WO2015139416A1

WO2015139416A1 - Recess filling slat for airplane wing, high-lift system, and noise reduction method

Info

Publication number: WO2015139416A1
Application number: PCT/CN2014/084770
Authority: WO
Inventors: 徐康乐; 陈迎春; 李亚林; 叶军科; 毛俊; 蔡锦阳
Original assignee: 中国商用飞机有限责任公司; 中国商用飞机有限责任公司上海飞机设计研究院
Priority date: 2014-03-19
Filing date: 2014-08-20
Publication date: 2015-09-24
Also published as: CN103879551B; CN103879551A

Abstract

The present invention provides a recess filling slat for an airplane wing, comprising: a deployable leading edge slat; and at least one recess filling element, movable between an internal folding position of the deployable leading edge slat and an external deploying position of the deployable leading edge slat, the at least one recess filling element being built to move from the folding position to the deploying position during deployment of the deployable leading edge slat, so as to form the recess filling slat together with the leading edge slat. The present invention further provides a low-noise high-lift system for an airplane wing and a method for reducing airplane noise related to a high-lift system. While ensuring a requirement for pneumatic performance of a high-lift system in a low speed state and saving precious space at a leading edge of a fixed wing, the present invention deploys a recess filling element to mitigate or shield a major sound source area of a leading edge slat.

Description

Filling slats and high lift systems and noise reduction methods for recesses of aircraft wings

The present invention relates to a device for achieving a low-noise characteristic of a leading edge slat that is deployed under high lift conditions and recovered in an aircraft cruise state, and is in the field of aircraft high lift systems. Background technique

Aircraft noise radiation levels are a very important indicator of the safety, economy, comfort, environmental protection (noise, carbon emissions, etc.) of modern large passenger aircraft. In recent decades, with high bypass ratio aviation The engine noise is significantly reduced, aircraft body noise becomes the most important source of noise during take-off and landing, and the aircraft's high-lift system aerodynamic noise is the most important part of aircraft body noise.

Modern large-scale civil aircraft high-lift system leading edge devices are usually in the form of slats. As shown in Fig. 1, the shape of the conventional leading edge slat 101 matches the leading edge of the aircraft fixed wing 102 to recover the leading edge slat 101 by a high lift mechanism in a cruise state. To this end, the rear surface 1 1 1 of the leading edge slat 101 is designed to generally form a pocket. In the unfolded state of the leading edge slat, the incoming flow will form a recirculation zone 121 in this recessed area. It is understood that the recirculation zone is mainly composed of a large vortex of strong strength, and the flow structure is unstable in the region of the cavity, so that the leading edge slat 101 generates a high level of noise radiation. In order to reduce the radiation level of the aerodynamic noise of the leading edge slat, a slat pocket filling technique has been proposed, that is, a recessed slat (SCF slat) is formed. However, in order to ensure that the aerodynamic performance of the high lift system is not impaired, the shape of the leading edge of the fixed wing must remain unchanged, which will result in a mismatch between the shape of the trailing edge of the leading edge slat and the leading edge of the fixed wing, resulting in the leading edge slat Cannot be recycled during cruise.

In order to achieve the recovery of the SCF slats at a high speed, the inventor A. Smirovich et al., in the Chinese Patent Application No. CN 102834315A, proposes to design the fixed-wing leading edge to be movable. Specifically, as shown in Figure 2, the patent application is In an embodiment of the exposed aircraft high lift system 400, the leading edge wing slat 202 is configured as a pocket filled slat, in which case the storage structure of the leading edge slat 202 will be if the conventional wing is still used An overlap region 208 is formed with the main wing member to form interference with the main wing member when the leading edge wing slat is in the storage position. In order to achieve recovery of the pocket fill slat, the patent also provides a rigid leading edge element 402 that is movably coupled to the main wing element, the rigid front edge element 402 being configured to connect the upper machine of the main wing element in the deployed position The outer edge of the wing surface 408 and the outer edge of the lower wing surface 410 thereby form a continuous outer mold line shape of the aircraft wing and are configured to be placed on the outer edge and lower machine of the upper wing surface 408 when in the storage position. Behind the outer edge of the wing surface 410 such that the leading edge wing slat 202 abuts the outer edge of the upper wing surface 408 and the lower wing surface 410 when the front edge wing slat 202 is retracted to the stowed position The outer edge thus forms a continuous outer mold line shape of the aircraft wing. To this end, the patent specifically designs a recovery mechanism that includes a plate 402, a linear drive mechanism 404, and a guide 406. As further shown in Fig. 2, the specific realization of the recovery of the leading edge wing slat 202 is as follows: When the plate member 402 is configured to be in the storage position, the plate member is placed within the main wing member. By using the linear actuator 404, the panel 402 is switched between a storage position (shown in phantom in the figure) and a deployed position. To aid in proper translation of the panel 402 between the deployed position and the stowed position, the guide 406 can guide and/or rotate the panel in place.

