations in controlling the swing amplitude, frequency, and phase of the blades, making it difficult to meet more complex and diverse experimental needs. This means that in low-speed wind tunnels, existing control methods are no longer able to fully simulate the actual response of aircraft under complex meteorological conditions, limiting the effectiveness of the experiments and the reliability of the results.

[0046] To address these issues, this application provides a vertical flow, bidirectionally adjustable gust generation system. By directly driving the blades with an electric motor, the system can flexibly control the blade's swing amplitude, frequency, and phase, without any restrictions during the control process, enabling arbitrary setting of these parameters. This innovative design effectively overcomes the existing limitations of inflexible control in low-speed wind tunnels, enabling the generation of a variety of gust types to meet more complex and diverse experimental needs.

[0047] Furthermore, because the wind tunnel involved in this application is a low-speed wind tunnel, the forces acting on the blades in the wind tunnel are relatively small, and the motor will not lose control due to excessive wind speeds causing the blades to be pushed in the opposite direction by the airflow. This design prevents the blades from being pushed in the opposite direction by the wind, causing the motor to rotate accordingly, thereby ensuring the normal operation of the motor and the accuracy of blade control. This design ensures the stability and reliability of the control system during the experiment, and helps to more accurately simulate and study the impact of gusts on aircraft, especially the response under complex meteorological conditions during takeoff or low-speed flight.

[0048] The following combination Figures 1 to 7 A vertical flow bidirectional adjustable gust generating system provided in an embodiment of the present application is described in detail through specific embodiments and application scenarios.

[0049] An embodiment of the present application provides a vertical flow bidirectional adjustable gust generating system, which is applied to a wind tunnel 10, especially a low-speed wind tunnel 10, that is, a wind tunnel 10 with a wind speed of less than 0.3 Mach. In some embodiments, the wind tunnel 10 has an air duct 13 and side walls. It can be understood that the air duct 13 is surrounded by the side walls. Specifically, the side walls can be understood as the boundary portion of the air duct 13. Exemplarily, the wind tunnel 10 in the present application can be a reflow wind tunnel 10. This design not only makes the airflow evenly distributed in the air duct 13, but also effectively controls the wind speed and airflow direction, providing a more stable aerodynamic environment for the experiment. The design of the reflow wind tunnel 10 allows the airflow to circulate again after passing through the blades 200, which helps to improve the generation and control of gusts.

[0050] Reference Figure 1 、 Figure 2 The system includes a support device 100, blades 200, and a motor 300, wherein the motor 300 and the blades 200 are both mounted on the support device 100, that is, the support device 100 provides a mounting base for the blades 200 and the motor 300. The support device 100 is arranged outside the wind tunnel 10, and the support device 100 and the wind tunnel 10 are arranged independently of each other, and a first gap 110 is provided between the support device 100 and the wind tunnel 10. In other words, there is no direct contact between the support device 100 and the wind tunnel 10. When the support device 100 vibrates or shakes, the support device 100 will not directly cause the wind tunnel 10 to shake. This isolation effect avoids the shaking of the wind tunnel 10 to a certain extent, thereby maintaining the stability of the wind tunnel 10.

[0051] The independent placement of support device 100 ensures a more stable airflow within wind tunnel 10, preventing external vibrations from affecting experimental conditions. This stability is crucial for aerodynamic experiments, as even the slightest disturbance can lead to inaccurate experimental data. Therefore, the design of support device 100 not only improves the overall reliability of the system but also provides a more ideal environment for simulating the effects of gusts on aircraft.

[0052] In some embodiments, reference Figure 1 、 Figure 2 The blade 200 is located in the air duct 13 and includes a body 220 and a rotating rod 210. The rotating rod 210 passes through the side wall of the wind tunnel 10 and is rotatably connected to the support device 100. This design not only optimizes the installation of the blade 200 in the air duct 13, but also ensures its effective movement under the action of wind flow.

