Circulation control airfoil profile of Coanda hyperbolic wall configuration and method

Abstract

The invention relates to a circular rector control airfoil profile of a Coanda hyperbolic wall configuration and a method. The structure comprises an airfoil main body, wherein a first Coanda curved wall and a second Coanda curved wall are arranged at the tail part of the airfoil main body; a jet flow channel is arranged in the airfoil main body, is connected to the first Coanda curved wall and the second Coanda curved wall, and forms jet flow outlets in the wall surface of the first Coanda curved wall and the wall surface of the second Coanda curved wall respectively; a control piece is hinged to the jet flow outlet; based on airflow blown out of the jet flow channel, the control piece moves around the hinged end. According to the invention, the circular rector control can be effectively enhanced, the lift force is improved, the attitude control precision is optimized, and the adaptability of the aircraft in a complex environment is improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aircraft, in particular to a circulation control airfoil of a Coanda hyperbolic wall configuration and a method thereof. Background Art

[0002] With the continuous advancement of aviation technology, aircraft design has gradually evolved from single-purpose aircraft to multi-mission, multi-scenario adaptability. However, traditional fixed-wing aircraft, helicopters, and multi-rotor aircraft often struggle to simultaneously meet multiple performance requirements, such as short takeoff and landing, high-speed level flight, and flexible control, when faced with diverse mission demands. The limitations of traditional aircraft layouts are becoming increasingly apparent, especially in terms of takeoff and landing and maneuverability in complex environments.

[0003] In addition, in the field of aerodynamics, active flow control technology has received widespread attention in recent years. It achieves precise control of aerodynamic forces by changing the flow field structure, providing a new approach for optimizing aircraft performance. However, existing active flow control technologies still have many shortcomings. For example, some jet drones have difficulty controlling airflow at high speeds due to their small jet flow rate, and cannot be efficiently integrated in practical applications. In addition, how to achieve efficient flow control within a limited aircraft volume while taking into account the different needs of take-off, landing and cruising stages remains a technical problem that needs to be solved urgently. The Coanda effect, as an effective fluid wall attachment phenomenon, has been widely used in the field of flow control.

[0004] In the existing technology, it is difficult for the circular airfoil using the Coanda effect to make the jet adhere perfectly to the wall surface. The design of the circular airfoil is based on the premise of destroying the original airfoil tip tail configuration, but it is impossible to reasonably utilize most of the angles of the Coanda wall to achieve attachment. Therefore, how to solve the above problems through innovative aerodynamic layout design and mechanical structure remains a very challenging problem. Summary of the Invention

[0005] Based on this, it is necessary to provide a circulation control airfoil and method of a Coanda hyperbolic wall configuration that can effectively utilize the Coanda wall and improve the adaptability of the aircraft in complex environments to address the above technical problems.

[0006] A circulation control airfoil of a Coanda double-curved wall configuration comprises an airfoil main body, a first Coanda curved wall and a second Coanda curved wall are arranged at the tail of the airfoil main body; A jet channel is provided in the airfoil body, the jet channel is connected to the first Coanda curved wall and the second Coanda curved wall, and jet outlets are formed on the wall surface of the first Coanda curved wall and the wall surface of the second Coanda curved wall respectively; On the jet outlet, a control member is hinged; based on the airflow blown out from the jet channel, the control member moves around the hinge end.

[0007] A circulation control method for a Coanda hyperbolic wall configuration, the method comprising: When there is no jet action, the control member closes the jet outlet; When there is jet action, the airflow blown out through the flow channel acts on the control member, and the control member is forced to move outward around the hinge end, and the jet outlet is opened; after the airflow is blown out, it adheres to the curved wall according to the Coanda effect, wherein the airflow blown out from the first jet outlet adheres to the second Coanda curved wall, and the airflow blown out from the second jet outlet adheres to the first Coanda curved wall; By controlling the opening and closing of the first jet outlet and / or the second jet outlet, the control of the aircraft is realized.

[0008] Compared with the prior art, the circulation control airfoil and method for a Coanda hyperbolic wall configuration provided by the present invention have the following beneficial effects: 1. When the airflow is blown out from the jet outlets of the first Coanda curved wall and the second Coanda curved wall through the jet channel, the control member moves around the hinge end to open, and the airflow adheres to the surface of the curved wall and flows due to the Coanda effect, forming an additional circulation around the airfoil, significantly improving the lift coefficient; in addition, the hyperbolic wall design can form a cross-circulation enhancement effect, further strengthening the pressure difference between the upper and lower surfaces of the airfoil and effectively enhancing the circulation control.

