CN112632703A - Wing airfoil front and rear edge deformation shape parameterization method meeting structural constraint - Google Patents
Wing airfoil front and rear edge deformation shape parameterization method meeting structural constraint Download PDFInfo
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Abstract
The invention discloses a method for parameterizing the deformation shape of the front edge and the rear edge of a wing airfoil, which meets structural constraints, and adopts a camber line and a thickness line corresponding to the front edge and the rear edge of the wing airfoil to represent the deformation shape of the front edge and the rear edge of the wing airfoil. The method is applied to the design of the deformed shape of the front edge and the rear edge of the wing profile of the variable camber wing, the problems that a high-efficiency pneumatic shape structure cannot be realized, the structure can realize lower shape pneumatic efficiency and the like can be effectively solved by simultaneously and accurately describing the shape characteristics and the structural constraint characteristics, the pneumatic design efficiency of the deformed shape of the front edge and the rear edge is greatly improved, and the engineering realizability of the deformed shape of the front edge and the rear edge is ensured.
Description
Technical Field
The invention belongs to the field of aircraft design, and particularly relates to a method for parameterizing deformation shapes of front and rear edges of a wing airfoil, which meets structural constraints.
Background
Along with the technical maturity of the flexible deformation structure of the wing is continuously improved, the self-adaptive deformation technology of the front and rear edges of the wing based on the flexible structure is paid more and more attention, and in the process of developing the research on the self-adaptive deformation of the front and rear edges of the wing, the expression of the deformation appearance of the front and rear edges is mainly based on the difference of the concerned contents to adopt two ideas: firstly, the pneumatic benefit of the deformation of the front edge and the rear edge is focused on, the conventional two-dimensional curve parameterization method is mainly adopted for the description of the shape of the front edge and the rear edge, the method can only ensure the smoothness of the described geometric shape and has enough design space, but the geometric shapes expressed by different parameter combinations lack correlation and cannot ensure the realizability of the structure on different deformation shapes; secondly, the characteristics of the internal deformation structure of the front edge and the rear edge are focused on, the deformation appearance of the front edge and the deformation appearance of the rear edge are mainly determined by the appearance of the internal structure, and the problem that the description capability of the deformation appearance of the front edge and the rear edge is obviously insufficient exists. In order to solve the problem that aerodynamics and structures cannot be considered at the same time in the wing front and rear edge deformation shape parameterization in the wing front and rear edge adaptive deformation technology research, it is necessary to establish a wing front and rear edge deformation shape parameterization method meeting structural constraints, so that the method not only has enough deformation space, but also can ensure the structural realizability.
Disclosure of Invention
Object of the Invention
The invention provides a parameterization method for deformation shapes of front and rear edges of wing airfoil profiles meeting structural constraints, which is based on a CST parameterization method capable of describing two-dimensional curve shapes, modifies parameterization solving flows of the front and rear edge shapes of the wing airfoil profiles aiming at the structural constraint characteristics of the front and rear edges of the wing airfoil with variable camber, and has sufficient describing capability for the deformation shapes of the front and rear edges while automatically meeting the structural constraint of the front and rear edges of the wing by reasonably setting parameter ranges. The method can be applied to aerodynamic or structural optimization design of the front and rear edge profiles of variable-camber wings or aircraft design with self-adaptive wing front and rear edge structures.
Technical solution of the invention
The method adopts a camber line and a thickness line corresponding to a curve of the front edge and the rear edge of the wing airfoil to represent the deformation profile of the front edge and the rear edge of the wing airfoil, wherein the camber line and the thickness line of the front edge and the rear edge of the wing airfoil after deformation are determined by a CST parameter describing a two-dimensional curve, the camber line and the thickness line of the front edge and the rear edge of the wing airfoil without deformation and a deflection angle of the front edge and the rear edge. And multiplying the CST parameters describing the camber line and the thickness line of the front edge and the rear edge of the wing airfoil without deformation by a proportionality coefficient to obtain a CST parameter value range for describing the camber line and the thickness line of the front edge and the rear edge of the wing airfoil after deformation. The camber line and the thickness line of the front edge and the rear edge of the wing airfoil without deformation are mainly used for providing tangent constraint so as to ensure that the contour curve of the front edge and the rear edge of the wing after deformation is smoothly connected with the contour curve of the middle section of the wing, and the deflection angles of the front edge and the rear edge are mainly used for controlling the deformation amplitude of the contour of the front edge and the rear edge. The structural constraint of the deformed shape of the front edge and the rear edge of the wing airfoil is represented by the geometric constraint of the camber line and the thickness line of the front edge and the rear edge of the deformed wing airfoil.
