CN115214873A - Laminated hybrid composite wing structure - Google Patents
Laminated hybrid composite wing structure Download PDFInfo
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- CN115214873A CN115214873A CN202210867968.9A CN202210867968A CN115214873A CN 115214873 A CN115214873 A CN 115214873A CN 202210867968 A CN202210867968 A CN 202210867968A CN 115214873 A CN115214873 A CN 115214873A
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- layer
- wing
- skin
- skin layer
- composite material
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- 239000002131 composite material Substances 0.000 title claims abstract description 89
- 239000000463 material Substances 0.000 claims description 70
- 239000000835 fiber Substances 0.000 claims description 30
- 239000004917 carbon fiber Substances 0.000 claims description 21
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 18
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 18
- 239000003822 epoxy resin Substances 0.000 claims description 6
- 229920000647 polyepoxide Polymers 0.000 claims description 6
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 3
- 229910052799 carbon Inorganic materials 0.000 claims description 3
- 239000004643 cyanate ester Substances 0.000 claims description 3
- 239000003365 glass fiber Substances 0.000 claims description 3
- 229920005989 resin Polymers 0.000 claims description 3
- 239000011347 resin Substances 0.000 claims description 3
- 239000003733 fiber-reinforced composite Substances 0.000 description 3
- 238000009826 distribution Methods 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
- B64C3/182—Stringers, longerons
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
- B64C3/185—Spars
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/18—Spars; Ribs; Stringers
- B64C3/187—Ribs
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/20—Integral or sandwich constructions
-
- 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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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Laminated Bodies (AREA)
Abstract
The invention discloses a laminated hybrid composite wing structure. The wing ribs, the trusses and the wing beams are positioned in the wing skin shell, the wing ribs are uniformly arranged on the wing beams at intervals along the length direction of the wing beams, the wing ribs are connected through the trusses, and the outer peripheries of the wing ribs are tightly attached to the inner side surface of the wing skin shell; the wing structure is mounted on the fuselage of the aircraft by one end of a spar as a wing of the aircraft. The wing structure of the invention introduces the hybrid composite material into the optimized design of the wing, can meet the comprehensive requirements of the wing structure in various aspects such as cost, weight, performance and the like, can improve the strength and vibration characteristic of the wing structure under the condition of not improving the cost, and realizes the requirement of light weight, thereby improving the flight efficiency of the airplane.
Description
Technical Field
The invention relates to a wing structure, in particular to a laminated hybrid composite wing structure.
Background
The wing structure is a main bearing part for directly bearing the aerodynamic load of the airplane, and the weight and the performance of the wing structure influence the flying efficiency of the airplane. Therefore, the light weight, high strength and high efficiency optimization design is the development direction of the wing structure. The weight of the wing structure is reduced, and the strength and the vibration characteristic of the wing structure are improved, so that the direct and effective means for improving the flight efficiency of the airplane is provided. Due to the complexity of the actual working conditions of the wing structure, the metal material and the single composite material are difficult to meet the multi-target requirements of the wing skin under the complex working conditions, the weight and the performance of the wing structure cannot be comprehensively considered at the same time, and meanwhile, the aerodynamic load on each part of the wing structure is uneven, so that if the same type is adopted for each part, the redundancy or the insufficiency of the weight or the structural performance of the structure can be caused, and the ideal design requirements cannot be realized.
Disclosure of Invention
In order to solve the problems of the background art, the present invention provides a laminated hybrid composite wing structure.
The technical scheme adopted by the invention is as follows:
the laminated hybrid composite material wing structure comprises a plurality of wing ribs, trusses, wing spars and a wing skin shell, wherein the wing ribs, the trusses and the wing spars are positioned in the wing skin shell; the wing structure passes through the one end of spar and installs the flank as the aircraft on the aircraft fuselage, and the aircraft specifically can be middle-size and small-size fixed wing section unmanned aerial vehicle.
The planes of the wing ribs are parallel to each other, the wing beam penetrates through the wing ribs and is perpendicular to the plane of each wing rib, and the wing beam is close to the front edge of the wing structure.
The truss includes a plurality of stringers, each disposed along the length of the spar and connected in series to each of the ribs.
