A composite noise reduction design structure for aerodynamic noise control of a lift-enhancing device

Abstract

The application discloses a composite noise reduction design structure of a high-lift device aerodynamic noise control, and relates to the technical field of noise control. The composite noise reduction design structure of the high-lift device aerodynamic noise control comprises a main wing and a trailing edge flap connected to the trailing edge of the main wing, the trailing edge of the main wing is provided with a trailing edge groove, the trailing edge groove is provided with a trailing edge acoustic soft surface structure, and the leading edge of the trailing edge flap is provided with a flap acoustic soft surface structure; when the trailing edge flap is retracted, the trailing edge flap completely covers the trailing edge acoustic soft surface structure, and the main wing completely covers the flap acoustic soft surface structure. The composite noise reduction design structure of the high-lift device aerodynamic noise control provided by the application can effectively realize noise control of the high-lift device of an aircraft in a take-off and landing state, does not need to introduce an additional actuating mechanism and a complex configuration, and does not change the aerodynamic characteristics of the high-lift device of the aircraft in a cruising state.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of noise control, in particular to a composite noise reduction design structure for aerodynamic noise control of a high-lift device. BACKGROUND

[0002] The high-lift device is one of the main sources of aircraft noise, and it is of great significance to control the aerodynamic noise of the high-lift device. The high-lift device is mainly composed of a leading edge slat, a trailing edge flap and related sliding rails, and the noise is closely related to the unsteady flow in the corresponding area and the interference with the solid wall.

[0003] At present, the noise reduction measures of the high-lift device mainly include trailing edge serrations, groove shielding, groove filling, leading edge droop, porous permeable material, side edge fence structure, side edge winglet, side edge porous material, vortex generator and continuous transition fairing.

[0004] Although these noise reduction measures have achieved certain noise reduction effect, they also have some shortcomings, mainly reflected in the great influence on the aerodynamic performance of the wing-high-lift device, the influence on the action of the high-lift device, the complexity of the structure design implementation, the poor adaptability to the noise control of the real aircraft, and some measures will also affect the aerodynamic characteristics during the cruise stage of the flight. SUMMARY

[0005] The purpose of the present application is to provide a composite noise reduction design structure for aerodynamic noise control of a high-lift device, which solves the problems of the great influence of the existing noise reduction measures on the aerodynamic performance of the high-lift device, the influence on the action of the high-lift device, the complexity of the structure design implementation, and the poor adaptability to the noise control of the real aircraft.

[0006] The technical solution adopted by the present application to solve its technical problems is: a composite noise reduction design structure for aerodynamic noise control of a high-lift device, comprising a main wing and a trailing edge flap connected to the trailing edge of the main wing, the trailing edge of the main wing is provided with a trailing edge groove, the trailing edge groove is provided with a trailing edge acoustic soft surface structure, and the leading edge of the trailing edge flap is provided with a flap acoustic soft surface structure; when the trailing edge flap is retracted, the trailing edge flap completely covers the trailing edge acoustic soft surface structure, and the main wing completely covers the flap acoustic soft surface structure.

[0007] Further, a plurality of trailing edge recess structures are arranged in the trailing edge groove along the span direction of the main wing.

[0008] Further, the leading edge of the trailing edge flap is provided with a plurality of flap protruding structures, the flap protruding structures correspond one-to-one to the trailing edge recess structures, and when the trailing edge flap is retracted, the flap protruding structures are accommodated in the trailing edge recess structures corresponding thereto.

[0009] Further, the leading edge of the main wing is connected with a leading edge slat wing, the leading edge slat wing is provided with a slat wing groove towards one side of the main wing, and the slat wing groove is provided with a slat wing acoustic soft surface structure; when the leading edge slat wing is retracted, the main wing completely covers the slat wing acoustic soft surface structure.

[0010] Further, the leading edge of the main wing is provided with a leading edge acoustic soft surface structure, and when the leading edge slat wing is retracted, the leading edge slat wing completely covers the leading edge acoustic soft surface structure.