The invention has the advantages that: the method is applied to the design of the deformed shape of the front edge and the rear edge of the wing profile of the variable camber wing, the problems that a high-efficiency pneumatic shape structure cannot be realized, the structure can realize lower shape pneumatic efficiency and the like can be effectively solved by simultaneously and accurately describing the shape characteristics and the structural constraint characteristics, the pneumatic design efficiency of the deformed shape of the front edge and the rear edge is greatly improved, and the engineering realizability of the deformed shape of the front edge and the rear edge is ensured.
Drawings
FIG. 1 is a schematic view of an airfoil profile of a wing airfoil, camber line and thickness line.
FIG. 2 is a schematic view of camber lines of the leading, mid, and trailing edges of an airfoil.
FIG. 3 is a schematic illustration of airfoil, airfoil leading edge, and airfoil trailing edge thickness lines.
FIG. 4 is a schematic view of a camber line of an airfoil shaped deformation leading edge.
FIG. 5 is a schematic view of an airfoil shaped deformed trailing edge camber line.
FIG. 6 is a schematic view of a thickness line of an airfoil shaped deformation leading edge.
FIG. 7 is a schematic view of airfoil deformed trailing edge thickness lines.
FIG. 8 is a schematic view of a deformed profile of the leading and trailing edges of an airfoil.
In the figure: 1-wing airfoil profile thickness line, 2-wing airfoil profile curve, 3-wing airfoil profile camber line, 4-wing airfoil mid-section camber line, 5-wing airfoil leading edge camber line, 6-wing airfoil trailing edge camber line, 7-wing airfoil leading edge thickness line, 8-wing airfoil trailing edge thickness line, 9-wing airfoil leading edge deformed profile camber parameter curve, 10-wing airfoil leading edge deformed profile camber line, 11-wing airfoil trailing edge deformed profile camber parameter curve, 12-wing airfoil trailing edge deformed profile camber line, 13-wing airfoil leading edge deformed profile thickness parameter curve, 14-wing airfoil leading edge deformed profile thickness transition curve, 15-wing airfoil trailing edge deformed profile thickness parameter curve, 16-wing trailing edge deformed profile thickness transition curve, 17-wing airfoil trailing edge deformation profile curve and 18-wing airfoil leading edge deformation profile curve.
Detailed Description
The invention is realized by the following technical scheme.
The following embodiments are given in conjunction with fig. 1 to 8 to further explain the technical solution of the present invention. In order to complete the parametric description of the deformed shape of the front edge and the rear edge of the wing airfoil meeting the structural constraint, a thickness line 1 and a camber line 3 of the wing airfoil are solved aiming at a wing airfoil curve 2, the camber line 3 is divided into a wing airfoil middle-section camber line 4, a front edge camber line 5 and a rear edge camber line 6 according to the range of the front edge and the rear edge of the wing airfoil, and a front edge thickness line 7 and a rear edge thickness line 8 with the length as a unit length are solved by combining the thickness line 1 and through coordinate scaling. Aiming at the front edge camber line 5, rotating and translating in the plane where the front edge camber line is located to change the front edge camber line into a front edge deformation profile camber parameter curve 9 with front and back endpoints in the same horizontal line and a front end in an origin; aiming at the trailing edge camber line 6, rotating and translating in the plane where the trailing edge camber line is located to change the trailing edge camber line into a trailing edge deformation profile camber parameter curve 11 with front and rear endpoints in the same horizontal line and a front end in an origin; for the front edge thickness line 7, firstly, the front edge thickness line is changed into a front edge deformation shape thickness transition curve 14 with the front end point and the rear end point in the same horizontal line and the length of the front edge deformation shape thickness transition curve being unit length based on the rotation and the scaling of the rear end point in the plane where the front edge thickness line is located, and then the front edge deformation shape thickness transition curve 14 is translated into a front edge deformation shape thickness parameter curve 13 with the front end at the origin; for the trailing edge thickness line 8, firstly, the trailing edge deformation profile thickness transition curve 16 with the front end point and the rear end point on the same horizontal line is formed by rotating and translating in the plane, and then the trailing edge deformation profile thickness transition curve 15 with the front end point on the origin point is formed by translating. The curve profile which needs to be described by CST parameters through the CST parameterization method is represented by a leading edge deformation profile camber parameter curve 9, a trailing edge deformation profile camber parameter curve 11, a leading edge deformation