Wing skin shell connect gradually by first skin layer, second skin layer, third skin layer, fourth skin layer, fifth skin layer and sixth skin layer and enclose into, first skin layer, second skin layer, third skin layer, fourth skin layer, fifth skin layer and sixth skin layer are long sheet-like structure, the length direction of first skin layer, second skin layer, third skin layer, fourth skin layer, fifth skin layer and sixth skin layer all is on a parallel with the length direction of wing spar and length all equals the distance between first rib to the last rib.
The first skin layer, the second skin layer and the third skin layer are positioned above each wing rib, and the fourth skin layer, the fifth skin layer and the sixth skin layer are positioned below each wing rib; the first skin layer and the sixth skin layer are proximate to a leading edge of the airfoil structure and the third skin layer and the fourth skin layer are proximate to a trailing edge of the airfoil structure.
First skin layer, the second skin layer, the third skin layer, the fourth skin layer, fifth skin layer and sixth skin layer are one deck skin layer that eight layers of combined material layer coincide formed, eight layers of combined material layer are first layer combined material layer from the outside of wing skin shell to the medial surface in proper order, second layer combined material layer, third layer combined material layer, fourth layer combined material layer, fifth layer combined material layer, sixth layer combined material layer, seventh layer combined material layer and eighth layer combined material layer, wherein the fibre direction of the material of first layer combined material layer and eighth layer combined material layer is the same, the fibre direction of the material of second layer combined material layer and seventh layer combined material layer is the same, the fibre direction of the material of third layer combined material layer and sixth layer combined material layer is the same, the fibre direction of the material of fourth layer combined material layer and fifth layer combined material layer is the same, the fibre direction of the material of first to fourth layer combined material layer is all inequality.
When the fiber direction of the materials of the first composite material layer and the eighth composite material layer is 0 degree, the fiber direction of the materials of the second composite material layer and the seventh composite material layer is 45 degrees, the fiber direction of the materials of the third composite material layer and the sixth composite material layer is 90 degrees, and the fiber direction of the materials of the fourth composite material layer and the fifth composite material layer is-90 degrees.
The first skin layer and the fifth skin layer are made of carbon fiber/cyanate ester resin HS300/ET223; the second skin layer and the sixth skin layer are both made of carbon fiber composite material T800H/924C; the third skin layer is made of carbon fiber epoxy resin material HT7/5438; the fourth skin layer adopts carbon/glass fiber material BT250E-6.
The wing rib is made of high-strength carbon fiber materials IM6/3501-6 or carbon fiber epoxy resin materials HT3/5405.
The spar adopts carbon fiber prepreg unidirectional tape material HTS134/977-2.
The beneficial effects of the invention are:
1. the wing ribs, the wing spars and the trusses in the wing structural framework adopt different types of fiber reinforced composite materials according to the size of aerodynamic load borne by the wing structure, wherein the wing beam part with larger load in the wing structure adopts the fiber reinforced composite material with higher strength, and the other wing ribs and the wing beams with smaller load adopt the fiber reinforced composite material with lower strength, so that the weight of the wing composite structure can be effectively controlled.
2. The wing skin shell is designed and divided into six areas and adopts different materials, and the layout can effectively reduce the weight of the wing skin shell and improve the shock resistance of the wing skin shell.
3. The fiber laying mode of six different areas of the wing skin shell can improve the fundamental frequency of the wing skin shell so as to improve the rigidity of the skin.
In a word, the wing structure of the invention introduces the hybrid composite material into the optimized design of the wing, can meet the comprehensive requirements of the wing structure in various aspects such as weight, performance and the like, can improve the rigidity and strength characteristics of the wing structure, and realizes the requirement of light weight of the structure, thereby improving the flight efficiency and mechanical property of the airplane.
Drawings
FIG. 1 is a schematic view of the internal skeletal structure of the wing structure of the present invention;
FIG. 2 is a schematic view of the layout of the various regions of the wing skin shell and the lay-up of the skin laminate fibers of the present invention;
in the figure: 1. rib, 2, truss, 3, spar, 4, first skin layer, 5, second skin layer, 6, third skin layer, 7, fourth skin layer, 8, fifth skin layer, 9, sixth skin layer.