[0053] Specifically, blades 200 actively swing within duct 13, affecting the airflow therein. This swinging motion effectively simulates the characteristics of gusts. The through-hole design of the rotating rod 210 allows blades 200 to rotate freely without being affected by the internal structure of the wind tunnel 10. This structure effectively improves the response speed and flexibility of blades 200. By connecting the rotating rod 210 to the support device 100, the movement of blades 200 can be precisely controlled.

[0054] In some embodiments, reference Figure 1 、 Figure 2 , the motor 300 is arranged on the supporting device 100, and is used to drive the blades 200 to rotate. This design makes the connection between the motor 300 and the blades 200 tighter, ensuring the efficiency and stability of power transmission. Specifically, the motor 300 is connected to the blades 200 through the rotating rod 210, so that the power of the motor 300 can act directly on the blades 200. This structure allows the blades 200 to actively rotate in the air duct 13, thereby effectively changing the airflow in the air duct 13 and simulating the characteristics of gusts. Since the position of the motor 300 is close to the blades 200, it can reduce power loss and improve the response speed of the system.

[0055] This design not only allows blades 200 to flexibly adjust their swing amplitude, frequency, and phase according to experimental requirements, but also facilitates the generation of diverse gusts. The motor's adjustable capabilities allow experimenters to quickly adapt to varying experimental conditions, simulating gusts of varying intensities and patterns for more complex aerodynamic research.

[0056] For example, the motor 300 may be a motor capable of controlling the rotation angle and rotation speed. This design enables the experimenter to precisely adjust the rotation amplitude, frequency, and phase of the blade 200 to meet different experimental requirements.

[0057] Specifically, the motor 300, with its adjustable rotation angle and speed, flexibly controls the movement of the blades 200 within the air duct 13. This control capability not only enables precise adjustment of the blades' oscillation but also generates various gusts to simulate aircraft flight conditions under varying weather conditions. By adjusting the parameters of the motor 300 in real time, experimenters can quickly adapt to varying experimental scenarios and aerodynamic conditions, thereby obtaining more accurate and reliable experimental data.

[0058] According to an alternative embodiment, referring to Figure 1 、 Figure 2 , the output shaft of the motor 300 is coaxially connected to the rotating rod 210. This design enables the motor 300 to directly drive the rotating rod 210, thereby effectively controlling the movement of the blade 200.

[0059] Specifically, the motor 300 transmits power directly to the rotating rod 210 through the rotation of its output shaft, causing it to rotate synchronously. This coaxial connection reduces power loss during transmission, ensuring efficient energy transfer. This design also improves the system's response speed, enabling the blades 200 to quickly adapt to airflow changes and flexibly simulate various gust conditions.

[0060] Through a coaxial connection, the motor 300 can precisely adjust the angle and speed of the rotating rod 210, thereby achieving detailed control over the swing amplitude, frequency, and phase of the blade 200. This design allows experimenters to quickly adjust parameters in different experimental scenarios to meet the diverse needs of aerodynamic research.

[0061] According to an alternative embodiment, motor 300 is either a servo motor or a stepper motor. Servomotors are known for their high precision and fast response speed, making them suitable for applications requiring precise control of rotation angle and speed. By using a servo motor, the swing amplitude, frequency, and phase of blade 200 can be more finely adjusted, meeting the experimental requirements of complex gust simulations.

[0062] On the other hand, a stepper motor has better positioning accuracy and larger output torque, and is suitable for situations requiring step-by-step control. In some specific experiments, a stepper motor can accurately adjust the position of the blade 200 in discrete steps to meet specific experimental parameter requirements.

[0063] According to an alternative embodiment, referring to Figure 3 、 Figure 4The sidewall of the wind tunnel 10 is provided with a connection hole 11, through which a rotating rod 210 passes for rotational connection to the support device 100. A second gap 211 is provided between the rotating rod 210 and the connection hole 11. This design prevents the rotating rod 210 from directly contacting the sidewall of the wind tunnel 10 during rotation, effectively preventing vibration from the motor 300 from affecting the wind tunnel 10 and ensuring that vibration from the rotating blades 200 is not transmitted to the wind tunnel 10. This isolation helps maintain the stability of the airflow within the wind tunnel 10 and improves the reliability of the experimental results.

