CN206544592U - A kind of unmanned plane wing is integrally combined girder construction - Google Patents
A kind of unmanned plane wing is integrally combined girder construction Download PDFInfo
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- CN206544592U CN206544592U CN201621348785.2U CN201621348785U CN206544592U CN 206544592 U CN206544592 U CN 206544592U CN 201621348785 U CN201621348785 U CN 201621348785U CN 206544592 U CN206544592 U CN 206544592U
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- edge strip
- web
- base material
- enhancement layer
- layer
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Abstract
Girder construction is integrally combined the utility model discloses a kind of unmanned plane wing.Including by along the edge strip base material of beam bearing of trend, web base material, square substrates and the internal packed layer beam entity structure constituted and the edge strip enhancement layer and web enhancement layer that are coated on outside beam entity structure, two blocks of parallel web base materials are respectively supported at 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 mutually build the square substrates that internal packed layer and internally positioned packed layer two ends are set in the intermediate cavity to be formed, and are consequently formed beam entity structure；And edge strip enhancement layer is covered with the outer surface of edge strip base material, web enhancement layer is coated in the outer surface of edge strip enhancement layer and entity structure, web base material lateral surface is provided with the positioning hole for being connected with rib.The utility model is simple in construction, rationally, low manufacture cost, disclosure satisfy that bending resistance of the high aspect ratio unmanned plane wing to beam, antitorque requirement.
Description
Technical field
The utility model belongs to aeronautical engineering technical field of structures, more particularly to a kind of integral composite beam knot of unmanned plane wing
Structure.
Background technology
The unmanned plane of long endurance 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.Spar as wing main stress
Part, the intensity to wing serves vital effect.The spar manufacture method of the wing of current high aspect ratio is generally model：
The edge strip up and down and web of spar are generally full carbon fiber or glass-reinforced plastic material is molded in a mold.The spar that this method is obtained, by force
Degree is high, and the intensity distribution of spar everywhere, can be by changing the quantity of fiber laying, and direction is realized.But, because making
Process needs to match the mould of spar shapes, and corollary equipment, and cost remains high.So needing a kind of easy to make, structure
Rationally, the new spar easily promoted.
Utility model content
The purpose of this utility model there is provided a kind of unmanned plane wing integrally compound girder construction, realize low cost, system
Make the new spar of convenient, rational in infrastructure and easy popularization, its performance meets requirement of the high aspect ratio wing to beam strength.
The technical solution adopted in the utility model is：
Structure is included by constituting along the edge strip base material of beam bearing of trend, web base material, square substrates and internal packed layer
Beam entity structure and the edge strip enhancement layer and web enhancement layer being coated on outside beam entity structure, two blocks of parallel web base materials point
Both sides between two blocks of parallel edge strip base materials are not supported on, and two blocks of edge strip base materials and two blocks of web base materials mutually build the centre to be formed
The square substrates at internal packed layer and internally positioned packed layer two ends are set in chamber, beam entity structure is consequently formed；And in edge strip
The outer surface of base material is covered with edge strip enhancement layer, and web enhancement layer, web are coated in the outer surface of edge strip enhancement layer and entity structure
Base material lateral surface is provided with the positioning hole for being connected with rib.
The effect of base material is resistance to compression of shaping and bear.
Described edge strip base material, square substrates, web base material and internal packed layer uses wood materials or resistance to compression foam, edge
Bar enhancement layer and web enhancement layer use fibre reinforced composites.
Fibre reinforced composites are specifically to be 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.
Sectional dimension of the described edge strip enhancement layer and web enhancement layer along beam bearing of trend is extended to gradual change, 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 is using timber, measuring body foam (PMI, XPS) or cellular sandwich layer.
Described web enhancement layer is to be wrapped on the outside of beam entity structure to be formed with the shape of grid by reinforcing fibre.
In order to obtain optimal stiffening effect, on the outside of edge strip base material, fixed edge strip enhancement layer, it uses 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.
Fibre reinforced composites specifically can use fiberglass or carbon fibre reinforced composite (cFRP).
