CN108248824B - Wing surface leading edge structure of micro unmanned aerial vehicle, forming die and preparation method of wing surface leading edge structure - Google Patents
Wing surface leading edge structure of micro unmanned aerial vehicle, forming die and preparation method of wing surface leading edge structure Download PDFInfo
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- CN108248824B CN108248824B CN201711484479.0A CN201711484479A CN108248824B CN 108248824 B CN108248824 B CN 108248824B CN 201711484479 A CN201711484479 A CN 201711484479A CN 108248824 B CN108248824 B CN 108248824B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
- B64C3/14—Aerofoil profile
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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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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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
- B64C3/14—Aerofoil profile
- B64C2003/146—Aerofoil profile comprising leading edges of particular shape
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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
Abstract
The invention provides a wing surface leading edge structure of a micro unmanned aerial vehicle, a forming die and a preparation method of the wing surface leading edge structure, belongs to the technical field of unmanned aerial vehicles, and can avoid the wing surface leading edge from cracking in the using process, control the weight of the structure and reduce the production and processing cost. The upper wall plate and the lower wall plate are connected together through the flexible cloth layer at the front edge, when the wing surface is not assembled into a complete wing surface, the upper wall plate and the lower wall plate can turn over along the axis of the flexible cloth layer at the front edge, and are of an integral connection structure, and the structure can ensure that the front edge of the wing surface is not cracked under the condition of increasing less structural weight, labor intensity and cost; the corresponding forming die is characterized in that the upper wall plate and the lower wall plate of the airfoil are arranged in the same die, the upper wall plate is overturned for 180 degrees along the separation axis of the leading edge of the airfoil and is unfolded, and the leading edge of the upper wall plate is next to the leading edge of the lower wall plate along the separation axis.
Description
Technical Field
The invention relates to the technical field of unmanned aerial vehicles, in particular to a wing surface leading edge structure of a micro unmanned aerial vehicle, a forming die and a preparation method of the wing surface leading edge structure.
Background
The microminiature unmanned aerial vehicle has light weight and small load, and has particularly strict requirements on weight control of the unmanned aerial vehicle body. The general unmanned aerial vehicle airfoil structure all comprises upper wall plate, lower wallboard, roof beam, rib etc. wherein upper and lower wallboard adopts sandwich structure as the owner, and thickness is all generally thinner, is less than 3mm, and leading edge cementing face is little. As shown in fig. 1, the conventional airfoil is divided into two separate wall plates, namely an upper airfoil wall plate 1 and a lower airfoil wall plate 3, in order to increase the bonding effect of the butt-jointed surface of the leading edge and prevent the leading edge from cracking in the use process, the bonding effect is generally improved by locally increasing the thickness of the leading edge, and then a cloth layer 2 is additionally laid to reinforce the outer surface of the leading edge of the airfoil, which is formed by the butt-jointed upper airfoil wall plate 1 and the lower airfoil wall plate 3. The front edge gluing effect is increased by paving the rubberized layers after the upper and lower wall plates are glued in a butt joint mode by adopting the airfoil front edge structure, the rubberized layers need to be polished for secondary rubberizing in the process, if the upper and lower wall plates are sprayed with the rubberized clothes during manufacturing, surface spraying needs to be carried out additionally after the rubberizing, the attractiveness and smoothness of the overall appearance are damaged, the workload is increased, the front edges of the upper and lower wall plates of the airfoil are locally thickened, and the structure weight and the production and processing workload are also increased.
Disclosure of Invention
The invention provides a wing surface leading edge structure of a micro unmanned aerial vehicle, a forming die and a preparation method of the wing surface leading edge structure, which can avoid the wing surface leading edge from cracking in the using process, and can reduce the production and processing cost while controlling the weight of the wing surface leading edge structure.