However, the above-mentioned recycling mechanism necessarily requires a large amount of space occupying the leading edge of the main wing element, which is bound to be greatly limited by other actuators and piping in the main wing element. In addition, in the low speed up state, the aerodynamic load on the leading edge of the main wing element is large, requiring the movable plate member 402 to have a large rigidity, and at the same time requiring the plate member 402 and the main wing member to be in front of the recess filling slat 202. The other parts of the rim should have good sealing properties after joining. Summary of the invention

The present invention is advantageous in that a four-hole filling slat is formed by combining a conventional leading edge slat and a pocket filling element, which can realize a pocket filling seam without changing the shape of the leading edge of the fixed wing of the aircraft. The wing is recovered at high speed while reducing aircraft noise and ensuring aerodynamic performance of the high lift system. To this end, in accordance with one aspect of the invention, an aircraft wing recessed slat is provided, comprising:

Expandable leading edge slat;

At least one pocket filling member movable between a retracted position inside the expandable leading edge slat and a deployed position outside the expandable leading edge slat, the at least one pocket filling element construction The unfolded leading edge slat is moved from the recovery position to the deployed position to form the pocket fill slat with the leading edge slat.

^ Particularly preferably, the pocket filling element is a pocket filling sheet.

Further preferably, the at least one pocket filling element is configured to pivot outwardly to the deployed position and pivot inwardly to the retracted position.

Still further preferably, the at least one pocket filling element comprises an upper pocket fill sheet and a lower pocket fill sheet.

Still further preferably, the upper pocket filler sheet is coupled to the rear surface of the slat of the deployable leading edge slat by an upper hinge, the lower pocket filler sheet being passed through the lower hinge and the expandable leading edge The lower surface of the slat of the slat is connected.

Still further preferably, the upper pocket filler sheet and the lower pocket filler sheet are respectively coupled with an actuating mechanism to automatically pivot outwardly to the deployed position upon exiting the recovery position.

Still further preferably, the actuating mechanism comprises a spring mechanism or a hydraulic mechanism, the spring mechanism or hydraulic mechanism being disposed inside the deployable leading edge slat.

According to another aspect of the present invention, a low noise high lift system for an aircraft wing is provided, comprising:

a fixed wing comprising a leading edge upper surface and a leading edge lower surface;

a leading edge slat operatively coupled to the fixed wing for movement between a recovery position including a slat upper surface, a slat lower surface, and a slat rear surface, the seam The upper surface of the wing and the lower surface of the slat are configured to form a continuous contour with the upper surface of the leading edge and the lower surface of the leading edge, respectively, in the recovery position;

At least one pocket filling element movably coupled to the leading edge slat, wherein the at least one pocket filling element is configured to retract to the front in the retracted position The edge slats extend inside the deployed position to the outside of the slat rear surface to form a pocket fill slat with the leading edge slat.

Preferably, the pocket filling element is a pocket filling sheet.

Still further preferably, the upper pocket filler sheet is joined to the rear surface of the slat by an upper hinge, and the lower pocket filler sheet is joined to the lower surface of the slat by a lower hinge.

Still further preferably, the actuating mechanism comprises a spring mechanism or a hydraulic mechanism, the spring mechanism or hydraulic mechanism being disposed inside the leading edge slat.