profile thickness parameter curve 13 and a trailing edge deformation profile thickness parameter curve 15. In order to obtain a proper parameter value range, a CST parameter combination capable of describing a leading edge deformation shape camber parameter curve 9, a trailing edge deformation shape camber parameter curve 11, a leading edge deformation shape thickness parameter curve 13 and a trailing edge deformation shape thickness parameter curve 15 is reversely solved by utilizing a CST parameterization method, then the group of CST parameters are multiplied by a coefficient smaller than 1 to serve as a lower bound of a design variable for describing a leading edge deformation profile and a trailing edge deformation profile, and multiplied by a coefficient larger than 1 to serve as an upper bound of the design variable for describing the leading edge deformation profile and the trailing edge deformation profile, and besides, the skewness of the leading edge deformation profile and the trailing edge deformation profile is selected to serve as the design. Selecting parameters describing the front and rear edge deformation shapes of the wing profile between the determined upper and lower limits of the CST parameters and within the determined skewness range to obtain a new front edge deformation shape camber parameter curve 9, a new rear edge deformation shape camber parameter curve 11, a new front edge deformation contour thickness parameter curve 13 and a new rear edge deformation contour thickness parameter curve 15, then combining a front edge camber line 5, a rear edge camber line 6, a front edge thickness line 7 and a rear edge thickness line 8 of the basic wing profile with the non-deformation front edge and the non-deformation rear edge to obtain a front edge camber line, a rear edge camber line, a front edge thickness line and a rear edge thickness line of the wing profile with the deformation front edge and the rear edge, respectively marking the front edge camber line, the rear edge camber line, the front edge camber line, the rear edge camber line and the rear edge camber line as 5A, 6A and then combining the front edge skewness parameters and the rear edge skewness parameters to rotate the front edge camber line 5A. According to the characteristics of the front and rear edge flexible deformation structure, converting the structural constraint into curve constraint, including converting skin length constraint and curvature constraint into front and rear edge outline curve constraint, converting internal structural constraint into camber line constraint and thickness constraint, and the like, and zooming the front edge deformed outline camber line 10 and the rear edge deformed outline camber line 12 according to the constraints to obtain a front edge deformed outline camber line 10A and a rear edge deformed outline camber line 12A which meet the structural constraint. And finally, generating a front edge deformation outline curve 18 and a rear edge deformation outline curve 17 according to the relation between the camber line and the thickness line of the basic airfoil profile based on the front edge thickness line 7A, the rear edge thickness line 8A, the front edge deformation outline camber line 10A and the rear edge deformation outline camber line 12A. Because the CST parameterization method can describe the curve shape deformation to the maximum extent when adopting a proper order, the curve of the front and rear edge deformation shapes can be ensured to have enough design space by describing the curve of the front and rear edge deformation shapes by the CST parameterization method through the camber line and the thickness line, and the deformation shapes of the front and rear edges can also be ensured to meet the structural constraint by decomposing the deformation shapes of the front and rear edges into the camber line and the thickness line, for example, the skin and deformation structure length constraint is met by the scaling of the camber line, and the deformation structure thickness constraint is met by the thickness line.
The method for parameterizing the deformation shape of the front edge and the rear edge of the wing airfoil meeting the structural constraint is suitable for designing the flexible deformation shape of the front edge and the rear edge of the wing with the flexible deformation structural constraint.
The above-mentioned embodiments are merely illustrative of the technical ideas and features of the present invention, and the purpose thereof is to enable those skilled in the art to understand the contents of the present invention and to implement the same, and not to limit the scope of the present invention, and all equivalent changes or modifications made according to the spirit of the present invention should be covered by the scope of the present invention. The techniques, shapes, and configurations not described in detail in the present invention are all known techniques.
Claims (8)
1. The method is characterized in that the deformation shape of the front edge and the rear edge of the wing airfoil is represented by a camber line and a thickness line corresponding to the front edge and the rear edge of the wing airfoil.