Detailed Description
The invention is further described in detail below with reference to the drawings and specific embodiments.
As shown in fig. 1, the wing structure of the present invention includes a plurality of ribs 1, a truss 2, a spar 3 and a wing skin shell, each rib 1, truss 2 and spar 3 are located inside the wing skin shell, each rib 1 is uniformly arranged on the spar 3 at intervals along the length direction of the spar 3, the ribs 1 are connected with each other by the truss 2, and the outer periphery of each rib 1 is tightly attached to the inner side surface of the wing skin shell; the wing structure passes through the wing spar 3 one end and installs on the aircraft fuselage as the flank of aircraft, and the aircraft specifically can be middle-size and small-size fixed wing section unmanned aerial vehicle. The planes of the ribs 1 are all parallel to each other, the spars 3 penetrate through the ribs 1 and are perpendicular to the plane of each rib 1, and the spars 3 are close to the front edge of the wing structure. The wing rib 1 adopts high-strength carbon fiber material IM6/3501-6 or carbon fiber epoxy resin material HT3/5405. The spar 3 adopts carbon fiber prepreg unidirectional tape material HTS134/977-2. The number of ribs 1 may in particular be 17. The truss 2 comprises a number of stringers, each stringer running the length of a spar 3 and connecting in turn a respective rib 1. The material layout of the internal framework of the wing structure is designed according to the loading condition of the wing, the loading sizes of all areas of the wing are different, the required strength is different, under the condition of comprehensively considering factors in multiple aspects such as weight, performance and the like, wing spars, wing ribs and stringers of the wing are designed into parts of different materials, the weight of the structure is reduced under the condition of meeting aerodynamic load, and therefore the flight efficiency is improved.
As shown in fig. 2, the wing skin shell is formed by sequentially connecting a first skin layer 4, a second skin layer 5, a third skin layer 6, a fourth skin layer 7, a fifth skin layer 8 and a sixth skin layer 9 to form a circle, the first skin layer 4, the second skin layer 5, the third skin layer 6, the fourth skin layer 7, the fifth skin layer 8 and the sixth skin layer 9 are all of a long sheet structure, the length directions of the first skin layer 4, the second skin layer 5, the third skin layer 6, the fourth skin layer 7, the fifth skin layer 8 and the sixth skin layer 9 are all parallel to the length direction of the wing spar 3, and the length is equal to the distance between the first wing rib 1 and the last wing rib 1.
The first skin layer 4, the second skin layer 5 and the third skin layer 6 are positioned above each rib 1, and the fourth skin layer 7, the fifth skin layer 8 and the sixth skin layer 9 are positioned below each rib 1; the first skin layer 4 and the sixth skin layer 9 are near the leading edge of the wing structure and the third skin layer 6 and the fourth skin layer 7 are near the trailing edge of the wing structure. The wing skin is divided into six areas, and different material distributions are given to each area, so that the design and the manufacture of the skin structure are facilitated on one hand, and the load on the wing skin is approximately in gradient distribution from the wing root to the wing tip from the chord direction to the span direction on the other hand, so that the stress on the surface of the wing skin is uneven, the bearing strength required by the surface of the wing is different, the wing skin is divided into different areas, the area with higher load is made of composite materials with higher strength, and the area with lower load is made of composite materials with lower strength. The weight of the wing skin can be reduced, the strength of the skin structure is improved, and the flying efficiency of the airplane is further improved.
The first skin layer 4, the second skin layer 5, the third skin layer 6, the fourth skin layer 7, the fifth skin layer 8 and the sixth skin layer 9 are one skin layer formed by overlapping eight composite material layers, the eight composite material layers are a first composite material layer from the outer side surface to the inner side surface of the wing skin shell, a second composite material layer, a third composite material layer, a fourth composite material layer, a fifth composite material layer, a sixth composite material layer, a seventh composite material layer and an eighth composite material layer in sequence, wherein the fiber directions of the materials of the first composite material layer and the eighth composite material layer are the same, the fiber directions of the materials of the second composite material layer and the seventh composite material layer are the same, the fiber directions of the materials of the third composite material layer and the sixth composite material layer are the same, the fiber directions of the materials of the fourth composite material layer and the fifth composite material layer are the same, and the fiber directions of the materials of the first composite material layer to the fourth composite material layer are different.