In order to achieve the purpose, the invention adopts the following technical scheme:
a wing surface leading edge structure of a micro unmanned aerial vehicle comprises a wing surface upper wall plate 1, a wing surface lower wall plate 3 and a flexible cloth layer 4; the front edge of the airfoil upper wall plate 1 is close to the front edge of the airfoil lower wall plate 3, the airfoil upper wall plate 1 and the airfoil lower wall plate 3 are of an integral connecting structure, the airfoil upper wall plate 1 and the airfoil lower wall plate 3 are connected together through the flexible cloth layer 4, when the airfoil upper wall plate and the airfoil lower wall plate are not assembled into a complete airfoil, the airfoil upper wall plate 1 and the airfoil lower wall plate 3 can be overturned along the middle axis, the flexible cloth layer 4 is integrally manufactured with the airfoil upper wall plate 1 and the airfoil lower wall plate 3, as shown in figure 3, the cloth layer cannot break during overturning due to the adoption of the flexible cloth layer 4, and therefore the situation that the front edge does not break is guaranteed.
In the structure, the flexible cloth layer 4 is positioned on the inner side or the outer side of the outer skin of the airfoil upper wall plate 1 and the airfoil lower wall plate 3; the flexible cloth layer 4 is aramid fiber cloth, nylon fiber cloth, polyester fiber cloth or polyethylene fiber cloth.
A forming die for a wing surface leading edge structure of a micro unmanned aerial vehicle is shown in figure 4 and comprises a wing surface upper wall plate molded surface 5 and a wing surface lower wall plate molded surface 6, wherein the upper wall plate molded surface is turned over for 180 degrees along a wing surface leading edge separation axis and is close to the lower wall plate molded surface along the separation axis, and the cross section of the forming die is shown in figure 5; the mold is of a solid structure or a structure with a lightening groove on the back, wherein the structure with the lightening groove on the back is shown in figure 6; the die is made of aluminum alloy or steel.
A method for preparing a wing surface leading edge structure of a micro unmanned aerial vehicle comprises the following steps:
(1) the flexible cloth layer 4, the airfoil upper wall plate 1 and the airfoil lower wall plate 3 are symmetrically paved on the middle axial line of the mold, and the outer skin of the carbon fiber cloth or the glass fiber cloth is covered on the middle axial line of the mold;
(2) then, respectively laying a layer of PMI (polymethacrylimide) foam, respectively laying a layer of carbon fiber cloth or glass fiber cloth on the PMI foam, and butting but not lapping at the position of a middle axis;
(3) and (5) performing vacuum pumping, curing and post-shaping assembly, jointing and gluing the upper wall plate and the lower wall plate, and curing and shaping to obtain the airfoil leading edge structure.
In the above step, when the flexible cloth layer 4 is located at the outer side of the outer skin, the step (1) is that the flexible cloth layer 4 is firstly symmetrically laid and attached at the position of the middle axis of the mould, and then the outer skin is laid and attached on the flexible cloth layer 4, and the outer skin is butted but not lapped at the position of the middle axis; when the flexible cloth layer 4 is positioned on the inner side of the outer skin, the step (1) is that firstly, the outer skin is paved on a mould, the outer skin is butted but not overlapped at the position of a middle axial line, and then the flexible cloth layer 4 is symmetrically paved at the position of the middle axial line on the outer skin; the thickness of the outer skin is 0.125mm, the thickness of the PMI foam is 2mm, and the thickness of the flexible cloth layer 4 is 0.1 mm.
The invention has the beneficial effects that: the invention provides a wing surface leading edge structure of a micro unmanned aerial vehicle and a forming die thereof.A top wall plate and a bottom wall plate are of an integral connecting structure and are connected together through a flexible cloth layer of the leading edge, so that the leading edge of the wing surface is not broken in the using process, the flexible cloth layer is manufactured by integrally forming the top wall plate and the bottom wall plate instead of being laid after the top wall plate and the bottom wall plate are closed, the polishing workload required by the traditional wing surface leading edge cloth attaching is reduced, and the weight and the corresponding workload of the traditional wing surface leading edge gluing surface thickening are reduced.
