A single-chamber device with fast switching of circulation volume control and single-side blowing

Abstract

The present invention provides a single-cavity device for rapidly switching circulation control and single-side blowing, and relates to the technical field of active flow control. The present invention comprises an airfoil, which is arranged in the wing of an aircraft, wherein a jet plenum is provided throughout the airfoil, and the two ends of the airfoil respectively have an air source inlet and a jet outlet connected to the jet plenum; a circulation trailing edge module, which is movably arranged in the jet plenum and close to the jet outlet, wherein a first jet gap is formed between the circulation trailing edge module and the upper inner wall of the jet outlet, and a second jet gap is formed between the circulation trailing edge module and the lower inner wall of the jet outlet; and a driving mechanism, which is installed on the airfoil, and the driving mechanism is used to drive the circulation trailing edge module to rotate in the jet outlet. Compared with the prior art, the present invention has the advantage of improving the response frequency during aircraft control.

Description

Technical Field

[0001] The invention relates to the technical field of active flow control, and in particular to a single-cavity device for rapidly switching circulation volume to control single-side blowing. Background Art

[0002] In the design of traditional airfoils, a sharp trailing edge structure is usually used. However, the sharp trailing edge will prevent the airflow from bypassing the trailing edge at a limited speed on the upper surface and flowing to the lower surface. Due to this phenomenon, the airflow will separate near the trailing edge, thereby limiting the lift of the airfoil. At a certain angle of attack, flow separation will lead to a lack of maximum lift of the airfoil, which is a significant technical problem in aviation design.

[0003] In order to solve this problem, some designs propose to change the trailing edge shape of the airfoil to an arc shape to reduce the impact of airflow separation. The basic principle of this scheme is to set an airflow chamber inside the airfoil and open a small slit in front of the trailing edge of the upper airfoil, through which the airflow is ejected in the tangential direction. This kind of jet airflow is called a wall jet, which flows through the airfoil surface and forms a boundary layer, and then the airflow is transformed into a free jet at a distance from the surface. The characteristics of the wall jet vary with the changes in the jet velocity, jet direction, slot height, and the geometry and curvature radius of the trailing edge surface (i.e., Coanda surface).

[0004] This wall jet can deflect the airflow to a certain extent along the turning angle of the curved surface. Studies have shown that the deflection angle of the jet can reach 180° under certain conditions. The turning effect of this streamline is equivalent to the aerodynamic curvature of the airfoil surface, thereby increasing the circulation and lift, achieving an effect similar to that of a mechanical high-lift device. In particular, the jet can maintain attachment to the curved surface through the balance of pressure in the airflow and the centrifugal force formed around the curved surface. This phenomenon is called the Coanda Effect.

[0005] Compared with traditional mechanical lift devices, the maximum lift coefficient of the circulation-controlled airfoil is significantly improved. For example, the maximum lift coefficient of the circulation-controlled airfoil can be as high as 9, while the lift coefficient of a complex mechanical lift device is only 6. Therefore, circulation control technology provides a new solution for improving the lift of airfoils.

[0006] By setting a jet slit on the upper or lower surface of the airfoil, the jet airflow can change the flow characteristics around the airfoil and accurately control the lift and the position of the aerodynamic center according to the direction and strength of the jet airflow. If the airflow is ejected from the upper wing surface, it can increase the lift and improve the aerodynamic characteristics; while the airflow ejected from the lower wing surface can reduce the lift or change the position of the aerodynamic center. By accurately adjusting the strength and direction of the jet, the control functions of the aircraft can be realized in different flight states, including turning, pitching and rolling.

[0007] The advantage of this technology is that it reduces the reliance on traditional control surfaces and simplifies the structure of the aircraft. Taking steering control as an example, by strengthening the jet on one side of the upper wing and weakening the jet on the other side, the yaw control of the aircraft can be achieved. This design without external control surfaces not only reduces aerodynamic resistance, but also improves flight efficiency. In addition, by adjusting the jet intensity in real time, the aircraft can be flexibly controlled according to the flight status, making the aircraft more maneuverable and flexible.

[0008] The application of circulation control technology in the field of UAVs has shown its wide potential, especially when designing aircraft with high maneuverability and low radar cross-section characteristics. Circulation control technology without rudder surface has become a novel control method. This technology not only improves the lift performance of the aircraft through the characteristics of air jets and the Coanda effect, but also simplifies the design of the aircraft. With the continuous development of technology, circulation control technology is expected to be applied to more types of aircraft in the future.

[0009] Although circulation control technology has significant advantages in improving the lift and maneuverability of aircraft, there are still several technical difficulties in its implementation.

[0010] 1. Complexity of device design: Common forms of circulation control technology currently require a dual-cavity jet booster chamber and two separate air valves. This design not only occupies valuable space inside the aircraft, but also increases the complexity of the system. Especially under the compact design requirements of the aircraft, the rational use of space becomes particularly important. In addition, the complex system structure also increases the cost of manufacturing and maintenance.

[0011] 2. Limitation of response frequency: Existing circulation control systems usually have a low response frequency, which is particularly evident when the aircraft is flying at high speed. Due to the high instantaneous control requirements of the aircraft in flight, the circulation control system with a low response frequency is difficult to meet the instantaneous control requirements during fast flight, thus limiting the practical application of the technology, especially in scenarios that require rapid turning or rapid adjustment of flight attitude.