[0011] Further, the slat wing groove is provided with a plurality of slat wing recess structures along the span direction of the leading edge slat wing.

[0012] Further, the leading edge of the main wing is provided with a plurality of leading edge convex structures, the leading edge convex structures correspond to the slat wing recess structures one by one, and when the leading edge slat wing is retracted, the leading edge convex structures are accommodated in the slat wing recess structures corresponding thereto.

[0013] Further, the leading edge slat wing is provided with a resonance sound absorption structure unit below the slat wing acoustic soft surface structure, and the slat wing acoustic soft surface structure is arrayed with through holes.

[0014] Further, the resonance sound absorption structure unit comprises a perforated plate provided with perforations, and a back cavity is formed between the perforated plate and the leading edge slat wing.

[0015] The beneficial effects of the present application are as follows:

[0016] The composite noise reduction design structure for aerodynamic noise control of the lift increasing device provided by the embodiments of the present application can effectively realize noise control of the lift increasing device of the aircraft in the take-off and landing state, does not need to introduce additional actuators and complex configurations, does not change the aerodynamic characteristics of the lift increasing device of the aircraft in the cruising state, has little influence on the action of the lift increasing device, and is simple in structure design and good in adaptability to real aircraft noise control. BRIEF DESCRIPTION OF DRAWINGS

[0017] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following will briefly introduce the drawings needed to be used in the embodiments. It should be understood that the following drawings only show some embodiments of the present application, and therefore should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can also be obtained without creative labor on the basis of these drawings.

[0018] Figure 1 is a structural schematic view of the connection of the lift increasing device and the main wing;

[0019] Figure 2 is a structural schematic view of the main wing;

[0020] Figure 3 is Figure 2 enlarged view of A in FIG. 1;

[0021] Figure 4 is a structural schematic view of a trailing edge flap;

[0022] Figure 5 is Figure 4 enlarged view of B in FIG. 1;

[0023] Figure 6 is a structural schematic view of a leading edge slat;

[0024] Figure 7 is Figure 6 enlarged view of C in FIG. 1;

[0025] Figure 8 is a structural schematic view of another angle of the main wing;

[0026] Figure 9 is Figure 8 enlarged view of D in FIG. 1;

[0027] Figure 10 is a sectional view of the leading edge slat;

[0028] Figure 11 is Figure 10 enlarged view of E in FIG. 1.

[0029] Reference signs:

[0030] 10-main wing; 101-trailing edge groove; 102-trailing edge acoustic soft surface structure; 103-trailing edge concave structure; 104-leading edge acoustic soft surface structure; 105-leading edge convex structure;

[0031] 20-trailing edge flap; 201-flap acoustic soft surface structure; 202-flap convex structure;

[0032] 30-leading edge slat; 301-slat groove; 302-slat acoustic soft surface structure; 303-slat concave structure; 304-resonance sound absorption structure unit; 305-perforated plate; 306-back cavity. DETAILED DESCRIPTION

[0033] In order to make the purpose, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application.

[0034] It should be noted that similar reference numerals and letters refer to like items throughout the accompanying drawings, and once an item is defined in one drawing, it is not necessary to further define and explain it in the subsequent drawings. The embodiments in the present application and the features in the embodiments can be combined with each other in the case of no conflict.

[0035] In the description of the embodiments of the present application, the indicated orientation or positional relationship is based on the orientation or positional relationship shown in the drawings, or the orientation or positional relationship commonly placed when the product of the application is used, or the orientation or positional relationship commonly understood by those skilled in the art. The terms "provided", "opened", "mounted", "connected", "linked" should be understood broadly, for example, can be fixedly connected, detachably connected and integrally connected; can be mechanically connected or electrically connected; can be directly connected or indirectly connected through an intermediate medium; and can be connected inside two elements.

