CN114291249B - Variable-thickness wing structure - Google Patents
Variable-thickness wing structure Download PDFInfo
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- CN114291249B CN114291249B CN202111672971.7A CN202111672971A CN114291249B CN 114291249 B CN114291249 B CN 114291249B CN 202111672971 A CN202111672971 A CN 202111672971A CN 114291249 B CN114291249 B CN 114291249B
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Abstract
The application belongs to aircraft wing structure technical field, concretely relates to thickness variation wing structure includes: the front beam of the front edge is fixedly connected with the rear beam of the rear edge through the wing box; a flexible skin laid over the integral structural member formed by the leading edge, the wing box and the trailing edge; the driving shafts are distributed on the upper side and the lower side of the wing box, and the two ends of each driving shaft are respectively hinged with the front beam and the rear beam; the driver is used for driving a corresponding driving shaft to rotate; and the flexible skin is movably supported by the arc-shaped outer contour of the fan-shaped part of the flexible skin, and is simultaneously constructed into the same shape as the outer contour of the flexible skin. The variable thickness wing structure has the advantages of simple and compact structural form and higher engineering practicability, and can effectively realize the complex thickness change of the upper wing surface and the lower wing surface of the wing.
Description
Technical Field
The application belongs to the technical field of aircraft wing structures, and particularly relates to a variable-thickness wing structure.
Background
The variable thickness wing structure based on the curved disk drive is a variable thickness wing structure which deforms through the curved disk drive wing skin and further changes the wing thickness. The design aim is to realize the self-adaptive adjustment of the thickness of the wing along with the change of the flying speed. As the flight speed of an aircraft increases, the range of speeds experienced by its flight envelope is increasing, and the desired profile of the wing is different at different flight speeds. For wide speed range aircraft, the optimum aerodynamic profile thickness is greater at low speeds and the aerodynamic profile is thinner at high speeds. Through the self-adaptive change of the wing thickness, the resistance and aerodynamic efficiency of the aircraft can be obviously improved.
However, the existing variable-thickness wing structural scheme still has difficulty in meeting engineering application requirements of high-speed aircrafts in terms of reliability, weight and the like.
Disclosure of Invention
In order to solve at least one technical problem existing in the prior art, the application provides a variable thickness wing structure.
The application discloses a variable thickness wing structure includes:
the wing box is positioned between the front beam and the rear beam and fixedly connects the front beam with the rear beam;
a flexible skin laid over the monolithic structure constituted by the leading edge, the wing box and the trailing edge;
the driving shafts are distributed on the upper side and the lower side of the wing box, and the two ends of each driving shaft are respectively hinged with the front beam and the rear beam so that each driving shaft can rotate around the axis under the action of external force;
a plurality of drivers, each of which is used for driving a corresponding one of the driving shafts to rotate;
the flexible skin is movably supported by the curved discs through the arc-shaped outer contours of the fan-shaped parts, and the flexible skin is simultaneously constructed to be the same as the outer contours of the flexible skin in shape.
According to at least one embodiment of the present application, the number of the driving shafts on the upper and lower sides of the wing box is the same, and the driving shafts on the upper side or the driving shafts on the lower side are parallel to each other and are uniformly spaced.
According to at least one embodiment of the present application, the plurality of curved discs on each of the driving shafts are uniformly distributed along the axial direction of the driving shaft.
According to at least one embodiment of the application, the flexible skin is a metal skin, and two ends of the metal skin located in the chord direction of the wing structure are telescopic.
According to at least one embodiment of the present application, the flexible skin is a honeycomb skin.
According to at least one embodiment of the present application, the driver is a driving motor, which is disposed on the front beam or the rear beam and is connected to a corresponding driving shaft.
According to at least one embodiment of the application, the section of the wing box along the chord-wise direction of the wing structure is in a shape of a Chinese character 'hui'.
The application has at least the following beneficial technical effects:
1) According to the variable-thickness wing structure, through design and combination of different curved plates, any shape can be theoretically realized, so that complex thickness changes of upper and lower wing surfaces of the wing can be effectively realized;
2) In the variable-thickness wing structure, the curved disc can play a role of a driver and a role of load transmission, so that the variable-thickness wing structure is simple and compact in structural form and high in engineering practicability;
3) The variable thickness wing structure of this application needs the drive to drive the axle rotation, and drive form is simple, can realize through traditional driving motor, and driving efficiency is high.