2. The method of parameterizing the deformed profile of the leading and trailing edges of a wing airfoil according to claim 1, wherein the curvature and thickness of the deformed leading and trailing edges of the wing airfoil are determined by the CST parameters describing the two-dimensional curve, the curvature and thickness of the undeformed leading and trailing edges of the wing airfoil, and the leading and trailing edge deflection angles.
3. The method of claim 2, wherein the CST parameter range describing the two-dimensional curve is obtained by multiplying a scaling factor based on the reference CST parameter obtained by solving the camber and thickness lines of the front and back edges of the wing profile without deformation.
4. The method of claim 2, wherein the upper and lower bounds of the CST parameters describing the camber line and thickness line of the deformed leading and trailing edges are determined based on the camber line and thickness line of the undeformed leading and trailing edges, and the integrated leading and trailing edge deformed profile parameters are formed by combining the leading and trailing edge deflection variables.
5. The method of claim 4, wherein the parameters of the deformed shape of the leading and trailing edges are selected to generate a curve of the deformed shape of the leading and trailing edges according to the characteristic relationship between the curvature line and the thickness line of the undeformed leading and trailing edges, and the curvature line and the thickness line are processed according to specific structural constraints.
6. The method of claim 5, wherein the processing of the camber and thickness lines comprises scaling, rotating, translating.
7. The method for parameterizing the deformed shape of the front and rear edges of the wing airfoil meeting the structural constraint of claim 5, wherein a thickness line (1) and a camber line (3) of the wing airfoil are obtained for a wing airfoil curve (2), the camber line (3) is divided into a wing airfoil middle-section camber line (4), a front-edge camber line (5) and a rear-edge camber line (6) according to the range of the front and rear edges of the wing airfoil, a front-edge thickness line (7) and a rear-edge thickness line (8) with the length of a unit length are obtained by combining the thickness line (1) and scaling coordinates, the specific process of processing the camber line and the thickness line is that the front-edge camber line (5) is rotated and translated in a plane where the front-edge camber line is located to become a front-edge deformed shape camber parameter curve (9) with the front-rear end point in the same horizontal line and the front end in the origin, and the rear-edge camber, rotating and translating in the plane where the curve is positioned to change the curve into a trailing edge deformation profile camber parameter curve (11) with front and rear end points in the same horizontal line and a front end in an origin; aiming at the front edge thickness line (7), firstly changing the front edge thickness line into a front edge deformation shape thickness transition curve (14) with the front end point and the rear end point in the same horizontal line and the length as the unit length based on the rotation and the scaling of the rear end point in the plane of the front edge thickness line, and then translating the front edge deformation shape thickness transition curve (14) into a front edge deformation shape thickness parameter curve (13) with the front end at the origin; and (3) regarding the trailing edge thickness line (8), firstly, the trailing edge thickness line is rotated and translated in the plane to become a trailing edge deformation profile thickness transition curve (16) with the front end point and the rear end point in the same horizontal line, and then the trailing edge deformation profile thickness transition curve is changed into a trailing edge deformation profile thickness parameter curve (15) with the front end point in the origin point through translation.
8. The method for parameterizing the deformed shape of the leading and trailing edges of the wing airfoil according to claim 7, wherein the specific method for determining the upper and lower bounds of the CST parameters describing the camber line and the thickness line of the deformed leading and trailing edges comprises: firstly, a CST parameter combination capable of describing a leading edge deformation shape camber parameter curve (9), a trailing edge deformation shape camber parameter curve (11), a leading edge deformation shape thickness parameter curve (13) and a trailing edge deformation shape thickness parameter curve (15) is solved reversely by using a CST parameterization method, then the CST parameter combination is multiplied by a coefficient smaller than 1 to be used as a lower bound for describing a front edge deformation shape design variable and a coefficient larger than 1 to be used as an upper bound for describing a front edge deformation shape design variable and a rear edge deformation shape design variable.
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| CN113962025A (en) * | 2021-10-26 | 2022-01-21 | 成都飞机工业（集团）有限责任公司 | Wing section optimization method and device for ultra-flat tailless layout supersonic aircraft |
| EP4095733A1 (en) * | 2021-05-21 | 2022-11-30 | Raytheon Technologies Corporation | Gradient free design environment including adaptive design space |
| CN113962025B (en) * | 2021-10-26 | 2024-05-14 | 成都飞机工业（集团）有限责任公司 | Wing section optimization method and device for ultra-flat tail-free supersonic aircraft |
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