[0012] 3. Precise adjustment and switching of jets: The circulation control system requires precise adjustment and switching of jets, especially when the jets between the upper and lower wing surfaces need to be dynamically switched. Ensuring the stability and consistency of the jets is a technical challenge. In practical applications, the stability of the jet is affected by many factors, including the speed of the airflow, pressure changes, and the interaction between the airflow and the airfoil surface. These factors make precise adjustment of the jet a challenging task.

[0013] Comprehensive consideration of multiple issues: When developing a circulation control system, it is necessary not only to consider aerodynamic performance, but also to comprehensively consider multiple aspects such as structural strength, airtightness, and integrated design of the system. This requires that when designing the system, the reliability of the system and its adaptability in practical applications must be considered while ensuring performance. How to solve the complexity and stability of the system while maintaining technical advantages is a major challenge facing circulation control technology. Summary of the invention

[0014] In order to solve the problems of complexity and stability when using circulation control technology to control an aircraft, the present application provides a single-cavity device with fast switching circulation control and single-side blowing.

[0015] The present application provides a single-cavity device for rapidly switching circulation volume to control single-side blowing, which adopts the following technical solution:

[0016] A single-cavity device for rapidly switching circulation control and single-side blowing, comprising: an airfoil, arranged in the wing of an aircraft, a jet plenum chamber being provided through the airfoil, and an air source inlet and a jet outlet being respectively provided at two ends of the airfoil, the airfoil being connected to the jet plenum chamber; a circulation trailing edge module, movably arranged in the jet plenum chamber and close to the jet outlet, a first jet slit being formed between the circulation trailing edge module and the upper inner wall of the jet outlet, and a second jet slit being formed between the circulation trailing edge module and the lower inner wall of the jet outlet; a driving mechanism, mounted on the airfoil, the driving mechanism being used to drive the circulation trailing edge module to rotate in the jet outlet, wherein the circulation trailing edge module has at least a switchable first state and a second state under the drive of the driving mechanism, and when the circulation trailing edge module is in the first state, the first jet slit allows the jet to pass through, and the second jet slit restricts the jet from passing through; when the circulation trailing edge module is in the second state, the first jet slit restricts the jet from passing through, and the second jet slit allows the jet to pass through.

[0017] Preferably, the annular trailing edge module is provided with a rotating shaft along its own axial direction, and the rotating shaft is rotatably connected to the inner wall of the jet pressurization chamber.

[0018] Preferably, the circulation trailing edge module has a drainage portion, which is located on the side of the rotation axis away from the jet outlet; the drainage portion has a first inclined surface and a second inclined surface that are opposite to each other, and the first inclined surface and the second inclined surface respectively correspond to the two inner walls of the jet booster chamber, and along the flow direction of the jet, the gap between the first inclined surface and the second inclined surface and the inner wall of the jet booster chamber gradually increases, and the thickness of the drainage portion gradually decreases; when the circulation trailing edge module is in the first state, the end of the second inclined surface away from the jet outlet abuts against the inner wall of the jet booster chamber, and the end of the first inclined surface away from the jet outlet is separated from the inner wall of the jet booster chamber; when the circulation trailing edge module is in the second state, the end of the first inclined surface away from the jet outlet abuts against the inner wall of the jet booster chamber, and the end of the second inclined surface away from the jet outlet is separated from the inner wall of the jet booster chamber.

[0019] Preferably, the circulation trailing edge module also has a guide portion, which is located on the side of the rotation axis close to the jet outlet; the guide portion has a first curved surface and a second curved surface that are opposite to each other, the first curved surface and the second curved surface respectively correspond to the two inner walls of the jet booster chamber, along the flow direction of the jet, the gap between the first curved surface and the second curved surface and the inner wall of the jet booster chamber gradually decreases, and the thickness of the guide portion gradually increases; the first jet slit is formed between the first curved surface and the inner wall of the jet booster chamber, and the second jet slit is formed between the second curved surface and the inner wall of the jet booster chamber, wherein the first jet slit corresponds to the first inclined surface along the flow direction of the jet, and the second jet slit corresponds to the second inclined surface along the flow direction of the jet.

[0020] Preferably, the maximum thickness of the guide portion is smaller than the width of the jet outlet, so that the first jet slot and the second jet slot portions close to the jet outlet are always in an open state.

[0021] Preferably, the driving mechanism includes a driving member and a transmission member, the driving member is mounted on the outer side wall of the airfoil, one end of the transmission member is connected to the driving member, and the other end is connected to the rotating shaft, and the transmission member is used to transmit the driving force of the driving member to the rotating shaft to rotate the rotating shaft.

[0022] Preferably, the driving member includes a steering gear, an output shaft of the steering gear is arranged parallel to the rotating shaft, and the transmission member is connected between the rotating shaft and the output shaft of the steering gear, and is used for synchronously transmitting the rotation of the output shaft of the steering gear to the rotating shaft.