Drawings
FIG. 1 is a schematic structural view (perspective view) of a variable thickness airfoil structure according to an embodiment of the present application;
FIG. 2 is a schematic structural view (front view) of the same example variable thickness wing structure as in FIG. 1;
FIG. 3 is a schematic view (front view) of a box portion of the same example variable thickness wing structure as in FIG. 1;
FIG. 4 is a schematic view of one of the curved plates in the variable thickness airfoil structure of the present application;
fig. 5 is a schematic diagram of a rotation driving principle of one of the curved discs in the variable thickness wing structure of the present application (wherein fig. 5a is before driving and fig. 5b is after driving).
Detailed Description
In order to make the purposes, technical solutions and advantages of the implementation of the present application more clear, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the accompanying drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are some, but not all, of the embodiments of the present application. The embodiments described below by referring to the drawings are exemplary and intended for the purpose of explaining the present application and are not to be construed as limiting the present application. All other embodiments, which can be made by one of ordinary skill in the art based on the embodiments herein without making any inventive effort, are intended to be within the scope of the present application.
It should be understood that technical terms such as "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. may be referred to in the description of the present application as indicating orientations or positional relationships based on the drawings, are merely for convenience in describing the present application and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and therefore should not be construed as limiting the scope of protection of the present application.
The variable thickness wing structure of the present application is described in further detail below in conjunction with figures 1-5.
The method aims at solving the problem of self-adaptive deformation of the wing in different speed ranges, provides a structural scheme aiming at the problem of variable thickness of the complex wing, improves the flight efficiency of the aircraft, and simultaneously provides a structural design method.
The application discloses a variable thickness wing structure, which can comprise a front edge 7, a wing box 5, a rear edge 8, a flexible skin 1, a driving shaft 3, a driver and a curved disc 4 which are sequentially arranged from front to back.
Specifically, as shown in fig. 1 and 2, the leading edge 7, the wing box 5 and the trailing edge 8 are of conventional design, i.e. are arranged in sequence from front to back; and, the front edge 7 includes the front beam 2 at the rear thereof, and the rear edge 8 includes the rear beam 6 at the front thereof and disposed in parallel with the front beam 2; in addition, the wing box 5 is located between the front beam 2 and the rear beam 6, and both ends (along the chord direction of the wing structure) of the wing box 5 are respectively fixed with the front beam 2 and the rear beam 6, so as to realize the fixed connection of the front beam 2 and the rear beam 6. It will be appreciated that the wing box 5 serves as a connection between the front spar 2 and the rear spar 6, so that in order to ensure strength, it is preferred in this embodiment that the wing box 5 has a cross section in the chord-wise direction of the wing structure that is shaped like a letter.
The flexible skin 1 is also laid in the same place as the conventional skin, in particular on the integral structural element consisting of the leading edge 7, the wing box 5 and the trailing edge 8; the flexible skin 1 needs to meet the length change caused by the thickness change, namely, has the capability of large deformation, and meanwhile, needs to meet the requirement of bearing. It will be appreciated that the flexible skin 1 may be selected from a variety of suitable materials known to date according to different needs, in this embodiment, it is preferred that the flexible skin 1 be a metal skin or a honeycomb skin; if the wing structure is selected as the metal skin, the two ends of the metal skin, which are positioned in the chord direction of the wing structure, are telescopic; in the case of a honeycomb skin, a high spanwise load must be met.
The number of the driving shafts 3 is plural, the driving shafts 3 are distributed on the upper side and the lower side of the wing box 5, and the two ends of each driving shaft 3 are respectively hinged with the front beam 2 and the rear beam 6, so that each driving shaft 3 can rotate around the axis thereof under the action of external force.
Correspondingly, the number of the drivers is a plurality, and each driver is used for driving a corresponding driving shaft 3 to rotate; it will also be appreciated that the specific construction of the drive may be suitably selected as desired, and that the specific mounting location of the drive may be designed according to the actual space and driving speed, in this embodiment it is preferred that the drive is a drive motor provided on the front beam 2 or the rear beam 6 (not shown in the figures) and connected to the corresponding drive shaft 3.
