CN111439368B - Variable camber wing based on flexible skin of composite material corrugated plate - Google Patents
Variable camber wing based on flexible skin of composite material corrugated plate Download PDFInfo
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- CN111439368B CN111439368B CN202010181111.2A CN202010181111A CN111439368B CN 111439368 B CN111439368 B CN 111439368B CN 202010181111 A CN202010181111 A CN 202010181111A CN 111439368 B CN111439368 B CN 111439368B
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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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/38—Adjustment of complete wings or parts thereof
- B64C3/44—Varying camber
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Abstract
A variable camber wing based on a flexible skin of a composite material corrugated plate comprises a plurality of sections of wing sections, a rotating shaft, a hinged structure, the composite material corrugated plate and an elastomer layer. The connection relationship is as follows: each wing section is connected through the pivot final phase to end, covers the combined material buckled plate between the adjacent wing section, and the combined material buckled plate is fixed respectively on the platform of wing section and back wing section in the front, and every combined material buckled plate middle part is equipped with hinge structure and links to each other with corresponding wing section, and the elastomer layer bonds at the surface of combined material buckled plate. The invention designs a variable camber wing structure by utilizing the characteristic that the flexible skin of the composite material corrugated plate has large deformation capacity along the corrugation direction, and applies out-of-plane constraint to the flexible skin of the composite material corrugated plate by using a hinge structure, so that the wing can realize the variable camber function, and the flexible skin of the composite material corrugated plate can not generate out-of-plane deformation outside the allowable range, thereby maintaining good pneumatic appearance.
Description
Technical Field
The invention provides a variable camber wing based on a composite material corrugated plate flexible skin, and belongs to the field of structural design.
Background
In the field of aviation, a "morphing aircraft" is an aircraft that can achieve enhanced performance within a mission profile by changing its geometry, with the most critical technology being morphing wings. The variant wing with the variable camber is one of variant wings, and compared with the traditional wing, the variant wing with the smooth and continuous variable camber has higher aerodynamic efficiency. The composite material corrugated plate has large tensile deformation capacity in the corrugation direction, good bending deformation capacity and large rigidity in the direction perpendicular to the corrugation, so that the composite material corrugated plate is suitable for being used as a flexible skin of a variable-camber wing. However, the corrugated plate made of the composite material is uneven and has a poor aerodynamic appearance, and an elastomer layer needs to be covered on the outer side of the corrugated plate made of the composite material, so that the flexible skin of the corrugated plate made of the composite material with a continuous smooth aerodynamic appearance is formed. In addition, the out-of-plane rigidity of the composite corrugated plate flexible skin is low, and when the composite corrugated plate flexible skin bears aerodynamic load or when a certain skin is pressed due to bending deformation of the wing, the composite corrugated plate flexible skin can generate large out-of-plane deformation, so that the aerodynamic appearance of the wing is damaged. Therefore, the invention provides a variable camber wing based on a composite material corrugated plate flexible skin, which consists of a plurality of sections of wing sections, a rotating shaft, a hinge structure, a composite material corrugated plate and an elastomer layer, can realize the variable camber function, and under the constraint of the hinge structure, the composite material corrugated plate flexible skin cannot generate out-of-plane deformation outside an allowable range when being subjected to pneumatic load or wing bending deformation, thereby keeping good pneumatic appearance.
Disclosure of Invention
1. The purpose is as follows: the invention aims to provide a morphing wing based on a composite material corrugated plate flexible skin, which can realize the function of variable camber, and can maintain good aerodynamic shape without out-of-plane deformation outside the allowable range under the action of aerodynamic load or during the bending deformation of the wing.
