CN115556959A - Wing surface shear backswept form design method, deformation wing, wing and aircraft - Google Patents

Wing surface shear backswept form design method, deformation wing, wing and aircraft Download PDF

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Publication number
CN115556959A
CN115556959A CN202211113789.2A CN202211113789A CN115556959A CN 115556959 A CN115556959 A CN 115556959A CN 202211113789 A CN202211113789 A CN 202211113789A CN 115556959 A CN115556959 A CN 115556959A
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wing
point
leading edge
sweep
airfoil
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CN115556959B (en
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刘凯
苑凯华
刘燚
付志超
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Beijing Electromechanical Engineering Research Institute
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/38—Adjustment of complete wings or parts thereof

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  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Manufacturing & Machinery (AREA)
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Abstract

The invention provides a wing surface shear backswept form design method, a morphing wing, a wing and an aircraft. The design method comprises the following steps: in the process of changing shearing into sweepback, the slightly chord length and the root chord length of the designed airfoil along the direction of the incoming flow are always kept unchanged; after designing any nth sweep, the coordinates of any point on the airfoil are determined by: according to the coordinate of the wing root leading edge point and the n-th variable sweepback corresponding deformed airfoil leading edge rotation angle chi n Determining the coordinate of any point on the n-th variable-sweep front airfoil surface to determine the X of any point on the airfoil surface for changing shearing into sweep back n New coordinates after the angle, wherein the arbitrary point comprises the tip leading edge point. After the wing surface is designed in the shear sweepback mode, the wing rib keeps the flow direction unchanged in the rotating process, the good aerodynamic appearance is maintained, and the structure has better stability in the deformation process.

