A gust load alleviation device and method based on synthetic doublet flow cooperative control surface

Abstract

This invention belongs to the field of aircraft, specifically relating to a gust load reduction device and method based on a synthetic dual-jet cooperative control surface. The gust load reduction device includes a wing body, a flap rotatably mounted on the trailing edge of the wing body, and a synthetic dual-jet actuator mounted on the flap. The two jet outlets of the synthetic dual-jet actuator are located on the lower surface of the flap; and the angle between the two jet outlets and the lower surface of the flap in the downstream direction is adjustable. The larger the angle between the flap and the wing body, the smaller the angle between the two jet outlets and the lower surface of the flap. The synthetic dual-jet actuator of this invention can reduce gust load from multiple aspects, achieving a good gust load reduction effect while being simple in structure, lightweight, and requiring no additional air source.

Description

Technical Field

[0001] This invention belongs to the field of aircraft, specifically relating to a gust load reduction device and method based on a synthetic dual-jet cooperative control surface. Background Technology

[0002] With increasing demands for flight comfort and safety, the disturbances and loads caused by gusts have gradually attracted attention. When an aircraft is subjected to sudden longitudinal disturbances from gusts, the sudden increase in lift aerodynamic loads can damage the structure and cause turbulence during flight. Currently, gust mitigation methods mainly rely on mechanical control surfaces such as spoilers and ailerons. However, mechanical control surfaces are limited by their own driving frequency and have certain shortcomings when facing high-frequency gust loads, thus limiting the upper limit of lift load mitigation.

[0003] Currently, active flow control technology has been initially explored in the field of gust load mitigation. However, the mainstream exciter drive units, such as centrifugal fans, axial fans, and engine-driven active jet devices, all have certain limitations. These limitations not only introduce additional complexity to the mechanical structure design 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 disposed on the trailing edge of the wing body, and a synthetic dual-jet exciter disposed on the flap;

[0006] The two jet outlets of the synthetic dual-jet exciter are located on the lower surface of the flap; and the angle between the two jet outlets and the lower surface of the flap in the downstream direction is adjustable.

[0007] The larger the angle between the flap and the wing body, the smaller the angle between the two jet outlets and the lower surface of the flap.

[0008] In one embodiment, 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°.

[0009] In one embodiment, the two jet outlets of the synthetic dual-jet actuator are located upstream of the lower surface of the flap.

[0010] In one embodiment, the jet outlet is a strip-shaped hole along the span of the flap.

[0011] In one embodiment, the jet outlet is formed by two rotating plates hinged to the lower surface of the flap, and also includes a rotating plate rotation drive mechanism that can drive the four rotating plates to rotate synchronously.

[0012] In one embodiment, the synthetic dual-jet exciter includes two cavities, each cavity having a corresponding jet outlet, and the two cavities are separated by a vibrating diaphragm.

[0013] In one embodiment, the synthetic dual-jet exciter is disposed inside the flap, and the outer end of the jet outlet is disposed on the lower surface of the flap.

[0014] In one embodiment, the gust load reduction device based on the synthetic dual-jet cooperative control surface also includes a controller and an acceleration sensor;

[0015] The acceleration sensor is installed on the outer surface of the aircraft, wing, or flap to measure the state of the aircraft under gust disturbance.

[0016] The controller is connected to the acceleration sensor, the power supply of the synthetic dual-jet exciter, the flap rotation drive mechanism, and the rotating plate rotation drive mechanism that drives the adjustment of the jet outlet angle, so as to adjust the flap angle, the jet outlet angle, and the jet intensity at the jet outlet according to the state of the aircraft under gust disturbance, and realize closed-loop control.

[0017] The present invention also provides a gust load reduction method based on a synthetic dual-jet cooperative control surface, using the above-mentioned gust load reduction device based on a synthetic dual-jet cooperative control surface;

[0018] When the aircraft encounters gusts of wind, the flaps deflect upwards, changing the original wing curvature, reducing the airflow velocity on the upper surface of the wing, and increasing the airflow velocity on the lower surface of the wing. The resulting pressure difference causes the wing to generate a downward force, which cancels out the additional lift caused by the gusts.

[0019] The synthetic dual-jet exciter is activated to form a forward jet on the lower surface of the flap, continuously injecting energy into the separation layer, delaying the flow separation caused by the flap deflection, and strengthening the downward force generated by the flap.