2. The technical scheme is as follows: the invention relates to a variable camber wing based on a flexible skin of a composite material corrugated plate, which consists of a plurality of sections of wing sections, a rotating shaft, a hinged structure, the composite material corrugated plate and an elastomer layer. The main body of the skin of the variant camber wing based on the composite corrugated plate flexible skin is the composite corrugated plate, the cross section of the composite corrugated plate is continuous corrugated units, each corrugated unit consists of smoothly connected arcs, the outer side of the composite corrugated plate is covered with an elastomer layer, and the composite corrugated plate and the elastomer layer form the flexible skin of the variant wing. The variant camber wing based on flexible skin of composite material buckled plate comprises four sections of wing sections, wherein the first section of wing section near the leading edge is a fixed section, adjacent wing sections are connected through a rotating shaft, and the rotating shaft is driven by a motor and can drive the next section of wing section to rotate. Covering the combined material buckled plate between the adjacent wing panel, the combined material buckled plate is fixed respectively on the platform of preceding wing panel and back wing panel, and the elastomer layer bonds at the surface of combined material buckled plate to maintain glossy aerodynamic shape, combined material buckled plate and elastomer layer have constituted the flexible covering of combined material buckled plate jointly. The middle part of each composite corrugated plate is provided with a hinged structure, the lower base of the hinged structure is arranged on the corresponding wing section, the upper base of the hinged structure is arranged at the corresponding wave crest of the composite corrugated plate, and the upper base and the lower base are connected through a rigid rod. The motor drives each rotating shaft to drive the corresponding wing section to rotate, and the platform of each wing section can drive the flexible skin of the composite material corrugated plate to deform, so that the function of bending degree changing is realized. The hinge structure in the middle of each composite corrugated plate can apply out-of-plane constraint on the flexible skin of the composite corrugated plate, so that the flexible skin of the composite corrugated plate has the capacity of resisting pneumatic load. Simultaneously, for the solid connection of propping up, the hinge structure can not be to the flexible covering of combined material buckled plate overstraining, can not hinder or reduce the deformability of the flexible covering of combined material buckled plate, can not make the flexible covering of combined material buckled plate produce discontinuous deformation. The composite corrugated plate has high bending rigidity in the long direction of the wingspan, so that the hinge structures do not need to be continuously arranged in the long direction of the wingspan, and the hinge structures can be arranged at intervals according to the bending modulus of the composite corrugated plate in the long direction of the wingspan, so that the structural weight of the variant camber wing based on the flexible skin of the composite corrugated plate is reduced.
The composite corrugated plate is a unidirectional belt laminated corrugated plate made of carbon fibers, glass fibers, Kevlar fibers and boron fibers, and a woven material corrugated plate made of the carbon fibers, the glass fibers, the Kevlar fibers and the boron fibers.
The elastomer layer is made of silicon rubber, nitrile rubber, fiber reinforced silicon rubber, fiber reinforced nitrile rubber, piezoelectric fiber silicon rubber composite material and piezoelectric fiber nitrile rubber composite material.
Drawings
The invention is further illustrated by the following figures and examples:
fig. 1 is a schematic cross-sectional view of a composite corrugated plate, the cross section of the flexible composite corrugated plate is continuous corrugated units, each corrugated unit is composed of continuous smooth connected circular arcs with a central angle theta and a radius R, and the composite corrugated plate has large tensile deformation capacity and bending deformation capacity in the corrugation direction.
Figure 2 is a composite corrugated sheet flexible skin morphing wing without a hinge structure in an initial state. In fig. 2: part 2 is a first section wing section, part 3 is a second section wing section, part 4 is a third section wing section, part 5 is a fourth section wing section, part 6 is a rotating shaft connecting the first and second section wing sections, part 7 is a rotating shaft connecting the second and third section wing sections, part 8 is a rotating shaft connecting the third and fourth section wing sections, part 9 is a composite material corrugated plate on the upper surface of the wing, part 10 is a composite material corrugated plate on the lower surface of the wing, part 11 is an elastomer layer on the upper surface of the wing, and part 12 is an elastomer layer on the lower surface of the wing.
Figure 3 is a composite corrugated sheet flexible skin morphing wing without a hinge structure in a deformed state.
Figure 4 is a composite corrugated sheet flexible skin morphing wing with a hinge structure in an initial state. In fig. 4: the component 13 is a hinged structure for a composite corrugated sheet flexible skin morphing wing.
Fig. 5 is a detailed view of the hinge structure.