Description

Wing surface shear backswept form design method, deformation wing, wing and aircraft
Technical Field
The invention belongs to the technical field of variant aircrafts, and relates to a wing surface shear backswept form design method, a morphing wing, a wing and an aircraft.
Background
In recent years, the world's field of aircraft has been devoted to developing variant aircraft that have flight environment (e.g., altitude, speed, climate, etc.) adaptation, can perform a variety of tasks (e.g., cruise, hover, maneuver, etc.). The structure and the aerodynamic layout of the aircraft can be changed autonomously according to flight mission requirements, and good flight performance is kept under the complex flight environment condition. The variant technology can adaptively change important parameters such as wing shape, thickness, camber and the like according to tasks and environments through intelligent design and control, so that the aircraft can obtain ideal pneumatic characteristics in different flight states, the use performance of the aircraft at different speeds is considered, the contradiction in the pneumatic layout design of the modern aircraft is solved, and the method has a very important effect on improving the comprehensive performance of the military aircraft. After the century, with the development of new advanced fighters and unmanned aerial vehicles, the variant technology has become one of the subversive technologies which determine the performance of future aircrafts and have epoch-making significance.
Fixed wing aircraft have been confronted with the contradiction between high-speed and low-speed flight performance requirements: the large-sweepback-angle wing can effectively reduce the shock resistance, but has lower flying efficiency in a subsonic state; the straight wing has better flight performance in low-speed flight, but the shock resistance is increased in geometric times in the transonic speed stage. The variable sweepback angle wing is suitable for the airplane to have better economy during supersonic cruise flight and obtain satisfactory low-speed flight performance. The current variable sweep wing cannot maintain a good aerodynamic profile during rotation.
Disclosure of Invention
The present invention is directed to solving at least one of the problems of the prior art.
Therefore, the invention provides an airfoil shear backswept form design method, a morphing wing, a wing and an aircraft.
The technical solution of the invention is as follows:
according to a first aspect, there is provided a method of designing an airfoil shear sweep profile, the method comprising:
in the process of changing shearing into sweepback, the slightly chord length and the root chord length of the designed airfoil along the direction of the incoming flow are always kept unchanged;
after designing any nth sweep, the coordinates of any point on the airfoil are determined by:
according to the coordinates of the leading edge point of the wing root and the n-th variable sweepback correspondenceThe leading edge rotation angle x of the deformed airfoil n And determining the coordinates of any point on the n-th variable-sweep front airfoil surface to determine the shearing variable-sweep χ of any point on the airfoil surface n New coordinates after the angle, wherein the arbitrary point comprises the tip leading edge point.
Further, according to the coordinate of the leading edge point of the wing root and the rotating angle chi of the leading edge of the deformed wing corresponding to the n-th time of changing sweepback n Determining the coordinate of any point on the n-th variable-sweep front airfoil surface to determine the X of any point on the airfoil surface for changing shearing into sweep back n New coordinates corresponding after the angle, wherein the arbitrary point comprises a tip leading edge point, comprising:
according to the coordinates of the wing root leading edge point and the coordinates of the n-th time variable sweepback front wing tip leading edge point, the position X of the leading edge corresponding to any point p (X, y) to the position X is solved front_n ；
According to x front_n Wing root leading edge point coordinate and rotation angle χ n And determining the coordinates of any point on the n-th time varying sweep front airfoil surface to determine the shearing varying sweep x of any point on the airfoil surface n New coordinates after the angle.
Further, the position X-direction position X of the leading edge corresponding to any point p (X, y) is calculated according to the coordinate of the leading edge point of the wing root and the coordinate of the leading edge point of the nth variable sweepback forward wing tip through the following formula front_n ：
x front_n ＝kx+b
k＝(x 1 -x 2_n-1 )/(y 1 -y 2_n-1 )
b＝(y 1 x 2_n-1 -y 2_n-1 x 1 )/(y 1 -y 2_n-1 )
Wherein p is 1 (x 1 ,y 1 ) As the coordinate of the leading edge point of the wing root, p 2 (x 2_n-1 ,y 2_n-1 ) The coordinate of the point of the slightly leading edge of the forward wing with the n-th variable sweepback is shown.
Further, according to x by the following formula front_n Wing root leading edge point coordinate and rotation angle χ n And determining the coordinates of any point on the n-th time varying sweep front airfoil surface to determine the shearing varying sweep x of any point on the airfoil surface n New coordinates after angle:
x new_n ＝((x front_n -x 1 )*cos(χ 1 )+(y-y 1 )*sin(χ n )+x 1 )+(x-x front_n )
y new_n ＝(y-y 1 )*cos(χ n )-(x front_n -x 1 )*sin(χ n )+y 1
wherein (x) new_n ,y new_n ) New coordinates corresponding to p (x, y) after the nth sweep.
According to a second aspect, a morphing wing is provided, which takes the form of a shear sweep designed using the above design method.