When the fiber direction θ 1 of the materials of the first composite material layer and the eighth composite material layer is 0 °, the fiber direction θ 2 of the materials of the second composite material layer and the seventh composite material layer is 45 °, the fiber direction θ 3 of the materials of the third composite material layer and the sixth composite material layer is 90 °, and the fiber direction θ 4 of the materials of the fourth composite material layer and the fifth composite material layer is-90 °. In order to improve the vibration characteristic of the wing skin structure under the condition of gust flight, the layering sequence of the wing skin is improved to obtain larger frequency characteristic, and the fiber laying angles of the same layer position of each area are the same in the design, so that the manufacturing difficulty is further reduced.
The first skin layer 4 and the fifth skin layer 8 both adopt carbon fiber/cyanate ester resin HS300/ET223; the second skin layer 5 and the sixth skin layer 9 are both made of carbon fiber composite material T800H/924C; the third skin layer 6 adopts a carbon fiber epoxy resin material HT7/5438; the fourth skin layer 7 is made of carbon/glass fiber material BT250E-6.
The invention relates to a laminated hybrid composite material wing structure, which is characterized in that the material layout and the laminated stacking sequence of the wing structure are adopted, the material layout of an internal framework and an external skin of the wing is designed according to the loading condition of the wing and by comprehensively considering factors in various aspects such as weight, performance and the like, the rigidity and the strength characteristic of the wing structure can be finally improved, the light weight requirement of the structure is realized, and the flight efficiency and the mechanical property of an airplane are improved.
Claims (10)
1. A laminated hybrid composite wing structure characterized by: the wing comprises a plurality of wing ribs (1), trusses (2), wing spars (3) and a wing skin shell, wherein the wing ribs (1), the trusses (2) and the wing spars (3) are positioned in the wing skin shell, the wing ribs (1) are uniformly arranged on the wing spars (3) at intervals along the length direction of the wing spars (3), the wing ribs (1) are connected through the trusses (2), and the outer peripheries of the wing ribs (1) are tightly attached to the inner side face of the wing skin shell; the wing structure is mounted on the fuselage of the aircraft through one end of a spar (3) as a wing of the aircraft.
2. A laminated hybrid composite wing structure according to claim 1, wherein: the planes of the wing ribs (1) are parallel to each other, the wing beams (3) penetrate through the wing ribs (1) and are perpendicular to the planes of the wing ribs (1), and the wing beams (3) are close to the front edge of the wing structure.
3. A laminated hybrid composite wing structure according to claim 1, wherein: the truss (2) comprises a plurality of stringers, and each stringer is arranged along the length direction of the spar (3) and is sequentially connected with each rib (1).
4. A laminated hybrid composite wing structure according to claim 1, wherein: wing skin shell connect gradually by first skin layer (4), second skin layer (5), third skin layer (6), fourth skin layer (7), fifth skin layer (8) and sixth skin layer (9) and enclose, first skin layer (4), second skin layer (5), third skin layer (6), fourth skin layer (7), fifth skin layer (8) and sixth skin layer (9) are long sheet structure, first skin layer (4), second skin layer (5), third skin layer (6), fourth skin layer (7), the length direction of fifth skin layer (8) and sixth skin layer (9) all is on a parallel with the length direction of wing spar (3) and length all equals the distance between first wing rib (1) to last wing rib (1).
5. A laminated hybrid composite wing structure according to claim 4, wherein: the first skin layer (4), the second skin layer (5) and the third skin layer (6) are positioned above each wing rib (1), and the fourth skin layer (7), the fifth skin layer (8) and the sixth skin layer (9) are positioned below each wing rib (1); the first skin layer (4) and the sixth skin layer (9) are close to the leading edge of the wing structure, and the third skin layer (6) and the fourth skin layer (7) are close to the trailing edge of the wing structure.