Figure 6 is a composite corrugated sheet flexible skin camber airfoil with hinge structures in a deformed state.
Detailed Description
The invention is further described below with reference to the drawings and the examples.
The invention relates to a morphing wing based on a composite corrugated plate flexible skin. The flexible skin (shown in figure 1) of the composite material corrugated plate is formed by smoothly connecting continuous corrugated units, the central angle of each corrugated unit is theta, the corrugated radius is R, and the composite material corrugated plate has the stretching and bending deformation capacity in the corrugation direction and has larger rigidity in the direction perpendicular to the corrugation direction. The composite corrugated plate is a unidirectional belt laminated corrugated plate made of carbon fibers, glass fibers, Kevlar fibers and boron fibers, and a woven material corrugated plate made of the carbon fibers, the glass fibers, the Kevlar fibers and the boron fibers. The morphing wing structure (as shown in figure 2) is composed of a wing panel 2, a wing panel 3, a wing panel 4 and a wing panel 5 which are connected end to end, wherein the wing panel 2 and the wing panel 3 are connected through a rotating shaft 6, the wing panel 3 and the wing panel 4 are connected through a rotating shaft 7, and the wing panel 4 and the wing panel 5 are connected through a rotating shaft 8. The rotating shaft 6, the rotating shaft 7 and the rotating shaft 8 are driven by a motor and can respectively drive the wing sections 3, 4 and 5 to rotate. Each wing section is provided with a platform from top to bottom, and the platforms are attached to wing profiles. The upper surface skin 9 and the lower surface skin 10 of wing are the combined material buckled plate, paste elastomer layer 11 and 12 respectively in the combined material buckled plate outside of upper and lower surface, combined material buckled plate and elastomer layer have constituted combined material buckled plate flexible skin jointly, and wherein, the elastomer layer is silicon rubber, nitrile rubber, fibre reinforcement silicon rubber, fibre reinforcement nitrile rubber, piezoelectric fiber silicon rubber combined material and piezoelectric fiber nitrile rubber combined material. The upper and lower surface skins 9 and 10 are attached to the platform on the wing sections 2, 3, 4 and 5 by four glue points, respectively. When the composite corrugated plate flexible skin variant wing without the hinged structure rotates, the motor drives each rotating shaft to drive the corresponding wing section to rotate, the platform of each wing section can drive the composite corrugated plate flexible skin to deform, one surface skin of the wing is pulled, the other surface skin is pressed, the corrugated structure flexible composite skin of the pressed surface can be sunken inwards, and if the rotating angle of the wing is too large, the pressed surface skin can be unstable (as shown in figure 3), so that the pneumatic appearance of the wing is damaged. For the composite material corrugated plate flexible skin variant wing without the hinged structure, the composite material corrugated plate between the adjacent platforms is lack of constraint, the out-of-plane rigidity of the flexible skin of the composite material corrugated plate is small, and when the wing is subjected to large out-of-plane load, the skin is out-of-plane deformed outside an allowable range, so that the aerodynamic appearance is damaged. In order to always have a good aerodynamic profile during the rotation of the wing, a modified wing based on a composite corrugated sheet flexible skin with a hinge structure is designed (as shown in fig. 4), and the part 13 in fig. 4 is a hinge structure. In the invention, a hinge structure (shown in figure 5) is designed between a composite material corrugated plate and a corresponding wing section structure in the middle of two adjacent platforms, a lower base of the hinge structure is arranged on the corresponding wing section structure, an upper base of the hinge structure is arranged at the wave crest of the corresponding composite material corrugated plate, and the upper base and the lower base are connected through a rigid rod. The hinge structure can provide out-of-plane restraint for the flexible skin of the composite corrugated plate, so that the flexible skin of the composite corrugated plate has the capability of resisting aerodynamic load, and the flexible skin of the composite corrugated plate is prevented from being sunken or protruded when being subjected to aerodynamic load or bending deformation of wings. Meanwhile, the hinge structure does not apply over-constraint on the flexible skin of the composite corrugated plate, and the upper base and the lower base which are hinged to each other have rotational freedom in one direction with the rigid rod, so that the hinge structure does not obstruct or reduce the deformation capacity of the flexible skin of the composite corrugated plate. Meanwhile, the composite corrugated plate has high bending rigidity in the long direction of the wing span, so that the hinge structures do not need to be continuously arranged in the long direction of the wing span, and the hinge structures can be arranged at intervals according to the bending modulus of the composite corrugated plate in the long direction of the wing span, so that the weight of the wing structure is reduced. When the morphing wing of the composite corrugated plate flexible skin containing the hinge structure is bent and deformed (as shown in fig. 6), the hinge structure can provide out-of-plane constraint for the composite corrugated plate flexible skin, but the flexible deformation of the composite corrugated plate flexible skin can not be influenced, so that the wing can always keep a better aerodynamic shape in the deformation process of the wing.