[0064] According to an alternative embodiment, referring to Figure 2 、 Figure 3 and Figure 4 A third gap 222 is defined between the ends of the main body 220 and the sidewalls of the wind tunnel 10 in the axial direction of the rotating rod 210. This design prevents the ends of the rotating rod 210 from contacting the sidewalls during blade 200 rotation, thereby preventing additional noise and vibration caused by friction between the rotating rod 210 and the sidewalls of the wind tunnel 10. This design not only improves the durability of the system but also helps reduce interference with experimental data, ensuring the accuracy of aerodynamic experiments.

[0065] By providing the second gap 211 and the third gap 222, this embodiment effectively optimizes the freedom of movement of the rotating rod 210, enhancing the stability and reliability of the system. This structural design provides a more ideal experimental environment for gust simulation in the low-speed wind tunnel 10, facilitating in-depth research on aircraft performance in complex weather conditions.

[0066] According to an optional embodiment, the connection hole 11 is located within the projected area of ​​the blade 200 along the axial direction of the rotating rod 210. This design ensures that the end surface of the blade 200 can effectively block the connection hole 11, thereby reducing the amount of airflow overflowing to the outside through the connection hole 11. This structural design is of great significance for improving the stability of the airflow in the air duct 13.

[0067] Specifically, during the rotation of the blade 200, its end face shielding the connection hole 11 effectively prevents some airflow from escaping through the connection hole 11, ensuring a more concentrated and stable airflow within the air duct 13. This airflow stability is crucial for gust simulation experiments because it reduces interference caused by airflow fluctuations, thereby improving the accuracy and reliability of experimental data.

[0068] By optimizing the position of connection hole 11, this embodiment achieves better airflow management and enhances the aerodynamic characteristics of wind tunnel 10. The shielding effect of blades 200 on connection hole 11 not only improves the overall performance of air duct 13 but also provides more ideal experimental conditions for aerodynamic experiments in low-speed wind tunnel 10, facilitating in-depth analysis of aircraft flight performance in complex weather conditions.

[0069] According to an alternative embodiment, referring to Figure 4 、 Figure 6 The body 220 is detachably connected to the rotating rod 210, and the rotating rod 210 includes a first end 212 and a second end 213. This design allows different bodies 220 to be easily replaced under different test requirements to generate different gust conditions.

[0070] Specifically, because different experiments may require simulating gusts of varying strength and characteristics, the shape and size of the body 220 may vary. The detachable connection allows experimenters to quickly replace the body 220, ensuring experimental flexibility and adaptability. This design greatly simplifies the process of replacing the body 220, reduces experimental preparation time, and thus improves experimental efficiency.

[0071] The detachable connection structure not only enhances the system's flexibility but also provides more possibilities for aerodynamic experiments, allowing experimenters to adjust the system to meet specific research needs. This flexibility is crucial for in-depth research on aircraft performance in complex weather conditions, helping to obtain more reliable and diverse experimental data.

[0072] According to an alternative embodiment, referring to Figure 1 、 Figure 2 、 Figure 3 、 Figure 4 and Figure 5 The support device 100 includes a main body 190 and a first support portion 120 and a second support portion 130 arranged relative to the main body 190. The first support portion 120 is located on one side of the wind tunnel 10, and the second support portion 130 is located on the other side of the wind tunnel 10. The first end 212 is rotatably connected to the first support portion 120, and the second end 213 is rotatably connected to the second support portion 130. The first support portion 120 is detachably connected to the main body 190, and the first support portion 120 is detachably connected to the rotating rod 210.

