CN106585955A - Composite beam structure of unmanned aerial vehicle wing and manufacturing method thereof - Google Patents
Composite beam structure of unmanned aerial vehicle wing and manufacturing method thereof Download PDFInfo
- Publication number
- CN106585955A CN106585955A CN201611129389.5A CN201611129389A CN106585955A CN 106585955 A CN106585955 A CN 106585955A CN 201611129389 A CN201611129389 A CN 201611129389A CN 106585955 A CN106585955 A CN 106585955A
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- edge strip
- web
- base material
- enhancement layer
- unmanned plane
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Classifications
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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
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/25—Fixed-wing aircraft
-
- 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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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Laminated Bodies (AREA)
- Rod-Shaped Construction Members (AREA)
Abstract
The invention discloses a composite beam structure of an unmanned aerial vehicle wing and a manufacturing method thereof. The composite beam structure of the unmanned aerial vehicle wing comprises a beam entity structure composed of edge strip substrates, web substrates, square substrates and an internal packing layer in the beam extending direction, and edge strip reinforcing layers and web reinforcing layers which are wrapped outside the beam entity structure; two parallel web substrates are supported at both sides of two parallel edge strip substrates respectively, the internal packing layer is arranged in an intermediate cavity formed by constructing two edge strip substrates and two web substrates, and the square substrates are located at both ends of the internal packing layer, so that the beam entity structure is formed; the edge strip reinforcing layers are covered on the outside surfaces of the edge strip substrates, the web reinforcing layers are covered on the outside surfaces of the edge strip reinforcing layers and the entity structure, and location holes used to connect to wing ribs are formed in the outside surfaces of the web substrates. The composite beam structure of the unmanned aerial vehicle wing disclosed by the invention has the advantages of simple and reasonable structure and low manufacturing cost, and can meet the anti-bending and anti-torsion requirements of the unmanned aerial vehicle wing with high aspect ratio for beams.
Description
Technical field
The invention belongs to aeronautical engineering technical field of structures, more particularly to a kind of compound girder construction of unmanned plane wing one and
Its manufacture method.
Background technology
Unmanned plane during long boat is pursued, more using the design of high aspect ratio, to reduce induced drag, lift-drag ratio is improved.But
It is, the wing of high aspect ratio that its root needs to bear huge moment of flexure, and torsional moment.Main stress of the spar as wing
Part, to the intensity of wing vital effect is served.At present the spar manufacture method of the wing of high aspect ratio mostly is model：
The edge strip up and down of spar and web are generally full carbon fiber or glass-reinforced plastic material molding in a mold.The spar that this method is obtained, by force
Degree is high, and spar intensity distributions everywhere, can pass through the quantity for changing fiber laying, and direction is realizing.But, because making
Process needs the mould for matching spar shapes, and corollary equipment, cost to remain high.So needing a kind of easy to make, structure
Rationally, the new spar easily promoted.
The content of the invention
It is an object of the invention to provide a kind of compound girder construction of unmanned plane wing one and its manufacture method, realize low
Cost, the new spar of popularization easy to make, rational in infrastructure and easy, its performance meets high aspect ratio wing and beam strength is wanted
Ask.
The technical solution used in the present invention is：
First, the compound girder construction of a kind of unmanned plane wing one：
Including the beam reality being made up of the edge strip base material along beam bearing of trend, web base material, square substrates and internal packed layer
Body structure and the edge strip enhancement layer being coated on outside beam entity structure and web enhancement layer, two blocks of parallel web base materials are propped up respectively
Support both sides between two blocks of parallel edge strip base materials, two blocks of edge strip base materials and two blocks of web base materials are mutually built in the intermediate cavity to be formed
The square substrates at internal packed layer and internally positioned packed layer two ends are set, beam entity structure is consequently formed；And in edge strip base material
Outer surface be covered with edge strip enhancement layer, edge strip enhancement layer and entity structure outer surface coat web enhancement layer, web base material
Lateral surface is provided with the location hole for being connected with rib.
The effect of base material is to shape and bear resistance to compression.