[0036] The high-lift devices of the aircraft can include leading edge slats and trailing edge flaps, or only trailing edge flaps. At present, the high-lift device is one of the main sources of noise of the aircraft, and it is of great significance to realize the control of its aerodynamic noise. The noise mechanism of the leading edge slat includes flow separation, boundary layer / shear layer instability, generation / shedding / mixing of vortex structure, shear layer / vortex and wall interference, flow field-sound field coupling, cavity self-excited oscillation, slit resonance, etc. The noise mechanism of the trailing edge flap includes trailing edge flow separation / vortex shedding, turbulent pulsation, side edge large-scale vortex structure generation / mixing / shedding, and unsteady interaction of shear layer / side edge vortex and wall.

[0037] At present, the noise reduction measures for the leading edge slat mainly include trailing edge serrations, groove shielding, groove filling, leading edge droop, porous permeable material, etc. The noise reduction measures for the trailing edge flap mainly include side edge fence structure, side edge winglet, side edge porous material, vortex generator, continuous transition fairing, etc. However, these existing noise reduction measures have some deficiencies in specific research scenarios, mainly reflected in the influence on the aerodynamic performance of the wing-high lift device, the influence on the action of the high-lift device, the complexity of the structural design implementation, the adaptability to the noise control of the real aircraft, etc. Some measures will also affect the aerodynamic characteristics during the cruise stage of the flight process. For example, although the leading edge droop can achieve certain noise reduction effect, existing studies have pointed out that it may affect the aerodynamic performance, including the maximum stall angle of attack and the maximum lift drop. Although the bionic noise reduction design of the airfoil trailing edge serration can achieve good noise reduction effect at a certain Reynolds number, it will change the aerodynamic characteristics of the cruise configuration when used in the flap design, or it will require additional structural design to realize the configuration change in different flight stages, etc.

[0038] In order to solve the problem that the existing noise reduction measures have a great influence on the aerodynamic performance of the high-lift device, the embodiment of the present application provides a composite noise reduction design structure for aerodynamic noise control of a high-lift device, which can effectively realize noise control of the high-lift device of an aircraft in a take-off and landing state, and does not need to introduce additional actuators and complex configurations, nor change the aerodynamic characteristics of the high-lift device of the aircraft in a cruising state, has little influence on the action of the high-lift device, and is simple in structure design and good in adaptability to real aircraft noise control.

[0039] Referring to Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 , the composite noise reduction design structure for aerodynamic noise control of a high-lift device provided by the embodiment of the present application comprises a main wing 10 and a trailing edge flap 20 connected to the trailing edge of the main wing 10, the trailing edge of the main wing 10 is provided with a trailing edge groove 101, the trailing edge groove 101 is provided with a trailing edge acoustic soft surface structure 102, and the leading edge of the trailing edge flap 20 is provided with a flap acoustic soft surface structure 201; when the trailing edge flap 20 is retracted, the trailing edge flap 20 completely covers the trailing edge acoustic soft surface structure 102, and the main wing 10 completely covers the flap acoustic soft surface structure 201.

[0040] Referring to Figure 1 , the trailing edge of the main wing 10 is connected with the trailing edge flap 20, for the sake of simplifying the view, Figure 1 , the connecting structure between the main wing 10 and the trailing edge flap 20 is not shown. It should be understood by those skilled in the art that the main wing 10 and the trailing edge flap 20 are connected by using an existing connecting structure. Referring to Figure 1 , Figure 2 , Figure 3 , the trailing edge of the main wing 10 is provided with a trailing edge groove 101 extending along the span direction thereof, and the trailing edge groove 101 is provided with a trailing edge acoustic soft surface structure 102. Exemplarily, the trailing edge acoustic soft surface structure 102 can adopt a felt structure, a small-size soft protrusion array structure, a composite structure composed of a high-molecular fiber material and a foam matrix, or the like. For example, the trailing edge acoustic soft surface structure 102 is a rectangular structure, the length direction of which extends along the span direction of the main wing 10, and the trailing edge acoustic soft surface structure 102 can be installed by using adhesion, bolt and compression strip cooperation, or the like. The trailing edge acoustic soft surface structure 102 can be directly installed on the surface of the trailing edge groove 101; of course, the surface of the trailing edge groove 101 can also be provided with a mounting groove for accommodating the trailing edge acoustic soft surface structure 102, the trailing edge acoustic soft surface structure 102 is installed in the mounting groove, and the surface of the trailing edge acoustic soft surface structure 102 is flush with the surface of the trailing edge groove 101.