[0073] This design provides a stable support structure while ensuring the flexibility and adjustability of the rotating rod 210. Because the first support portion 120 and the main body 190 are detachably connected, researchers can easily maintain and adjust the support device 100. Furthermore, the detachable connection between the first support portion 120 and the rotating rod 210 simplifies replacement of the main body 220, further enhancing the adaptability and flexibility of the system.

[0074] The design of this support device 100 effectively supports the main body 220 in various experiments and ensures that the main body 220 maintains good stability during rotation. This structure not only enhances the overall reliability of the system but also provides more ideal experimental conditions for gust simulation in the low-speed wind tunnel 10, facilitating in-depth research on aircraft flight performance in complex weather conditions.

[0075] Specifically, a bearing, such as a ball bearing, is provided at the connection between the first end 212 and the first support portion 120. The inner ring of the bearing is fixed to the first end 212 of the rotating rod 210, while the outer ring is connected to the first support portion 120 by an interference fit. When the first support portion 120 needs to be separated from the rotating rod 210, the first support portion 120 can be removed from the main body 190. During this process, the first end 212 of the rotating rod 210 will be separated from the inner ring of the bearing, which means that the bearing will remain on the first support portion 120. When reinstalling, the first end 212 of the rotating rod 210 can be aligned with the inner ring of the bearing and the first support portion 120 can be installed back into the main body 190 to complete the rotational connection between the rotating rod 210 and the first support portion 120.

[0076] It is understandable that a similar bearing may also be provided at the rotational connection between the second end 213 and the second support portion 130 to achieve the corresponding rotation function.

[0077] According to an alternative embodiment, referring to Figure 3 、 Figure 4 The side wall of the wind tunnel 10 includes a first cover plate 12, which is detachably mounted on the wind tunnel 10. The first cover plate 12 is provided with a connection hole 11 and is located near the first end 212. This design significantly improves the convenience of replacing the body 220.

[0078] When replacing the main body 220, the experimenter only needs to open the first support portion 120 and then remove the first cover 12 to easily access the main body 220 in the air duct 13. This structural design not only reduces the tedious steps during the replacement process, but also greatly shortens the experimental preparation time and improves experimental efficiency.

[0079] The removable first cover 12 allows experimenters to quickly replace different bodies 220 to meet different experimental needs. This flexibility facilitates effective aerodynamic experiments under varying gust conditions, providing reliable technical support for in-depth research on aircraft performance in complex weather conditions.

[0080] According to an alternative embodiment, referring to Figure 4 、 Figure 6The body 220 is provided with a through-hole 221, through which the rotating rod 210 slides. The first end 212 can be extended from one end of the through-hole 221 to the other end. The rotating rod 210 is provided with a stopper 214, which cooperates with the body 220 to limit rotation in the circumferential direction of the rotating rod 210. The design of the through-hole 221 allows experimenters to easily remove the body 220 from the rotating rod 210, thereby simplifying the maintenance and replacement process. This structure provides support for experimental flexibility, allowing the system configuration to be quickly adjusted under different experimental conditions.

[0081] The provision of the rotation stop 214 ensures that the body 220 can rotate synchronously with the rotating rod 210, avoiding the situation where the body 220 and the rotating rod 210 cannot move in coordination when the rotating rod 210 rotates. This synchronous rotation design helps to improve the accuracy and reliability of the experiment, making the airflow simulation more accurate.

[0082] For example, referring to Figure 6 The rotation stop 214 can be a protrusion 214a provided on one of the rotating rod 210 or the main body 220, and the other is provided with a groove 223 that cooperates with the protrusion 214a. The protrusion 214a can be snapped into the groove 223 along the axial direction of the rotating rod 210, thereby achieving stable rotation restriction. This design not only enhances the overall stability of the system, but also provides more ideal experimental conditions for gust simulation in the low-speed wind tunnel 10, and helps to conduct in-depth research on the performance of aircraft under complex meteorological conditions. Moreover, through the cooperation of the protrusion 214a and the groove 223, the position of the main body 220 and the rotating rod 210 in the axial direction of the rotating rod 210 can be effectively limited. This design ensures that the main body 220 always remains in the predetermined position during the rotation process, thereby improving the stability of the system and the accuracy of operation.