In accordance with still another aspect of the present invention, a method for reducing aircraft noise associated with a high lift system is provided, comprising:

Spreading the leading edge slat from the leading edge of the fixed wing to a high lift position;

Resetting at least one four-hole filling element associated with the leading edge slat from a recovery position inside the leading edge slat to a deployed position, in the deployed position, the at least one pocket filling element and the front The edge slats together form a pocket-filled slat.

Preferably, the pocket filling element comprises a pocket filling sheet, wherein resetting the at least one pocket filling sheet comprises pivoting the at least one pocket filling sheet outward to the deployed position to form the pocket filling Slatted outline.

Further preferably, the at least one pocket filling sheet comprises an upper pocket filling sheet and a lower pocket filling sheet, wherein the at least one pocket filling element associated with the leading edge slat comprises the upper pocket A filler panel is coupled to the rear surface of the slat of the leading edge slat by an upper hinge, and the lower pocket filler sheet is coupled to the lower surface of the slat of the leading edge slat by a lower hinge.

Still further preferably, pivoting the at least one pocket filler sheet outward comprises including The actuating mechanism coupled to the at least one pocket filler sheet is released from its retracted position to the extended position.

Still more preferably, the actuating mechanism includes a spring mechanism or a hydraulic mechanism, and the spring mechanism or hydraulic mechanism is disposed inside the leading edge slat.

By the above, the invention does not need to change the shape of the leading edge of the fixed wing of the aircraft, so that the valuable space of the leading edge of the fixed wing can be saved. At the same time, since the aerodynamic load on the rear surface of the slat is small, the load of the pocket filling element of the leading edge slat is small, and it is not easy to be bent and deformed. The invention reduces the aerodynamic noise radiation level of the slat by weakening or shielding the main sound source area of the leading edge slat by expanding the recess filling element while ensuring the aerodynamic performance requirement of the high lift system in the low speed state.

These and other aspects of the present invention will be apparent from and elucidated with reference to the embodiments described herein. DRAWINGS

The structure and operation of the present invention, as well as further objects and advantages will be better understood from the following description in conjunction with the accompanying drawings in which

Figure 1 is a schematic diagram showing the principle of aerodynamic noise generation in the pocket of the leading edge slat under the existing large lift system;

Figure 2 is a schematic cross-sectional view of another prior art high lift system in which the leading edge slat is a pocket filled slat and the main wing element is provided with a movable panel;

3 is a cross-sectional view of a high lift system in accordance with a preferred embodiment of the present invention in which the two pocket fill sheets associated with the leading edge slats assume different states in the deployed position and the retracted position. detailed description

Specific embodiments of the invention are disclosed herein as required. However, it should be reflected in various forms. Therefore, the specific details disclosed herein are not considered to be limiting. It is intended to be the basis of the claims, and as a matter of the teachings of

It should be noted that the orientations of the structures and actions used to explain the various parts of the disclosed embodiments, such as the upper surface, the lower surface, the inward, the outward, etc., are not absolute, but rather . These representations are suitable when the various parts of the disclosed embodiments are located in the positions shown in the figures. If the position or frame of reference of the disclosed embodiment changes, these representations also change depending on the location or frame of reference of the disclosed embodiment.

A low noise high lift system for an aircraft wing in accordance with a preferred embodiment of the present invention is shown in FIG. As shown in Fig. 3, in the present embodiment, the low noise high lift system for an aircraft wing includes a fixed wing 10, a leading edge slat 30, an upper pocket filling piece 51 and a lower pocket filling piece 53. The fixed wing 10 has a leading edge upper surface 1 1 and a leading edge lower surface 13. The leading edge slat 30 has two different positions relative to the fixed wing 10, namely a recovery position (shown in phantom) and a deployed position. The leading edge slat 30 is operatively coupled to the fixed wing 10, such as by rails 70, such that it is recovered and deployed through the rail 70. As shown in Fig. 3, the guide rail 70 is limited by the front beam 15 of the fixed wing 10 and extends beyond the front edge of the fixed wing and retracts inside the fixed wing to effect deployment and recovery of the leading edge slat 30.