Claims (6)
1. A variable camber wing based on composite material corrugated plate flexible skins comprises a plurality of sections of wing sections, a rotating shaft, a hinged structure, composite material corrugated plates and an elastomer layer, wherein the first section of wing section close to the front edge of the wing is a fixed section, each wing section is connected through the rotating shaft in sequence, the composite material corrugated plate flexible skins cover between the adjacent wing sections, the composite material corrugated plate flexible skins are respectively fixed on platforms of a front wing section and a rear wing section, the middle part of each composite material corrugated plate flexible skin is provided with a hinge structure which connects the composite material corrugated plate flexible skin with the corresponding wing section, the variable camber wing based on the composite material corrugated plate flexible skin can realize the function of variable camber, and when the wing is subjected to aerodynamic load or wing bending deformation, out-of-plane deformation outside the allowable range can not occur, so that a good aerodynamic shape is maintained.
2. The wing of claim 1, wherein the flexible skin is composed of a composite corrugated plate and an elastomer layer, and the composite corrugated plate and the elastomer layer are connected in the following manner: the cross section of the composite material corrugated plate is a continuous corrugated unit, each corrugated unit is composed of smoothly connected circular arcs, the elastomer layer is bonded on the outer layer of the composite material corrugated plate, the composite material corrugated plate has large tensile deformation and bending deformation capacity in the corrugation direction, and has large bending rigidity in the corrugation direction perpendicular to the composite material corrugated plate, and the elastomer layer enables the flexible skin of the composite material corrugated plate to have a continuous smooth pneumatic appearance, so that the requirements of the deformation capacity and the pneumatic appearance of the variable-camber wing can be met.
3. The wing with variable camber based on the flexible skin of the composite material corrugated plate, according to claim 1, the hinge structure is arranged in the middle of the composite material corrugated plate covered between the adjacent wing sections, the lower base of the hinge structure is arranged on the corresponding wing section, the upper base of the hinge structure is arranged at the wave crest of the composite material corrugated plate, the upper base and the lower base are connected through the rigid rod, the base is connected with the rigid rod in a hinged manner, the hinge structure in the middle of each composite material corrugated plate can apply out-of-plane constraint on the flexible skin of the composite material corrugated plate, so that the flexible skin of the composite material corrugated plate has the capability of resisting pneumatic load, simultaneously, for the solid connection of propping up, the hinge structure can not be to the flexible covering of combined material buckled plate overstraining, can not hinder or reduce the deformability of the flexible covering of combined material buckled plate, can not make the flexible covering of combined material buckled plate produce discontinuous deformation.
4. The wing of claim 2, wherein the composite corrugated plate is a unidirectional tape laminated corrugated plate made of carbon fiber, glass fiber, Kevlar fiber and boron fiber, and a braided corrugated plate made of carbon fiber, glass fiber, Kevlar fiber and boron fiber.
5. The variable camber airfoil based on composite corrugated sheet flexible skin according to claim 2, the elastomer layer being silicone rubber, nitrile rubber, fiber-reinforced silicone rubber, fiber-reinforced nitrile rubber, piezoelectric fiber silicone rubber composite, and piezoelectric fiber nitrile rubber composite.