Described edge strip base material, square substrates, web base material and internal packed layer are using wood materials or resistance to compression foam, edge
Bar enhancement layer and web enhancement layer adopt fibre reinforced composites.
Fibre reinforced composites are specifically lived nylon using carbon fiber, aramid fiber, glass fibre, basalt fibre
The enhanced fibers such as fiber.
In manufacturing process, the edge strip enhancement layer and web enhancement layer with the edge strip base material of beam entity structure outer surface and
It is viscous together by adhesive.
Described edge strip enhancement layer and web enhancement layer is extended to gradual change along the sectional dimension of beam bearing of trend, and size is from root
Portion to taper from large to small.
Described adhesive is unsaturated polyester (UP), vinylite, epoxy resin, phenolic resin or structure glue.
Described inside packed layer adopts timber, measuring body foam (PMI, XPS) or cellular sandwich layer.
Described web enhancement layer is to be wrapped in beam entity structure outside with the shape of grid by reinforcing fibre to be formed.
2nd, a kind of unmanned plane wing one composite beam structure making process：
1) sheet material is taken as the edge strip base material of the upper and lower edge of beam entity structure, cut grinding process；
2) fibre reinforced composites are taken and are anisotropically placed in edge strip substrate outer surface according to stressing conditions along spanwise,
Add quantity of resin glue on fibre reinforced composites again, material is carried out to be placed on the vacuum bag of strip after localization process
In, evacuation treats glue curing so that make edge strip enhancement layer in edge strip substrate surface；
3) the surface edge strip base material with edge strip enhancement layer is taken out after solidification, deburring and suitable dimension is polishing to；
4) by the gluing formation T-type structure of edge strip base material and respective square substrates, connect internal between two T-type structures
Packed layer, then with web base material with gluing integral；
5) it is last to wind fibre reinforced composites to intersect grid-like fashion in outside, and in surface-coated resin glue,
Evacuation solidifies.
The evacuation treats that glue curing and evacuation solidification are under conditions of vacuum pressure is -0.09Mpa, from normal
Temperature is heated to 65 DEG C of solidification temperature, stands 12 hours.
Described resin glue adopts EL2 epoxide-resin glues.
In edge strip base material and fibre reinforced composites solidification process, by mould, it is ensured that straight.
In order to obtain optimal stiffening effect, on the outside of edge strip base material, fixed edge strip enhancement layer, it adopts fiber reinforcement to answer
Condensation material, anisotropy has very strong tensile property along machine direction, and after being combined with base material, combination property is more excellent.
Described web base material, using anisotropic timber, its grain direction is perpendicular to spanwise, it is therefore intended that dimension
Spar shapes are held, upper and lower edge strip is prevented because being deformed by pultrusion, structural instability.
Described web enhancement layer, by the way of fibre reinforced composites winding, is coated on one beam outside, fiber
Direction is tilting.This measure, can form connection fulcrum between edge strip enhancement layer and edge strip base material, effectively prevent edge strip enhancement layer from shelling
From, and cause malformation, separately, tilting fabric reinforcement is conducive to improving the shear behavior of web, and overall anti-of beam
Torsion ability, further improves the mechanical property of one beam.
The invention has the beneficial effects as follows：
It is strong to spar that the compound girder construction of the one of the present invention can be widely applied for long endurance unmanned aircraft, solar energy unmanned plane etc.
The unmanned plane that degree has high demands.
Present configuration is simple, rationally, draws materials easily, and manufacturing conditions are easy to push away without too high requirement, low cost of manufacture
Extensively.
Present configuration is reasonable in design, and beam reinforcement material is arranged in beam upper and lower surface, and along spanwise stress section gradually
Become, web enhancement layer is tilting, improve the torsional property of web shear behavior and beam, overall mechanical properties are excellent, meet great Zhan strings
Than requirement of the unmanned plane wing to beam strength.
Location hole is left on one web of the present invention, is easy to being accurately positioned for framework rib, reduce the assembling of next step
Difficulty, improves the precision of assembling, and then improves reliability of structure.