[0009] 2. The control member realizes stepless rotation through the air pressure, and the aerodynamic characteristics of the airfoil can be continuously changed, improving the fineness and response speed of flight control; by controlling the movement of the control members on the first Coanda curved wall and the second Coanda curved wall simultaneously or separately, the opening and closing of the jet outlet are controlled, so as to adjust the position of the curved wall where the flow adheres and the circulation distribution, which can effectively increase the lift and optimize the attitude control accuracy, and improve the adaptability of the aircraft in a complex environment.

[0010] 3. The design of the hyperbolic wall can make full use of most of the angles of the Coanda wall surface as much as possible, delay the separation point from moving backward, and enable the airfoil to maintain attached flow at a higher angle of attack.

[0011] 4. The complex mechanical structure of the traditional rudder surface is cancelled, the overall structure is simple and compact, which can effectively reduce the maintenance cost, improve the system reliability, and has the characteristics of light weight. At the same time, its excellent aerodynamic characteristics and maneuverability expand the flight envelope and provide more extensive application possibilities. Brief Description of the Drawings

[0012] To more clearly illustrate the technical solutions in the embodiments of the present invention or in the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, without creative efforts, other drawings can also be obtained based on the structures shown in these drawings.

[0013] Figure 1 Schematic diagram of the circulation control airfoil structure with Coanda hyperbolic wall configuration provided in one embodiment; Figure 2 Schematic diagram of the circulation control airfoil structure with Coanda hyperbolic wall configuration arranged on the wing in one embodiment; Figure 3 Schematic diagram of the traditional Coanda wall structure in one embodiment; Figure 4 Schematic diagram of the working principle of the circulation control airfoil with Coanda hyperbolic wall configuration provided in one embodiment; Figure 5 Schematic diagram of the action mechanism after arranging the circulation control airfoil with Coanda hyperbolic wall configuration at the rear of the main wing of the three-section wing in one embodiment; Figure 6 Overall flow field velocity cloud map after applying control through the circulation control airfoil with Coanda hyperbolic wall configuration provided in one embodiment; Figure 7 Local flow field velocity cloud map after applying control through the circulation control airfoil with Coanda hyperbolic wall configuration provided in one embodiment.

[0014] Explanation of reference numerals: Airfoil body 1, Coanda hyperbolic wall configuration 2, first Coanda curved wall 21, second Coanda curved wall 22, first jet outlet 31, second jet outlet 32, upper jet channel wall surface 41, lower jet channel wall surface 42, first jet channel 43, second jet channel 44, transition surface 45, first control member 51, second control member 52, pivot member 6.

[0015] The realization of the object, functional features, and advantages of the present invention will be further described in conjunction with the embodiments with reference to the drawings. Detailed implementation manners

[0016] Next, the technical solutions in the embodiments of the present invention will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all embodiments. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0017] It should be noted that all directional indications (such as up, down, left, right, front, back...) in the embodiments of the present invention are only used to explain the relative positional relationship and movement conditions between components in a specific posture. If the specific posture changes, the directional indications will also change accordingly.

[0018] In addition, the descriptions such as "first" and "second" in the present invention are only for descriptive purposes, and cannot be understood as indicating or implying their relative importance or implicitly indicating the quantity of the indicated technical features. Thus, the features defined with "first" and "second" may explicitly or implicitly include at least one of such features. In the description of the present invention, "a plurality" means at least two, such as two, three, etc., unless otherwise specifically defined.

[0019] In the present invention, unless otherwise clearly defined and limited, the terms "connection", "fixation", etc. shall be understood in a broad sense. For example, "fixation" may be a fixed connection, a detachable connection, or integrated; it may be a mechanical connection, an electrical connection, a physical connection or a wireless communication connection; it may be directly connected, or indirectly connected through an intermediate medium, and may be the internal connection of two components or the interaction relationship between two components, unless otherwise clearly defined. For those of ordinary skill in the art, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0020] It can be understood that the technical solutions between the various embodiments of the present invention can be combined with each other, but it must be based on the ability of those of ordinary skill in the art to implement. When the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such a combination of technical solutions does not exist and is not within the protection scope required by the present invention.