[0041] The flap acoustic soft surface structure 201 can adopt a felt structure, a small-size soft convex array structure, a composite structure composed of a polymer fiber material and a foam matrix, or the like. For example, the flap acoustic soft surface structure 201 is a rectangular structure, the length direction of which extends along the span direction of the trailing edge flap 20, and the flap acoustic soft surface structure 201 can be installed by means of bonding, screwing, and cooperation with a pressing strip, or the like. The flap acoustic soft surface structure 201 can be directly installed on the surface of the trailing edge flap 20. Of course, the trailing edge flap 20 can also be provided with a mounting groove for accommodating the flap acoustic soft surface structure 201, and the flap acoustic soft surface structure 201 is installed in the mounting groove, and the surface of the flap acoustic soft surface structure 201 is flush with the surface of the trailing edge flap 20.

[0042] The composite noise reduction design structure for controlling the aerodynamic noise of the lift-increasing device provided by the embodiments of the present application can reduce the unsteady force of the shear layer generated in the trailing edge groove 101 impacting the surface of the trailing edge groove 101 when the aircraft is in the take-off and landing state, and the trailing edge acoustic soft surface structure 102 has a rough soft surface, which can generate a turbulence effect on the flow in the trailing edge groove 101, weaken the coherence of the airflow, and affect vortex shedding, so as to achieve the suppression of the unsteady flow and the solid wall effect, and further achieve the noise reduction effect. The flap acoustic soft surface structure 201 is arranged at the leading edge of the trailing edge flap 20, which can reduce the unsteady force of the shear layer generated in the trailing edge groove 101 impacting the leading edge wall surface of the trailing edge flap 20, and the rough soft surface of the flap acoustic soft surface structure 201 can also weaken the coherence of the airflow in the gap between the main wing 10 and the trailing edge flap 20, so as to achieve the suppression of the unsteady flow and the solid wall effect, and improve the noise reduction effect. When the aircraft is in the cruising state, the trailing edge flap 20 is retracted, the trailing edge acoustic soft surface structure 102 is completely covered by the trailing edge flap 20, and the flap acoustic soft surface structure 201 is completely covered by the main wing 10, so that the overall external structure is consistent with the basic configuration without the trailing edge acoustic soft surface structure 102 and the flap acoustic soft surface structure 201, and the aerodynamic shape and performance are not changed.

[0043] When the aircraft is in the cruising state, the trailing edge acoustic soft surface structure 102 and the flap acoustic soft surface structure 201 are completely covered, so that the contact between the trailing edge acoustic soft surface structure 102 and the flap acoustic soft surface structure 201 and the high-speed airflow is reduced, the wear of the trailing edge acoustic soft surface structure 102 and the flap acoustic soft surface structure 201 is reduced, the service life of the trailing edge acoustic soft surface structure 102 and the flap acoustic soft surface structure 201 is improved, and the maintenance cost is reduced. Referring to Figure 2 、 Figure 3 、 Figure 4 、 Figure 5The trailing edge acoustic soft surface structure 102 and the flap acoustic soft surface structure 201 can be arranged with a plurality of small holes in an array to form different levels of spoiler surfaces, further improving the noise reduction effect.