[0020] The combination of flap deflection and synthetic dual-jet exciter reduces the airflow velocity on the upper surface of the wing body while increasing the airflow velocity on the lower surface of the wing body, thereby changing the velocity difference between the upper and lower surfaces of the wing body and reducing the lift load of the aircraft under gusts, thus mitigating the gust load.

[0021] In one embodiment, when the aircraft encounters a gust of wind, the flaps begin to deflect upwards. In the initial stage of deflection, the flap deflection angle 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 at a large angle, forming a negative gust flap effect, which directly reduces the gust load. As the flap deflection angle increases, the angle between the two jet outlets and the lower surface of the flap gradually decreases until the flap deflects to the maximum deflection angle. At this time, the angle between the two jet outlets and the lower surface of the flap is the smallest. The two jets generated by the two jet outlets flow out obliquely and adhere to the lower surface of the flap, suppressing the separation zone caused by the flap deflection and enhancing the efficiency of the lift load reduction caused by the flap deflection.

[0022] The beneficial effects of this invention are that the gust load reduction device based on the synthetic dual-jet synergistic control surface can help improve the gust load reduction effect of flap deflection, increase the airflow velocity on the lower surface of the flap, change the velocity difference between the upper and lower surfaces of the wing, and reduce the gust load. In the early stage of flap deflection, the synthetic dual-jet exciter can combine with the flap to form a negative Gurney flap effect, directly reducing the gust load. After the flap deflection, the two jets generated by the synthetic dual-jet exciter will flow together on the lower surface of the flap, suppressing the separation zone caused by the flap deflection and enhancing the efficiency of reducing the lift load caused by the flap deflection. In other words, the synthetic dual-jet exciter can reduce the gust load from multiple aspects, and improve the gust load reduction effect with simple structure, light weight, and no need for an additional air source. Attached Figure Description

[0023] Appendix Figure 1 This is a schematic diagram of the gust load reduction device based on the synthetic dual-jet cooperative control surface of the present invention;

[0024] Appendix Figure 2 This is a partial structural diagram of the flap portion in the gust load reduction device based on the synthetic dual-jet cooperative control surface of the present invention;

[0025] Appendix Figure 3 This is a schematic diagram of the jet outlet section in the gust load reduction device based on the synthetic dual-jet cooperative control surface of the present invention.

[0026] Appendix Figure 4 This is a velocity cloud map of the gust load reduction device based on the synthetic dual-jet cooperative control surface of the present invention;

[0027] Appendix Figure 5 This is a schematic diagram of the overall flow field structure after the application of control by the gust load reduction device based on the synthetic dual-jet cooperative control surface of the present invention.

[0028] Appendix Figure 6This is a schematic diagram of the flow field structure of the flap section after the gust load reduction device based on the synthetic dual-jet cooperative control surface of the present invention has been controlled.

[0029] In the figure, 1-wing body; 2-synthetic dual-jet exciter; 21-cavity; 22-jet outlet; 221-rotating plate; 23-vibrating diaphragm; 3-flap. Detailed Implementation

[0030] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative effort are within the scope of protection of the present invention.

[0031] It should be noted that all directional indications (such as up, down, left, right, front, back, etc.) in the embodiments of the present invention are only used to explain the relative positional relationship and movement of each component in a certain specific posture (as shown in the figure). If the specific posture changes, the directional indication will also change accordingly.

[0032] Furthermore, in this invention, descriptions involving "first," "second," etc., are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0033] In this invention, unless otherwise explicitly specified and limited, the terms "connection," "fixed," etc., should be interpreted broadly. For example, "fixed" can mean a fixed connection, a detachable connection, or an integral part; it can mean a mechanical connection, an electrical connection, a physical connection, or a wireless communication connection; it can mean a direct connection or an indirect connection through an intermediate medium; it can mean the internal communication of two elements or the interaction between two elements, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0034] Furthermore, the technical solutions of the various embodiments of the present invention can be combined with each other, but only if they are feasible for those skilled in the art. If the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such combination of technical solutions does not exist and is not within the scope of protection claimed by the present invention.