[0021] Next, the embodiments of the present invention will be described in detail in conjunction with the accompanying drawings in the embodiments of the present invention.

[0022] Embodiment 1 As Figure 1 And Figure 2As shown in the figure, this embodiment discloses a circulation control airfoil with a Coanda hyperbolic wall configuration, including an airfoil body 1, and a Coanda hyperbolic wall configuration 2 is arranged at the tail of the airfoil body 1. The Coanda hyperbolic wall configuration 2 includes a first Coanda curved wall 21 and a second Coanda curved wall 22. A jet channel is arranged in the airfoil body 1. The jet channel is connected to the first Coanda curved wall 21 and the second Coanda curved wall 22, and jet outlets are respectively formed on the wall surfaces of the first Coanda curved wall 21 and the second Coanda curved wall 22. A control member is hinged on the jet outlet. Based on the airflow blown out of the jet channel, the control member moves around the hinge end.

[0023] Specifically, the first Coanda curved wall 21 and the second Coanda curved wall 22 have the same structure and are symmetrically arranged along the central axis of the airfoil body 1. Among them, the first Coanda curved wall 21 is arranged above, and the second Coanda curved wall 22 is arranged below. The lower curved surface of the first Coanda curved wall 21 and the upper curved surface of the second Coanda curved wall 22 form an intersection point O on the central axis. The connection between the upper curved surface of the first Coanda curved wall 21 and the upper surface of the airfoil body 1, and the connection between the lower curved surface of the second Coanda curved wall 22 and the lower surface of the airfoil body 1 are evenly transitioned and are smooth transition curves, which can be calculated and generated by the smooth transition curve fitting method of cubic Bezier curves.

[0024] A first jet outlet 31 is opened on the first Coanda curved wall 21, and a second jet outlet 32 is opened on the second Coanda curved wall 22. The first jet outlet 31 is located on the lower curved surface of the first Coanda curved wall 21; the second jet outlet 32 is located on the upper curved surface of the second Coanda curved wall 22. The first jet outlet 31 and the second jet outlet 32 are arranged close to the intersection point O. Among them, the central axis of the first jet outlet 31 is consistent with the slope of the upper curved surface of the second Coanda curved wall, and the central axis of the second jet outlet 32 is consistent with the slope of the lower curved surface of the first Coanda curved wall 21, so as to ensure that the airflow blown out of the first jet outlet 31 adheres better to the surface of the second Coanda curved wall with curvature based on the Coanda effect, and the airflow blown out of the second jet outlet 32 adheres better to the surface of the first Coanda curved wall with curvature based on the Coanda effect.

[0025] It can be understood that the Coanda wall surface realizes fluid traction due to the Coanda effect, but as Figure 3As shown, the traditional Coanda wall cannot make the air flow fully adhere to the upper wall or the lower wall. Through the Coanda hyperbolic wall configuration 2 design of the present invention, the upper surface of the first Coanda curved wall 21 and the lower surface of the second Coanda curved wall 22 are both streamlined designs, which can enable the air flow to flow smoothly, and the first jet outlet 31 is located on the lower surface of the first Coanda curved wall 21; the second jet outlet 32 is located on the upper surface of the second Coanda curved wall 22, which can enable the air flow to act better on the Coanda curved wall, thereby effectively utilizing most angles of the Coanda wall and enhancing the circulation control effect.

[0026] Inside the airfoil body 1, a jet channel is arranged near the tail position, and the jet channel is enclosed by an upper jet channel wall surface 41 and a lower jet channel wall surface 42. In this embodiment, two jet channels are arranged, namely a first jet channel 43 and a second jet channel 44. The first jet channel 43 and the second jet channel 44 are arranged in parallel, have the same structure, and are symmetric about the central axis of the airfoil body 1. Among them, one end of the first jet channel 43 and the second jet channel 44 is communicated with a jet air source, and the other ends are respectively communicated with the first jet outlet 31 and the second jet outlet 32. The lengths and widths of the first jet channel 43 and the second jet channel 44 are designed according to the specific situation of the jet.

[0027] As can be seen from the figure, in this embodiment, the width of the jet channel is the same as the width of the jet outlet. Such a design can make the air flow velocity stable, the wall attachment effect uniform, and can form a uniform circulation distribution. When the stable air flow acts on the control member, it can make the rotational torque around the hinge end uniform, and avoid the jitter or impact of the control member caused by the sudden change of the flow velocity.