[0044] Referring to Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 The trailing edge recess 101 is provided with a plurality of trailing edge recess structures 103 along the span direction of the main wing 10. The leading edge of the trailing edge flap 20 is provided with a plurality of flap protruding structures 202, which correspond one-to-one with the trailing edge recess structures 103. When the trailing edge flap 20 is retracted, the flap protruding structure 202 is accommodated in the corresponding trailing edge recess structure 103.

[0045] Referring to Figure 2 , Figure 3 The trailing edge recess structure 103 can be integrally formed with the main wing 10, that is, a metal skin structure with a local recess is directly used, or a recess structure made of metal material or high polymer material is separately processed and then installed on the main wing 10 by bonding or bolt fixing. Of course, the trailing edge recess structure 103 can also be integrally formed with the trailing edge acoustic soft surface structure 102, so that the trailing edge recess structure 103 forms a soft recess structure. Compared with other structures, the interaction between the recess position and the airflow is weakened, but still has good noise reduction effect.

[0046] Referring to Figure 4 , Figure 5 The flap protruding structure 202 can be integrally formed with the trailing edge flap 20, that is, a metal skin structure with a local protrusion is directly used, or a protruding structure made of metal material or high polymer material is separately processed and then installed on the trailing edge flap 20 by bonding or bolt fixing. Of course, the flap protruding structure 202 can also be integrally formed with the flap acoustic soft surface structure 201, so that the flap protruding structure 202 forms a soft protruding structure. Compared with other structures, the interaction between the protruding position and the airflow is weakened, but still has good noise reduction effect.

[0047] The composite noise reduction design structure for aerodynamic noise control of a lift-enhancing device provided in an embodiment of the present application is such that, when the aircraft is in the take-off and landing state, a trailing edge recessed structure 103 is provided in the trailing edge groove 101 of the main wing 10, which will cause disturbances to the airflow passing through the lower surface of the trailing edge of the main wing 10, thereby suppressing the development of the shear layer and reducing the intensity of the unsteady flow; and a flap protruding structure 202 is provided at the leading edge of the trailing edge flap 20, which will have a disturbing effect on the airflow in the gap between the main wing 10 and the trailing edge flap 20, suppressing its separation and the generation of large-scale vortices, thereby improving the noise reduction effect; when the aircraft is in the cruising state, the trailing edge flap 20 is retracted, and the flap protruding structure 202 is accommodated in the trailing edge recessed structure 103 corresponding thereto, so that the overall external structure is consistent with the basic configuration without the trailing edge recessed structure 103 and the flap protruding structure 202, without changing the aerodynamic shape and performance.

[0048] See also Figure 1 、 Figure 6 、 Figure 7 In an embodiment of the present application, a composite noise reduction design structure for aerodynamic noise control of a high-lift device is provided. A leading edge slat 30 is connected to the leading edge of the main wing 10. A slat groove 301 is provided on the side of the leading edge slat 30 facing the main wing 10. A slat acoustic soft surface structure 302 is provided in the slat groove 301. When the leading edge slat 30 is retracted, the main wing 10 completely covers the slat acoustic soft surface structure 302.

[0049] See also Figure 1 , the leading edge of the main wing 10 is connected to the leading edge slat 30, to simplify the view, Figure 1 The connection structure between the two is not shown. It should be known to those skilled in the art that the main wing 10 and the leading edge slat 30 are connected using an existing connection structure. Figure 1 、 Figure 6 、 Figure 7 The side of the leading edge slat 30 facing the main wing 10 is provided with a slat groove 301 extending along the span of the leading edge slat 30. A slat acoustic soft surface structure 302 is disposed within the slat groove 301. For example, the slat acoustic soft surface structure 302 can be a felt structure, an array of small-scale soft protrusions, or a composite structure composed of a polymer fiber material and a foam matrix. For example, the slat acoustic soft surface structure 302 is a rectangular structure, with its length extending along the span of the leading edge slat 30. The slat acoustic soft surface structure 302 can be installed using methods such as bonding, bolts, and a combination of battens. The slat acoustic soft surface structure 302 can be directly installed on the surface of the slat groove 301; of course, the surface of the slat groove 301 can also be provided with a mounting groove for accommodating the slat acoustic soft surface structure 302, and the slat acoustic soft surface structure 302 is installed in the mounting groove, and the surface of the slat acoustic soft surface structure 302 is flush with the surface of the slat groove 301.