As shown in FIG. 3, in the present embodiment, the leading edge slat 30 includes a slat upper surface 31, a slat lower surface 33, and a slat rear surface 35, and the slat upper surface 31 and the slat lower surface 33 are configured to be in a recovery position. A continuous contour is formed with the leading edge upper surface 1 1 and the leading edge lower surface 13, respectively.

As shown in FIG. 3, in the present embodiment, the upper pocket filling piece 51 and the lower pocket filling piece 53 are pivotally connected to the leading edge slats 30, respectively, to collectively constitute a pocket filling slat, for example, a concave The hole filling piece 51 is connected to the slat rear surface 35 through the upper chain 61, and the lower pocket filling piece 53 is connected to the slat lower surface 33 through the lower hinge 63. Wherein the upper pocket filler sheet 51 and the lower pocket filler sheet 53 are configured to retract to the interior of the leading edge slat 30 when in the retracted position and to extend beyond the slat rear surface 35 to the leading edge when in the deployed position. Slat 30 Together, a pocket fill slat is formed.

Specifically, when the aircraft is in the low speed up state, the upper pocket filling piece 51 and the lower pocket filling piece 53 are associated with the leading edge slat 30 by a hinge, and thus can be actuated by means of a spring mechanism or a hydraulic mechanism ( Figure not shown) Automatically pivots outward to the deployed position to form a complete pocket fill profile that meets the designed pocket fill slat profile; when the aircraft is in a cruise state, the upper pocket fills the 51 and the lower The pocket filling piece 53 is pushed into the recovery state by the leading edge of the fixed wing 10 during the recovery of the leading edge slat 30, or the actuating mechanism is automatically pivoted inward to the recovery state. In this retracted state, both the upper pocket filling piece 51 and the lower pocket filling piece 53 are housed inside the leading edge slit 30. The actuating means for the recovery and deployment of the pocket filler can be mounted, for example, inside the rear surface 35 of the slat, following the movement of the leading edge slat 30.

Although there are two pocket filling sheets in this embodiment, it should be understood that in other embodiments, the number of pocket filling sheets may be one or, if possible, a plurality.

It should be understood that in the present embodiment, the slat upper surface 31 of the recovered leading edge slat 30 forms a continuous contour with the leading edge upper surface 1 1 of the fixed wing 10, and the curvature is continuous. The slat lower surface 33 of the leading edge slat 30 forms a continuous contour with the leading edge lower surface 13 of the fixed wing 10, and the curvature is also continuous. The recovered slat lower surface 33 and the leading edge lower surface 13 can be made airtight by means of rubber strips or rubber gaskets to prevent external airflow from flowing from the lower surface joint of the aircraft wing during cruising. The inside of the wing affects the aerodynamic performance of the wing.

It should be noted that, in FIG. 3, a broken line L indicates a position where the upper pocket filling sheet 51 and the lower pocket filling sheet 53 are not in the retracted position, but due to the above configuration of the filling sheet, They are in the retracted position such that the slat rear surface 35 of the leading edge slat 30 conforms to the leading edge surface of the fixed wing 10 to complete the recovery of the leading edge slat 30.

The technical contents and technical features of the present invention have been disclosed as above, but it will be understood that those skilled in the art can make various changes and modifications to the above-described structures and shapes, including separately disclosed or claimed herein. a combination of technical features, Other combinations of these features are explicitly included. These variations and/or combinations are all within the technical scope of the present invention and fall within the scope of the claims of the present invention. It is to be noted that the use of a single element in the claims is intended to include one or more of such elements. In addition, any reference signs in the claims should not be construed as limiting the scope of the invention.

Claims

Claim

WHAT IS CLAIMED IS: 1. An aircraft wing fills a slat with a pocket, the method comprising:

Expandable leading edge slat;

At least one pocket filling element movable between a retracted position inside the deployable leading edge slat and a deployed position outside the deployable leading edge slat, the at least one pocket filling element Constructed to move from the retracted position to the deployed position when the expandable leading edge slat is deployed, thereby forming the pocket fill slat with the leading edge slat.

The pocket filling slat for an aircraft according to claim 1, wherein the pocket filling member is a pocket filling sheet.

3. The recessed slat for aircraft according to claim 2, wherein the at least one 1HJ pocket filling element is configured to pivot outwardly to the deployed position and pivot inwardly to the recovery position.