[0028] The first jet channel 43 and the first jet outlet 31, and the second jet channel 44 and the second jet outlet 32 are designed to have a height difference. When a height difference is set, a smooth transition surface 45 is arranged at the height difference to connect. Further, the transition surface 45 is an arc surface. The setting of having a height difference between the jet channel and the jet outlet can avoid the direct injection of radar signals during the opening of the control member, thereby realizing the covering effect of the jet channel.

[0029] It should be noted that when the first jet channel 43 and the first jet outlet 31, and the second jet channel 44 and the second jet outlet 32 are set to have a height difference, it is necessary to ensure that the air flow blown out from the jet channel blows out along the slope of the central axis of the jet outlet to ensure that it can be effectively attached to the Coanda curved wall.

[0030] The control member includes a first control member 51 and a second control member 52; the first control member 51 is hinged on the first jet outlet 31, and the second control member 52 is hinged on the second jet outlet 32.

[0031] The first control member 51 and the second control member 52 can adopt multiple groups of rotatable vanes. When multiple groups of rotatable vanes are adopted, any device that can cause passive induced jet deflection, such as array-adjustable guide vanes or array-variable geometry vanes, can be used; the multiple groups of rotatable vanes are hinged, and the vanes cover the jet outlet. Then, through the control of a driving member, such as a motor, the vanes can be deflected left and right or up and down, so as to realize the up and down or left and right deflection of the jet flow at the outlet, and further realize circulation control. The fixing method and driving method of the multiple groups of rotatable vanes are conventional designs and will not be elaborated here.

[0032] The first control member 51 and the second control member 52 can also adopt spring plates. When spring plates are adopted, the spring plates are hinged to the side wall of the jet outlet through elastic members, so that the control member can rotate relative to the jet outlet around the pivot member 6. Specifically, a pivot member 6 is arranged on the side wall of the jet outlet; the elastic member is sleeved on the pivot member 6, and the elastic member is fixedly connected to the pivot member 6; the end of the elastic member is connected to the control member. The elastic member has a natural state and a stressed state; when air flow blows out, the control member moves outward under force, applies a force to the movable end of the elastic member, and causes the elastic member to undergo elastic deformation and be in a stressed state; when no air flow blows out, the elastic member returns to the natural state, driving the control member to fit and close the jet outlet, forming a complete streamline curved wall.

[0033] More specifically, both the first jet outlet 31 and the second jet outlet 32 have an upper side wall and a lower side wall, and the lower side wall of the first jet outlet 31 intersects the upper side wall of the second jet outlet 32 at the intersection point O. The upper end of the first spring plate is hinged to the upper side wall of the first jet outlet 31 through the combination of the pivot member 6 and the elastic member, and the lower end is a free end. When the elastic member is in the natural state, its lower end contacts and fits with the lower side wall of the first jet outlet 31 and is connected to the curved surface contour of the first Coanda wall 21 to form a complete streamline curved surface to ensure the integrity of the aerodynamic shape of the airfoil tail.

[0034] The lower end of the second spring plate is hinged to the lower side wall of the second jet outlet 32 through the combination of the pivot member 6 and the elastic member, and the upper end is a free end. When the elastic member is in the natural state, its upper end contacts and fits with the upper side wall of the second jet outlet 32 and is connected to the curved surface contour of the second Coanda wall 22 to form a complete streamline curved surface to ensure the integrity of the aerodynamic shape of the airfoil tail.

[0035] The shapes of the first spring plate and the second spring plate are respectively adapted to the lower curved surface of the first Coanda wall 21 and the upper curved surface of the second Coanda wall 22, so that they can fit well on the curved wall when closed. The elastic member is preferably a torsion spring, and the pivot member 6 is preferably a roller. The control member in this embodiment is preferably in the form of a spring plate.

[0036] In addition, a jet air source is connected inside the jet channel; and / or an acceleration sensor is arranged on the surface of the main structure; and / or a controller is arranged on the main structure. The jet air source can be set to one or two. When set to one, it is respectively connected to the first jet channel 43 and the second jet channel 44, and then the on-off control is respectively carried out through the control module of the jet air source. When set to two, it is respectively connected to the first jet channel 43 and the second jet channel 44, and the on-off control is carried out through the control module of the jet air source. The jet air source includes, but is not limited to, any device such as an air tank, a high-pressure gas cylinder, a compressor air extraction device, and a diaphragm.

[0037] The acceleration sensor is mainly arranged on the outer surface of the aircraft, the wing body or the flap to measure the flow separation state of the aircraft during high-speed flight.

[0038] The controller is electrically connected to the acceleration sensor and the control module of the jet air source respectively to adjust the wing angle of attack and the jet intensity at the jet outlet according to the flow separation state of the aircraft and achieve closed-loop control. The control module of the jet air source is mainly a power supply or a valve controller. It should be noted that the settings of the jet air source, the acceleration sensor, and the controller are conventional settings and will not be elaborated here.

[0039] During operation, after the acceleration sensor measures the state of the aircraft under flow separation, it transmits the longitudinal acceleration of the aircraft to the controller. Subsequently, the controller controls the control module of the jet air source according to the real-time longitudinal acceleration of the aircraft, adjusts the jet size, thereby controlling the change in the energy of the blown jet. The change in the jet energy will change the flow field structure of the aircraft and then change the lift coefficient of the aircraft; the above adjustment is used to change the longitudinal acceleration of the aircraft and finally achieve closed-loop control.

[0040] It can be understood that the Coanda hyperbolic wall configuration 2 proposed by the present invention is mainly applied to the tail of the airfoil body 1. The airfoil body 1 includes, but is not limited to, the tail of the wing, the rear end of the main wing of the multi-segment wing, or the rear of the flap, etc.

[0041] As Figure 4 shown, it is a schematic diagram of the working principle of the circulation control airfoil of the Coanda hyperbolic wall configuration. A high-speed jet is ejected from the first jet outlet 31. The first control member 51 is blown open with the pivot member 6 on the upper side as the center. The second control member 52 is in the closed state at this time, maintaining the overall streamline of the second Coanda curved wall 22. The high-speed jet adheres to the second Coanda curved wall 22 according to the Coanda effect, realizing the downward deviation of the mainstream on the outer side of the wing and achieving the lift augmentation effect similar to a "virtual flap". This is the control mechanism of the circulation control method of the Coanda hyperbolic wall configuration. Or as Figure 5As shown, by setting a Coanda hyperbolic wall configuration circulation control configuration at the trailing edge of the main wing of the three-segment wing, separation control of the three-segment wing during severe flow separation at a large angle of attack can be achieved, and the flow separation that has spread to the main wing can be delayed to the flap.

[0042] In one embodiment, Figure 3 The control effects of the traditional Coanda wall airfoil shown and the circulation control airfoil with the Coanda hyperbolic wall configuration proposed in the present invention are compared. The incoming flow Mach number is set to 0.1Ma, the chord length of the aircraft is uniformly set to 0.92 m, the jet slot outlet is uniformly set to 1.92 mm, and the pressure ratios of the original upper jet port 4 and the first jet outlet 31 are both set to NPR = 1.2. Through simulation, it is determined that the lift coefficient is increased by 25.11% and the lift-drag ratio is increased by 9.58%, proving the superiority of the Coanda hyperbolic wall configuration 2 proposed in the present invention.

[0043]

[0044] In one embodiment, as Figure 6 、 Figure 7 shown, the Coanda hyperbolic wall configuration circulation control velocity contour map obtained by simulation proves that the incoming flow on both the upper and lower sides of the wing is guided downward by the jet, achieving the effect of a "virtual flap".

[0045] Aiming at the problems of insufficient utilization of the Coanda wall surface and low aerodynamic efficiency in the original circulation control aircraft, by combining the unique advantages of the Coanda effect and the hyperbolic wall configuration, the first control member 51 and the second control member 52 used close the jet outlet when jet control is not required, realizing the efficient utilization of the Coanda effect and better ensuring the streamline shape of the airfoil. This design makes more perfect use of every angle of the Coanda wall surface than the traditional circulation airfoil, greatly improving the lift of the aircraft, reducing the requirements for the takeoff and landing site, significantly enhancing the adaptability of the aircraft in complex environments, and providing a new technical path for the multi-functional and high-efficiency development of future aircraft. At the same time, by canceling the complex mechanical structure of the traditional control surface, the structure of the aircraft is made more concise and compact, the maintenance cost is reduced, and the system reliability is improved. It can support the aircraft to complete various tasks such as logistics distribution, power inspection, and geographical mapping, giving full play to the characteristics of high-efficiency load and flexible reliability.

[0046] Embodiment 2 Based on the Coanda hyperbolic wall configuration circulation control airfoil method in Embodiment 1, this embodiment discloses a Coanda hyperbolic wall configuration circulation control method, and the method includes: When there is no jet action, the control member closes the jet outlet.

[0047] When there is a jet effect, an air flow is blown out through the flow channel and acts on the control member. The control member is forced to move outward around the hinge end, and the jet outlet is opened. After the air flow is blown out, it adheres to the curved wall according to the Coanda effect. Among them, the air flow blown out from the first jet outlet adheres to the second Coanda curved wall, and the air flow blown out from the second jet outlet adheres to the first Coanda curved wall.

[0048] By controlling the opening and closing of the first jet outlet and / or the second jet outlet, the control of the aircraft is achieved.

[0049] It can be understood that in most working conditions during the flight process, if the lift of the wing itself is sufficient to meet the working requirements, the first control member 51 and the second control member 52 are kept closed, and the jet circulation control is not carried out. The Coanda double-curved wall configuration circulation control jet is only turned on when the aircraft performs pitching, rolling, yawing or undergoes severe flow control. This method can save energy better.

[0050] Specifically, when the aircraft is flying normally, no air flow is blown out from the first jet outlet 31 and the second jet outlet 32. Therefore, the first control member 51 and the second control member 52 are kept closed, and the airfoil body 1 maintains a complete streamline shape.

[0051] During the takeoff phase of the aircraft, in order to achieve the short takeoff and landing effect, high-speed jets are ejected from the first jet outlets 31 inside the wings on both sides of the aircraft. The first control member 51 is blown open with the pivot member 6 on the upper side as the center. At this time, the second control member 52 is in the closed state, maintaining the overall streamline shape of the second Coanda curved wall 22. The high-speed jets blown out from the first jet outlets 31 adhere to the second Coanda curved wall 22 according to the Coanda effect, realizing the downward deviation of the mainstream on the outer side of the wing and achieving the lift-increasing effect of the "virtual flap".

[0052] During the pitching phase of the aircraft, in the head-down phase, like the takeoff phase, it relies on the high-speed jets ejected from the first jet outlets 31 inside the wings on both sides of the aircraft. In the head-up phase, it relies on the high-speed jets ejected from the second jet outlets 32 inside the wings on both sides of the aircraft. The second control member 52 will be blown open with the pivot member 6 on the lower side as the center. At this time, the first control member 51 is in the closed state, maintaining the overall streamline shape of the first Coanda curved wall 21. The high-speed jets blown out from the second jet outlets 32 will adhere to the first Coanda curved wall 21 according to the Coanda effect, realizing the upward deviation of the mainstream on the outer side of the wing and achieving the head-up effect of the "virtual flap".

[0053] During the rolling stage of the aircraft, relying on the high-speed jets ejected from the left first jet outlet 31 and the right second jet outlet 32 inside the wings on both sides of the aircraft, the left first control member 51 is blown open with the pivot member 6 on the upper side as the center, and the right second control member 52 is blown open with the pivot member 6 on the lower side as the center. The high-speed jets will adhere to the corresponding Coanda curved walls according to the Coanda effect, achieving the right-rolling effect of the mainstream on the left side of the wing moving upward and the mainstream on the right side moving downward. The left-rolling is vice versa.

[0054] During the yawing stage of the aircraft, relying on the high-speed jets ejected from the first jet outlet 31 and the second jet outlet 32 inside the left wing of the aircraft, the left first control member 51 is blown open with the pivot member 6 on the upper side as the center, and the left second control member 52 is blown open with the pivot member 6 on the lower side as the center. The high-speed jets achieve the thrust vector effect, realizing right yaw. The left yaw is vice versa.

[0055] The method provided by the present invention has broad application prospects, can realize the short takeoff and landing and rudderless flight of the unmanned aerial vehicle, improve the rudder effect, and has excellent aerodynamic performance and control characteristics. By using the Coanda double-curved wall configuration 2, the aerodynamic efficiency and attitude control accuracy of the aircraft can be significantly enhanced, while eliminating the mechanical complexity and aerodynamic losses brought by traditional rudders. The present invention not only greatly reduces the requirements for the takeoff and landing site, but also improves the adaptability of the aircraft in complex environments, expands its mission execution range, and has unique advantages. It is applicable to urban logistics distribution, disaster rescue, power inspection, and geographical mapping and other tasks, giving full play to its characteristics of high-efficiency load, flexibility, and reliability. In addition, since there is no need for traditional rudder design, the structure of the aircraft is more concise, the maintenance cost is lower, and the reliability is higher, further enhancing the market competitiveness. [[ID=~]]

[0056] The technical features of the above embodiments can be combined arbitrarily. For the sake of brevity of description, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, it should be considered as the scope described in this specification.