[0050] The composite noise reduction design structure for aerodynamic noise control of the high-lift device provided in the embodiments of the present application can reduce the unsteady force of the shear layer generated in the slat groove 301 impacting the surface thereof when the aircraft is in the take-off and landing state by arranging the slat acoustic soft surface structure 302 in the slat groove 301 of the leading edge slat 30. Meanwhile, the rough soft surface of the slat acoustic soft surface structure 302 can generate a turbulence effect on the flow in the slat groove 301, weaken the coherence of the airflow, and affect vortex shedding, so as to inhibit the interaction between the unsteady flow and the solid wall surface, and further achieve the effect of noise reduction. When the aircraft is in the cruising state, the leading edge slat 30 is retracted, and the slat acoustic soft surface structure 302 is completely covered by the main wing 10, so that the overall external structure is consistent with the basic configuration without the slat acoustic soft surface structure 302, and the aerodynamic shape and performance are not changed.

[0051] Referring to Figure 1 , Figure 8 , Figure 9 The leading edge of the main wing 10 is provided with a leading edge acoustic soft surface structure 104. After the leading edge slat 30 is retracted, the leading edge slat 30 completely covers the leading edge acoustic soft surface structure 104.

[0052] The leading edge acoustic soft surface structure 104 can adopt a felt structure, a small-size soft protrusion array structure, a composite structure composed of a high polymer fiber material and a foam matrix, or the like. For example, the leading edge acoustic soft surface structure 104 is a rectangular structure, the length direction of which extends along the span direction of the main wing 10, and the leading edge acoustic soft surface structure 104 can be installed by means of adhesion, screwing, and cooperation with a pressing strip, or the like. The leading edge acoustic soft surface structure 104 can be directly installed on the surface of the main wing 10. Of course, the main wing 10 can also be provided with a mounting groove for accommodating the leading edge acoustic soft surface structure 104, and the leading edge acoustic soft surface structure 104 is installed in the mounting groove, and the surface of the leading edge acoustic soft surface structure 104 is flush with the surface of the main wing 10.

[0053] The composite noise reduction design structure for aerodynamic noise control of the high-lift device provided in the embodiments of the present application can reduce the unsteady force of the shear layer generated in the slat groove 301 impacting the surface thereof when the aircraft is in the take-off and landing state by arranging the slat acoustic soft surface structure 302 in the slat groove 301 of the leading edge slat 30. Meanwhile, the rough soft surface of the slat acoustic soft surface structure 302 can generate a turbulence effect on the flow in the slat groove 301, weaken the coherence of the airflow, and affect vortex shedding, so as to inhibit the interaction between the unsteady flow and the solid wall surface, and further achieve the effect of noise reduction. When the aircraft is in the cruising state, the leading edge slat 30 is retracted, and the slat acoustic soft surface structure 302 is completely covered by the main wing 10, so that the overall external structure is consistent with the basic configuration without the slat acoustic soft surface structure 302, and the aerodynamic shape and performance are not changed.

[0054] When the aircraft is in cruising state, the contact of the slat acoustic soft surface structure 302 and the acoustic soft surface structure 104 with high-speed airflow is reduced due to the full coverage of the slat acoustic soft surface structure 302 and the acoustic soft surface structure 104, the wear of the slat acoustic soft surface structure 302 and the acoustic soft surface structure 104 is reduced, the service life of the slat acoustic soft surface structure 302 and the acoustic soft surface structure 104 is improved, and the maintenance cost is reduced. See Figure 6 、 Figure 7 、 Figure 8 、 Figure 9 The slat acoustic soft surface structure 302 and the acoustic soft surface structure 104 can be arranged with a plurality of small holes in an array to form different levels of spoiler surfaces, further improving the noise reduction effect.