[0083] According to an alternative embodiment, referring to Figure 3 、 Figure 5 The gust generating system includes a first state and a second state. When the gust generating system is in the first state, the number of blades 200 is two; when the gust generating system is in the second state, the number of blades 200 is one; the number of motors 300 is set in a one-to-one correspondence with the number of blades 200.

[0084] This design provides flexibility for the gust generation system, allowing the number of blades 200 to be quickly switched based on experimental requirements, generating gusts of varying intensities and characteristics. In the first state, two blades 200 can work together to simulate more complex airflow patterns; in the second state, a single blade 200 can be used for simpler gust simulations.

[0085] This state switching mechanism allows experimenters to effectively adjust to specific testing requirements, improving the adaptability and diversity of experiments. This structural design provides a richer range of simulation conditions for aerodynamic experiments in the low-speed wind tunnel 10, facilitating in-depth analysis of aircraft flight performance in various weather conditions.

[0086] According to an alternative embodiment, referring to Figure 5 、 Figure 7 The supporting device 100 includes a first fixing position 140, a second fixing position 150 and a third fixing position 160 for fixing the motor 300. The second fixing position 150 is located between the first fixing position 140 and the third fixing position 160. The first fixing position 140 is provided with a first bolt 170, and the third fixing position 160 is provided with a second bolt 180.

[0087] When the gust generation system is in the first state, there are two motors 300: one motor 300 is secured to the first fixing position 140 via a first bolt 170, and the other motor 300 is secured to the third fixing position 160 via a second bolt 180. In this state, the system can achieve dual-motor drive, improving the flexibility and strength of gust simulation.

[0088] When the gust generating system is in the second state, the motor 300 is fixed to the second fixing position 150, and at least some of the first bolts 170 and at least some of the second bolts 180 fix the motor 300 to the second fixing position 150. Here, at least some of the first bolts 170 may refer to all or some of the first bolts 170. At least some of the second bolts 180 may refer to all or some of the second bolts 180.

[0089] For example, referring to Figure 7 There are four first bolts 170 and four second bolts 180, with the four first bolts 170 distributed at the four corners of the first fixing location 140, and the four second bolts 180 distributed at the four corners of the third fixing location 160. It is noteworthy that the two first bolts 170 near the second fixing location 150 are located within the second fixing location 150, and the two second bolts 180 near the second fixing location 150 are also located within the second fixing location 150. These bolts located within the second fixing location 150 are precisely distributed at the four corners of the second fixing location 150, thereby enabling the motor 300 to be securely fixed to the fixing location via the first bolts 170 and second bolts 180 located within the second fixing location 150.

[0090] This design ensures that the center of gravity of the support device 100 remains at its center when the gust generating system is in both the first and second states. This design effectively prevents the center of gravity of the support device 100 from shifting, thereby reducing vibration or shaking caused by an unstable center of gravity. This means that during use, the support device 100 can maintain a high degree of stability, reducing unnecessary vibration during system operation and ensuring the accuracy and reliability of experimental data.

[0091] Overall, this structural design not only enhances the support effectiveness of the motor 300 under various operating conditions, but also optimizes the stability and operational ease of the overall gust generation system, providing a more reliable guarantee for gust simulation. This allows experimenters to focus more on data collection and analysis under various experimental conditions, promoting in-depth research.

[0092] The above description is only a specific embodiment of the present invention, but the scope of protection of the present invention is not limited thereto. Any technician familiar with this technical field can easily think of changes or replacements within the technical scope disclosed by the present invention, which should be covered by the scope of protection of the present invention.