The pocket filling slat for an aircraft according to claim 3, wherein the at least one pocket filling member comprises an upper pocket filling sheet and a lower pocket filling sheet.

The pocket filling slat for an aircraft according to claim 4, wherein the upper pocket filling piece is connected to a rear surface of the slat of the deployable leading edge slat by an upper hinge, The lower pocket filler is coupled to the lower surface of the slat of the deployable leading edge slat by a lower hinge.

The pocket filling slat for an aircraft according to claim 5, wherein the upper pocket filling piece and the lower pocket filling piece are respectively connected with an actuating mechanism so as to be able to leave the recycling position When it is automatically pivoted outward to the deployed position.

The recessed slat for aircraft according to claim 6, wherein the actuating mechanism comprises a spring mechanism or a hydraulic mechanism, and the spring mechanism or hydraulic mechanism is disposed on the expandable front edge slit Wing interior.

8. A low noise, high lift system for aircraft wings, comprising:

a leading edge slat operatively coupled to the fixed wing for movement between a recovery position including a slat upper surface, a slat lower surface, and a slat rear surface, the seam The upper surface of the wing and the lower surface of the slat are configured to be respectively in the recovery position The upper surface of the leading edge and the lower surface of the leading edge form a continuous contour line;

At least one pocket filling member movably coupled to the leading edge slat, wherein the at least one pocket filling element is configured to retract inside the leading edge slat at the retracted position The deployed position projects out of the rear surface of the slat to form a pocket-filling slat with the leading edge slat.

9. A low noise, high lift system for an aircraft wing according to claim 8 wherein said pocket filling member is a pocket fill sheet.

10. The low noise high lift system for aircraft wing of claim 9, wherein the at least one pocket filling element is configured to pivot outwardly to the deployed position and pivot inwardly to Recall the location.

11. A low noise, high lift system for aircraft wing according to claim 10, wherein said at least one pocket filling element comprises an upper pocket fill sheet and a lower pocket fill sheet.

12 . The low noise high lift system for an aircraft wing according to claim 1 , wherein the upper pocket filling piece is connected to the rear surface of the slat by an upper hinge, the lower pocket filling piece. Attached to the lower surface of the slat by a lower hinge.

13. A low noise, high lift system for an aircraft wing according to claim 12, characterized in that it is automatically pivotable outwardly to the deployed position upon exiting the recovery position.

The low noise high lift system for an aircraft wing according to claim 13, wherein the actuating mechanism comprises a spring mechanism or a hydraulic mechanism, and the spring mechanism or hydraulic mechanism is disposed on the leading edge slat internal.

15. A method for reducing aircraft noise associated with a high lift system, comprising: deploying a leading edge slat from a leading edge of the fixed wing to a high lift position;

Resetting at least one pocket filling element associated with the leading edge slat from a recovery position inside the leading edge slat to a deployed position, in the read deployed position, the at least one pocket filling element and the leading edge The slats together form a pocket-filled slat.

16. The method for reducing aircraft noise associated with a high lift system according to claim 15, wherein the pocket filling element is a pocket fill sheet, wherein resetting at least one four-hole fill sheet comprises The at least one pocket filler sheet pivots outward to The deployed position to form the pocket fill slat profile.

17. The method for reducing aircraft noise associated with a high lift system according to claim 16, wherein said at least one pocket filling sheet comprises an upper pocket filling sheet and a lower pocket filling sheet, wherein The leading edge slat associated with the at least one four-hole filling element includes connecting the upper pocket filler sheet to an slat rear surface of the leading edge slat through an upper hinge, and the lower pocket filling sheet Attached to the lower surface of the slat of the leading edge slat by a lower hinge.

18. The method for reducing aircraft noise associated with a high lift system of claim 17, wherein pivoting the at least one pocket fill sheet comprises: attaching to the at least one pocket fill The actuation mechanism of the sheet is released from its retracted position to the extended position.

19. The method for reducing aircraft noise associated with a high lift system according to claim 18, wherein said actuating mechanism comprises a spring mechanism or a hydraulic mechanism, said spring mechanism or hydraulic mechanism being disposed in said The leading edge of the slat is inside.