[0035] As attached Figure 1 -Appendix Figure 6 As shown, the present invention provides a gust load reduction device based on a synthetic dual-jet cooperative control surface, including a wing body 1, a flap 3 rotatably disposed on the trailing edge of the wing body 1, and a synthetic dual-jet exciter 2 disposed on the flap 3, wherein the flap 3 can be angled by a flap rotation drive mechanism.

[0036] The two jet outlets 22 of the synthetic dual-jet exciter 2 are disposed 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;

[0037] The larger the angle between the flap 3 and the wing body 1, the smaller the angle between the two jet outlets 22 and the lower surface of the flap 3.

[0038] The gust load reduction device based on the synthetic dual-jet cooperative control surface provided by this invention can perform the following gust load reduction method based on the synthetic dual-jet cooperative control surface:

[0039] When the aircraft encounters gusts of wind, the flaps 3 deflect upwards, changing the original camber of the wing body 1, reducing the airflow velocity on the upper surface of the wing body 1, and increasing 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 cancels out the additional lift caused by the gusts, thereby reducing the sudden lift when the aircraft encounters gust disturbances.

[0040] The synthetic dual-jet exciter 2 is activated, forming 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.

[0041] The flap 3 deflects in combination with the synthetic dual-jet exciter 2, which reduces 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 velocity difference between the upper and lower surfaces of the wing body 1 and reducing the lift load of the aircraft under gusts, thus mitigating the gust load.

[0042] The synthetic dual-jet exciter 2 is used to enhance the downward force generated by the deflection of the flap 3, and assist the flap 3 in reducing the sudden lift of the aircraft when it encounters gust disturbance. On the other hand, it can also increase the airflow speed on the lower surface of the wing body 1, and change the speed difference between the upper and lower surfaces of the wing body 1 to reduce the lift load of the aircraft under gusts, thereby mitigating the gust load. The synthetic dual-jet exciter 2 improves the mitigation effect of gust load from multiple aspects and angles.

[0043] Furthermore, when the aircraft encounters gusts, flap 3 begins to deflect upwards. In the initial stage of deflection, the deflection angle of flap 3 is small, and the angle between the two jet outlets 22 and the lower surface of flap 3 is large. The two jets generated by the two jet outlets 22 are ejected at large angles, for example, the angle between the jets and the lower surface of flap 3 is 90°, forming a negative gust flap effect, which directly reduces the gust load. At this time, the synthetic dual-jet exciter 2 can not only enhance the deflection effect of flap 3 and increase the airflow speed on the lower surface of wing body 1, but also combine with the deflection of flap 3 to make flap 3 a negative gust flap. This creates a negative Gurney flap effect, directly mitigating gust loads. As the deflection angle of flap 3 increases, the angle between the two jet outlets 22 and the lower surface of flap 3 gradually decreases until flap 3 deflects to its maximum angle, at which point the angle between the two jet outlets 22 and the lower surface of flap 3 is minimal. For example, if the angle between the jet and the lower surface of flap 3 is 30°, the two jets generated by the two jet outlets 22 flow out obliquely and adhere to the lower surface of flap 3, suppressing the separation zone caused by the deflection of flap 3 and enhancing the efficiency of reducing lift loads caused by the deflection of flap 3. Thus, by synchronously adjusting the angle of flap 3 and the angle of jet outlets 22, the lift load mitigation effect is improved through different principles in the initial and later stages of adjustment.

[0044] In addition, as the deflection angle of flap 3 changes and the angle between the two jet outlets 22 and the lower surface of flap 3 changes, the additional lift generated by the gust gradually decreases. This allows the aircraft and wing body 1 to reduce the gust load while ensuring flight stability, without a sudden drop in gust load, thus preventing aircraft turbulence caused by a sudden drop in gust load.

[0045] The present invention relates to a gust load reduction device based on a synthetic dual-jet synergistic control surface. The synthetic dual-jet exciter 2 and its arrangement can assist in improving the gust load reduction effect of flap 3 deflection. It can also increase the airflow velocity on the lower surface of flap 3, change the velocity difference between the upper and lower surfaces of the wing body 1, and reduce the gust load. In the initial stage of flap 3 deflection, the synthetic dual-jet exciter 2 can combine with flap 3 to form a negative Gurney flap effect, directly reducing the gust load. After flap 3 deflection, the two jets generated by the synthetic dual-jet exciter 2 will flow together and adhere to the lower surface of flap 3, suppressing the separation zone caused by flap 3 deflection and enhancing the lift load reduction efficiency caused by flap 3 deflection. In other words, the synthetic dual-jet exciter 2 can reduce the gust load from multiple aspects, and improve the gust load reduction effect with simple structure, light weight, and no need for an additional air source.