Drawings
FIG. 1 is a diagram of a conventional airfoil leading edge configuration;
FIG. 2 is a view of the leading edge of an airfoil according to embodiments 1-5 of the present invention;
FIG. 3 is a block diagram of the airfoil of examples 1-5 of the present invention with the top and bottom wall panels misaligned;
FIG. 4 is a view of the airfoil forming mold of the present invention;
FIG. 5 is a cross-sectional view of an airfoil shaped mold configuration of the present invention;
FIG. 6 is a back relief groove configuration of the airfoil forming mold of the present invention.
Wherein, 1 is airfoil upper panel, 2 is traditional airfoil leading edge shop rubberizing layer, and 3 is airfoil lower panel, and 4 is the flexible cloth layer, and 5 is airfoil upper panel profile, and 6 is airfoil lower panel profile.
Detailed Description
The following further describes the embodiments of the present invention with reference to the drawings and examples.
Example 1
The wing surface leading edge structure consists of a wing surface upper wall plate 1, a wing surface lower wall plate 3 and aramid fiber cloth 4 with the thickness of 0.1mm in the middle, and the wing surface can be turned over along the central axis of the aramid fiber cloth before being assembled and is of an integral structure; wherein, the inner surface and the outer surface of the airfoil upper wall plate 1 and the airfoil lower wall plate 3 are respectively provided with a layer of carbon fiber cloth with the thickness of 0.125mm, and the middle part is PMI foam with the thickness of 2 mm.
The manufacturing related mould is as shown in figure 4, the upper wall plate and the lower wall plate are integrated together, the upper wall plate is overturned for 180 degrees along the separation axis of the leading edge of the airfoil, the leading edge of the profile of the upper wall plate is next to the leading edge of the profile of the lower wall plate along the separation axis, the mould is of a solid structure and made of aluminum alloy, when in use, a layer of aramid fiber cloth with the thickness of 0.1mm is symmetrically paved on the middle axis of the mould, then a layer of carbon fiber cloth with the thickness of 0.125mm is paved on the outer skin of the upper wall plate and the lower wall plate, the carbon fiber cloth is butted and not lapped on the middle axis, then a layer of PMI foam with the thickness of 2mm is paved on each carbon fiber cloth layer, a layer of carbon fiber cloth with the thickness of 0.125mm is paved on each foam, and butted and lapped on the middle axis, the middle axis is vacuumized and cured and then shaped, thus obtaining the product as shown in figure 3, assembling ribs, beams and the like, the leading edge butting faces and other adhesive surfaces are coated, and the upper wall plate is coated with the upper wall plate, And (3) jointing and gluing the lower wall plates, and curing and modifying to obtain the airfoil shown in figure 2.
Example 2
The airfoil leading edge structure consists of an airfoil upper wall plate 1, an airfoil lower wall plate 3 and nylon cloth 4 with the thickness of 0.1mm in the middle, and the airfoil can be turned over along the middle axis of the nylon cloth before being assembled and is of an integral structure; wherein, the inner surface and the outer surface of the airfoil upper wall plate 1 and the airfoil lower wall plate 3 are respectively provided with 1 layer of carbon fiber cloth with the thickness of 0.125mm, and the middle part is PMI foam with the thickness of 2 mm.
The manufacturing related mould is as shown in figure 4, the upper wall plate and the lower wall plate are integrated together, the upper wall plate is overturned for 180 degrees along the separation axis of the front edge of the airfoil and unfolded, the front edge of the upper wall plate is next to the front edge of the lower wall plate along the separation axis, the back of the mould is designed to be a lightening groove structure, the material is steel, when in use, a layer of nylon cloth with the thickness of 0.1mm is symmetrically paved on the middle axis of the mould, then a layer of carbon fiber cloth with the thickness of 0.125mm is paved on the outer skin of the upper wall plate and the lower wall plate, the carbon fiber cloth is butted and not lapped on the middle axis, then a layer of PMI foam with the thickness of 2mm is paved on each carbon fiber cloth layer, a layer of carbon fiber cloth with the thickness of 0.125mm is paved on the foam, and butted and lapped on the middle axis, the carbon fiber cloth is vacuumized and cured and then shaped, thus obtaining the product as shown in figure 3, assembling ribs, beams and the like, the front edge butting faces and other cementing faces are coated with cementing agents, and the upper wall plate is formed, And (3) jointing and gluing the lower wall plates, and curing and modifying to obtain the airfoil shown in figure 2.