[0023] Preferably, the transmission member includes a first support rod, a connecting rod and a second support rod, the first support rod is vertically connected to the output shaft of the servo; one end of the rotating shaft extends outside the airfoil, and the second support rod is vertically connected to the end of the rotating shaft located outside the airfoil; the connecting rod has a first end and a second end, the first end of the connecting rod is hinged to the first support rod away from the output shaft of the servo, and the second end of the connecting rod is hinged to an end of the second support rod away from the rotating shaft.

[0024] Preferably, along the flow direction of the jet, the opening length from the gas source inlet to the jet outlet gradually increases and the opening width gradually decreases; and / or the jet outlet is configured as a long strip-shaped gap.

[0025] Preferably, the inner wall of the jet pressurization chamber is covered with a polytetrafluoroethylene layer, and the end of the annular trailing edge module smoothly contacts the inner wall of the jet pressurization chamber.

[0026] The present invention has the following advantages and beneficial effects:

[0027] The present application can accurately adjust the distribution of airflow and realize the rapid switching of unilateral blowing through the adjustable state switching (first state and second state) of the circulation trailing edge module, thereby optimizing the aerodynamic performance of the aircraft, enhancing the accuracy and response speed of flight control, and being able to flexibly respond to various aerodynamic requirements, especially under changing working conditions. Secondly, the smooth contact design between the circulation trailing edge module and the inner wall of the jet booster chamber, and the polytetrafluoroethylene layer covered on the inner wall of the jet booster chamber, effectively reduce friction and airflow turbulence, ensure the stability and consistency of the airflow, improve the control accuracy of the blowing effect, and avoid performance fluctuations caused by unstable airflow. Furthermore, the polytetrafluoroethylene inner wall coating improves the wear resistance, sealing and corrosion resistance of the device, prolongs the service life of the jet booster chamber, enhances the durability and reliability of the equipment, and is particularly suitable for long-term high-intensity working environments. Further, the drive mechanism is connected to the precise transmission member through the steering gear, realizes the synchronous transmission of the driving force, ensures the precise adjustment and rapid response of the circulation trailing edge module, and ensures the reliable switching of the device under different states. In general, the present invention not only improves the accuracy and stability of airflow control, but also improves the durability and reliability of the device, and has broad application prospects. BRIEF DESCRIPTION OF THE DRAWINGS

[0028] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. 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 creative work.

[0029] Figure 1 It is a schematic diagram of the structure of some implementation methods of the present application;

[0030] Figure 2 It is a partial cross-sectional view of some embodiments of the present application Figure 1 ;

[0031] Figure 3 It is a partial cross-sectional view of some embodiments of the present application Figure 2 ;

[0032] Figure 4 is a side view of some embodiments of the present application Figure 1 ;

[0033] Figure 5 yes Figure 4 A magnified view of part A in FIG.

[0034] Figure 6 is a side view of some embodiments of the present application Figure 2 ;

[0035] Figure 7 yes Figure 6 A magnified view of part B in FIG.

[0036] Figure 8 is a side view of some embodiments of the present application Figure 3 ;

[0037] Fig. 9 yes Figure 8 The enlarged view of the C part in FIG.

[0038] Fig.10 It is a partial schematic diagram for illustrating the driving mechanism of some embodiments of the present application.

[0039] The markings in the figure are:

[0040] 100, airfoil; 110, jet booster chamber; 120, air source inlet; 130, jet outlet; 200, circulation trailing edge module; 210, rotating shaft; 220, drainage portion; 221, first inclined surface; 222, second inclined surface; 230, guide portion; 231, first arcuate surface; 232, second arcuate surface; 300, first jet slot; 400, second jet slot; 500, driving mechanism; 510, driving member; 511, steering gear; 520, transmission member; 521, first support rod; 522, connecting rod; 523, second support rod. DETAILED DESCRIPTION

[0041] To make the purpose, technical solution and advantages of the present invention clearer, the technical solution of the present invention will be described in detail below. Obviously, the described embodiments are only part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other implementation methods obtained by ordinary technicians in this field without creative work belong to the scope of protection of the present invention.

[0042] The terms "first", "second", etc. in the specification and claims of the present application are used to distinguish similar objects, and are not used to describe a specific order or sequence. It should be understood that the data used in this way can be interchangeable under appropriate circumstances, so that the embodiments of the present application can be implemented in an order other than those illustrated or described here, and the objects distinguished by "first", "second", etc. are generally of one type, and the number of objects is not limited. For example, the first object can be one or more. In addition, "and / or" in the specification and claims represents at least one of the connected objects, and the character " / " generally indicates that the objects associated with each other are in an "or" relationship.

[0043] Please refer to Figure 1 to Figure 10 , the device includes an airfoil 100, a circulation trailing edge module 200 and a driving mechanism 500, wherein the airfoil 100 is arranged in the wing of an aircraft. Exemplarily, the aircraft here can refer to either an aircraft or an aircraft model. A jet plenum 110 is provided throughout the airfoil 100, and both ends of the airfoil 100 are respectively provided with an air source inlet 120 and a jet outlet 130 connected to the jet plenum 110. Exemplarily, after the gas enters the jet plenum 110 from the air source inlet 120, it flows out from the jet outlet 130 along the jet plenum 110.