[0046] In one embodiment, 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 flap 3 deflection, the angle between the jet outlets 22 and the downstream direction of the lower surface of the flap 3 is 90°, and after the flap 3 deflects to the final angle, the angle between the jet outlets 22 and the downstream direction of the lower surface of the flap 3 is 30°. This ensures the negative Gurney flap effect in the initial stage of flap 3 deflection and the suppression effect of the separation zone caused by flap 3 deflection after flap 3 deflection.

[0047] In one embodiment, the two jet outlets 22 of the synthetic dual-jet exciter 2 are located upstream of the lower surface of the flap 3, thereby regulating the flow field downstream of the lower surface of the flap 3 to ensure the mitigation effect of gust load.

[0048] In one embodiment, the jet outlet 22 is a strip-shaped hole along the span of the flap 3, and its length direction is perpendicular to the flow direction of the external flow field to ensure uniformity of gust load reduction in the span of the flap 3.

[0049] In one embodiment, the jet outlet 22 is formed by two rotating plates 221 hinged to the lower surface of the flap 3. There are a total of four rotating plates 221 for the two jet outlets 22. The gust load reduction device based on the synthetic dual jet cooperative control surface also includes a rotating plate rotation drive mechanism that can drive the four rotating plates 221 to rotate synchronously. The synchronous rotation of the four rotating plates 221 ensures that the angle of the jet outlet 22 is adjusted synchronously.

[0050] In one embodiment, the synthetic dual-jet exciter 2 includes two cavities 21, each corresponding to a jet outlet 22. The two cavities 21 are separated by a vibrating diaphragm 23. A voltage is applied to the vibrating diaphragm 23 by a power source, causing the diaphragm 23 to vibrate, thereby generating alternating suction and jet at the two jet outlets 22. In this embodiment, the synthetic dual-jet exciter 2 adopts a single-diaphragm dual-cavity structure, enabling the exciter's vibrating diaphragm 23 to generate an effective blowing jet during reciprocating vibration, continuously reducing the gust response load of the aircraft. Furthermore, since the synthetic dual-jet exciter 2 operates at a high frequency, it responds quickly to gust loads and exhibits superior control performance when facing high-frequency gusts. The synthetic dual-jet exciter 2 has a simple structure, is lightweight, and does not require an additional air source, making it suitable for engineering applications.

[0051] In one embodiment, the synthetic dual-jet exciter 2 is disposed 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 disposed on the lower surface of the flap 3.

[0052] In one embodiment, the gust load reduction device based on the synthetic dual-jet cooperative control surface also includes a controller and an acceleration sensor;

[0053] The acceleration sensor is installed on the outer surface of the aircraft, wing 1 or flap 3 to measure the state of the aircraft under gust disturbance;

[0054] The controller is connected to the acceleration sensor, the power supply of the synthetic dual-jet exciter 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.

[0055] In this embodiment, after the acceleration sensor measures the aircraft's state under gust disturbance, it transmits the aircraft's longitudinal acceleration to the controller. Subsequently, the controller adjusts the voltage of the power supply of the synthetic dual-jet exciter 2 according to the aircraft's real-time longitudinal acceleration, thereby changing the amplitude of the vibrating diaphragm 23 in the synthetic dual-jet exciter 2, and thus changing the jet energy of the synthetic dual-jet exciter 2. The change in jet energy further affects the lift coefficient of the aircraft due to the change in the flow field structure. At the same time, the controller also adjusts the flap rotation drive mechanism of the flap 3 according to the aircraft's real-time longitudinal acceleration to adjust the flap 3 angle. Simultaneously, the controller also adjusts the rotation drive mechanism of the rotating plate for adjusting the angle of the jet outlet 22 according to the aircraft's real-time longitudinal acceleration, which can adjust the angle of the jet outlet 22. The angle of the jet outlet 22 and the angle of the flap 3 are adjusted synchronously. All three adjustments are used to change the longitudinal acceleration of the aircraft, ultimately achieving closed-loop control.