[0055] See Figure 1 、 Figure 6 、 Figure 7 、 Figure 8 、 Figure 9 The slat recess 301 is provided with a plurality of slat recess structures 303 along the span direction of the leading edge slat 30. The leading edge of the main wing 10 is provided with a plurality of leading edge protruding structures 105, and the leading edge protruding structure 105 corresponds to the slat recess structure 303 one by one. When the leading edge slat 30 is retracted, the leading edge protruding structure 105 is accommodated in the corresponding slat recess structure 303.

[0056] See Figure 6 、 Figure 7 The slat recess structure 303 can be integrally machined with the leading edge slat 30, that is, a metal skin structure with a local recess is directly used, or the recess structure made of metal material or high polymer material is separately processed and then installed on the leading edge slat 30 by bonding or bolt fixing. Of course, the slat recess structure 303 can also be integrally formed with the slat acoustic soft surface structure 302, so that the slat recess structure 303 forms a soft recess structure. Compared with other structures, this structure weakens the interaction between the recess position and the airflow, but still has good noise reduction effect.

[0057] See Figure 8 、 Figure 9The leading edge protruding structure 105 can be integrally formed with the main wing 10, that is, a metal skin structure with local protrusions can be directly used. Alternatively, a protruding structure made of metal or polymer materials can be separately processed and then installed on the main wing 10 by bonding or bolting. Of course, the leading edge protruding structure 105 can also be integrally formed with the leading edge acoustic soft surface structure 104, thus forming a soft protruding structure. Compared with other structures, this structure weakens the interaction between the protruding position and the airflow, but still has a good noise reduction effect.

[0058] The composite noise reduction design structure for aerodynamic noise control of a lift-enhancing device provided in an embodiment of the present application is such that, when the aircraft is in a take-off and landing state, a slat recessed structure 303 is provided in the slat groove 301 of the leading edge slat 30, which will interfere with the large-scale vortex structure and motion coherence in the slat groove 301; and a leading edge protruding structure 105 is provided at the leading edge of the main wing 10, which will disturb the airflow in the gap between the main wing 10 and the leading edge slat 30, inhibiting its separation and the generation of large-scale vortices, thereby improving the noise reduction effect; when the aircraft is in a cruising state, the leading edge slat 30 is retracted, and the leading edge protruding structure 105 is accommodated in the corresponding slat recessed structure 303, so that the overall external structure is consistent with the basic configuration without the rear slat recessed structure 303 and the leading edge protruding structure 105, and the aerodynamic shape and performance are not changed.

[0059] See also Figure 10 、 Figure 11 The leading edge slat 30 is provided with a resonance sound absorption structure unit 304 located below the slat acoustic soft surface structure 302 , and the slat acoustic soft surface structure 302 is provided with through holes arranged in an array.

[0060] Illustratively, the resonant sound absorbing structural unit 304 includes a perforated plate 305 having perforations thereon, and a back cavity 306 is formed between the perforated plate 305 and the slat 30. The perforated plate 305 can be connected to the slat 30 by bonding, welding, or bolting.

[0061] The composite noise reduction design structure for aerodynamic noise control of a lift-boosting device provided in an embodiment of the present application has a resonant sound-absorbing structural unit 304 provided. When the aircraft is in the take-off and landing state, the noise can be transmitted to the resonant sound-absorbing structural unit 304 through the through-holes on the slat acoustic soft surface structure 302. The noise enters the back cavity 306 through the perforations of the perforated plate 305. When excited by fluid pulsations of a corresponding frequency, it will produce a function similar to that of a Helmholtz resonator to absorb the acoustic energy of the noise, thereby achieving the purpose of noise reduction. At the same time, air vibrations will also cause micro-disturbance to the fluid in the slat groove 301, further improving the noise reduction effect.