Described web base material, using the timber of anisotropic, its grain direction is perpendicular to spanwise, it is therefore intended that dimension
Hold spar shapes, prevent above and below edge strip because being deformed by pultrusion, structural instability.
Described web enhancement layer, by the way of fibre reinforced composites are wound, is coated on the outside of integral beam, 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, in addition, tilting fabric reinforcement, be conducive to improving the shear behavior of web, and overall anti-of beam
Torsion ability, further improves the mechanical property of integral beam.
The beneficial effects of the utility model are：
One of the present utility model is combined girder construction and can be widely applied for long endurance unmanned aircraft, and solar energy unmanned plane etc. is to the wing
Beam strength requires high unmanned plane.
The utility model is simple in construction, rationally, and materials are easy, and manufacturing conditions are without too high requirement, and manufacturing cost is low, just
In popularization.
The utility model reasonable in design, beam reinforcement material is arranged in beam upper and lower surface, and is cut along spanwise stress
Face gradual change, web enhancement layer is tilting, improves the torsional property of web shear behavior and beam, and overall mechanical properties are excellent, meets big
Requirement of the aspect ratio unmanned plane wing to beam strength.
Positioning hole is left on the utility model one web, is easy to being accurately positioned for framework rib, reduction next step
Difficulty is assembled, the precision of assembling is improved, and then improve reliability of structure.
Brief description of the drawings
Fig. 1 is structural representation of the present utility model, 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 the utility model web base material.
Fig. 3 is the utility model cross-sectional view.
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,
Positioning hole, 7, square substrates.
Embodiment
Below in conjunction with drawings and examples, embodiment of the present utility model is described.
As shown in figure 1, integrally compound girder construction is included by the edge along beam bearing of trend (i.e. spanwise) the utility model
Beam entity structure and be coated on beam entity structure that bar base material 1, web base material 2, square substrates 7 and internal packed layer 5 are constituted
Outer edge strip enhancement layer 3 and web enhancement layer 4, two blocks of parallel web base materials 2 are respectively supported at two blocks of parallel edge strip base materials 1
Between both sides, two blocks of edge strip base materials 1 and two blocks of web base materials 2, which are mutually built, sets internal packed layer 5 and position in the intermediate cavity to be formed
Square substrates 7 in the internal two ends of packed layer 5, are consequently formed beam entity structure；And it is covered with edge strip in the outer surface of edge strip base material 1
Enhancement 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 is provided with use
In the positioning hole 6 being connected with rib.
Embodiment of the present utility model and its implementation preparation process are as follows：
In specific implementation, inside filling is placed on the inside of integral beam, for structure resistance to compression, anti-structural instability, this implementation
In example, internal packing material is used as using PMI foams.
Internal packed layer, need to be Nian Jie with the box-structure of outside edge strip base material and web substrate combination close, this reality
Apply in 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 normal temperature
The epoxy resin of solidification.
Web enhancement layer is, it is necessary to along spanwise gradually section gradual change, in the present embodiment, roll over wide carbon fiber wire using 12K and make
For reinforcing fibre, by arranging different number of filament in diverse location, to reach the effect of section gradual change, the present embodiment
In, a length of 2.7m of spar, from the root of spar to taper, is spaced 300mm, is respectively arranged 14,13,12,11,10
Root, 8,6,4,1, more specifically arrangement is, first arranges the 12K filaments one of 2.7m length, then from root
The filament 3 of arrangement 2.4m length is played, the 12K filaments 2 of 2.1M length are then arranged from root, by that analogy.Until beam
The filament 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 filament quantity of upper edge strip actual arrangement, arrange quantity for lower edge strip 1.5 times.
Edge strip base material and edge strip enhancement layer, are integrally formed after Combined Processing, in the present embodiment, the edge after Combined Processing
Bar, it is be bonded with square substrates 7, form T-shaped edge strip, such structure, beneficial to the cemented in place with web.
The utility model solves existing integral composite wing spar manufacturing cost height, and common one spar performance is not good
Deficiency, with more good operability.Manufacturing cycle is short, and the cost of material is low, makes precision high.With significant technology effect
Really.