[0057] The above-described embodiments only represent several implementation manners of the present invention, and their descriptions are relatively specific and detailed, but should not be construed as limiting the scope of the invention. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present invention, several deformations and improvements can be made, and these all belong to the protection scope of the present invention. Therefore, the protection scope of the present invention should be subject to the appended claims.

Claims

1. A Coanda double-curved wall configuration circulation control airfoil, comprising an airfoil body, characterized in that, A first Coanda curved wall and a second Coanda curved wall are provided at the tail of the airfoil body; A jet flow channel is provided in the airfoil body, and the jet flow channel is connected to the first Coanda curved wall and the second Coanda curved wall, and jet flow outlets are respectively formed on the wall surface of the first Coanda curved wall and the wall surface of the second Coanda curved wall; A control member is hinged on the jet flow outlet; based on the air flow blown out from the jet flow channel, the control member moves around the hinge end.

2. The Coanda double-curved wall configuration circulation control airfoil according to claim 1, wherein The jet flow outlet includes a first jet flow outlet and a second jet flow outlet; The first jet flow outlet is provided on the lower curved surface of the first Coanda curved wall; the second jet flow outlet is provided on the upper curved surface of the second Coanda curved wall.

3. The Coanda circulation control airfoil with a Coanda hyperbolic wall configuration according to claim 2, characterized in that, The jet flow channel includes a first jet flow channel and a second jet flow channel; wherein, the first jet flow channel is communicated with the first jet flow outlet, and the second jet flow channel is communicated with the second jet flow outlet.

4. The Coanda double-curved wall configuration circulation control airfoil according to claim 3, characterized in that, There is a height difference between the first jet flow channel and the first jet flow outlet, and between the second jet flow channel and the second jet flow outlet; when there is a height difference, a smooth transition curved surface is provided at the height difference for connection.

5. The Coanda double-curved wall configuration circulation control airfoil according to any one of claims 2 to 4, characterized in that The control member includes a first control member and a second control member; The first control member is hinged on the first jet flow outlet, and the second control member is hinged on the second jet flow outlet.

6. The Coanda circulation control airfoil with a Coanda hyperbolic wall configuration according to claim 5, characterized in that, The control member is a plurality of groups of rotatable blades; the plurality of groups of rotatable blades are hinged, and the blades cover the jet flow outlet.

7. The Coanda double-curved wall configuration circulation control airfoil according to claim 5, characterized in that, The control member is a spring piece, and the spring piece is hinged on the side wall of the jet flow outlet through an elastic member, so that the control member can rotate relative to the jet flow outlet based on the elastic member.

8. The Coanda double-curved wall configuration circulation control airfoil according to claim 7, characterized in that, A pivot member is provided on the side wall of the jet flow outlet; The elastic member is sleeved on the pivot member, and the elastic member is fixedly connected to the pivot member; the end of the elastic member is connected to the control member.

9. The Coanda circulation control airfoil with a Coanda hyperbolic wall configuration according to any one of claims 2 to 4, characterized in that, A jet flow air source is connected in the jet flow channel; and / or an acceleration sensor is provided on the surface of the main body structure; and / or a controller is provided on the main body structure; The controller is electrically connected to the acceleration sensor and the control module of the jet flow air source.

10. A circulation control method for a Coanda hyperbolic wall configuration, characterized in that, Using the circulation control airfoil with the Coanda double curved wall configuration according to any one of claims 1 to 9, the method includes: When there is no jet flow action, the control member closes the jet flow outlet; When there is jet flow action, the air flow blown out through the flow channel acts on the control member, and the control member is forced to move outwards around the hinge end, and the jet flow outlet is opened; after the air flow is blown out, it adheres to the curved wall according to the Coanda effect, wherein the air flow blown out from the first jet flow outlet adheres to the second Coanda curved wall, and the air flow blown out from the second jet flow outlet adheres to the first Coanda curved wall; By controlling the opening and closing of the first jet flow outlet and / or the second jet flow outlet, the control of the aircraft is realized.

Images