[0044] At the same time, the circulation trailing edge module 200 is movably arranged in the jet plenum chamber 110 and close to the jet outlet 130, and a first jet slit 300 is formed between the circulation trailing edge module 200 and the upper inner wall of the jet outlet 130, and a second jet slit 400 is formed between the circulation trailing edge module 200 and the lower inner wall of the jet outlet 130. Exemplarily, the movement mode of the circulation trailing edge module 200 in the jet plenum chamber 110 is rotation. Of course, in other embodiments, it can also roll or move. The rotation of the circulation trailing edge module 200 in the jet plenum chamber 110 controls the airflow to pass through the first jet slit 300 or the second jet slit 400.

[0045] Furthermore, the driving mechanism 500 is mounted on the airfoil 100, and the driving mechanism 500 is used to drive the circular trailing edge module 200 to rotate in the jet outlet 130. Exemplarily, the circular trailing edge module 200 has at least a switchable first state and a second state under the drive of the driving mechanism 500. When the circular trailing edge module 200 is in the first state, the first jet slit 300 allows the jet to pass through, and the second jet slit 400 restricts the jet from passing through; when the circular trailing edge module 200 is in the second state, the first jet slit 300 restricts the jet from passing through, and the second jet slit 400 allows the jet to pass through.

[0046] On this basis, the device is provided with a jet plenum 110 that runs through the entire airfoil 100. By adopting a single-cavity design, the occupancy of the internal space of the wing by the traditional double-cavity structure is significantly reduced, and the structural layout of the overall device is effectively simplified, thereby providing greater freedom for the arrangement of other functional components of the aircraft. In addition, the single-cavity design reduces the manufacturing difficulty and system weight, and further improves the comprehensive performance of the aircraft. Secondly, through the upper and lower jet slits formed by the circulation trailing edge module 200 and the inner wall of the jet outlet 130, under the action of the driving mechanism 500, the circulation trailing edge module 200 can be flexibly switched between the first state and the second state, realizing the dynamic control of the upper jet slit and the lower jet slit. When the circulation trailing edge module 200 is in the first state, the airflow of the jet plenum 110 is discharged only through the upper jet slit, thereby realizing the circulation control of the upper wing surface; when the circulation trailing edge module 200 is switched to the second state, the airflow is discharged through the lower jet slit and acts on the lower wing surface, thereby realizing the circulation control of the lower wing surface. This two-way switching circulation control method can not only achieve rapid response, but also accurately adjust the lift and aerodynamic center according to the different requirements of the flight state, providing the aircraft with efficient control capabilities under various working conditions.

[0047] Furthermore, the use of a rotatable circulation trailing edge module 200 avoids the complexity of switching through multi-way air valves in traditional designs, which not only improves the response speed, but also significantly reduces the failure rate and maintenance cost of the system. This module achieves precise angle adjustment through the drive of the drive mechanism 500, so that the distribution of the jet in the jet slot is more uniform, and the flow characteristics of the jet are further optimized. This design can ensure the stability and consistency of the jet under high-speed flight conditions, thereby improving the reliability and durability of the circulation control device. At the same time, the clever application of the Coanda effect in the device of this embodiment enables the jet to flow along the curved surface of the circulation trailing edge module 200, enhances the attachment effect of the jet, further improves the lift coefficient, and thus significantly improves the aerodynamic performance of the aircraft.

[0048] In addition, the fast switching circulation control device of the present invention takes into account aerodynamic performance, structural strength, airtightness, system integration and other factors through an integrated design concept, and can reduce the aerodynamic resistance of the aircraft while achieving high lift and high maneuverability. Since there is no need for the participation of traditional rudders, the device simplifies the external structure of the aircraft and helps to reduce the radar cross section. By adjusting the intensity and direction of the jet in real time, the device can achieve flexible yaw, pitch and roll control during flight, providing the aircraft with high flexibility and adaptability, especially in complex flight missions. In summary, the present invention overcomes the shortcomings of the prior art through the innovative single-cavity structure design and the dynamic switching of the circulation trailing edge module 200, and has significant advantages in space utilization, response speed and system simplification. At the same time, it can significantly improve the control ability and aerodynamic performance of the aircraft, and has a wide range of practical application value and promotion prospects.

[0049] In some embodiments, Figure 4 , Figure 5 As shown, the circulation trailing edge module 200 is provided with a rotating shaft 210 along its own axial direction, and the rotating shaft 210 is rotatably connected to the inner wall of the jet plenum 110. Exemplarily, the rotating shaft 210 is arranged in the jet plenum 110 and close to the jet outlet 130, the cross-sectional shape of the jet outlet 130 is rectangular, and the length direction of the rotating shaft 210 is consistent with the length direction of the jet outlet 130.

[0050] In this way, the circulation trailing edge module 200 is provided with a rotating shaft 210 along its own axis, and is rotatably connected to the inner wall of the jet plenum chamber 110 through the rotating shaft 210, so that the circulation trailing edge module 200 can stably rotate in the jet outlet 130. This design not only simplifies the movement mode of the circulation trailing edge module 200, but also improves the stability of the module rotation, ensures the switching accuracy of the jet slit, and thus greatly improves the response speed and control accuracy of the device. In addition, the rotating shaft 210 is located in the jet plenum chamber 110 and close to the jet outlet 130. Through this layout, the disturbance of the jet flow field during the rotation of the circulation trailing edge module 200 can be effectively reduced, thereby maintaining the uniformity of the airflow distribution of the jet outlet 130, enhancing the attachment effect of the jet, and further improving the aerodynamic performance of the circulation control device.