According to a third aspect, there is provided a wing comprising a fixed wing and a morphing wing as described above, the morphing wing being rotatably connected to the fixed wing, the morphing wing undergoing shear morphing during rotation in the form of said shear-to-sweep.
According to a fourth aspect, an aircraft is provided, comprising a wing as described above.
According to the technical scheme, a shearing-to-sweepback mode is designed, wherein in the shearing-to-sweepback process, the slight chord length and the root chord length of the airfoil along the direction of the current flow are designed to be always constant, the position coordinate of any point of the deformed airfoil is determined according to parameters such as the coordinate of the leading edge point of the airfoil root, the rotating angle of the leading edge of the deformed airfoil and the like, and after the airfoil is designed by adopting the shearing-to-sweepback mode, the flow direction of a rib is kept constant in the rotating process, a good aerodynamic shape is maintained, and the structure has good stability in the deforming process.
Drawings
The accompanying drawings, which are included to provide a further understanding of the embodiments of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention. It is obvious that the drawings in the following description are only some embodiments of the invention, and that for a person skilled in the art, other drawings can be derived from them without inventive effort.
FIG. 1 is a schematic view of a shear-variant swept-back airfoil profile according to an embodiment of the invention;
fig. 2 is a schematic diagram illustrating parameters of a shear-change swept-back airfoil according to an embodiment of the invention.
Detailed Description
It should be noted that, in the present application, the embodiments and features of the embodiments may be combined with each other without conflict. The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
It is noted that the terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments according to the present application. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, and it should be understood that when the terms "comprises" and/or "comprising" are used in this specification, they specify the presence of stated features, steps, operations, devices, components, and/or combinations thereof, unless the context clearly indicates otherwise.
The relative arrangement of the components and steps, the numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present invention unless specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective portions shown in the drawings are not drawn in an actual proportional relationship for the convenience of description. Techniques, methods, and apparatus known to those of ordinary skill in the relevant art may not be discussed in detail but are intended to be part of the specification where appropriate. In all examples shown and discussed herein, any particular value should be construed as merely illustrative, and not limiting. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, further discussion thereof is not required in subsequent figures.
In one embodiment of the present invention, as shown in fig. 1-2, there is provided an airfoil shear sweep design method, comprising:
step one, in the process of changing shearing into sweepback, the slight chord length and the root chord length of the designed airfoil along the direction of the incoming flow are always kept unchanged;
step two, after any nth sweep is designed, the coordinate of any point on the airfoil surface is determined by the following method:
according to the coordinate of the wing root leading edge point and the n-th variable sweepback corresponding deformed airfoil leading edge rotation angle chi n And determining the coordinates of any point on the n-th variable-sweep front airfoil surface to determine the shearing variable-sweep χ of any point on the airfoil surface n New coordinates after the angle, wherein the arbitrary point comprises the point of the leading edge of the wingtip.
For example, the profile of a swept wing is schematically illustrated in FIG. 1, where L is the half span length of the morphing airfoil, and c 2 A slight chord length, c 1 Is the chord length, and the airfoil surface flows along the direction c in the deformation process 1 And c 2 And keeping the parameters of the deformed wing after the rotating backsweeping, wherein the parameters of the deformed wing after the rotating backsweeping can be obtained by determining any point on the wing surface after each rotating backsweeping by adopting the method.
In the embodiment of the invention, the chord length, the wing root leading edge point and the wing tip leading edge point are all defined in the field.
Therefore, the embodiment of the invention designs a shear-to-sweep mode, wherein in the shear-to-sweep process, the slight chord length and the root chord length of the airfoil along the direction of the current flow are always designed to be constant, the position coordinate of any point of the deformed airfoil is determined according to parameters such as the coordinate of the leading edge point of the airfoil root, the rotating angle of the leading edge of the deformed airfoil and the like, and after the airfoil is designed by adopting the shear-to-sweep mode, the flow direction of a rib is kept constant in the rotating process, a good aerodynamic shape is maintained, and the structure has good stability in the deforming process.