6. The wing with variable camber based on the flexible skin of the composite corrugated plate, according to claim 3, the hinge structures can be arranged at intervals in the expanding direction of the wing, and the distance between the hinge structures can be reasonably set according to the bending rigidity of the composite corrugated plate perpendicular to the corrugation direction, so that the structural weight of the wing with variable camber based on the flexible skin of the composite corrugated plate is reduced.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010181111.2A CN111439368B (en) | 2020-03-16 | 2020-03-16 | Variable camber wing based on flexible skin of composite material corrugated plate |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010181111.2A CN111439368B (en) | 2020-03-16 | 2020-03-16 | Variable camber wing based on flexible skin of composite material corrugated plate |
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| CN111439368A CN111439368A (en) | 2020-07-24 |
| CN111439368B true CN111439368B (en) | 2021-08-27 |
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| CN112052515B (en) * | 2020-08-04 | 2022-09-20 | 大连理工大学 | Flexible skin wrinkle suppression method for deformable wing |
| CN112046729B (en) * | 2020-08-11 | 2021-12-14 | 南京航空航天大学 | Support connection structure of variable camber trailing edge sectional type wing rib and flexible skin |
| CN112550663B (en) * | 2020-12-08 | 2022-11-11 | 中国空气动力研究与发展中心设备设计及测试技术研究所 | Deformable wing based on intelligent driving device |
| CN112520013B (en) * | 2020-12-16 | 2022-02-25 | 中国空气动力研究与发展中心设备设计及测试技术研究所 | Deformable wing with variable bending degree based on connecting rod driving |
| CN113158337B (en) * | 2021-04-12 | 2022-06-14 | 北京航空航天大学 | Variable camber flexible trailing edge-based wing and gust response slowing method thereof |
| CN113720572B (en) * | 2021-06-22 | 2024-02-09 | 北京临近空间飞行器系统工程研究所 | Flexible skin multidimensional deformation test tool |
| KR20230021842A (en) * | 2021-08-06 | 2023-02-14 | 이창만 | Aircraft wing |
| KR102585822B1 (en) * | 2022-08-30 | 2023-10-05 | 이창만 | Supplementary thrust generating apparatus |
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|---|---|---|---|---|
| JPH1199993A (en) * | 1997-09-29 | 1999-04-13 | Fuji Heavy Ind Ltd | Composite material wing construction and manufacture thereof |
| CN102060101A (en) * | 2010-12-21 | 2011-05-18 | 南京航空航天大学 | Skin for morphing wings |
| CN107444617A (en) * | 2017-07-13 | 2017-12-08 | 北京航空航天大学 | A kind of variable adaptive wing structure of camber |
| CN110077572A (en) * | 2018-01-25 | 2019-08-02 | 波音公司 | Rib, the wing with rib and the method for manufacturing it |
| CN110510103A (en) * | 2019-08-19 | 2019-11-29 | 北京航空航天大学 | A kind of aircraft flexible composite covering and preparation method thereof |
| CN110654530A (en) * | 2019-11-01 | 2020-01-07 | 北京航空航天大学 | Variable camber wing structure with deformation feedback |
-
2020
- 2020-03-16 CN CN202010181111.2A patent/CN111439368B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH1199993A (en) * | 1997-09-29 | 1999-04-13 | Fuji Heavy Ind Ltd | Composite material wing construction and manufacture thereof |
| CN102060101A (en) * | 2010-12-21 | 2011-05-18 | 南京航空航天大学 | Skin for morphing wings |
| CN107444617A (en) * | 2017-07-13 | 2017-12-08 | 北京航空航天大学 | A kind of variable adaptive wing structure of camber |
| CN110077572A (en) * | 2018-01-25 | 2019-08-02 | 波音公司 | Rib, the wing with rib and the method for manufacturing it |
| CN110510103A (en) * | 2019-08-19 | 2019-11-29 | 北京航空航天大学 | A kind of aircraft flexible composite covering and preparation method thereof |
| CN110654530A (en) * | 2019-11-01 | 2020-01-07 | 北京航空航天大学 | Variable camber wing structure with deformation feedback |
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