Description of the drawings
Fig. 1 is the structural representation of the present invention, and section is the shape of the mouth as one speaks, strengthens the position that edge strip is arranged in upper and lower surface.
Fig. 2 is the top view of web base material of the present invention.
Fig. 3 is cross-sectional view of the present invention.
Fig. 4 is the basic flow sheet of present invention manufacture.
In figure：1st, edge strip base material, 2, web base material, 3, edge strip enhancement layer, 4, web enhancement layer, 5, internal packed layer, 6,
Location hole, 7, square substrates.
Specific embodiment
Below in conjunction with drawings and Examples, the specific embodiment of the present invention is described.
As shown in figure 1, the compound girder construction of present invention one is included by the edge strip base along beam bearing of trend (i.e. spanwise)
Beam entity structure and be coated on outside beam entity structure that material 1, web base material 2, square substrates 7 and internal packed layer 5 are constituted
Edge strip enhancement layer 3 and web enhancement layer 4, two blocks of parallel web base materials 2 are respectively supported between two blocks of parallel edge strip base materials 1
Both sides, two blocks of edge strip base materials 1 and two blocks of web base materials 2 are mutually built and arrange in the intermediate cavity to be formed internal packed layer 5 and positioned at interior
The square substrates 7 at the two ends of portion's packed layer 5, are consequently formed beam entity structure；And the outer surface in edge strip base material 1 is covered with edge strip reinforcement
Layer 3, in the outer surface cladding web enhancement layer 4 of edge strip enhancement layer 3 and entity structure, the lateral surface of web base material 2 be provided with for
The location hole 6 that rib is connected.
As shown in figure 4, embodiments of the invention and its enforcement preparation process are as follows：
In being embodied as, inside filling is placed on the inside of one beam, for structure resistance to compression, anti-structural instability, this enforcement
In example, using PMI foams as internal packing material.
Internal packed layer, need to be bonding with the box-structure of outside edge strip base material and web substrate combination tight, this reality
In applying example, both bondings are carried out using the epoxide-resin glue of normal temperature cure.
Edge strip base material and edge strip enhancement layer, are bonded together by gluing mode, in the present embodiment, employ room temperature
The epoxy resin of solidification.
Web enhancement layer, needs along spanwise gradually section gradual change, in the present embodiment, rolles over wide carbon fiber wire using 12K and makees
For reinforcing fibre, by arranging different number of cellosilk in diverse location the effect of section gradual change, the present embodiment are reached
In, a length of 2.7m of spar, from the root of spar to taper, is spaced 300mm, is respectively arranged 14,13,12,11, and 10
Root, 8,6,4,1, more specifically arrangement is, first arranges the 12K cellosilks one of 2.7m length, then from root
The cellosilk 3 of arrangement 2.4m length is played, the 12K cellosilks 2 of 2.1M length is then arranged from root, by that analogy.Until beam
The cellosilk of respective number is arranged everywhere.
In addition, in the present embodiment, it is contemplated that edge strip is mainly pressurized on wing, and the main tension of edge strip under wing, material
Tensile property is better than resistance to compression, so, the cellosilk quantity of upper edge strip actual arrangement is 1.5 times of lower edge strip arrangement quantity.
Edge strip base material and edge strip enhancement layer, are integrally formed after Combined Processing, the edge in the present embodiment, after Combined Processing
Bar, it is bonding with square substrates 7, form T-shaped edge strip, such structure, beneficial to the cemented in place with web.