By specific implementation, the utility model is in manufacturing process, it is not necessary to the mould specially matched with spar shapes,
Only need to the vacuum bag of a strip, and this bag of use common plastic casing on the market, therefore make simple, cost
It is low, it 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 humidification of edge strip enhancement layer is further played, with the reasonability in structure.
And on the outside of spar cross winding web enhancement layer, there is constraint effect to edge strip enhancement layer and edge strip base material,
Effectively prevent edge strip enhancement layer from mutually being peeled off with edge strip base material in the case of stress, and then cause malformation, unstability.Oblique pull
Web enhancement layer, Impact direction diagonally, is served in 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 with beam in gluing mode, is further increased it
Mechanical property.
Contrasted and put into practice by embodiment, find two similar appearance and sizes, the close spar of construction weight, contrast beam is used
The wooden edge strip of Varying-thickness (no edge strip enhancement layer, no web enhancement layer), in basic load 3KG experiment, contrast beam is tied
Structure is deformed, and this integral beam form is good, and simulation result show, and its safety coefficient now is 2.5, can meet practical flight
During to the requirement of the overload of beam.
As can be seen here, the utility model reasonable in design, improves the torsional property of web shear behavior and beam, mechanical property
Can be excellent, meet requirement of the high aspect ratio unmanned plane wing to beam strength.
Claims (6)
1. a kind of unmanned plane wing is integrally 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 set
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 positioning hole (6) for being connected with rib.
2. a kind of unmanned plane wing according to claim 1 is integrally 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) use wood materials or resistance to compression foam, edge strip enhancement layer
And web enhancement layer (4) uses fibre reinforced composites (3).
3. a kind of unmanned plane wing according to claim 1 is integrally combined girder construction, it is characterised in that：The edge strip is strengthened
The edge strip base material (1) and web base material (2) of layer (3) and web enhancement layer (4) with beam entity structure outer surface pass through adhesive
Glue together.
4. a kind of unmanned plane wing according to claim 1 is integrally combined girder construction, it is characterised in that：Described edge strip adds
The strong sectional dimension of layer (3) and web enhancement layer (4) along beam bearing of trend is extended to gradual change, and size is from root to taper by becoming greatly
It is small.
5. a kind of unmanned plane wing according to claim 1 is integrally combined girder construction, it is characterised in that：Described inside is filled out
Layer (5) is filled using timber, resistance to compression foam or cellular sandwich layer.
6. a kind of unmanned plane wing according to claim 1 is integrally combined girder construction, it is characterised in that：Described web adds
Strong layer (4) is wound around on the outside of beam entity structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621348785.2U CN206544592U (en) | 2016-12-09 | 2016-12-09 | A kind of unmanned plane wing is integrally combined girder construction |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201621348785.2U CN206544592U (en) | 2016-12-09 | 2016-12-09 | A kind of unmanned plane wing is integrally combined girder construction |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206544592U true CN206544592U (en) | 2017-10-10 |
Family
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201621348785.2U Withdrawn - After Issue CN206544592U (en) | 2016-12-09 | 2016-12-09 | A kind of unmanned plane wing is integrally combined girder construction |
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| CN (1) | CN206544592U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106585955A (en) * | 2016-12-09 | 2017-04-26 | 中国计量大学 | Composite beam structure of unmanned aerial vehicle wing and manufacturing method thereof |
-
2016
- 2016-12-09 CN CN201621348785.2U patent/CN206544592U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106585955A (en) * | 2016-12-09 | 2017-04-26 | 中国计量大学 | Composite beam structure of unmanned aerial vehicle wing and manufacturing method thereof |
| CN106585955B (en) * | 2016-12-09 | 2023-06-06 | 中国计量大学 | Unmanned aerial vehicle wing integrated composite beam structure and manufacturing method thereof |
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Granted publication date: 20171010 Effective date of abandoning: 20230606 |
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| AV01 | Patent right actively abandoned |
Granted publication date: 20171010 Effective date of abandoning: 20230606 |
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| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |