Gust load shedding device and method based on synthetic dual-jet cooperative control surface

Abstract

The invention belongs to the field of aircrafts, and particularly relates to a gust load shedding device and method based on a synthetic dual-jet cooperative control plane, and the gust load shedding device based on the synthetic dual-jet cooperative control plane comprises a wing body, a flap rotationally arranged at the rear edge of the wing body, and a synthetic dual-jet exciter arranged on the flap; two jet outlets of the synthetic dual-jet exciter are formed in the lower surface of the flap; included angles between the two jet outlets and the downstream direction of the lower surface of the flap are adjustable; the larger the included angle between the flap and the wing body is, the smaller the included angles between the two jet outlets and the lower surface of the flap are. According to the synthetic dual-jet exciter, the gust load can be relieved from multiple aspects, and the good gust load relieving effect is improved on the basis that the structure is simple, the mass is light, and no extra gas source is needed.

Description

Technical Field

[0001] The present invention belongs to the field of aircraft, and in particular relates to a gust load reduction device and method based on a synthetic dual-jet cooperative control surface. Background Art

[0002] With the increasing requirements for flight comfort and safety, the disturbances and loads caused by gusts have gradually attracted people's attention. When an aircraft is subjected to sudden longitudinal disturbances caused by gusts, the sudden increase in lift aerodynamic loads will cause damage to the structure on the one hand, and cause turbulence during flight on the other. The current gust mitigation method is mainly through mechanical control surfaces such as spoilers and ailerons, but mechanical control surfaces are limited by their own driving frequency and have certain shortcomings when facing high-frequency gust loads. There is a certain upper limit to the reduction of lift loads.

[0003] Currently, active flow control technology has been initially explored in the field of gust load mitigation. However, the current mainstream exciter drive units, such as centrifugal fans, axial fans, and engine-driven active jet devices, all have certain limitations. These not only bring additional complexity to the design of mechanical structures, but also pose challenges to the overall system performance due to their additional load requirements. Summary of the invention

[0004] The technical problem to be solved by the present invention is to provide a gust load reduction device and method based on a synthetic dual-jet cooperative control surface.

[0005] The present invention provides a gust load reduction device based on a synthetic dual jet cooperative control surface, comprising a wing body, a flap rotatably arranged at the trailing edge of the wing body, and a synthetic dual jet actuator arranged on the flap; The two jet outlets of the synthetic dual jet actuator are arranged on the lower surface of the flap; and the angles between the two jet outlets and the downstream direction of the lower surface of the flap are adjustable; The larger the included angle between the flap and the wing body, the smaller the included angle between the two jet outlets and the lower surface of the flap. In one of the embodiments, the angle between the two jet outlets and the downstream direction of the lower surface of the flap is in the range of 30°-90°.

[0006] In one of the embodiments, the two jet outlets of the synthetic dual jet actuator are arranged at an upstream position of the lower surface of the flap.

[0007] In one of the embodiments, the jet outlet is a strip-shaped hole along the span direction of the flap.

[0008] In one of the embodiments, the jet outlet is formed by enclosing two rotating plates hinged to the lower surface of the flap, and also includes a rotating plate rotation driving mechanism that can drive the four rotating plates to rotate synchronously.

[0009] In one embodiment, the synthetic dual-jet actuator includes two cavities, each cavity is correspondingly provided with one of the jet outlets, and the two cavities are separated by a vibrating diaphragm.

[0010] In one of the embodiments, the synthetic dual jet actuator is arranged inside the flap, and the outer end of the jet outlet is arranged on the lower surface of the flap.

[0011] In one of the embodiments, the gust load reduction device based on synthetic dual jet coordinated control surface further includes a controller and an acceleration sensor; The acceleration sensor is arranged on the outer surface of the aircraft, wing body or flap to measure the state of the aircraft under gust disturbance; The controller is respectively connected to the acceleration sensor, the power supply of the synthetic dual jet actuator, the flap rotation drive mechanism of the flap, and the rotating plate rotation drive mechanism that drives the jet outlet angle adjustment, so as to adjust the flap angle, the angle of the jet outlet and the jet intensity of the jet outlet according to the state of the aircraft under gust disturbance, and realize closed-loop control.