[0051] At the same time, the jet outlet 130 is designed to be a rectangular cross-section, and the length direction of the rotating shaft 210 is consistent with the length direction of the jet outlet 130. This matching design can minimize the impact of cross-section changes on jet characteristics when the circulation trailing edge module 200 rotates, thereby ensuring the stability of the aerodynamic performance of the device under various working conditions. The jet outlet 130 with a rectangular cross-section also has better flow control capabilities, which helps to improve the directionality and efficiency of the jet, and provides a strong guarantee for the device to achieve efficient single-sided blowing control. Through this optimized design, the present invention not only further reduces the complexity of the system, but also significantly improves the reliability and durability of the device, and is particularly suitable for the field of aircraft aerodynamic control that requires high circulation control accuracy.

[0052] In some embodiments, in combination Figure 6 , Figure 7 The circulation trailing edge module 200 has a drainage portion 220, which is located on the side of the rotation axis 210 away from the jet outlet 130. Exemplarily, the drainage portion 220 has a first inclined surface 221 and a second inclined surface 222 that are separated from each other, and the first inclined surface 221 and the second inclined surface 222 correspond to the two inner side walls of the jet plenum 110 respectively. Along the flow direction of the jet, the gap between the first inclined surface 221 and the second inclined surface 222 and the inner side wall of the jet plenum 110 gradually increases, and the thickness of the drainage portion 220 gradually decreases.

[0053] Exemplarily, when the circulation trailing edge module 200 is in the first state, the end of the second inclined surface 222 away from the jet outlet 130 abuts against the inner wall of the jet booster chamber 110, and the end of the first inclined surface 221 away from the jet outlet 130 is separated from the inner wall of the jet booster chamber 110; when the circulation trailing edge module 200 is in the second state, the end of the first inclined surface 221 away from the jet outlet 130 abuts against the inner wall of the jet booster chamber 110, and the end of the second inclined surface 222 away from the jet outlet 130 is separated from the inner wall of the jet booster chamber 110.

[0054] On this basis, the design of the guide portion 220, including the relative arrangement of the first inclined surface 221 and the second inclined surface 222, enables the jet to transition more smoothly when switching states, avoiding the problems of sudden changes in airflow or uneven distribution that may occur in traditional designs. Specifically, the first inclined surface 221 and the second inclined surface 222 correspond to the two inner walls of the jet booster chamber 110, respectively, and the gap between them and the inner walls gradually increases, forming an orderly flow channel. As the gap gradually increases, the jet can maintain a stable flow velocity and direction when passing through the area, avoiding airflow disturbances near the jet outlet 130, thereby ensuring the stability of the jet. This flow channel design makes the jet switch between the two states smoother, avoids instability caused by sudden changes in airflow, and improves the control accuracy and response efficiency of the entire system.

[0055] Secondly, the thickness of the drainage portion 220 is gradually reduced, which further optimizes the flow of air. As the thickness decreases, the jet can pass through the drainage portion 220 more smoothly, reducing the friction loss of the airflow, thereby improving the efficiency of the system. This design effectively reduces the friction resistance between the annular trailing edge module 200 and the inner wall of the jet boost chamber 110, reduces energy loss, and allows the jet to be more effectively converted into lift and control force. This is crucial to the aerodynamic performance of the aircraft, especially when flying at high speed or in high-maneuverability operations, to ensure efficient use of the jet.

[0056] When the circulation trailing edge module 200 is in the first state, the end of the second inclined surface 222 away from the jet outlet 130 contacts the inner wall of the jet boost chamber 110, closing the second jet slit 400, and the first jet slit 300 is opened to allow the jet to pass through. This configuration can effectively control the direction and intensity of the jet, providing precise lift regulation and aerodynamic center control for the aircraft. When the module is switched to the second state, the first inclined surface 221 contacts the inner wall of the jet boost chamber 110, closing the first jet slit 300, and the second jet slit 400 is opened, thereby changing the discharge direction and intensity of the jet. This flexible switching mechanism can accurately control the lift distribution, aerodynamic center and control ability of the aircraft under different flight conditions.

[0057] The introduction of this technical feature not only improves the lift regulation performance of the aircraft, but also greatly enhances the controllability of the aircraft. For example, when a quick turn is required, the yaw and pitch of the aircraft can be precisely controlled by adjusting the direction and intensity of the jet. More importantly, the design can dynamically adjust the jet according to the flight status in real time, thereby providing the best control effect in different flight stages, reducing aerodynamic drag and improving flight efficiency.

