CN110920861B - Flexible skin structure of wing - Google Patents
Flexible skin structure of wing Download PDFInfo
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- CN110920861B CN110920861B CN201911190177.1A CN201911190177A CN110920861B CN 110920861 B CN110920861 B CN 110920861B CN 201911190177 A CN201911190177 A CN 201911190177A CN 110920861 B CN110920861 B CN 110920861B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
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Abstract
The invention relates to a wing flexible skin structure and a wing, wherein the wing flexible skin structure comprises a plurality of flanges and chiral units which are periodically arranged among the flanges; the chiral units are symmetric about a structural center, and comprise four structural subunits, wherein each structural subunit comprises: the first arc-shaped ligament is connected with the second arc-shaped ligament; the first end of the first circular arc ligament and the first end of the second circular arc ligament are tangent to the circular ring, the second end of the first circular arc ligament is connected with the second end of the first circular arc ligament of the adjacent structure subunit, and the second end of the second circular arc ligament is connected with the flange on the outer side. The wing flexible skin structure not only can meet the requirement of large deformation, but also ensures the rigidity requirement of the structure.
Description
Technical Field
The invention relates to the field of structural design, in particular to a flexible skin structure of a wing and the wing.
Background
In the flying process of the aircraft, the wing skin needs to expand and contract with the wing framework on a large scale, and meanwhile, the wing skin needs to have enough rigidity to resist aerodynamic load. Conventional aircraft wings primarily employ a second type of skin. The first type is a rubber material with high flexibility, the rubber skin has good air tightness and can deform in a large scale, and the bearing of the first type is mainly realized by the internal structure of the wing. The second type is that the split type movable traditional hard skin is adopted, so that the bearing performance is good, large deformation can occur, and the requirements of the wing on bearing and deformation are met.
The rubber skin structure mainly adopts a form of combining a honeycomb composite material structure and a silicon rubber skin. But the overall load-bearing capacity of the wing is not high due to the limited ability of the rubber skin to carry aerodynamic loads. Although the split type movable traditional hard skin meets the requirements of wing bearing and deformation, the split type movable traditional hard skin cannot meet the requirements of smooth and continuous wing surface, integral air tightness and the like, so that the aerodynamic efficiency of the deformed wing cannot reach the optimum.
Disclosure of Invention
The invention aims to solve the technical problems that the existing skin structures such as rubber and split skin structures are low in integral bearing capacity and uneven in deformation, and provides a wing flexible skin structure with a specific chiral unit structure and a wing.
In order to solve the technical problem, the invention provides a flexible skin structure of a wing, which comprises a plurality of flanges and chiral units periodically arranged among the flanges; the chiral units are symmetric about a structural center, and comprise four structural subunits, wherein each structural subunit comprises: the first arc-shaped ligament is connected with the second arc-shaped ligament; the first end of the first circular arc ligament and the first end of the second circular arc ligament are tangent to the circular ring, the second end of the first circular arc ligament is connected with the second end of the first circular arc ligament of the adjacent structure subunit, and the second end of the second circular arc ligament is connected with the flange on the outer side.
In the flexible skin structure of the wing according to the invention, preferably, the circular mandrels of the circular ring, the first circular arc ligament and the second circular arc ligament are located on the same horizontal plane and are arranged at equal intervals; the circular mandrel of the first circular arc-shaped ligament is positioned on a vertical symmetrical plane of the chiral unit, and the circular mandrel of the second circular arc-shaped ligament is positioned on the outer side of the flange.
In the wing flexible skin structure according to the invention, the thickness of the wing flexible skin structure is preferably 18-20 mm.
In the flexible skin structure of the wing according to the invention, preferably, the chiral units satisfy the following dimensional relationship:
wherein R is the radius of the first and second arc-shaped ligaments, dcIs the inner diameter of the ring, W1Is the distance between the outer sides of the two flanges, delta2Is the wall thickness of the ring, E1Is a first constant with a value range of 0-1 mm.
In the wing flexible skin structure according to the invention, preferably, the wall thicknesses δ of the circular ring, the first circular arc ligament and the second circular arc ligament2Equal, and satisfy:
δ2＝2*δ1；
wherein delta1The wall thickness of the flange.
In the flexible skin structure of the wing according to the invention, preferably, the height H of the chiral units is:
H＝2*(2R+E2)；
wherein E2Is the second constant and has a value range of 1-1.5 mm.
In the flexible skin structure of the wing according to the invention, preferably, the radius of each of the first circular arc ligament and the second circular arc ligament is 9.25mm, the inner diameter of the ring is 3.5mm, the distance between the outer sides of the two flanges is 25mm, the height of the chiral unit is 40mm, the distance between the circular mandrels of the ring, the first circular arc ligament and the second circular arc ligament from the horizontal symmetry plane of the chiral unit is 10mm, and the distance between the circular mandrel of the second circular arc ligament from the outer sides of the flanges is 0.5 mm.
In the flexible skin structure of the wing according to the invention, preferably, the wall thickness of the flange is 0.5mm, and the wall thicknesses of the ring, the first circular arc ligament and the second circular arc ligament are 1.0 mm.
In the wing flexible skin structure according to the invention, preferably, the wing flexible skin structure is made of a shape memory alloy material.
The invention also provides a wing comprising a wing flexible skin structure as described above.
The wing flexible skin structure and the wing have the following beneficial effects: the wing flexible skin structure is optimized on the basis of the four-ligament chiral structure unit, and the negative Poisson ratio property of the structure is removed by deleting part of ligaments, so that the complete pneumatic appearance of the wing flexible skin structure in the deformation process is ensured; meanwhile, the extensible capability of the structure is improved by uniform curvature and the number of large-radian ligaments is increased, stress and strain concentration is reduced, the requirement of large deformation is met, and the requirement on the rigidity of the structure is ensured.
Drawings
FIG. 1 is a perspective view of a wing flexible skin structure according to a preferred embodiment of the present invention;
FIG. 2 is a schematic plan view of a chiral element of a wing flexible skin structure according to a preferred embodiment of the invention;
FIGS. 3a and 3b are a schematic plan view and a perspective view, respectively, of a first prior art ligamentum triad chiral structure before and after a tensile deformation;
FIGS. 4a and 4b are a schematic plan view and a perspective view, respectively, of a second prior art ligamentum triad chiral structure before and after a tensile deformation;
FIGS. 5a and 5b are a schematic plan view and a perspective view, respectively, of a prior art anti-chiral structure of a ligamentum tetrandrum before and after a tensile deformation;
FIG. 6 is a schematic plan view of a chiral unit according to a preliminary design of the present invention;
FIGS. 7a-7c are schematic plan views of chiral units optimally designed according to the present invention;
FIG. 8 is a schematic representation of chiral cell dimensions of a flexible skin structure for a wing in accordance with a preferred embodiment of the present invention;
FIG. 9 is a tensile test chart of a wing flexible skin structure of the present invention;
FIG. 10 is a graph of a compression test of a flexible skin structure for a wing of the present invention.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, 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 some, but not all, embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
Referring to fig. 1 and fig. 2, a perspective view and a schematic plan view of a chiral unit of a flexible skin structure of a wing according to a preferred embodiment of the invention are shown. As shown in fig. 1, this embodiment provides a solar cell including a plurality of flanges 2 and chiral units 1 periodically arranged between the flanges 2. Preferably, the plurality of flanges 2 are arranged in parallel and equidistantly. As shown in the cross-sectional view of fig. 2, the chiral unit 1 is symmetrical about the structural center, and includes four structural subunits, such as an upper left structural subunit, an upper right structural subunit, a lower left structural subunit, and a lower right structural subunit in fig. 2, which are symmetrical to each other along the horizontal center line and symmetrical to each other along the vertical center line. Wherein each structural subunit comprises: a ring 11, a first circular arc shaped ligament 12 and a second circular arc shaped ligament 13. The first end of the first circular arc ligament 12 and the first end of the second circular arc ligament 13 are both tangent to the ring 11. Preferably, the tangent points of the two and the circular ring 11 are respectively positioned at the inner side and the outer side of the circular ring 11 and are distributed at 180 degrees. In the invention, the vertical center line of the chiral unit 1 in fig. 2 is taken as the inner side, and the flange is taken as the outer side. The second end of the first circular arc ligament 12 is connected with the second end of the first circular arc ligament 12 of the adjacent structural subunit to form a semicircular ring with a circular arc angle of 180 degrees. The second end of the second circular arc ligament 13 is connected with the flange 1 on the outer side.
Preferably, the circular arbour o3 of the circular ring 11, the circular arbour o1 of the first circular arc shaped ligament 12 and the circular arbour o2 of the second circular arc shaped ligament 13 are located on the same horizontal plane and are arranged equidistantly. And the circular axis o1 of the first circular arc ligament 12 is located on the vertical symmetry plane of the chiral unit, that is to say the circular axis o1 of the first circular arc ligament 12 is located on the vertical central line in the depiction of fig. 2, and the circular axis o2 of the second circular arc ligament 13 is located outside the flange.
The design principle of the wing flexible skin structure of the present invention is described in detail below.
The shape memory alloy can bear large deformation, and the flexible skin structure of the wing can bear enough in-plane deformation. The chiral structure adopts the principles of ring node rotation and ligament bending to increase the deformation of the structure and reduce stress concentration, so that the chiral structure has the capability of resisting large deformation under limited material strain. The large deformation generable property of the skin structure is considered in the design process of the wing flexible skin structure, and the basic aerodynamic shape of the exterior of the structure is kept unchanged after the wing is deformed, so that the structure needs to be designed with zero Poisson ratio.
Please refer to fig. 3a and 3b, which are a schematic plan view and a perspective view of a first three-ligament chiral structure before and after stretching deformation in the prior art, respectively. Fig. 4a and 4b are a schematic plan view and a perspective view of a second prior art ligamentum teres chiral structure before and after stretching deformation, respectively. Fig. 5a and 5b are a schematic plan view and a perspective view of a prior art anti-chiral structure of a ligamentum tetrandrum before and after stretching deformation. After 20% of tensile deformation of the three different chiral structures, the maximum material strains of the first and second triphatic and tetraligamentic anti-chiral structures were 54.81%, 6.34%, 15.07%. The first three-ligament chiral structure is obviously not suitable for structural design due to overlarge material strain, and the analysis unit is deformed to find that the second three-ligament chiral structure has an obvious stress concentration phenomenon, so that the basic unit form of the wing flexible skin structure is determined to be a four-ligament anti-chiral structure with small material strain and relatively uniform stress, and the unit structure is optimized on the basis of the four-ligament anti-chiral structure.
Fig. 6 is a schematic plan view of a chiral unit preliminarily designed according to the present invention. As shown in fig. 6, the invention is designed on the basis of the original four ligament anti-chiral structure in two steps:
s1, bending the ligament, and increasing the ability of the structure to bear large deformation;
s2, removing partial ligaments, removing the negative Poisson' S ratio property of the structure, and ensuring the complete aerodynamic shape of the flexible skin structure of the wing in the deformation process.
As shown in fig. 7a-7c, are schematic plan views of chiral units optimally designed according to the present invention. The chiral unit of fig. 7a can be obtained after the preliminary design through the above steps S1-S2, but there is a problem of non-uniform stress, and the present invention solves the problem of non-uniform stress through uniform ligament curvature, resulting in the chiral unit structure of fig. 7 b. The structure of fig. 7b was measured to have an excessive strain problem with a maximum material strain of 2.21%, thus the invention increases the number of large arc ligaments and obtains the chiral unit structure shown in fig. 7 c.
The invention optimizes the relative density of the chiral units on the basis of obtaining the chiral unit structure, and designs the units in a light weight way. Preferably, the relative density is less than 20%.
The calculation formula of the relative density of the scheme is
The scheme is that
On the basis of the flexible skin structure of the wing, the invention optimizes all size parameters through a large number of tests and experience summary.
Fig. 8 is a schematic diagram showing the dimensions of chiral cells of a flexible skin structure of a wing according to a preferred embodiment of the invention. In some preferred embodiments of the invention, the chiral units satisfy the following dimensional relationships:
where R is the radius of the first and second arcuate ligaments 12, 13, dcIs the inner diameter, W, of said ring 111Is the distance between the outer sides of the two flanges, delta2Is the wall thickness of the ring 11, E1Is a first constant. E1The value range of (A) is 0-1 mm.
Multiple groups of experimental data show that the tensile deformation of the flexible wing skin structure meeting the size relation is about 20%, the material strain is less than 1%, and the flexible wing skin structure has the characteristics of large deformation bearing capacity, good ductility and small material strain, and does not have a stress concentration phenomenon.
More preferably, the wall thickness δ of ring 11, first circular-arc ligament 12 and second circular-arc ligament 132Equal, and satisfy:
δ2＝2*δ1；
wherein delta1The wall thickness of the flange.
More preferably, the height H of the chiral units is:
H＝2*(2R+E2)；
wherein E2Is the second constant and has a value range of 1-1.5 mm.
In a specific embodiment, the radius R of the first circular arc ligament 12 and the second circular arc ligament 13 is 9.25mm, and the radius R is from the center of the circle to the outer edge of the circular arc ligament, including the wall thickness of the circular arc ligament. Inner diameter d of the ring 11c3.5mm, the inner diameter being the inner diameter. The distance W between the outer sides of two adjacent flanges1Is 25mm and the height H of the chiral units is 40 mm. The distance from the circle center axis of the ring 11, the first circular arc ligament 12 and the second circular arc ligament 13 to the horizontal symmetry plane of the chiral unit is 10mm, and the distance from the circle center axis o2 of the second circular arc ligament 13 to the outer side of the flange is 0.5 mm. Namely, in the plan view of fig. 8, the distances from the centers of the ring 11, the first circular arc ligament 12 and the second circular arc ligament 13 to the horizontal center line are all 10mm, and the distance from the center of the second circular arc ligament 13 to the outer side of the flange is 0.5 mm. Preferably, the overall structural thickness of the wing flexible skin structure (i.e. the thickness perpendicular to the direction of figure 8) is 18-20mm, in this embodiment 20 mm.
More preferably, the wall thickness δ of the flange 210.5mm, the wall thickness δ of the ring 11, the first arc ligament 12 and the second arc ligament 132Is 1.0 mm. Relative density in the cell size given in FIG. 8
The content was 18.89%.
The invention carries out tensile test and compressive rigidity test on the wing flexible skin structure with the specific size. Referring to fig. 9 and 10, a tensile test chart and a compressive test chart of the flexible skin structure of the wing of the invention are shown, respectively. LE in fig. 9 represents true material strain value and U in fig. 10 represents deflection. In the tensile test, the left end of the flexible skin structure of the wing is fixed, and 20% of displacement load is applied to the right end. In the compression rigidity test, the left end and the right end of the wing flexible skin structure are fixed, and uniform load of 0.08MPa is applied outside the plane (vertical paper surface).
And (3) testing results: as LE in FIG. 9 represents the true material strain value, the maximum material strain of the flexible skin structure of the wing is 6.989E-03 after the flexible skin structure is subjected to 20% in-plane deformation, and the deformation is uniform. Meanwhile, as shown in fig. 10, under the action of an out-of-plane uniform load of 0.08MPa, the maximum deflection of the wing flexible skin structure reaches 2.677mm, and the wing flexible skin structure occurs in the middle of the skin structure, so that the basic condition that the structure is not crushed under the action of the out-of-plane load is achieved, and the wing flexible skin structure can have enough rigidity under the action of a pneumatic load.
In addition, the present invention also tested the performance of the wing flexible skin structure for various dimensional parameters, as shown in table 1, in units (mm).
Table 1
The flexible skin structure of the wing can be manufactured by adopting shape memory alloy in a 3D printing mode. The shape memory alloy includes, but is not limited to, TiNi alloy.
The invention also provides a wing which can adopt the wing flexible skin structure. The size of the wing flexible skin structure of the present invention can be adjusted, for example scaled, by those skilled in the art according to the actual engineering application.
In summary, the invention optimizes the four ligament anti-chiral structural unit, and provides a novel chiral unit structure. The chiral unit structure is improved in two steps: part of ligaments are deleted, the negative Poisson ratio property of the structure is removed, and the complete aerodynamic appearance of the flexible skin structure of the wing in the deformation process is ensured; uniform curvature and increased number of large arc ligaments to improve the ductile ability of the structure and reduce stress-strain concentration. The chiral unit structure of the invention mainly comprises a central ring and a plurality of ligaments. Under the effect of external load, the ring can take place to rotate, and the many ligaments that link to each other with the ring can take place to warp this moment, and ring and ligament in the structure have increased extra design parameter for structural design, consequently sign cell structure is used for the structure to bear the weight of fields such as lightweight, shock resistance more.
Therefore, the flexible skin structure of the wing provided by the invention can be obtained by adopting a mode of periodic arrangement of chiral unit structures, has a simple structure, and is convenient for optimizing and improving the structure. The flexible skin structure of the wing has the capacity of bearing large deformation, good ductility, small material strain and no stress concentration phenomenon. And the flexible skin structure of the wing meets the requirement of aerodynamic shape integrity of the wing structure in the deformation process, and can have enough rigidity under aerodynamic load.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; and such modifications or substitutions do not depart from the spirit and scope of the corresponding technical solutions of the embodiments of the present invention.
Claims (9)
1. The flexible skin structure of the wing is characterized by comprising a plurality of flanges and chiral units which are periodically arranged between the flanges; the chiral units are symmetric about a structural center, and comprise four structural subunits, wherein each structural subunit comprises: the first arc-shaped ligament is connected with the second arc-shaped ligament; the first end of the first circular arc ligament and the first end of the second circular arc ligament are both tangent to the circular ring, the second end of the first circular arc ligament is connected with the second end of the first circular arc ligament of the adjacent structure subunit, and the second end of the second circular arc ligament is connected with the flange on the outer side;
the chiral units satisfy the following dimensional relationships:
wherein R is the radius of the first and second arc-shaped ligaments, dcIs the inner diameter of the ring, W1Is the distance between the outer sides of the two flanges, delta2Is the wall thickness of the ring, E1Is a first constant with a value range of 0-1 mm.
2. The wing flexible skin structure of claim 1, wherein the circular mandrels of the circular ring, the first circular arc ligament and the second circular arc ligament are located on the same horizontal plane and are arranged at equal distances; the circular mandrel of the first circular arc-shaped ligament is positioned on a vertical symmetrical plane of the chiral unit, and the circular mandrel of the second circular arc-shaped ligament is positioned on the outer side of the flange.
3. The wing flexible skin structure of claim 1, wherein the wing flexible skin structure has a thickness of 18-20 mm.
4. The wing flexible skin structure of claim 1, wherein the annular ring, the first radiused ligament, and the second radiused ligament have a wall thickness δ2Equal, and satisfy:
δ2＝2*δ1；
wherein delta1The wall thickness of the flange.
5. The wing flexible skin structure of claim 1, wherein the chiral elements have a height H of:
H＝2*(2R+E2)；
wherein E2Is the second constant and has a value range of 1-1.5 mm.
6. The wing flexible skin structure of claim 1, wherein the first and second circular arc ligaments have a radius of 9.25mm, the inner diameter of the ring is 3.5mm, the distance between the outer sides of the two flanges is 25mm, the height of the chiral unit is 40mm, the distances from the circular mandrels of the ring, the first circular arc ligament and the second circular arc ligament to the horizontal symmetry plane of the chiral unit are 10mm, and the distance from the circular mandrel of the second circular arc ligament to the outer sides of the flanges is 0.5 mm.
7. The wing flexible skin structure of claim 1, wherein the wall thickness of the flange is 0.5mm, and the wall thickness of the ring, the first radiused ligament, and the second radiused ligament is 1.0 mm.
8. The wing flexible skin structure of claim 1, wherein the wing flexible skin structure is made of a shape memory alloy material.
9. A wing comprising a wing flexible skin structure according to any of claims 1 to 8.
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