[0012] The present invention also provides a gust load reduction method based on a synthetic dual-jet cooperative control surface, using the gust load reduction device based on a synthetic dual-jet cooperative control surface; When the aircraft encounters a gust of wind, the flap deflects upward, changing the original curvature of the wing body, reducing the airflow velocity on the upper surface of the wing body, and increasing the airflow velocity on the lower surface of the wing body. The resulting pressure difference causes the wing body to generate a downward force, which offsets the additional lift caused by the gust of wind; The synthetic dual jet actuator is turned on to form a forward jet on the lower surface of the flap, which continuously injects energy into the separation layer, delays the flow separation caused by the flap deflection, and strengthens the downward force generated by the flap. The flap deflection is combined with a synthetic dual jet actuator to reduce the airflow velocity on the upper surface of the wing body while increasing the airflow velocity on the lower surface of the wing body, changing the speed difference between the upper and lower surfaces of the wing body, thereby reducing the lift load of the aircraft under gusts and achieving gust load mitigation.

[0013] In one of the embodiments, when the aircraft encounters a gust, the flap begins to deflect upward. In the initial stage of deflection, the deflection angle of the flap is small, and the angle between the two jet outlets and the lower surface of the flap is large. The two jets generated by the two jet outlets are ejected in a large angle direction, forming a negative Gurney flap effect, which directly reduces the gust load; as the deflection angle of the flap increases, the angle between the two jet outlets and the lower surface of the flap gradually decreases until the flap is deflected to the maximum deflection angle, at which time the angle between the two jet outlets and the lower surface of the flap is the smallest, and the two jets generated by the two jet outlets flow out obliquely and adhere to the lower surface of the flap to flow, thereby suppressing the separation area caused by the deflection of the flap and enhancing the efficiency of the lift load reduction caused by the deflection of the flap.

[0014] The beneficial effect of the present invention is that the gust load reduction device based on the synthetic dual-jet cooperative control surface of the present invention, wherein the synthetic dual-jet actuator and its arrangement can assist in improving the effect of flap deflection on reducing the gust load, and can also increase the airflow velocity on the lower surface of the flap, change the speed difference between the upper and lower wing surfaces of the wing body, and achieve gust load reduction. In the early stage of flap deflection, the synthetic dual-jet actuator can form a negative Gurney flap effect in combination with the flap to directly reduce the gust load. After the flap is deflected, the two jets generated by the synthetic dual-jet actuator will flow on the lower surface of the flap, suppress the separation zone caused by the flap deflection, and enhance the lift load reduction efficiency caused by the flap deflection. That is, the synthetic dual-jet actuator can achieve gust load reduction from many aspects, and improve the good gust load reduction effect on the basis of simple structure, light weight, and no need for additional air source. BRIEF DESCRIPTION OF THE DRAWINGS

[0015] Attached Figure 1 It is a structural schematic diagram of a gust load reduction device based on a synthetic dual-jet cooperative control surface according to the present invention; Attached Figure 2 It is a schematic diagram of the partial structure of the flap part in the gust load reduction device based on the synthetic double jet cooperative control surface of the present invention; Attached Figure 3 It is a schematic structural diagram of the jet outlet portion in the gust load reduction device based on the synthetic double jet cooperative control surface of the present invention; Attached Figure 4 It is a velocity cloud diagram of the gust load reduction device based on the synthetic double jet cooperative control surface of the present invention; Attached Figure 5 It is a schematic diagram of the overall flow field structure after the gust load reduction device based on the synthetic double jet cooperative control surface of the present invention is controlled; Attached Figure 6 It is a schematic diagram of the flow field structure of the flap portion after the gust load reduction device based on the synthetic dual jet cooperative control surface of the present invention is controlled.

[0016] In the figure, 1-wing body; 2-synthetic dual jet actuator; 21-cavity; 22-jet outlet; 221-rotating plate; 23-vibrating diaphragm; 3-flap. DETAILED DESCRIPTION

[0017] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0018] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative position relationship, movement status, etc. between the components under a certain specific posture (as shown in the accompanying drawings). If the specific posture changes, the directional indication will also change accordingly.

[0019] In addition, in the present invention, descriptions such as "first", "second", etc. are only used for descriptive purposes and cannot be understood as indicating or implying their relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" or "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0020] In the present invention, unless otherwise clearly specified and limited, the terms "connection", "fixation", etc. should be understood in a broad sense. For example, "fixation" can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection, an electrical connection, a physical connection, or a wireless communication connection; it can be a direct connection, or an indirect connection through an intermediate medium, or it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0021] In addition, the technical solutions between the various embodiments of the present invention can be combined with each other, but it must be based on the fact that ordinary technicians in the field can implement it. When the combination of technical solutions is contradictory or cannot be implemented, it should be deemed that such combination of technical solutions does not exist and is not within the scope of protection required by the present invention.

[0022] As attached Figure 1 -Attached Figure 6As shown, the present invention provides a gust load reduction device based on a synthetic dual jet cooperative control surface, comprising a wing body 1, a flap 3 rotatably arranged at the trailing edge of the wing body 1, and a synthetic dual jet actuator 2 arranged on the flap 3, wherein the flap 3 can be angle-adjusted by a flap rotation driving mechanism; The two jet outlets 22 of the synthetic dual jet actuator 2 are arranged on the lower surface of the flap 3; and the angle between the two jet outlets 22 and the lower surface of the flap 3 in the downstream direction is adjustable; The larger the included angle between the flap 3 and the wing body 1 , the smaller the included angle between the two jet outlets 22 and the lower surface of the flap 3 .

[0023] The gust load reduction device based on the synthetic dual jet cooperative control surface provided by the present invention can perform the following gust load reduction method based on the synthetic dual jet cooperative control surface: When the aircraft encounters a gust, the flap 3 deflects upward, changes the original curvature of the wing body 1, reduces the airflow velocity on the upper surface of the wing body 1, and increases the airflow velocity on the lower surface of the wing body 1. The resulting pressure difference causes the wing body 1 to generate a downward force, which offsets the additional lift caused by the gust, thereby reducing the sudden lift of the aircraft when it encounters a gust disturbance; The synthetic dual jet actuator 2 is turned on to form a forward jet on the lower surface of the flap 3, continuously injecting energy into the separation layer, delaying the flow separation caused by the deflection of the flap 3, and strengthening the downward force generated by the flap 3; The deflection of the flap 3 is combined with the synthetic dual jet actuator 2 to reduce the airflow velocity on the upper surface of the wing body 1 while increasing the airflow velocity on the lower surface of the wing body 1, thereby changing the speed difference between the upper and lower wing surfaces of the wing body 1, thereby reducing the lift load of the aircraft under gusts and achieving gust load mitigation.

[0024] That is, the synthetic dual-jet actuator 2 is used, on the one hand, to enhance the strength of the downward force generated by the deflection of the flap 3, and to assist the deflection of the flap 3 in reducing the sudden lift of the aircraft when encountering gust disturbances; on the other hand, it can also increase the airflow velocity on the lower surface of the wing body 1, and change the speed difference between the upper and lower wing surfaces of the wing body 1, so as to reduce the lift load of the aircraft under gusts and achieve gust load mitigation, so as to improve the gust load mitigation effect from multiple aspects and angles through the synthetic dual-jet actuator 2.

[0025] In addition, when the aircraft encounters a gust of wind, the flap 3 begins to deflect upward. In the initial stage of deflection, the deflection angle of the flap 3 is small, and the angle between the two jet outlets 22 and the lower surface of the flap 3 is large. The two jets generated by the two jet outlets 22 are ejected in a large angle direction. For example, the angle between the jet and the lower surface of the flap 3 is 90°, forming a negative Gurney flap effect, which directly reduces the gust load. At this time, the synthetic dual jet actuator 2 can not only enhance the deflection effect of the flap 3 and increase the airflow speed on the lower surface of the wing body 1, but also combine the deflection of the flap 3 to make the flap 3 negative Gurney flap , forming a negative Gurney flap effect, directly reducing the gust load; as the deflection angle of the flap 3 increases, the angle between the two jet outlets 22 and the lower surface of the flap 3 gradually decreases until the flap 3 deflects to the maximum deflection angle, at which time the angle between the two jet outlets 22 and the lower surface of the flap 3 is the smallest, for example, the angle between the jet and the lower surface of the flap 3 is 30°, and the two jets generated by the two jet outlets 22 flow out obliquely and adhere to the lower surface of the flap 3 to flow, suppressing the separation zone caused by the deflection of the flap 3 and enhancing the efficiency of reducing the lift load caused by the deflection of the flap 3. In this way, by synchronously adjusting the angle of the flap 3 and the angle of the jet outlet 22, the lift load reduction effect is improved through different principles at the initial stage of adjustment and after adjustment.