Example 3
The wing surface leading edge structure consists of a wing surface upper wall plate 1, a wing surface lower wall plate 3 and aramid fiber cloth 4 with the thickness of 0.1mm in the middle, and the wing surface can be turned over along the central axis of the aramid fiber cloth before being assembled and is of an integral structure; wherein, the inner surface and the outer surface of the airfoil upper wall plate 1 and the airfoil lower wall plate 3 are respectively provided with a layer of 0.125mm thick glass fiber cloth, and the middle part is 2mm thick PMI foam.
The manufacturing related mould is as shown in figure 4, the upper wall plate and the lower wall plate are integrated together, the upper wall plate is overturned for 180 degrees along the separation axis of the leading edge of the airfoil, the leading edge of the profile of the upper wall plate is next to the leading edge of the profile of the lower wall plate along the separation axis, the mould is of a solid structure and made of aluminum alloy, when in use, a layer of aramid fiber cloth with the thickness of 0.1mm is symmetrically paved on the middle axis of the mould, then a layer of glass fiber cloth with the thickness of 0.125mm is paved on the outer skin of the upper wall plate and the lower wall plate, the glass fiber cloth is butted but not lapped on the middle axis, then a layer of PMI foam with the thickness of 2mm is paved on each glass fiber cloth layer, a layer of glass fiber cloth with the thickness of 0.125mm is paved on each foam, the middle axis is butted but lapped, the mould is vacuumized and cured and then is modified, thus obtaining the product as shown in figure 3, ribs, beams and the like are assembled, the leading edge butting faces and other adhesive faces are coated, and (3) jointing and gluing the upper wall plate and the lower wall plate, and curing and shaping to obtain the airfoil shown in figure 2.
Example 4
The wing surface leading edge structure consists of a wing surface upper wall plate 1, a wing surface lower wall plate 3 and aramid fiber cloth 4 with the thickness of 0.1mm in the middle, and the wing surface can be turned over along the central axis of the aramid fiber cloth before being assembled and is of an integral structure; wherein, the inner surface and the outer surface of the airfoil upper wall plate 1 and the airfoil lower wall plate 3 are respectively provided with a layer of 0.125mm thick glass fiber cloth, and the middle part is 2mm thick PMI foam.
The manufacturing related mould is as shown in figure 4, the upper wall plate and the lower wall plate are integrated together, the upper wall plate is turned over 180 degrees along the separation axis of the leading edge of the wing surface and unfolded, the leading edge of the profile of the upper wall plate is next to the leading edge of the profile of the lower wall plate along the separation axis, the mould is of a solid structure and made of aluminum alloy, when in use, a layer of 0.1mm thick polyester fiber cloth is symmetrically paved on the middle axis of the mould, then a layer of 0.125mm thick glass fiber cloth is paved on the outer skin of the upper wall plate and the lower wall plate, the glass fiber cloth is butted but not lapped on the middle axis, then a layer of 2mm thick PMI foam is paved on each glass fiber cloth layer, a layer of 0.125mm thick glass fiber cloth is paved on the foam, the middle axis is butted but lapped, the mould is vacuumized and cured, and then the mould is repaired, thus obtaining the product as shown in figure 3, assembling ribs, beams and the like, the leading edge butting surface and other glue joint surfaces are coated, and (3) jointing and gluing the upper wall plate and the lower wall plate, and curing and shaping to obtain the airfoil shown in figure 2.
Example 5
The wing surface leading edge structure consists of a wing surface upper wall plate 1, a wing surface lower wall plate 3 and aramid fiber cloth 4 with the thickness of 0.1mm in the middle, and the wing surface can be turned over along the central axis of the aramid fiber cloth before being assembled and is of an integral structure; wherein, the inner surface and the outer surface of the airfoil upper wall plate 1 and the airfoil lower wall plate 3 are respectively provided with a layer of 0.125mm thick glass fiber cloth, and the middle part is 2mm thick PMI foam.