[0062] The composite noise reduction design structure for the aerodynamic noise control of the lift-increasing device provided by the embodiment of the application can effectively achieve noise control of the lift-increasing device of the aircraft in the take-off and landing state, does not need to introduce additional actuators and complex configurations, does not change the aerodynamic characteristics of the lift-increasing device of the aircraft in the cruising state, has little influence on the action of the lift-increasing device, is simple in structure design, and is good in adaptability to the noise control of the real aircraft.

[0063] The above is only a preferred embodiment of the application, and does not limit the application in any form. According to the technical essence of the application, any simple modification, equivalent replacement and improvement of the above embodiment, and the like, still belong to the protection scope of the technical scheme of the application within the spirit and principles of the application.

Claims

1. A composite noise reduction design structure for aerodynamic noise control of a lift-enhancing device, characterized in that: The invention comprises a main wing (10) and a trailing edge flap (20) connected to the trailing edge of the main wing (10); the leading edge of the main wing (10) is connected to a leading edge slat (30); A slat groove (301) is provided on one side of the leading edge slat (30) facing the main wing (10), a slat acoustic soft surface structure (302) is provided in the slat groove (301), and a leading edge acoustic soft surface structure (104) is provided at the leading edge of the main wing (10); when the leading edge slat (30) is retracted, the main wing (10) completely covers the slat acoustic soft surface structure (302), and the leading edge slat (30) completely covers the leading edge acoustic soft surface structure (104); The trailing edge of the main wing (10) is provided with a trailing edge groove (101), a trailing edge acoustic soft surface structure (102) is provided in the trailing edge groove (101), and the leading edge of the trailing edge flap (20) is provided with a flap acoustic soft surface structure (201); when the trailing edge flap (20) is retracted, the trailing edge flap (20) completely covers the trailing edge acoustic soft surface structure (102), and the main wing (10) completely covers the flap acoustic soft surface structure (201); The slat acoustic soft surface structure (302), the leading edge acoustic soft surface structure (104), the trailing edge acoustic soft surface structure (102), and the flap acoustic soft surface structure (201) are all felt structures, soft protrusion array structures, or composite structures of polymer fiber materials and foam matrix; A plurality of trailing edge recessed structures (103) are provided in the trailing edge groove (101) of the main wing (10) along the span direction of the main wing (10), and a plurality of slat recessed structures (303) are provided in the slat groove (301) of the leading edge slat (30) along the span direction of the leading edge slat (30).

2. The composite noise reduction design structure for aerodynamic noise control of a lift-enhancing device according to claim 1 is characterized in that: The leading edge of the trailing edge flap (20) is provided with a plurality of flap protruding structures (202), the flap protruding structures (202) corresponding one to one with the trailing edge recessed structures (103), and when the trailing edge flap (20) is retracted, the flap protruding structures (202) are accommodated in the trailing edge recessed structures (103) corresponding thereto.

3. The composite noise reduction design structure for aerodynamic noise control of a lift-enhancing device according to claim 1, characterized in that: The leading edge of the main wing (10) is provided with a plurality of leading edge protruding structures (105), the leading edge protruding structures (105) corresponding one to one with the slat recessed structures (303), and when the leading edge slat (30) is retracted, the leading edge protruding structures (105) are accommodated in the corresponding slat recessed structures (303).

4. The composite noise reduction design structure for aerodynamic noise control of a lift-enhancing device according to claim 1, characterized in that: The leading edge slat (30) is provided with a resonance sound absorption structure unit (304) located below the slat acoustic soft surface structure (302), and the slat acoustic soft surface structure (302) is provided with through holes arranged in an array.

5. The composite noise reduction design structure for aerodynamic noise control of a lift-enhancing device according to claim 4 is characterized in that: The resonant sound absorption structural unit (304) comprises a perforated plate (305), the perforated plate (305) is provided with perforations, and a back cavity (306) is formed between the perforated plate (305) and the leading edge slat (30).

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