[0026] In addition, in the process of the change of the deflection angle of the flap 3 and the change of the angle between the two jet outlets 22 and the lower surface of the flap 3, the additional lift generated by the gust gradually decreases, so that the aircraft and the wing body 1 can reduce the gust load on the basis of ensuring flight stability without a sudden drop in the gust load, thereby eliminating the turbulence of the aircraft caused by the sudden drop in the gust load.

[0027] That is, the gust load reduction device based on the synthetic dual-jet cooperative control surface of the present invention, wherein the synthetic dual-jet exciter 2 and its arrangement can assist in improving the mitigation effect of the deflection of the flap 3 on the gust load, and can also increase the airflow speed on the lower surface of the flap 3, change the speed difference between the upper and lower wing surfaces of the wing body 1, and realize the mitigation of the gust load. In the early stage of the deflection of the flap 3, the synthetic dual-jet exciter 2 can form a negative Gurney flap effect in combination with the flap 3 to directly reduce the gust load. After the flap 3 is deflected, the two jets generated by the synthetic dual-jet exciter 2 will flow on the lower surface of the flap 3, suppress the separation zone caused by the deflection of the flap 3, and enhance the lift load reduction efficiency caused by the deflection of the flap 3. That is, the synthetic dual-jet exciter 2 can achieve the mitigation of the gust load from many aspects, and improve the good gust load mitigation effect on the basis of simple structure, light weight, and no need for additional air source. In one of the embodiments, the angle between the two jet outlets 22 and the downstream direction of the lower surface of the flap 3 is in the range of 30°-90°, that is, in the initial stage of deflection of the flap 3, the angle between the jet outlet 22 and the downstream direction of the lower surface of the flap 3 is 90°, and after the flap 3 is deflected to the final angle, the angle between the jet outlet 22 and the downstream direction of the lower surface of the flap 3 is 30°, thereby ensuring the negative Gurney flap effect in the initial stage of deflection of the flap 3 and the suppression effect of the separation zone caused by the deflection of the flap 3 after the deflection of the flap 3.

[0028] In one of the embodiments, the two jet outlets 22 of the synthetic dual jet actuator 2 are arranged upstream of the lower surface of the flap 3, so that the flow field downstream of the lower surface of the flap 3 can be regulated to ensure the gust load mitigation effect.

[0029] In one of the embodiments, the jet outlet 22 is a strip hole along the span direction of the flap 3 , and its length direction is perpendicular to the flow direction of the external flow field, so as to ensure the uniformity of gust load mitigation in the span direction of the flap 3 .

[0030] In one of the embodiments, the jet outlet 22 is formed by two rotating plates 221 hinged to the lower surface of the flap 3. The two jet outlets 22 have a total of four rotating plates 221. The gust load reduction device based on the synthetic dual-jet collaborative control surface also includes a rotating plate rotation drive mechanism that can drive the four rotating plates 221 to rotate synchronously. The four rotating plates 221 rotate synchronously to ensure the synchronous adjustment of the angle of the jet outlet 22.

[0031] In one embodiment, the synthetic dual jet actuator 2 includes two cavities 21, each cavity 21 is correspondingly provided with a jet outlet 22, and the two cavities 21 are separated by a vibrating diaphragm 23. A voltage is applied to the vibrating diaphragm 23 by a power supply to make the vibrating diaphragm 23 vibrate, thereby generating alternating reciprocating suction and jet at the two jet outlets 22. In this embodiment, the synthetic dual jet actuator 2 adopts a single-membrane dual-cavity structure, so that the actuator vibrating diaphragm 23 can generate effective blowing jets during the reciprocating vibration process, continuously reducing the gust response load of the aircraft. At the same time, since the working frequency of the synthetic dual jet actuator 2 is high frequency, it responds faster to the gust load, and has a more excellent control effect when facing high-frequency gusts. The synthetic dual jet actuator 2 has a simple structure, light weight, does not require an additional air source, and has a good engineering application background.