[0058] In some embodiments, reference Figure 8 , Fig. 9The gap between the first curved surface 231 and the second curved surface 232 of the guide part 230 and the inner wall of the jet plenum chamber 110 gradually decreases, and the thickness of the guide part 230 gradually increases. This design gradually guides the jet in the flow direction, reducing the instability of the airflow. During the flow of the jet, the gradual change of the first curved surface 231 and the second curved surface 232 forms a smooth flow channel, which can ensure that the flow of the jet through the plenum chamber is more uniform and stable, thereby avoiding uneven airflow distribution and possible vortex or oscillation, ensuring that the jet can flow accurately in the predetermined direction and play a more efficient role in circulation control.

[0059] In addition, the first jet slit 300 and the second jet slit 400 correspond to the first inclined surface 221 and the second inclined surface 222 along the flow direction of the jet, respectively, further enhancing the smoothness and accuracy of the jet switching. When the circulation trailing edge module 200 is in different working states, the opening and closing of the jet slit can be precisely controlled, thereby precisely controlling the position of the lift and the aerodynamic center under different working conditions of the aircraft, ensuring that the aircraft can achieve the desired control effect.

[0060] The design of the guide portion 230 reduces unnecessary reflections and disturbances of the airflow in the jet plenum chamber 110 by optimizing the flow path of the jet, thereby effectively improving the utilization efficiency of the jet. In particular, in flight conditions that require rapid response and precise control, this design can greatly improve the dynamic response capability of the system, ensuring that the aircraft can quickly and stably adjust its flight attitude in a complex flight environment and improve its control performance. In addition, the design of the guide portion 230 can also reduce aerodynamic resistance and improve flight efficiency by providing a smoother jet flow path.

[0061] Therefore, the present invention not only makes the guidance of the jet more precise and smooth by adding a guide portion 230 to the circulation trailing edge module 200, but also enhances the adjustability and flexibility of the circulation control system, so that the aircraft can more accurately adjust the lift, aerodynamic center and control force under different flight conditions, significantly improving the control performance and flight efficiency of the aircraft, and having significant technical advantages.

[0062] In some embodiments, in combination Figure 5 , Figure 7 as well as Fig. 9, the maximum thickness of the guide portion 230 is smaller than the width of the jet outlet 130, so that the first jet slit 300 and the second jet slit 400 near the jet outlet 130 are always in an open state. In this way, the circulation trailing edge module 200 can rotate normally at the jet outlet 130. At the same time, when the airflow switches the state of the circulation trailing edge module 200, the jet slit will not be partially closed or blocked due to structural changes. By keeping the jet slit always open, it is ensured that the airflow can pass through the jet boost chamber 110 continuously and stably, avoiding lift fluctuations or unstable control caused by changes in airflow resistance.

[0063] In some embodiments, reference Figure 1 , Figure 3 as well as Fig.10 The driving mechanism 500 includes a driving member 510 and a transmission member 520. The driving member 510 is mounted on the outer wall of the airfoil 100. One end of the transmission member 520 is connected to the driving member 510 and the other end is connected to the rotating shaft 210. The transmission member 520 is used to transmit the driving force of the driving member 510 to the rotating shaft 210 to rotate the rotating shaft 210. Exemplarily, the driving mechanism 500 is mounted inside the airfoil 100 so that the driving mechanism 500 is not easily disturbed by airflow during the flight of the aircraft or the flying vehicle model, and stably provides driving force.

[0064] Exemplarily, the driving member 510 includes a servo 511 , the output shaft of the servo 511 is arranged parallel to the rotating shaft 210 , and the transmission member 520 is connected between the rotating shaft 210 and the output shaft of the servo 511 for synchronously transmitting the rotation of the output shaft of the servo 511 to the rotating shaft 210 .

[0065] Exemplarily, the transmission member 520 includes a first support rod 521, a connecting rod 522 and a second support rod 523, the first support rod 521 is vertically connected to the output shaft of the servo 511; exemplary, one end of the rotating shaft 210 extends outside the airfoil 100, and the second support rod 523 is vertically connected to an end of the rotating shaft 210 located outside the airfoil 100; further, the connecting rod 522 has a first end and a second end, the first end of the connecting rod 522 is hinged to the output shaft of the first support rod 521 away from the servo 511, and the second end of the connecting rod 522 is hinged to an end of the second support rod 523 away from the rotating shaft 210.

[0066] On this basis, the driving member 510 includes a steering gear 511, the output shaft of which is arranged in parallel with the rotating shaft 210, and the rotation of the steering gear 511 is synchronously transmitted to the rotating shaft 210 through the transmission member 520 to control the rotation of the circulation trailing edge module 200. As a driving source, the steering gear 511 has a high response speed and accuracy, and can quickly and accurately adjust the angle of the rotating shaft 210 in the dynamic environment of the aircraft. In this way, the opening and closing state of the jet slot can be accurately controlled, thereby adjusting the distribution of the airflow, thereby affecting the lift and aerodynamic performance.

[0067] The design of the transmission member 520 includes a first support rod 521, a connecting rod 522, and a second support rod 523. The first support rod 521 is vertically connected to the output shaft of the steering gear 511, and the second support rod 523 is connected to the outer end of the rotating shaft 210. The two end points of the connecting rod 522 are respectively hinged to the first support rod 521 and the second support rod 523, forming a flexible mechanical transmission structure. This structure can achieve accurate transmission of the rotational motion of the output shaft of the steering gear 511 to the rotating shaft 210 through a simple design of a support rod and a connecting rod 522, ensuring that the circulation trailing edge module 200 can quickly and reliably switch the opening and closing states of the jet slot under different flight conditions.