6. A laminated hybrid composite wing structure according to claim 4, wherein: first skin layer (4), second skin layer (5), third skin layer (6), fourth skin layer (7), fifth skin layer (8) and sixth skin layer (9) are the one deck skin layer that eight layers of composite material layer coincide formed, eight layers of composite material layer are first layer composite material layer from the outside of wing skin shell to the medial surface in proper order, second layer composite material layer, third layer composite material layer, fourth layer composite material layer, fifth layer composite material layer, sixth layer composite material layer, seventh layer composite material layer and eighth layer composite material layer, wherein the fibre direction of the material of first layer composite material layer and eighth layer composite material layer is the same, the fibre direction of the material of second layer composite material layer and seventh layer composite material layer is the same, the fibre direction of the material of third layer composite material layer and sixth layer composite material layer is the same, the fibre direction of the material of fourth layer composite material layer and fifth layer composite material layer is the same, the fibre direction of the material of first to fourth layer composite material layer is all inequality.
7. A laminated hybrid composite wing structure according to claim 6, wherein: when the fiber direction of the materials of the first composite material layer and the eighth composite material layer is 0 degree, the fiber direction of the materials of the second composite material layer and the seventh composite material layer is 45 degrees, the fiber direction of the materials of the third composite material layer and the sixth composite material layer is 90 degrees, and the fiber direction of the materials of the fourth composite material layer and the fifth composite material layer is-90 degrees.
8. A laminated hybrid composite wing structure according to claim 6, wherein: the first skin layer (4) and the fifth skin layer (8) both adopt carbon fiber/cyanate ester resin HS300/ET223; the second skin layer (5) and the sixth skin layer (9) are both made of carbon fiber composite material T800H/924C; the third skin layer (6) is made of carbon fiber epoxy resin material HT7/5438; the fourth skin layer (7) adopts carbon/glass fiber material BT250E-6.
9. A laminated hybrid composite wing structure according to claim 1, wherein: the wing rib (1) is made of high-strength carbon fiber materials IM6/3501-6 or carbon fiber epoxy resin materials HT3/5405.
10. A laminated hybrid composite wing structure according to claim 1, wherein: the spar (3) adopts carbon fiber prepreg unidirectional tape material HTS134/977-2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210867968.9A CN115214873A (en) | 2022-07-22 | 2022-07-22 | Laminated hybrid composite wing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210867968.9A CN115214873A (en) | 2022-07-22 | 2022-07-22 | Laminated hybrid composite wing structure |
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| Publication Number | Publication Date |
|---|---|
| CN115214873A true CN115214873A (en) | 2022-10-21 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210867968.9A Pending CN115214873A (en) | 2022-07-22 | 2022-07-22 | Laminated hybrid composite wing structure |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104554704A (en) * | 2015-01-27 | 2015-04-29 | 新誉集团有限公司 | Transversely assembled wing structure with high aspect ratio and assembly method of wing structure |
| CN107592848A (en) * | 2015-03-20 | 2018-01-16 | 司盖普股份公司 | Traction air assembly, the air assembly for wind power installation, the wind power installation for power generation and the ship for being provided with traction air assembly |
| CN110422315A (en) * | 2019-09-04 | 2019-11-08 | 吉林大学 | A kind of Coupled Rigid-flexible unmanned plane deformation wing and its increasing material manufacturing method |
| CN113044204A (en) * | 2021-04-29 | 2021-06-29 | 吉林大学 | Carbon fiber wing skeleton structure |
| US20210237846A1 (en) * | 2018-07-16 | 2021-08-05 | Bae Systems Plc | Wing structure |
-
2022
- 2022-07-22 CN CN202210867968.9A patent/CN115214873A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104554704A (en) * | 2015-01-27 | 2015-04-29 | 新誉集团有限公司 | Transversely assembled wing structure with high aspect ratio and assembly method of wing structure |
| CN107592848A (en) * | 2015-03-20 | 2018-01-16 | 司盖普股份公司 | Traction air assembly, the air assembly for wind power installation, the wind power installation for power generation and the ship for being provided with traction air assembly |
| US20210237846A1 (en) * | 2018-07-16 | 2021-08-05 | Bae Systems Plc | Wing structure |
| CN110422315A (en) * | 2019-09-04 | 2019-11-08 | 吉林大学 | A kind of Coupled Rigid-flexible unmanned plane deformation wing and its increasing material manufacturing method |
| CN113044204A (en) * | 2021-04-29 | 2021-06-29 | 吉林大学 | Carbon fiber wing skeleton structure |
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