[0032] In one of the embodiments, the synthetic dual jet actuator 2 is arranged inside the flap 3 to avoid affecting the aerodynamic shape of the flap 3 and reduce the impact on the flight performance of the aircraft. The outer end of the jet outlet 22 is arranged on the lower surface of the flap 3.

[0033] In one of the embodiments, the gust load reduction device based on synthetic dual jet coordinated control surface further includes a controller and an acceleration sensor; The acceleration sensor is arranged on the outer surface of the aircraft, the wing body 1 or the flap 3 to measure the state of the aircraft under gust disturbance; The controller is respectively connected to the acceleration sensor, the power supply of the synthetic dual jet actuator 2, the flap rotation drive mechanism of the flap 3, and the rotating plate rotation drive mechanism that drives the angle adjustment of the jet outlet 22, so as to adjust the angle of the flap 3, the angle of the jet outlet 22 and the jet intensity of the jet outlet 22 according to the state of the aircraft under gust disturbance, and realize closed-loop control.

[0034] In this embodiment, after the acceleration sensor measures the state of the aircraft under the gust disturbance, the longitudinal acceleration of the aircraft is transmitted to the controller. Then the controller adjusts the voltage of the power supply of the synthetic dual jet actuator 2 according to the real-time longitudinal acceleration of the aircraft, so that the amplitude of the vibrating diaphragm 23 in the synthetic dual jet actuator 2 changes, and then the jet energy of the synthetic dual jet actuator 2 is changed. The change in the jet energy further affects the lift coefficient of the aircraft due to the change in the flow field structure of the aircraft. At the same time, the controller also adjusts the flap rotation drive mechanism of the flap 3 to adjust the angle of the flap 3 according to the real-time longitudinal acceleration of the aircraft. At the same time, the controller also adjusts the rotating plate rotation drive mechanism for adjusting the angle of the jet outlet 22 according to the real-time longitudinal acceleration of the aircraft, which can adjust the angle of the jet outlet 22, and the angle of the jet outlet 22 and the angle of the flap 3 are adjusted synchronously. The above three adjustments are all used to change the longitudinal acceleration of the aircraft and finally realize closed-loop control.

[0035] This method can save energy well and suppress the negative effect caused by the deflection of flap 3 in the cruise state. It is worth noting that the gust load reduction device based on the synthetic dual jet cooperative control surface in this embodiment is only activated when the aircraft encounters strong gust interference, specifically when the aircraft is subject to non-commanded longitudinal acceleration disturbance.

[0036] Reference Figure 4 When the gust disturbance is large, the jet energy is increased, the flow distance and stroke are increased, the wall attachment effect is increased, the separation area caused by the upward deflection of the flap 3 is reduced, and the airflow velocity on the lower surface of the flap 3 is further increased. Figure 5 and attached Figure 6 Since the wall jet 4 and the wall jet 5 suppress the lower separation zone well, the flow velocity on the lower surface based on the deflection of the flap 3 is increased, which can effectively improve the load reduction capability of the wing when encountering gusts.

[0037] The above is only an embodiment and does not limit the present invention in any way. Any person skilled in the art can use the above disclosed technical contents to make many possible changes, modifications or modifications to the technical solutions of the present invention into equivalent embodiments of equivalent changes without departing from the scope of the technical solutions of the present invention. Therefore, any simple modification, equivalent changes and modifications made to the above embodiments according to the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the scope of protection of the technical solutions of the present invention.

Claims

1. A gust load reduction device based on synthetic dual jet coordinated control surface, characterized in that: It comprises a wing body (1), a flap (3) rotatably arranged at the trailing edge of the wing body (1), and a synthetic dual-jet exciter (2) arranged on the flap (3); The two jet outlets (22) of the synthetic dual jet actuator (2) are arranged on the lower surface of the flap (3); and the angle between the two jet outlets (22) and the lower surface of the flap (3) in the downstream direction is adjustable; The larger the included angle between the flap (3) and the wing body (1), the smaller the included angle between the two jet outlets (22) and the lower surface of the flap (3).

2. The gust load reduction device based on synthetic dual jet coordinated control surface according to claim 1 is characterized in that: The angle between the two jet outlets (22) and the downstream direction of the lower surface of the flap (3) is in the range of 30°-90°.