[0056] This method can effectively conserve energy and suppress the negative effects caused by flap 3 deflection during cruise. It is worth noting that the gust load reduction device based on the synthetic dual-jet cooperative control surface in this embodiment is activated only when the aircraft encounters strong gust interference, specifically when the aircraft is subjected to uncommanded longitudinal acceleration disturbances.

[0057] Reference Appendix Figure 4 When there is significant gust disturbance, increasing the jet energy increases its flow distance and stroke, enhances its adhesion effect, reduces the separation zone caused by the upward deflection of flap 3, and further increases the airflow velocity on the lower surface of flap 3. (See attached diagram) Figure 5 and attached Figure 6 Since the attached wall jets 4 and 5 effectively suppress the lower separation zone and increase the flow velocity on the lower surface based on the deflection of the flap 3, the load reduction capability of the wing when encountering gusts can be effectively improved.

[0058] The above description is merely an embodiment and does not constitute any limitation on the present invention. Any person skilled in the art can make many possible variations, modifications, or alterations to the technical solutions of the present invention without departing from the scope of the present invention. Therefore, any simple modifications, equivalent changes, and alterations made to the above embodiments based on the technical essence of the present invention, without departing from the scope of the present invention, should fall within the protection scope of the present invention.

Claims

1. A gust load reduction device based on a synthetic dual-jet cooperative control surface, characterized in that, It includes a wing body (1), a flap (3) rotatably disposed on the trailing edge of the wing body (1), and a synthetic dual-jet exciter (2) disposed on the flap (3). The two jet outlets (22) of the synthetic dual jet exciter (2) are located 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 angle between the flap (3) and the wing (1), the smaller the angle between the two jet outlets (22) and the lower surface of the flap (3); The jet outlet (22) is a strip-shaped hole along the span of the flap (3); The jet outlet (22) is formed by two rotating plates (221) hinged to the lower surface of the flap (3), and also includes a rotating plate rotation drive mechanism that can drive the four rotating plates (221) to rotate synchronously. The synthetic dual-jet exciter (2) includes two cavities (21), each cavity (21) is provided with a corresponding jet outlet (22), and the two cavities (21) are separated by a vibrating diaphragm (23).

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

3. The gust load reduction device based on the synthetic dual-jet cooperative control surface as described in claim 1, characterized in that, The two jet outlets (22) of the synthetic dual-jet actuator (2) are located upstream of the lower surface of the flap (3).

4. The gust load reduction device based on the synthetic dual-jet cooperative control surface as described in claim 1, characterized in that, The synthetic dual-jet exciter (2) is disposed inside the flap (3), and the outer end of the jet outlet (22) is disposed on the lower surface of the flap (3).

5. The gust load reduction device based on a synthetic dual-jet cooperative control surface as described in any one of claims 1-4, characterized in that, It also includes a controller and an acceleration sensor; The acceleration sensor is located on the outer surface of the aircraft, wing (1) or flap (3) to measure the state of the aircraft under gust disturbance; The controller is connected to the power supply of the acceleration sensor, the synthetic dual jet exciter (2), the flap rotation drive mechanism of the flap (3), and the rotating plate rotation drive mechanism that drives the adjustment of the angle of the jet outlet (22) according to the state of the aircraft under gust disturbance, so as to realize closed-loop control.

6. A method for reducing gust load based on a synthetic dual-jet cooperative control surface, characterized in that, Use the gust load reduction device based on the synthetic dual-jet cooperative control surface as described in any one of claims 1-5; When the aircraft encounters a gust of wind, the flaps (3) deflect upward, change the original camber of the wing body (1), reduce the airflow velocity on the upper surface of the wing body (1), and increase 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 cancels out the additional lift caused by the gust of wind. Turn on the synthetic dual jet exciter (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 intensity of the downward force generated by the flap (3); The flap (3) deflection, combined with the synthetic dual jet exciter (2), reduces 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), changes the velocity difference between the upper and lower surfaces of the wing body (1), thereby reducing the lift load of the aircraft under gusts and mitigating the gust load.

7. The gust load reduction method based on the synthetic dual-jet cooperative control surface as described in claim 6, characterized in that, in 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 at a large angle, forming a negative gust flap effect, which directly reduces 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 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), suppressing the separation zone caused by the deflection of the flap (3) and enhancing the efficiency of the lift load reduction caused by the deflection of the flap (3).

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