CN106585955B - Unmanned aerial vehicle wing integrated composite beam structure and manufacturing method thereof - Google Patents
Unmanned aerial vehicle wing integrated composite beam structure and manufacturing method thereof Download PDFInfo
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- CN106585955B CN106585955B CN201611129389.5A CN201611129389A CN106585955B CN 106585955 B CN106585955 B CN 106585955B CN 201611129389 A CN201611129389 A CN 201611129389A CN 106585955 B CN106585955 B CN 106585955B
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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Abstract
The invention discloses an unmanned aerial vehicle wing integrated composite beam structure and a manufacturing method thereof. The beam solid structure comprises a beam solid structure formed by a marginal strip substrate, a web substrate, a square substrate and an inner filling layer along the extending direction of the beam, and a marginal strip reinforcing layer and a web reinforcing layer which are coated outside the beam solid structure, wherein two parallel web substrates are respectively supported at two sides between the two parallel marginal strip substrates, the inner filling layer and the square substrate positioned at two ends of the inner filling layer are arranged in a middle cavity formed by constructing the two marginal strip substrates and the two web substrates, so that the beam solid structure is formed; and the outer surface of the rim strip substrate is covered with a rim strip reinforcing layer, the outer surfaces of the rim strip reinforcing layer and the solid structure are covered with a web reinforcing layer, and the outer side surface of the web substrate is provided with positioning holes for being connected with ribs. The invention has simple and reasonable structure and low manufacturing cost, and can meet the requirements of the wing of the unmanned aerial vehicle with large aspect ratio on bending resistance and torsion resistance of the girder.
Description
Technical Field
The invention belongs to the technical field of aeronautical engineering structures, and particularly relates to an unmanned aerial vehicle wing integrated composite beam structure and a manufacturing method thereof.
Background
The unmanned aerial vehicle pursuing long voyage mostly adopts the design of high aspect ratio to reduce the induced resistance, improve the lift-drag ratio. However, the root of a wing with a large aspect ratio needs to bear huge bending moment and torsion moment. The wing spar is used as a main stress piece of the wing, and plays a vital role in the strength of the wing. At present, the manufacturing method of the wing spar with large aspect ratio is mainly modeling: the upper and lower flanges and webs of the spar are typically formed of all carbon fiber or glass reinforced plastic material in a mold. The spar obtained by the method has high strength, and the strength distribution of the spar can be realized by changing the number and the direction of fiber layering. However, because the manufacturing process requires a mold that matches the shape of the spar, and associated equipment, the cost is high. Therefore, a novel spar which is convenient to manufacture, reasonable in structure and easy to popularize is needed.
Disclosure of Invention
The invention aims to provide an unmanned aerial vehicle wing integrated composite beam structure and a manufacturing method thereof, and the novel wing beam structure has the advantages of low cost, convenience in manufacturing, reasonable structure and easiness in popularization, and the performance of the novel wing beam structure meets the requirement of a wing with a large aspect ratio on beam strength.
The technical scheme adopted by the invention is as follows:
1. unmanned aerial vehicle wing integrative composite beam structure:
the beam solid structure comprises a beam solid structure formed by a marginal strip substrate, a web substrate, a square substrate and an inner filling layer along the extending direction of the beam, and a marginal strip reinforcing layer and a web reinforcing layer which are coated outside the beam solid structure, wherein two parallel web substrates are respectively supported at two sides between the two parallel marginal strip substrates, the inner filling layer and the square substrate positioned at two ends of the inner filling layer are arranged in a middle cavity formed by constructing the two marginal strip substrates and the two web substrates, so that the beam solid structure is formed; and the outer surface of the rim strip substrate is covered with a rim strip reinforcing layer, the outer surfaces of the rim strip reinforcing layer and the solid structure are covered with a web reinforcing layer, and the outer side surface of the web substrate is provided with positioning holes for being connected with ribs.
The base material is used for shaping and bearing compression resistance.
The edge strip base material, the square base material, the web base material and the inner filling layer are made of wood materials or compression-resistant foams, and the edge strip reinforcing layer and the web reinforcing layer are made of fiber reinforced composite materials.