1) sheet material is taken as the edge strip base material 1 of the upper and lower edge of beam entity structure, cut grinding process；
2) fibre reinforced composites are taken and is anisotropically placed in the appearance of edge strip base material 1 according to stressing conditions along spanwise
Face, then add appropriate epoxide-resin glue on fibre reinforced composites, it is solid using EL2 epoxy resin and AT30 amines in embodiment
Agent, carries out being placed on after localization process in the vacuum bag of strip to material, and material is leaned against the long ruler length of side by evacuation,
Ensure that material is straight after solidification, under conditions of vacuum pressure is -0.09Mpa, from room temperature 65 DEG C of solidification temperature is heated to, stand
12 hours so that make edge strip enhancement layer 3 on the surface of edge strip base material 1, wait glue curing；
3) the surface edge strip base material 1 with edge strip enhancement layer 3 is taken out after solidification, deburring and suitable dimension is polishing to；
4) by the gluing formation T-type structure of edge strip base material 1 and respective square substrates 7, internal packed layer 5 is filled to centre
Again one is sticked into epoxide-resin glue (EL2 epoxy resin mixes with AT30 amine curing agents) with web base material 2, then, formed
Beam entity structure and edge strip enhancement layer integrative-structure, as shown in Figure 3；
5) it is last to wind fibre reinforced composites to intersect grid-like fashion in outside, and in surface-coated epoxy resin
Glue (EL2 epoxy resin mixes with AT30 amine curing agents), evacuation solidification, under conditions of vacuum pressure is -0.09Mpa,
65 DEG C of solidification temperature is heated to from room temperature, 12 hours are stood.
The present invention, solves existing one composite wing spar manufacturing cost height, and common one spar performance is not good not
Foot, with more good operability.Manufacturing cycle is short, and the cost of material is low, makes high precision.With significant technique effect.
By the present embodiment, it is seen that, the material required for the compound girder construction of this one is simple, in manufacturing process, no
The mould that needs specially match with spar shapes, it is only necessary to the vacuum bag of a strip, and this bag is using common on the market
Plastic casing, therefore make simple, low cost is easy to operate.
In addition, edge strip enhancement layer is arranged in the upper and lower surface of box girder construction, the structure that wing can be made full use of limited
Highly, the potentiation of edge strip enhancement layer is further played, with the reasonability in structure.
And on the outside of spar cross winding web enhancement layer, edge strip enhancement layer and edge strip base material are acted on constraint,
Effectively prevent edge strip enhancement layer from mutually peeling off with edge strip base material in the case of stress, and then cause malformation, unstability.Oblique pull
Web enhancement layer, Impact direction diagonally, in serving similar truss structure, the effect of diagonal web member, with antitorque and shearing resistance
Effect.In the present embodiment, the web enhancement layer is firmly bonded together in gluing mode with beam, further increases it
Mechanical property.
By contrasting practice, it is found that two similar overall dimensions, the close spar of construction weight, contrast beam is using thickening
Wooden edge strip (without edge strip enhancement layer, without web enhancement layer) is spent, in the test of basic load 3KG, contrast beam recurring structure becomes
Shape, and this one beam form is good, simulation result shows, its safety coefficient now is 2.5, can meet practical flight process
In the overload of beam is required.
As can be seen here, the present invention has its significant technique effect of protrusion, reasonable in design, beam edge strip reinforcement material cloth
Put in beam upper and lower surface, web reinforcement material is wrapped in outside beam with the shape of grid, improve the antitorque of web shear behavior and beam
Performance, excellent in mechanical performance meets requirement of the high aspect ratio unmanned plane wing to beam strength.
Claims (10)
1. a kind of unmanned plane wing one is combined girder construction, it is characterised in that：Including by the edge strip base material along beam bearing of trend
(1) beam entity structure and be coated on beam entity knot that, web base material (2), square substrates (7) and internal packed layer (5) are constituted
Edge strip enhancement layer (3) and web enhancement layer (4) outside structure, two blocks of parallel web base materials (2) be respectively supported at two pieces it is parallel
Both sides between edge strip base material (1), two pieces of edge strip base materials (1) and two pieces of web base materials (2) are mutually built in the intermediate cavity to be formed and are arranged
Internal packed layer (5) and the square substrates (7) at internally positioned packed layer (5) two ends, are consequently formed beam entity structure；And in edge strip
The outer surface of base material (1) is covered with edge strip enhancement layer (3), adds in the outer surface cladding web of edge strip enhancement layer (3) and entity structure
Strong layer (4), web base material (2) lateral surface is provided with the location hole (6) for being connected with rib.