[0068] The design of the transmission mechanism provides higher integration and lower system complexity. Compared with the traditional mechanical control system, it reduces redundant components and space occupation, and improves the response speed and operation accuracy of the system. The direct drive of the servo 511 and the synchronous action of the transmission member 520 ensure that the rotating shaft 210 can complete accurate rotation in a short time and quickly switch the state of the circular trailing edge module 200, so as to flexibly adjust the airflow characteristics during flight to meet the needs of different flight missions. This design effectively improves the control performance of the aircraft, so that it can still maintain good aerodynamic characteristics and responsiveness in high-speed flight and complex flight environments, and has significant technical advantages.

[0069] In some embodiments, in combination Figure 1 , Figure 2 as well as Figure 3 , along the flow direction of the jet, the opening length from the air source inlet 120 to the jet outlet 130 gradually increases and the opening width gradually decreases; and / or, the jet outlet 130 is configured as a long strip of slit. After such a setting, the distribution and injection characteristics of the airflow are optimized. As the opening length gradually increases, the airflow from the air source inlet 120 can be evenly distributed when entering the jet booster chamber 110, avoiding the jet instability caused by uneven airflow. The design of gradually decreasing opening width can enhance the concentration of the airflow, so that the airflow can more accurately form a high-speed jet along the jet outlet 130, thereby improving the control effect of the jet on the surface of the airfoil 100.

[0070] In addition, the jet outlet 130 is configured as a long strip slit design, which effectively increases the controlled area of ​​the jet, so that the jet can form a uniform and stable airflow channel on the surface of the airfoil 100. This shape of the jet outlet 130 can optimize the boundary layer control of the airflow, improve the lift performance, and reduce the occurrence of airflow separation in practical applications, thereby reducing aerodynamic drag and improving the overall flight efficiency of the aircraft. The long strip slit design also has high adjustability and flexibility, and can adapt to the requirements for airflow intensity and distribution under different flight conditions, further enhancing the applicability and stability of the device in various flight environments.

[0071] In some embodiments, the inner wall of the jet plenum 110 is covered with a polytetrafluoroethylene layer, and the end of the loop trailing edge module 200 smoothly contacts the inner wall of the jet plenum 110. After such a configuration, the polytetrafluoroethylene layer, as a material with excellent wear resistance and corrosion resistance, can effectively reduce the friction of the airflow in the contact area between the inner wall of the jet plenum 110 and the loop trailing edge module 200, thereby reducing the wear or surface damage problems that may occur to the device under the action of high-speed airflow. This improvement in wear resistance can extend the service life of the device, especially during long-term, high-frequency flights or tests, to ensure the stable operation of the device.

[0072] Secondly, the low friction coefficient of the polytetrafluoroethylene layer enables the end of the annular trailing edge module 200 to slide smoothly in the jet plenum chamber 110, thereby reducing the turbulence and instability of the airflow. The smooth contact surface can ensure the flexibility and precise adjustment of the annular trailing edge module 200, avoiding control errors caused by excessive friction. In addition, the chemical stability of polytetrafluoroethylene also effectively reduces the corrosion of pollutants in the airflow to the device, further improving the reliability of the device. Furthermore, after the end of the annular trailing edge module 200 slides against the inner wall of the jet plenum chamber 110, it can still rotate, and the gap between the end of the annular trailing edge module 200 and the inner wall of the jet plenum chamber 110 is also blocked, improving the sealing performance.

[0073] In summary, the use of a polytetrafluoroethylene layer covering the inner wall of the jet booster chamber 110 and in smooth contact with the end of the circulation trailing edge module 200 can significantly improve the wear resistance, stability and airflow control accuracy of the device, provide the aircraft with more efficient and longer-lasting aerodynamic performance, and ensure the smooth operation of rapid switching of circulation control.

[0074] The above description is only a specific implementation mode of the present invention, but the protection scope of the present invention is not limited thereto. Any technician familiar with the technical field can easily think of changes or substitutions within the technical scope disclosed by the present invention, which should be covered by the protection scope of the present invention.