The manufacturing related mould is as shown in figure 4, the upper wall plate and the lower wall plate are integrated together, the upper wall plate is turned over 180 degrees along the separation axis of the leading edge of the wing surface and unfolded, the leading edge of the profile of the upper wall plate is next to the leading edge of the profile of the lower wall plate along the separation axis, the mould is of a solid structure and made of aluminum alloy, when in use, a layer of polyethylene fiber cloth with the thickness of 0.1mm is symmetrically paved on the middle axis of the mould, then a layer of glass fiber cloth with the thickness of 0.125mm is paved on the outer skin of the upper wall plate and the lower wall plate, the glass fiber cloth is butted but not lapped on the middle axis, then a layer of PMI foam with the thickness of 2mm is paved on each glass fiber cloth layer, a layer of glass fiber cloth with the thickness of 0.125mm is paved on each foam, the middle axis is butted but lapped, the mould is vacuumized and cured, thus obtaining the product shown in figure 3, assembling ribs, beams and the like, the leading edges are painted with the jointing surfaces and other adhesive surfaces, and (3) jointing and gluing the upper wall plate and the lower wall plate, and curing and shaping to obtain the airfoil shown in figure 2.
Example 6
The wing surface leading edge structure consists of a wing surface upper wall plate 1, a wing surface lower wall plate 3 and aramid fiber cloth 4 with the thickness of 0.1mm in the middle, and the wing surface can be turned over along the central axis of the aramid fiber cloth before being assembled and is of an integral structure; wherein, the inner surface and the outer surface of the airfoil upper wall plate 1 and the airfoil lower wall plate 3 are respectively provided with a layer of 0.125mm thick glass fiber cloth, and the middle part is 2mm thick PMI foam.
The manufacturing related mould is as shown in figure 4, the upper wall plate and the lower wall plate are integrated together, the upper wall plate is overturned for 180 degrees along the separation axis of the leading edge of the wing surface and unfolded, the leading edge of the profile of the upper wall plate is next to the leading edge of the profile of the lower wall plate along the separation axis, the mould is of a solid structure and made of aluminum alloy, when in use, glass fiber cloth with the thickness of 0.125mm is firstly paved on the mould, the glass fiber cloth is butted but not overlapped at the position of the middle axis, then aramid fiber cloth with the thickness of 0.1mm is symmetrically paved at the position of the middle axis of the glass fiber cloth, then a PMI foam with the thickness of 2mm is paved at each layer, then a glass fiber cloth with the thickness of 0.125mm is paved on the foam, the fiberglass cloth is butted but overlapped at the position of the middle axis, vacuum pumping, curing and then shaping assembly is carried out, the upper wall plate and the lower wall plate are butted and shaped, and the leading edge structure of the wing surface is obtained after curing.
The foregoing is only a preferred embodiment of the present invention, and it should be noted that those skilled in the art can make various improvements and modifications without departing from the principle of the present invention, and these improvements and modifications should also be construed as the protection scope of the present invention.
Claims (6)
1. A method for preparing a wing surface leading edge structure of a micro unmanned aerial vehicle is characterized by comprising the following steps:
(1) the flexible cloth layer (4), the airfoil upper wall plate (1) and the airfoil lower wall plate (3) are symmetrically paved on the middle axial line of the mold, and the outer skin of the carbon fiber cloth or the glass fiber cloth is covered on the outer skin of the airfoil upper wall plate and the outer skin of the airfoil lower wall plate;
(2) laying a layer of PMI foam, then laying a layer of carbon fiber cloth or glass fiber cloth on the PMI foam, and butting but not overlapping at the position of the middle axis;
(3) and (5) performing vacuum pumping, curing and post-shaping assembly, jointing and gluing the upper wall plate and the lower wall plate, and curing and shaping to obtain the airfoil leading edge structure.