In the above embodiment, in order to accurately coordinate any point on the deformed airfoil, the rotation angle χ of the leading edge of the deformed airfoil corresponding to the nth sweep is obtained according to the coordinate of the leading edge point of the root n Determining the coordinate of any point on the n-th variable-sweep front airfoil surface to determine the X of any point on the airfoil surface for changing shearing into sweep back n New coordinates corresponding to the post-angle, including:
according to the coordinates of the wing root leading edge point and the coordinates of the n-th time variable sweepback front wing tip leading edge point, the position X of the leading edge corresponding to any point p (X, y) to the position X is solved front_n ；
According to x front_n Wing root leading edge point coordinate and rotation angle χ n And determining the coordinates of any point on the n-th time varying sweep front airfoil surface to determine the shearing varying sweep x of any point on the airfoil surface n New coordinates after the angle.
It can be seen that, in the embodiment of the present invention, the coordinates of the leading edge point of the wing root are always unchanged, the coordinates of the leading edge point of the wing tip change with each deformation, the initial value of the coordinates is a known value (the coordinates of the leading edge point of the wing tip with the 1 st time of changing sweep-back is the initial value), and the calculation method of the coordinates corresponding to the deformed wing tip is the same as the calculation method of the coordinates corresponding to any point on the wing surface after the deformation.
In the embodiment of the invention, the position X-direction position X of the leading edge corresponding to any point p (X, y) is calculated according to the coordinate of the leading edge point of the wing root and the coordinate of the leading edge point of the nth variable sweepback forward wing tip by the following formula front_n ：
x front_n ＝kx+b
k＝(x 1 -x 2_n-1 )/(y 1 -y 2_n-1 )
b＝(y 1 x 2_n-1 -y 2_n-1 x 1 )/(y 1 -y 2_n-1 )
Wherein p is 1 (x 1 ,y 1 ) As the coordinate of the leading edge point of the wing root, p 2 (x 2_n-1 ,y 2_n-1 ) Is changed into a sweepback front wing tip for the nth timeLeading edge point coordinates.
In the examples of the present invention, the following formula is used to describe the formula front_n Wing root leading edge point coordinate and rotation angle χ n And determining the coordinates of any point on the n-th time varying sweep front airfoil surface to determine the shearing varying sweep x of any point on the airfoil surface n New coordinates after angle:
x new_n ＝((x front_n -x 1 )*cos(χ 1 )+(y-y 1 )*sin(χ n )+x 1 )+(x-x front_n )
y new_n ＝(y-y 1 )*cos(χ n )-(x front_n -x 1 )*sin(χ n )+y 1
wherein (x) new_n ,y new_n ) New coordinates corresponding to p (x, y) after the nth sweep.
According to another embodiment, a morphing wing is provided that takes the form of a shear sweep designed using the design method described above.
Therefore, the deformation wing adopts a shearing sweepback-changing mode, so that the flow direction of the wing rib is kept unchanged in the sweepback-changing process, and the aerodynamic appearance can be well maintained.
According to another embodiment, there is also provided a wing comprising a fixed wing and the above-mentioned morphing wing, the morphing wing being rotatably connected to the fixed wing, the morphing wing undergoing shear deformation during rotation in the form of said shear-to-sweep.
In the embodiment of the invention, the specific connection mode of the fixed wing and the deformation wing can be designed by adopting a conventional technical means.
For example, airfoils employ the shear-sweep design described above, wherein the spars rotate about an axis of rotation at the root, while the ribs maintain a constant flow direction during rotation, maintaining a good aerodynamic profile. The structure has better stability in the deformation process.
According to another embodiment, there is also provided an aircraft comprising a wing as described above.
Features that are described and/or illustrated above with respect to one embodiment may be used in the same way or in a similar way in one or more other embodiments and/or in combination with or instead of the features of the other embodiments.
It should be emphasized that the term "comprises/comprising" when used herein, is taken to specify the presence of stated features, integers, steps or components but does not preclude the presence or addition of one or more other features, integers, steps, components or groups thereof.
The above methods of the present invention may be implemented by hardware, or may be implemented by hardware in combination with software. The present invention relates to a computer-readable program which, when executed by a logic section, enables the logic section to realize the above-described apparatus or constituent section, or to realize the above-described various methods or steps. The present invention also relates to a storage medium such as a hard disk, a magnetic disk, an optical disk, a DVD, a flash memory, or the like, for storing the above program.
The many features and advantages of these embodiments are apparent from the detailed specification, and thus, it is intended by the appended claims to cover all such features and advantages of these embodiments which fall within the true spirit and scope thereof. Further, since numerous modifications and changes will readily occur to those skilled in the art, it is not desired to limit the embodiments of the invention to the exact construction and operation illustrated and described, and accordingly, all suitable modifications and equivalents may be resorted to, falling within the scope thereof.
The invention has not been described in detail and is not limited thereto.

Claims (7)

1. An airfoil shear sweep design method, the design method comprising:
in the process of changing shearing into sweepback, the slightly chord length and the root chord length of the designed airfoil along the direction of the incoming flow are always kept unchanged;
after designing any nth sweep, the coordinates of any point on the airfoil are determined by:
according to the coordinate of the wing root leading edge point and the leading edge rotating angle chi of the deformed airfoil corresponding to the n-th variable sweepback n N-th time sweep backThe coordinate of any point on the front airfoil surface determines the shearing change backswept x' of any point on the airfoil surface n New coordinates after the angle, wherein the arbitrary point comprises the tip leading edge point.
2. The method of claim 1, wherein the deformed airfoil leading edge rotation angle χ corresponding to the n-th sweep is determined according to the root leading edge point coordinates n Determining the coordinate of any point on the n-th variable-sweep front airfoil surface to determine the X of any point on the airfoil surface for changing shearing into sweep back n New coordinates corresponding after the angle, wherein the arbitrary point comprises a tip leading edge point, comprising:
according to the coordinates of the wing root leading edge point and the coordinates of the n-th time variable sweepback front wing tip leading edge point, the position X of the leading edge corresponding to any point p (X, y) to the position X is solved front_n ；
According to x front_n Wing root leading edge point coordinate and rotation angle χ n And determining the coordinate of any point on the n-th variable-sweep front airfoil surface to determine the shearing variable-sweep x' of any point on the airfoil surface n New coordinates after the angle.
3. An airfoil shear sweep design method according to claim 2, characterized in that the position X-direction position X of the leading edge corresponding to any point p (X, y) is calculated according to the coordinates of the leading edge point of the root and the coordinates of the leading edge point of the tip of the nth time variable sweep forward wing according to the following formula front_n ：
x front_n ＝kx+b
k＝(x 1 -x 2_n-1 )/(y 1 -y 2_n-1 )
b＝(y 1 x 2_n-1 -y 2_n-1 x 1 )/(y 1 -y 2_n-1 )
Wherein p is 1 (x 1 ,y 1 ) As the coordinate of the leading edge point of the wing root, p 2 (x 2_n-1 ,y 2_n-1 ) The coordinate of the point of the slightly leading edge of the forward wing with the n-th variable sweepback is shown.
4. A method as claimed in claim 3An airfoil shear sweep design method characterized by the following equation according to x front_n Wing root leading edge point coordinate and rotation angle χ n And determining the coordinate of any point on the n-th variable-sweep front airfoil surface to determine the shearing variable-sweep x' of any point on the airfoil surface n New coordinates after angle:
x new_n ＝((x front_n -x 1 )*cos(χ 1 )+(y-y 1 )*sin(χ n )+x 1 )+(x-x front_n )
y new_n ＝(y-y 1 )*cos(χ n )-(x front_n -x 1 )*sin(χ n )+y 1
wherein (x) new_n ,y new_n ) New coordinates corresponding to p (x, y) after the nth sweep.
5. A morphing wing wherein the morphing wing is in shear sweep form, the shear sweep form being designed using the design method of any of claims 1 to 4.
6. A wing comprising a fixed wing and a morphing wing according to claim 5, the morphing wing being rotatably connected to the fixed wing, the morphing wing undergoing shear deformation during rotation in the form of said shear-to-sweep.
7. An aircraft, characterized in that it comprises a wing according to claim 6.
CN202211113789.2A 2022-09-14 2022-09-14 Design method of wing surface shear sweepback form, deformed wing, wing and aircraft Active CN115556959B (en)

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Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3447761A (en) * 1967-06-12 1969-06-03 Boeing Co Supersonic airplane variable-sweep integrated airfoil system
GB1286104A (en) * 1968-09-25 1972-08-23 Messerschmitt Boelkow Blohm Improvements relating to aircraft having variable sweep wings
CN104487342A (en) * 2012-06-21 2015-04-01 庞巴迪公司 Morphing wing for an aircraft
CN113536458A (en) * 2021-07-13 2021-10-22 北京航空航天大学 Deformable wing rapid geometric modeling method based on class shape function transformation

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3447761A (en) * 1967-06-12 1969-06-03 Boeing Co Supersonic airplane variable-sweep integrated airfoil system
GB1286104A (en) * 1968-09-25 1972-08-23 Messerschmitt Boelkow Blohm Improvements relating to aircraft having variable sweep wings
CN104487342A (en) * 2012-06-21 2015-04-01 庞巴迪公司 Morphing wing for an aircraft
CN113536458A (en) * 2021-07-13 2021-10-22 北京航空航天大学 Deformable wing rapid geometric modeling method based on class shape function transformation

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
刘凯;曹晓飞;李营;方岱宁: "基于手性超结构设计的可变形机翼研究进展", 航空科学技术, vol. 33, no. 001, 25 January 2022 (2022-01-25), pages 20 - 36 *

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