Claims

1. A vertical flow bidirectional adjustable gust generating system, applied to a low-speed wind tunnel (10), wherein the wind tunnel (10) has an air duct (13), characterized in that: include: A support device (100) is located outside the wind tunnel (10), the support device (100) and the wind tunnel (10) are arranged independently of each other, and a first gap (110) is arranged between the support device (100) and the wind tunnel (10); a blade (200) located in the wind duct (13), the blade (200) comprising a body (220) and a rotating rod (210), the rotating rod (210) penetrating a side wall of the wind tunnel (10) and being rotatably connected to the supporting device (100); A motor (300), arranged on the supporting device (100), and used for driving the blade (200) to rotate; The output shaft of the motor (300) is coaxially connected to the rotating rod (210); The side wall of the wind tunnel (10) is provided with a connection hole (11), and the rotating rod (210) passes through the connection hole (11) and is rotatably connected to the supporting device (100), wherein: A second gap (211) is provided between the rotating rod (210) and the connecting hole (11); In the axial direction of the rotating rod (210), a third gap (222) is provided between the two ends of the body (220) and the side wall of the wind tunnel (10); The rotating rod (210) comprises a first end (212) and a second end (213); the supporting device (100) comprises a main body (190) and a first supporting portion (120) and a second supporting portion (130) arranged relative to the main body (190); the first supporting portion (120) is located on one side of the wind tunnel (10); the second supporting portion (130) is located on the other side of the wind tunnel (10); the first end (212) is rotatably connected to the first supporting portion (120); the second end (213) is rotatably connected to the second supporting portion (130); the first supporting portion (120) is detachably connected to the main body (190); and the first supporting portion (120) is detachably connected to the rotating rod (210).

2. A vertical flow bidirectional adjustable gust generating system according to claim 1, characterized in that: The motor (300) is one of a servo motor and a stepper motor.

3. A vertical flow bidirectional adjustable gust generating system according to claim 1, characterized in that: The connection hole (11) is located within a projection area of ​​the blade (200) along the axial direction of the rotating rod (210).

4. A vertical flow bidirectional adjustable gust generating system according to claim 1, characterized in that: The body (220) is detachably connected to the rotating rod (210).

5. A vertical flow bidirectional adjustable gust generating system according to claim 1 or 4, characterized in that: The side wall of the wind tunnel (10) comprises a first cover plate (12), the first cover plate (12) being detachably mounted on the wind tunnel (10), the first cover plate (12) being provided with the connecting hole (11), and the first cover plate (12) being located close to the first end (212).

6. A vertical flow bidirectional adjustable gust generating system according to claim 5, characterized in that: The body (220) is provided with a through hole (221), the rotating rod (210) is slidably inserted into the through hole (221), the first end (212) can be inserted from one end of the through hole (221) to the other end, and the rotating rod (210) is provided with a stopper (214), the stopper (214) and the body (220) are rotationally limitedly matched in the circumferential direction of the rotating rod (210).

7. A vertical flow bidirectional adjustable gust generating system according to claim 1, characterized in that: The gust generating system includes a first state and a second state; When the gust generating system is in a first state, the number of the blades (200) is two; When the gust generating system is in the second state, the number of the blade (200) is one; The number of the motors (300) and the number of the blades (200) are arranged in one-to-one correspondence.

8. A vertical flow bidirectional adjustable gust generating system according to claim 7, characterized in that: The supporting device (100) comprises a first fixing position (140), a second fixing position (150), and a third fixing position (160) for fixing the motor (300), the second fixing position (150) being located between the first fixing position (140) and the third fixing position (160), the first fixing position (140) being provided with a first bolt (170), and the third fixing position (160) being provided with a second bolt (180); When the gust generating system is in the first state, there are two motors (300), one of the motors (300) is fixed to the first fixing position (140) by a first bolt (170), and the other motor (300) is fixed to the third fixing position (160) by a second bolt (180); When the gust generating system is in a second state, the motor (300) is fixed to the second fixing position (150), and at least part of the first bolts (170) and at least part of the second bolts (180) fix the motor (300) to the second fixing position (150).

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