2. The method for preparing the wing leading edge structure of the micro unmanned aerial vehicle as claimed in claim 1, wherein when the flexible cloth layer (4) is located at the outer side of the outer skin, the step (1) is to lay the flexible cloth layer (4) symmetrically at the middle axis position of the mold, and then lay the outer skin on the flexible cloth layer (4), and the outer skin is butted but not overlapped at the middle axis position.
3. The method for preparing the wing leading edge structure of the micro unmanned aerial vehicle as claimed in claim 1, wherein when the flexible cloth layer (4) is located on the inner side of the outer skin, the step (1) is to lay the outer skin on the mold, the outer skin is butted but not overlapped at the position of the middle axis, and then the flexible cloth layer (4) is laid symmetrically at the position of the middle axis on the outer skin.
4. The method for preparing an airfoil leading edge structure of a microminiature unmanned aerial vehicle as claimed in claim 1, wherein the thickness of the outer skin is 0.125mm, the thickness of the PMI foam is 2mm, and the thickness of the flexible cloth layer (4) is 0.1 mm.
5. The method for preparing an airfoil leading edge structure of a micro unmanned aerial vehicle as claimed in claim 1, wherein the mold in step (1) comprises an upper wall plate profile (5) and a lower wall plate profile (6), the upper wall plate profile (5) is turned 180 ° along the separation axis of the airfoil leading edge and is next to the lower wall plate profile (6) along the separation axis of the airfoil leading edge.
6. The method for preparing the wing leading edge structure of the micro unmanned aerial vehicle according to claim 1, wherein the wing leading edge structure obtained in the step (3) comprises a wing upper wall plate (1), a wing lower wall plate (3) and a flexible cloth layer (4); the front edge of the airfoil upper wall plate (1) is next to the front edge of the airfoil lower wall plate (3), the airfoil upper wall plate (1) and the airfoil lower wall plate (3) are of an integral connecting structure and are connected together through the flexible cloth layer (4), when the airfoil upper wall plate and the airfoil lower wall plate are not assembled into a complete airfoil, the airfoil upper wall plate (1) and the airfoil lower wall plate (3) can turn over along the axis of the front edge flexible cloth layer (4), and the flexible cloth layer (4) is integrally formed with the airfoil upper wall plate (1) and the airfoil lower wall plate (3).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201711484479.0A CN108248824B (en) | 2017-12-29 | 2017-12-29 | Wing surface leading edge structure of micro unmanned aerial vehicle, forming die and preparation method of wing surface leading edge structure |
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| CN201711484479.0A CN108248824B (en) | 2017-12-29 | 2017-12-29 | Wing surface leading edge structure of micro unmanned aerial vehicle, forming die and preparation method of wing surface leading edge structure |
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| CN103253367A (en) * | 2013-04-25 | 2013-08-21 | 南京航空航天大学 | Composite material air propeller and preparation die and preparation method thereof |
| CN204822056U (en) * | 2015-05-25 | 2015-12-02 | 中国航天空气动力技术研究院 | Combined material aileron structure |
| CN205150216U (en) * | 2015-11-24 | 2016-04-13 | 中国航天时代电子公司 | Unmanned aerial vehicle's foam presss from both sides core wing |
| GB201522327D0 (en) * | 2015-12-17 | 2016-02-03 | Airbus Operations Ltd | Wing structure |
| CN106273542B (en) * | 2016-10-13 | 2018-07-06 | 西安爱生技术集团公司 | Composite material is straight empennage twin beams box section entirety co-curing forming method |
| CN106393515B (en) * | 2016-10-20 | 2018-11-13 | 西安爱生技术集团公司 | Empennage twin beams box section entirety co-curing molding tooling that composite material is straight |
| CN106828967A (en) * | 2016-12-29 | 2017-06-13 | 航天神舟飞行器有限公司 | Full-height foaming structure multi-rotor unmanned aerial vehicle manufacture method |
| CN106828873B (en) * | 2017-02-15 | 2018-10-30 | 南京航空航天大学 | A kind of up-front forming method of aerofoil profile with piezoelectricity deicing function |
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2017
- 2017-12-29 CN CN201711484479.0A patent/CN108248824B/en active Active
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