The fiber reinforced composite material is specifically reinforced fiber such as carbon fiber, aramid fiber, glass fiber, basalt fiber, nylon fiber and the like.
In the manufacturing process, the edge strip reinforcing layer and the web reinforcing layer are adhered together with the edge strip base material on the outer surface of the beam solid structure and through an adhesive.
The cross section sizes of the edge strip reinforcing layer and the web reinforcing layer along the extending direction of the beam gradually change along the expanding direction, and the sizes of the edge strip reinforcing layer and the web reinforcing layer are changed from large to small from root to tip.
The adhesive is unsaturated polyester, vinyl resin, epoxy resin, phenolic resin or structural adhesive.
The inner filling layer adopts wood, compression-resistant foam (PMI, XPS) or honeycomb sandwich layer.
The web reinforcing layer is formed by winding reinforcing fibers on the outer side of the beam solid structure in a grid shape.
2. A manufacturing method of an unmanned aerial vehicle wing integrated composite beam structure comprises the following steps:
1) Taking the sheet material as a marginal strip substrate of the upper edge and the lower edge of the beam solid structure, and cutting and polishing;
2) The fiber reinforced composite material is taken and unevenly placed on the outer surface of the rim strip substrate along the span direction according to the stress condition, a proper amount of resin glue is added on the fiber reinforced composite material, the material is positioned and then placed in a strip-shaped vacuum bag, and vacuumizing is carried out until the glue is solidified, so that a rim strip reinforcing layer is manufactured on the surface of the rim strip substrate;
3) Taking out the rim strip substrate with the rim strip reinforcing layer on the surface after solidification, trimming and polishing to a proper size;
4) Adhering the edge strip base material and the square base material to form a T-shaped structure, connecting an inner filling layer between the two T-shaped structures, and adhering the two T-shaped structures and the web base material into a whole;
5) Finally, winding the fiber reinforced composite material outside in a cross grid mode, coating resin glue on the surface, and vacuumizing and curing.
And the vacuumizing treatment is carried out under the conditions that the vacuum pressure is-0.09 Mpa, the glue is heated to the curing temperature of 65 ℃ from normal temperature, and the glue is kept stand for 12 hours.
The resin glue adopts EL2 epoxy resin glue.
In the curing process of the rim strip base material and the fiber reinforced composite material, flatness is ensured by virtue of a die.
In order to obtain the best reinforcing effect, the rim reinforcing layer is fixed on the outer side of the rim base material, is made of fiber reinforced composite material, has anisotropy, has strong tensile property along the fiber direction, and has more excellent comprehensive performance after being compounded with the base material.
The web substrate adopts anisotropic wood, the wood grain direction of the web substrate is perpendicular to the span direction, and the purpose of the web substrate is to maintain the shape of the wing spar and prevent the upper and lower edge strips from being deformed due to extrusion and pulling and the structure from being unstable.
The web reinforcing layer is wrapped on the outer side of the integral beam in a fiber reinforced composite material winding mode, and the fiber direction is inclined. According to the structure, a connecting fulcrum can be formed between the rim strip reinforcing layer and the rim strip base material, peeling of the rim strip reinforcing layer is effectively prevented, and structural deformation is caused.
The beneficial effects of the invention are as follows:
the integrated composite beam structure can be widely applied to unmanned aerial vehicles with long endurance, solar unmanned aerial vehicles and other unmanned aerial vehicles with high requirements on spar strength.
The invention has simple and reasonable structure, easy material acquisition, low manufacturing cost and convenient popularization, and the manufacturing conditions do not have too high requirements.
The invention has reasonable structural design, beam reinforcing materials are arranged on the upper surface and the lower surface of the beam, the stressed section is gradually changed along the span direction, the web reinforcing layers are obliquely arranged, the shear resistance of the web and the torsion resistance of the beam are improved, the overall mechanical property is excellent, and the requirement of the high aspect ratio unmanned aerial vehicle wing on the beam strength is met.
The positioning holes are reserved on the integrated beam web plate, so that the accurate positioning of the framework rib is facilitated, the next assembly difficulty is reduced, the assembly precision is improved, and the reliability of the structure is further improved.
Drawings
FIG. 1 is a schematic view of the structure of the present invention, with a cross section of a die, and reinforcing strips disposed at the upper and lower surfaces.
Fig. 2 is a top view of a web substrate of the present invention.
Fig. 3 is a schematic cross-sectional view of the present invention.
Fig. 4 is a basic flow chart of the manufacture of the present invention.
In the figure: 1. rim base material, 2, web base material, 3, rim enhancement layer, 4, web enhancement layer, 5, inside filling layer, 6, locating hole, 7, square base material.
Detailed Description
The following describes specific embodiments of the present invention with reference to the drawings and examples.
As shown in fig. 1, the integral composite beam structure of the invention comprises a beam solid structure formed by a marginal strip substrate 1, a web substrate 2, a square substrate 7 and an inner filling layer 5 along the extending direction (namely the span direction) of the beam, and a marginal strip reinforcing layer 3 and a web reinforcing layer 4 which are coated outside the beam solid structure, wherein two parallel web substrates 2 are respectively supported at two sides between the two parallel marginal strip substrates 1, and an inner filling layer 5 and square substrates 7 positioned at two ends of the inner filling layer 5 are arranged in a middle cavity formed by constructing the two marginal strip substrates 1 and the two web substrates 2; and cover the marginal strip reinforcement layer 3 on the surface of the marginal strip substrate 1, cover the web reinforcement layer 4 on the surface of marginal strip reinforcement layer 3 and solid structure, the lateral surface of web substrate 2 opens and is used for the locating hole 6 that is connected with the rib.
As shown in fig. 4, the embodiment of the present invention and the implementation and preparation process thereof are as follows:
in specific implementation, the inner filling layer is arranged in the integral beam and used for structure compression resistance and structure instability prevention, and in the embodiment, PMI foam is adopted as an inner filling material.
The inner filling layer is tightly adhered to the box structure formed by combining the outer edge strip substrate and the web substrate, and in the embodiment, the inner filling layer and the web substrate are adhered by using epoxy resin glue cured at normal temperature.
The rim base material and the rim reinforcing layer are bonded together by means of gluing, and in this embodiment, an epoxy resin cured at normal temperature is used.
The web reinforcing layer needs gradual cross section gradual change along the span direction, in this embodiment, 12K rolled wide carbon fiber yarns are used as reinforcing fibers, the effect of gradual cross section change is achieved by arranging different numbers of fiber yarns at different positions, in this embodiment, the length of the spar is 2.7M, 14, 13, 12, 11, 10, 8, 6, 4 and 1 are respectively arranged from the root to the tip of the spar at intervals of 300mm, more specifically, one 12K fiber yarn with the length of 2.7M is firstly arranged, 3 fiber yarns with the length of 2.4M are arranged from the root, and 2 12K fiber yarns with the length of 2.1M are arranged from the root, so that the method is pushed. Until a corresponding number of filaments are arranged around the beam.
In addition, in the embodiment, considering that the upper edge strip of the wing is mainly pressed and the lower edge strip of the wing is mainly pulled, the tensile property of the material is better than that of the compressive property, and therefore, the number of fiber wires actually arranged by the upper edge strip is 1.5 times that of the lower edge strip.
The rim substrate and the rim reinforcing layer are integrated after being subjected to composite treatment, in the embodiment, the rim after the composite treatment is bonded with the square substrate 7 to form a T-shaped rim, and the structure is beneficial to bonding and positioning with a web plate.
1) Taking a sheet material as a marginal strip substrate 1 of the upper edge and the lower edge of a beam solid structure, and cutting and polishing;
2) The fiber reinforced composite material is arranged on the outer surface of the rim strip substrate 1 unevenly along the span direction according to the stress condition, a proper amount of epoxy resin glue is added on the fiber reinforced composite material, in the embodiment, EL2 epoxy resin and AT30 amine curing agent are adopted, the material is positioned and then is placed in a strip-shaped vacuum bag, the material is vacuumized, the material is leaned against the side length of a long ruler, the cured material is ensured to be straight, the material is heated to the curing temperature of 65 ℃ from normal temperature under the condition that the vacuum pressure is minus 0.09Mpa, and is kept stand for 12 hours, so that a rim strip reinforcing layer 3 is manufactured on the surface of the rim strip substrate 1, and the glue is cured;
3) Taking out the rim strip substrate 1 with the rim strip reinforcing layer 3 on the surface after solidification, trimming and polishing to a proper size;
4) Bonding the edge strip base material 1 and the respective square base material 7 to form a T-shaped structure, filling the inner filling layer 5 into the middle, bonding the inner filling layer and the web base material 2 into a whole by using epoxy resin glue (mixing EL2 epoxy resin and AT30 amine curing agent), and forming a beam entity structure and edge strip reinforcing layer integrated structure, as shown in figure 3;
5) Finally, winding the fiber reinforced composite material in a cross grid mode outside, coating epoxy resin glue (mixing EL2 epoxy resin and AT30 amine curing agent) on the surface, vacuumizing and curing, heating to the curing temperature of 65 ℃ from normal temperature under the condition that the vacuum pressure is-0.09 Mpa, and standing for 12 hours.
The invention solves the defects of high manufacturing cost and poor performance of the common integral wing spar of the existing integral composite wing spar, and has better operability. Short manufacturing period, low material cost and high manufacturing precision. Has remarkable technical effects.
Through this embodiment, it is difficult to find that this integrative composite beam structure needs the material simple, and in the manufacturing process, need not special mould with spar shape assorted, only need a rectangular vacuum bag, and this bag adopts the common plastics casing on the market can, so simple manufacture, with low costs, convenient operation.
In addition, the rim strip reinforcing layer is arranged on the upper surface and the lower surface of the box beam structure, so that the limited structural height of the wing can be fully utilized, the reinforcing effect of the rim strip reinforcing layer is further exerted, and the structural rationality is realized.
The web reinforcing layers which are wound in a crossed mode on the outer sides of the wing spars have a binding effect on the rim reinforcing layers and the rim base materials, and the rim reinforcing layers are effectively prevented from being peeled off from the rim base materials under the condition of being stressed, so that structural deformation and instability are caused. The oblique-pulling web reinforcing layer has the stress direction along the oblique direction, plays the role of the oblique web member in the similar truss structure, and has the effects of torsion resistance and shearing resistance. In this embodiment, the web reinforcement layer is firmly bonded to the beam by means of adhesive, further increasing its mechanical properties.
Through comparison practice, two similar overall dimensions, the spar that the structural weight is close, the comparison roof beam adopts the wooden rim of variable thickness (there is not the rim enhancement layer, there is not the web enhancement layer), in static load 3 KG's test, the structural deformation takes place for the comparison roof beam, and this integrative roof beam form is good, and simulation result shows that factor of safety is 2.5 this moment, can satisfy the overload requirement to the roof beam in the actual flight.
Therefore, the invention has the remarkable technical effects that the structural design is reasonable, the beam edge strip reinforcing materials are arranged on the upper surface and the lower surface of the beam, the web reinforcing materials are wound outside the beam in the shape of a grid, the shearing resistance of the web and the torsion resistance of the beam are improved, the mechanical properties are excellent, and the requirement of the high aspect ratio unmanned aerial vehicle wing on the beam strength is met.
Claims (10)
1. An integrative composite beam structure of unmanned aerial vehicle wing, its characterized in that: the beam comprises a beam solid structure formed by a rim strip substrate (1), a web substrate (2), square substrates (7) and an inner filling layer (5) along the extending direction of the beam, and a rim strip reinforcing layer (3) and a web reinforcing layer (4) which are coated outside the beam solid structure, wherein two parallel web substrates (2) are respectively supported at two sides between the two parallel rim strip substrates (1), and an inner filling layer (5) and square substrates (7) positioned at two ends of the inner filling layer (5) are arranged in a middle cavity formed by constructing the two rim strip substrates (1) and the two web substrates (2), so that the beam solid structure is formed; and cover rim strip enhancement layer (3) at the surface of rim strip substrate (1), cover web enhancement layer (4) at the surface cladding web enhancement layer (3) of rim strip enhancement layer (3) and roof beam entity structure, the lateral surface of web substrate (2) opens has locating hole (6) that are used for being connected with the rib.
2. An unmanned aerial vehicle wing integral composite beam structure according to claim 1, wherein: the edge strip base material (1), the square base material (7), the web base material (2) and the inner filling layer (5) are made of wood materials or compressive foams, and the edge strip reinforcing layer (3) and the web reinforcing layer (4) are made of fiber reinforced composite materials.
3. An unmanned aerial vehicle wing integral composite beam structure according to claim 1, wherein: the edge strip reinforcing layer (3) and the web reinforcing layer (4) are adhered with the edge strip base material (1) on the outer surface of the beam solid structure through an adhesive.
4. An unmanned aerial vehicle wing integral composite beam structure according to claim 1, wherein: the cross section sizes of the edge strip reinforcing layer (3) and the web reinforcing layer (4) along the extending direction of the beam gradually change along the expanding direction, and the sizes of the edge strip reinforcing layer and the web reinforcing layer are changed from large to small from root to tip.
5. An unmanned aerial vehicle wing integral composite beam structure according to claim 3, wherein: the adhesive is unsaturated polyester, vinyl resin, epoxy resin, phenolic resin or structural adhesive.
6. An unmanned aerial vehicle wing integral composite beam structure according to claim 1, wherein: the inner filling layer (5) adopts wood, compression-resistant foam or honeycomb sandwich layers.
7. An unmanned aerial vehicle wing integral composite beam structure according to claim 1, wherein: the web reinforcing layer (4) is formed by winding reinforcing fibers on the outer side of the beam solid structure in a grid shape.
8. A method of manufacturing an integrated composite beam structure for use in an unmanned aircraft wing according to any one of claims 1 to 7, comprising the steps of:
taking a sheet material as a marginal strip base material (1) of the upper edge and the lower edge of the beam solid structure, and cutting and polishing;
the fiber reinforced composite material is taken and unevenly arranged on the outer surface of the rim strip base material (1) along the span direction, then resin glue is added on the fiber reinforced composite material, the fiber reinforced composite material is placed in a strip-shaped vacuum bag, and vacuum pumping is carried out until the glue is solidified, so that a rim strip reinforcing layer (3) is manufactured on the surface of the rim strip base material (1);
taking out the rim strip substrate (1) with the rim strip reinforcing layer (3) on the surface after solidification, trimming and polishing;
adhering the edge strip base materials (1) and the square base materials (7) to form T-shaped structures, connecting an inner filling layer (5) between the two T-shaped structures, and adhering the two T-shaped structures and the web base materials (2) into a whole;
finally, winding the fiber reinforced composite material outside in a cross grid mode, coating resin glue on the surface, and vacuumizing and curing.
9. The method for manufacturing the unmanned aerial vehicle wing integrated composite beam structure according to claim 8, wherein: and the vacuumizing treatment is carried out under the conditions that the vacuum pressure is-0.09 Mpa, the glue is heated to the curing temperature of 65 ℃ from normal temperature, and the glue is kept stand for 12 hours.
10. The method for manufacturing the unmanned aerial vehicle wing integrated composite beam structure according to claim 8, wherein: the resin glue adopts EL2 epoxy resin glue.
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| CN110217377A (en) * | 2019-06-14 | 2019-09-10 | 深圳供电局有限公司 | Unmanned plane |
| CN113044202B (en) * | 2021-03-05 | 2023-05-02 | 西北工业大学 | Box-type structural carbon fiber PMI composite beam and preparation method thereof |
| CN113830287A (en) * | 2021-10-11 | 2021-12-24 | 贵州贵飞飞机设计研究院有限公司 | Control surface with separated beam body edge strip and web plate surface and manufacturing method thereof |
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