Claims

1. A single-chamber device with fast switching circulation control and single-side blowing, characterized in that: include: An airfoil (100) is arranged in a wing of an aircraft, a jet plenum (110) is provided through the airfoil (100), and two ends of the airfoil (100) are respectively provided with an air source inlet (120) and a jet outlet (130) which are connected to the jet plenum (110); a circular measuring trailing edge module (200) movably disposed in the jet plenum chamber (110) and close to the jet outlet (130); a first jet slit (300) is formed between the circular measuring trailing edge module (200) and the upper inner wall of the jet outlet (130); and a second jet slit (400) is formed between the circular measuring trailing edge module (200) and the lower inner wall of the jet outlet (130); A driving mechanism (500) is installed on the airfoil (100), and the driving mechanism (500) is used to drive the circular trailing edge module (200) to rotate in the jet outlet (130), wherein: The circulation trailing edge module (200) has at least a switchable first state and a second state under the drive of the driving mechanism (500); when the circulation trailing edge module (200) is in the first state, the first jet slit (300) allows the jet to pass through, and the second jet slit (400) restricts the jet from passing through; when the circulation trailing edge module (200) is in the second state, the first jet slit (300) restricts the jet from passing through, and the second jet slit (400) allows the jet to pass through; The annular trailing edge module (200) is provided with a rotating shaft (210) along its own axial direction, and the rotating shaft (210) is rotatably connected to the inner side wall of the jet plenum chamber (110); The annular trailing edge module (200) comprises a drainage portion (220), wherein the drainage portion (220) is located on a side of the rotating shaft (210) away from the jet outlet (130); The drainage portion (220) has a first inclined surface (221) and a second inclined surface (222) that are separated from each other, the first inclined surface (221) and the second inclined surface (222) respectively corresponding to two inner side walls of the jet plenum (110), and along the flow direction of the jet, the gap between the first inclined surface (221) and the second inclined surface (222) and the inner side wall of the jet plenum (110) gradually increases, and the thickness of the drainage portion (220) gradually decreases; When the annular trailing edge module (200) is in a first state, an end of the second inclined surface (222) away from the jet outlet (130) abuts against an inner wall of the jet plenum (110), and an end of the first inclined surface (221) away from the jet outlet (130) is separated from the inner wall of the jet plenum (110); When the annular trailing edge module (200) is in the second state, an end of the first inclined surface (221) away from the jet outlet (130) abuts against the inner wall of the jet plenum chamber (110), and an end of the second inclined surface (222) away from the jet outlet (130) is separated from the inner wall of the jet plenum chamber (110).

2. A single-cavity device for rapid switching of circulation volume control and single-side blowing according to claim 1, characterized in that: The circulation trailing edge module (200) further comprises a guide portion (230), wherein the guide portion (230) is located on a side of the rotation axis (210) close to the jet outlet (130); The guide portion (230) has a first curved surface (231) and a second curved surface (232) that are separated from each other, the first curved surface (231) and the second curved surface (232) respectively corresponding to two inner side walls of the jet plenum (110), and along the flow direction of the jet, the gap between the first curved surface (231) and the second curved surface (232) and the inner side wall of the jet plenum (110) gradually decreases, and the thickness of the guide portion (230) gradually increases; The first jet slit (300) is formed between the first curved surface (231) and the inner wall of the jet pressurizing chamber (110), and the second jet slit (400) is formed between the second curved surface (232) and the inner wall of the jet pressurizing chamber (110), wherein the first jet slit (300) corresponds to the first inclined surface (221) along the flow direction of the jet, and the second jet slit (400) corresponds to the second inclined surface (222) along the flow direction of the jet.

3. A single-cavity device for rapid switching of circulation volume control and single-side blowing according to claim 2, characterized in that: The maximum thickness of the guide portion (230) is smaller than the width of the jet outlet (130), so that the portions of the first jet slit (300) and the second jet slit (400) close to the jet outlet (130) are always in an open state.

4. A single-cavity device for rapidly switching circulation control and single-side blowing according to claim 1, characterized in that: The driving mechanism (500) comprises a driving member (510) and a transmission member (520); the driving member (510) is mounted on an outer side wall of the airfoil (100); one end of the transmission member (520) is connected to the driving member (510) and the other end is connected to the rotating shaft (210); the transmission member (520) is used to transmit the driving force of the driving member (510) to the rotating shaft (210) so as to rotate the rotating shaft (210).

5. A single-cavity device for rapidly switching circulation control and single-side blowing according to claim 4, characterized in that: The driving member (510) comprises a steering gear (511), wherein an output shaft of the steering gear (511) is arranged in parallel with the rotating shaft (210), and the transmission member (520) is connected between the rotating shaft (210) and the output shaft of the steering gear (511) and is used for synchronously transmitting the rotation of the output shaft of the steering gear (511) to the rotating shaft (210).

6. A single-cavity device for rapidly switching circulation control and single-side blowing according to claim 5, characterized in that: The transmission member (520) comprises a first support rod (521), a connecting rod (522) and a second support rod (523); the first support rod (521) is vertically connected to the output shaft of the steering gear (511); One end of the rotating shaft (210) extends outside the airfoil (100), and the second support rod (523) is vertically connected to one end of the rotating shaft (210) located outside the airfoil (100); The connecting rod (522) has a first end and a second end, the first end of the connecting rod (522) being hinged to an output shaft of the first support rod (521) away from the steering gear (511), and the second end of the connecting rod (522) being hinged to an end of the second support rod (523) away from the rotating shaft (210).

7. A single-cavity device for rapidly switching circulation control and single-side blowing according to any one of claims 1 to 6, characterized in that: Along the flow direction of the jet, the opening length from the gas source inlet (120) to the jet outlet (130) gradually increases, and the opening width gradually decreases; And / or, the jet outlet (130) is configured as a long strip-shaped slit.

8. A single-cavity device for rapidly switching circulation control and single-side blowing according to any one of claims 1 to 6, characterized in that: The inner side wall of the jet plenum (110) is covered with a polytetrafluoroethylene layer, and the end of the annular trailing edge module (200) smoothly contacts the inner side wall of the jet plenum (110).

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