2. a kind of unmanned plane wing one according to claim 1 is combined girder construction, it is characterised in that：Described edge strip base material
(1), square substrates (7), web base material (2) and internal packed layer (5) are using wood materials or resistance to compression foam, edge strip enhancement layer
And web enhancement layer (4) adopts fibre reinforced composites (3).
3. a kind of unmanned plane wing one according to claim 1 is combined girder construction, it is characterised in that：The edge strip enhancement layer
(3) and web enhancement layer (4) with the edge strip base material (1) of beam entity structure outer surface and (2) by adhesive it is viscous together with.
4. a kind of unmanned plane wing one according to claim 1 is combined girder construction, it is characterised in that：Described edge strip enhancement layer
(3) extend to gradual change along the sectional dimension of beam bearing of trend with web enhancement layer (4), size from root to taper from large to small.
5. a kind of unmanned plane wing one according to claim 3 is combined girder construction, it is characterised in that：Described adhesive is not
Saturated polyester, vinylite, epoxy resin, phenolic resin or structure glue.
6. a kind of unmanned plane wing one according to claim 1 is combined girder construction, it is characterised in that：Described inside packed layer
(5) using timber, measuring body foam (PMI, XPS) or cellular sandwich layer.
7. a kind of unmanned plane wing one according to claim 1 is combined girder construction, it is characterised in that：Described web enhancement layer
(4) it is to be wrapped in beam entity structure outside with the shape of grid by reinforcing fibre to be formed.
8. a kind of manufacture method that the arbitrary unmanned plane wing one of claim 1-7 is combined girder construction, its feature are applied to
It is to comprise the following steps：
Sheet material is taken as the edge strip base material (1) of the upper and lower edge of beam entity structure, grinding process is cut；
Take fibre reinforced composites and be anisotropically placed in edge strip base material (1) outer surface along spanwise, then it is multiple in fiber reinforcement
Add resin glue on condensation material, in being placed on the vacuum bag of strip, evacuation treats glue curing so that in edge strip base material (1) table
Make edge strip enhancement layer (3) in face；
Take out the edge strip base material (1) that surface after solidification has had edge strip enhancement layer (3), deburring and polishing；
By edge strip base material (1) and the gluing formation T-type structure of respective square substrates (7), connect internal between two T-type structures
Packed layer (5), then with web base material (2) with gluing integral；
It is last to wind fibre reinforced composites to intersect grid-like fashion in outside, and in surface-coated resin glue, evacuation
Solidification.
9. a kind of unmanned plane wing one composite beam structure making process according to claim 7, it is characterised in that：It is described
Evacuation treats that glue curing and evacuation solidification are under conditions of vacuum pressure is -0.09Mpa, from room temperature solidification to be heated to
65 DEG C of temperature, stands 12 hours.
10. a kind of unmanned plane wing one composite beam structure making process according to claim 7, it is characterised in that：Institute
The resin glue stated adopts EL2 epoxide-resin glues.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611129389.5A CN106585955B (en) | 2016-12-09 | 2016-12-09 | Unmanned aerial vehicle wing integrated composite beam structure and manufacturing method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611129389.5A CN106585955B (en) | 2016-12-09 | 2016-12-09 | Unmanned aerial vehicle wing integrated composite beam structure and manufacturing method thereof |
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| Publication Number | Publication Date |
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| CN106585955A true CN106585955A (en) | 2017-04-26 |
| CN106585955B CN106585955B (en) | 2023-06-06 |
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| CN201611129389.5A Active CN106585955B (en) | 2016-12-09 | 2016-12-09 | Unmanned aerial vehicle wing integrated composite beam structure and manufacturing method thereof |
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Cited By (3)
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|---|---|---|---|---|
| CN110217377A (en) * | 2019-06-14 | 2019-09-10 | 深圳供电局有限公司 | Unmanned plane |
| CN113044202A (en) * | 2021-03-05 | 2021-06-29 | 西北工业大学 | Carbon fiber PMI composite beam with box-type structure and preparation method |
| 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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| 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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| Publication number | Publication date |
|---|---|
| CN106585955B (en) | 2023-06-06 |
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