3. The gust load reduction device based on synthetic dual jet coordinated control surface according to claim 1 is characterized in that: The two jet outlets (22) of the synthetic dual jet actuator (2) are arranged at upstream positions of the lower surface of the flap (3).

4. The gust load reduction device based on synthetic dual jet coordinated control surface according to claim 1 is characterized in that: The jet outlet (22) is a strip-shaped hole along the span direction of the flap (3).

5. The gust load reduction device based on synthetic dual jet coordinated control surface according to any one of claims 1 to 4, characterized in that: The jet outlet (22) is formed by enclosing two rotating plates (221) hinged to the lower surface of the flap (3), and also includes a rotating plate rotation driving mechanism capable of driving the four rotating plates (221) to rotate synchronously.

6. The gust load reduction device based on synthetic dual jet coordinated control surface according to claim 5 is characterized in that: The synthetic dual-jet actuator (2) comprises two cavities (21), each cavity (21) is correspondingly provided with one of the jet outlets (22), and the two cavities (21) are separated by a vibrating diaphragm (23).

7. The gust load reduction device based on synthetic dual jet coordinated control surface according to claim 6 is characterized in that: The synthetic dual jet actuator (2) is arranged inside the flap (3), and the outer end of the jet outlet (22) is arranged on the lower surface of the flap (3).

8. The gust load reduction device based on synthetic dual jet coordinated control surface according to any one of claims 1-4, 6 and 7, characterized in that: Also includes a controller and an acceleration sensor; The acceleration sensor is arranged on the outer surface of the aircraft, the wing body (1) or the flap (3) to measure the state of the aircraft under gust disturbance; The controller is respectively connected to the acceleration sensor, the power supply of the synthetic dual jet actuator (2), the flap rotation drive mechanism of the flap (3), and the rotation drive mechanism of the rotating plate for driving the angle adjustment of the jet outlet (22), so as to adjust the angle of the flap (3), the angle of the jet outlet (22), and the jet intensity of the jet outlet (22) according to the state of the aircraft under gust disturbance, and realize closed-loop control.

9. A gust load reduction method based on synthetic dual jet cooperative control surface, characterized in that: Using a gust load reduction device based on a synthetic dual jet cooperative control surface as described in any one of claims 1 to 8; When the aircraft encounters a gust of wind, the flap (3) deflects upward, changes the original curvature of the wing body (1), reduces the airflow velocity on the upper surface of the wing body (1), and increases the airflow velocity on the lower surface of the wing body (1). The resulting pressure difference causes the wing body (1) to generate a downward force, which offsets the additional lift caused by the gust of wind. Turning on the synthetic dual jet actuator (2) to form a forward jet on the lower surface of the flap (3), continuously injecting energy into the separation layer, delaying the flow separation caused by the deflection of the flap (3), and strengthening the strength of the downward force generated by the flap (3); The deflection of the flap (3) is combined with the synthetic dual jet actuator (2) to reduce the airflow velocity on the upper surface of the wing body (1) while increasing the airflow velocity on the lower surface of the wing body (1), thereby changing the speed difference between the upper and lower wing surfaces of the wing body (1), thereby reducing the lift load of the aircraft under gusts and achieving gust load mitigation.

10. The gust load reduction method based on synthetic dual jet coordinated control surface according to claim 9, characterized in that When the aircraft encounters a gust of wind, the flap (3) begins to deflect upward. In the initial stage of deflection, the deflection angle of the flap (3) is small, and the angle between the two jet outlets (22) and the lower surface of the flap (3) is large. The two jets generated by the two jet outlets (22) are ejected in a large angle direction, forming a negative Gurney flap effect, which directly reduces the gust of wind load. As the deflection angle of the flap (3) increases, the angle between the two jet outlets (22) and the lower surface of the flap (3) gradually decreases until the flap (3) deflects to a maximum deflection angle. At this time, the angle between the two jet outlets (22) and the lower surface of the flap (3) is the smallest. The two jets generated by the two jet outlets (22) flow out obliquely and adhere to the lower surface of the flap (3) to flow, thereby suppressing the separation zone caused by the deflection of the flap (3) and enhancing the efficiency of reducing the lift load caused by the deflection of the flap (3).

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