The number of the curved plates 4 is plural, and each curved plate 4 has a shape as shown in fig. 4 or 5, a connecting portion 41 located at a middle position and a fan-shaped portion 42 located at an outer side; wherein, a plurality of curved discs 4 are fixedly arranged on the corresponding driving shafts 3 through connecting parts 41 thereof, so as to be capable of rotating along with the driving shafts 3; and, each curved disc 4 movably supports (i.e., slidingly connects) the flexible skin 1 in contact with it by means of the arcuate outer contour of its sector 42, in such a way that, when the curved disc rotates, a sliding occurs between its outer contour and the skin), and simultaneously configures the flexible skin 1 to an external shape identical to the shape of its outer contour; in addition, the outer contour line of each sector 42 is an arc line of a non-circular arc, and the shape of the arc line is adapted to the pre-deformed shape of the wing box 5 (the variation of the wing thickness is achieved by the deformation of the wing box 5) and the specific position of the curved disc 4 corresponding to the arc line on the wing box 8.
The number of driving shafts 3 on the upper and lower sides of the wing box 5 and the arrangement positions thereof can be set appropriately according to the needs (the specific shape needs of the upper and lower wings when the wing thickness is changed), the number of the curved plates 4 on each driving shaft 3 and the arrangement positions of the plurality of curved plates 4 on the axis can be set appropriately according to the needs (the specific shape needs of the upper and lower wings when the wing thickness is changed), and the specific shape of the outer contour lines (i.e., the arcs) of the curved plates 4 at each position can be set appropriately according to the needs (the specific shape needs of the upper and lower wings when the wing thickness is changed).
In this embodiment, as shown in fig. 1 to 3, it is preferable that the number of the driving shafts 3 on the upper and lower sides of the wing box 5 is the same, and that the three driving shafts 3 on the upper side or the three driving shafts 3 on the lower side are not parallel to each other and are uniformly spaced. Further, it is preferable that the number of the curved plates 4 on each driving shaft 3 is three, and the three curved plates 4 are uniformly distributed in the axial direction of the driving shaft 3. And, the radius of any point on the outer contour line (i.e., the arc line) on each curved disc 4 from the axis varies.
Further, in the variable thickness wing structure of the present application, the principle of Qu Pan driving is shown in fig. 5, the position of the curved disc before driving is shown in fig. 5a, and the position of the curved disc after driving is shown in fig. 5 b. Because the outer contour of the curved disc 4 is a non-circular arc curve, when the curved disc 4 rotates, the distance between the contact point of the Qu Pan and the flexible skin 1 and the axis of the driving shaft 3 changes, and the change is directly related to the contour of the curved disc, so that the up-and-down movement of the flexible skin 1, namely the thickness change of the wing, is realized.
In summary, in the variable thickness wing structure of the present application, different profiles of the flexible skin 1 along the chord direction when the driving shaft 3 rotates can be achieved by designing the arrangement of the plurality of curved plates 4 along the chord direction and the outer profiles of the curved plates 4 at different positions. Likewise, it is also possible to produce different contours of the flexible skin 1 in the spanwise direction when the drive shaft 3 rotates by designing the arrangement of the plurality of curved discs 4 in the spanwise direction and the outer contours of the curved discs 4 at different positions. Further, by the outer profile design of the chordwise and spanwise camber 4 described above, complex profile variations of the entire airfoil upper and lower surfaces can be created.
Further, the design steps of the variable thickness wing structure of the present application are as follows:
1) Determining the initial appearance and the target appearance of the wing;
the aerodynamic efficiency of the wing under different working conditions is used as a target by adopting aerodynamic optimization software, the aerodynamic shape of the wing is described by adopting a parameterization method based on class shape transformation, and the aerodynamic shape of the wing under different working conditions is optimally designed by adopting a aerodynamic optimization design tool, so that the optimal aerodynamic shape under various working conditions is obtained. The number of operating conditions may be determined based on the number of operating conditions commonly used by the aircraft.
2) Taking a honeycomb type flexible skin as an example, selecting the skin and designing the structure;
according to the pneumatic load size and the material mechanical property parameters, a flexible honeycomb unit cell topological optimization design tool is adopted to design the honeycomb flexible skin, and the type of the honeycomb flexible skin and the connection mode of the honeycomb flexible skin with Qu Pan are determined.
3) Theoretical analysis of the curve profile;
according to the optimal aerodynamic profile determined in step 1) under different working conditions, determining a time-dependent variation curve of wing thickness (mainly referred to as the thickness of the wing box 5) at each position in the chord direction by an interpolation method, and determining the profile of the curved disc according to the curve.
4) Optimizing the number and the position of the curved discs;
and optimizing the number and the position of the curved disc along the chord direction according to the deformation precision fit requirement and the structural weight requirement of the variable-thickness wing, and designing by adopting a multi-objective-based heuristic optimization algorithm.
5) Variable thickness wing detailed design and driving system design;
and carrying out detailed design of the variable-thickness wing engineering prototype according to the design result, wherein the detailed design comprises detailed design of each connecting structure. In addition, the model of the variable thickness wing driving system motor is determined according to the speed, the rotation range and the driving load of the curved disc.
6) And (5) verifying the wing variable thickness function.
Finally, designing related clamps and test systems aiming at the designed variable-thickness wing engineering prototype, and performing variable-thickness functional verification.
The foregoing is merely specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions easily conceivable by those skilled in the art within the technical scope of the present application should be covered in the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (7)
1. A variable thickness wing structure, comprising:
front edges (7), wing boxes (5) and rear edges (8) are sequentially arranged from front to back, the front edges (7) comprise front beams (2) positioned at the rear parts of the front edges, the rear edges (8) comprise rear beams (6) positioned at the front parts of the front beams and arranged in parallel with the front beams (2), and the wing boxes (5) are positioned between the front beams (2) and the rear beams (6) and fixedly connect the front beams (2) with the rear beams (6);
-a flexible skin (1) laid on a monolithic structure constituted by said leading edge (7), wing box (5) and trailing edge (8);
the driving shafts (3) are distributed on the upper side and the lower side of the wing box (5), and two ends of each driving shaft (3) are respectively hinged with the front beam (2) and the rear beam (6) so that each driving shaft (3) can rotate around the axis under the action of external force;
a plurality of drivers, each for driving a corresponding one of the drive shafts (3) to rotate;
the flexible skin (1) is movably supported by each curved disc (4) through the arc-shaped outer contour of the fan-shaped part (42) of the curved disc (42), and the flexible skin (1) is configured to be the same as the outer contour of the curved disc, in addition, the outer contour line of each fan-shaped part (42) is an arc line which is not an arc, and the shape of the arc line is adapted to the pre-deformation shape of the wing box (5) and the specific position of the curved disc (4) corresponding to the arc line on the wing box (5).
2. Variable thickness wing structure according to claim 1, characterized in that the number of drive shafts (3) on the upper and lower sides of the wing box (5) is the same and that the drive shafts (3) on the upper side or the drive shafts (3) on the lower side are mutually parallel and evenly spaced.
3. Variable thickness wing structure according to claim 2, characterized in that the plurality of curved discs (4) on each drive shaft (3) are evenly distributed along the axial direction of the drive shaft (3).
4. Variable thickness wing structure according to claim 1, characterized in that the flexible skin (1) is a metal skin, and that the ends of the metal skin in the chord-wise direction of the wing structure are telescopic.
5. A variable thickness wing structure according to claim 1, characterized in that the flexible skin (1) is a honeycomb skin.
6. Variable thickness wing structure according to claim 1, characterized in that the drive is a drive motor which is arranged on the front beam (2) or rear beam (6) and is connected to a corresponding drive shaft (3).
7. Variable thickness wing structure according to claim 1, characterized in that the section of the wing box (5) in the chord-wise direction of the wing structure is shaped like a letter.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202111672971.7A CN114291249B (en) | 2021-12-31 | 2021-12-31 | Variable-thickness wing structure |
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| CN202111672971.7A CN114291249B (en) | 2021-12-31 | 2021-12-31 | Variable-thickness wing structure |
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| CN114291249A CN114291249A (en) | 2022-04-08 |
| CN114291249B true CN114291249B (en) | 2023-08-04 |
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| CN115571324B (en) * | 2022-12-09 | 2023-03-31 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Composite material bistable skin structure and application thereof to morphing wing |
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| CN114291249A (en) | 2022-04-08 |
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