CN108248824A - A kind of Small and micro-satellite aerofoil leading edge structure, molding die and preparation method thereof - Google Patents
A kind of Small and micro-satellite aerofoil leading edge structure, molding die and preparation method thereof Download PDFInfo
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- CN108248824A CN108248824A CN201711484479.0A CN201711484479A CN108248824A CN 108248824 A CN108248824 A CN 108248824A CN 201711484479 A CN201711484479 A CN 201711484479A CN 108248824 A CN108248824 A CN 108248824A
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- aerofoil
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- lower wall
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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
-
- 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
-
- 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
-
- 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)
- Manufacturing & Machinery (AREA)
- Remote Sensing (AREA)
- Transportation (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Moulding By Coating Moulds (AREA)
- Laminated Bodies (AREA)
Abstract
The present invention provides a kind of Small and micro-satellite aerofoil leading edge structures, molding die and preparation method thereof, belong to unmanned air vehicle technique field, can avoid cracking during the use of aerofoil leading edge, production and processing cost is reduced while control structure weight.Upper and lower siding of the invention is linked together by up-front flexible layer of cloth, when without complete aerofoil is made into, upper and lower siding can be overturn along the axis of leading edge flexibility layer of cloth, for whole binding structure, the structure can ensure that aerofoil leading edge does not crack in the case where increasing less construction weight, labor intensity and cost；Corresponding molding die is the upper and lower siding type face of aerofoil in same mold, and wainscot overturns 180 ° of expansion along aerofoil leading edge separation axis, and wainscot leading edge is located next to lower wall panels leading edge along separation axis.
Description
Technical field
The present invention relates to unmanned air vehicle technique fields, and in particular to a kind of Small and micro-satellite aerofoil leading edge structure, shaping mould
Tool and preparation method thereof.
Background technology
For Small and micro-satellite because itself is light-weight, load is small, body weight control is required particularly stringent.Generally nobody
Airfoil structure is all made of wainscot, lower wall panels, beam, rib etc., wherein upper and lower siding is used based on sandwich, thickness one
As all than relatively thin, less than 3mm, leading edge be glued face it is small.Tradition aerofoil is divided into aerofoil wainscot 1 and aerofoil lower wall panels 3 as shown in Figure 1
Two pieces of separated sidings in order to increase leading edge involutory surface bonding effect, prevent leading edge from process being used to crack, generally use leading edge
The mode that part increases thickness promotes splicing face effect, then in the aerofoil for completing 3 pairing of aerofoil wainscot 1 and aerofoil lower wall panels
Other paving layer of cloth 2 is strengthened during leading edge appearance.The paving cloth after the splicing of upper and lower siding pairing is needed using the aerofoil leading edge structure
Layer increases leading edge bonding effect, this process needs patch face of polishing for secondary patch, if having sprayed glue during upper and lower siding manufacture
Clothing then needs in addition to carry out surface spraying again after patch, destroys beauty and the fairing of overall appearance, increase workload,
And the upper and lower siding leading edge of aerofoil locally thickeies, and also increases construction weight and production and processing workload.
Invention content
The present invention provides a kind of Small and micro-satellite aerofoil leading edge structures, molding die and preparation method thereof, can keep away
Exempt from aerofoil leading edge to crack in use, production and processing cost can be reduced while control aerofoil leading edge structure weight.
In order to achieve the above object, the present invention adopts the following technical scheme that：
A kind of Small and micro-satellite aerofoil leading edge structure, including aerofoil wainscot 1, aerofoil lower wall panels 3, flexible layer of cloth 4；On aerofoil
1 leading edge of siding is located next to 3 leading edge of aerofoil lower wall panels, and aerofoil wainscot 1 and aerofoil lower wall panels 3 are whole binding structure, pass through flexibility
Layer of cloth 4 links together, and during without being made into complete aerofoil, aerofoil wainscot 1 and aerofoil lower wall panels 3 can be turned over along medial axis
Turn, flexible layer of cloth 4 is manufactured with aerofoil wainscot 1 and the integrated molding of aerofoil lower wall panels 3, as shown in figure 3, because using
Flexible layer of cloth 4, so layer of cloth will not be broken during overturning, so as to ensure that leading edge is not broken.
Flexible layer of cloth 4 is located at the inside or outer of 3 exterior skin of aerofoil wainscot 1 and aerofoil lower wall panels in structure described above
Side；Flexible layer of cloth 4 is aryl fiber cloth, nylon fiber cloth, polyester fiber cloth or polyvinyl fibre cloth.
A kind of Small and micro-satellite aerofoil leading edge structure molding die, as shown in figure 4, including 5 He of aerofoil upper wall template face simultaneously
Lower wall template face 6, wherein upper wall template face overturn 180 ° along aerofoil leading edge separation axis and are located next to lower wall panels along separation axis
Type face, mold sections are as shown in Figure 5；The mold is solid construction or the back side is to mitigate groove structure, and wherein the back side is recessed to mitigate
The structure of slot is as shown in Figure 6；Mold material therefor is aluminium alloy or steel.
A kind of Small and micro-satellite aerofoil leading edge structure preparation method, includes the following steps：
(1) in a mold between the symmetrical paving flexibility layer of cloth 4 of axial location and aerofoil wainscot 1,3 exterior skin carbon of aerofoil lower wall panels it is fine
Tie up cloth or glass fabric；
(2) each one layer of PMI of placed again（Polymethacrylimide）Foam, then each one layer of carbon fiber of paving on PMI foams
Cloth or glass fabric are docked at medial axis position but are not overlapped；
(3) repairing type is assembled after vacuumizing curing, and upper and lower siding pairing is glued, and aerofoil leading edge structure is obtained after curing repairing type.
In step described above, when flexible layer of cloth 4 is located on the outside of the exterior skin, the step (1) is first in mold
Medial axis positional symmetry paving flexibility layer of cloth 4, then the paving exterior skin on flexible layer of cloth 4, the exterior skin is in medial axis
It docks but does not overlap at position；When flexible layer of cloth 4 is located on the inside of the exterior skin, the step (1) is first on mold upper berth
Exterior skin is pasted, the exterior skin is docked at medial axis position but do not overlapped, then the medial axis positional symmetry on exterior skin
Paving flexibility layer of cloth 4；The thickness of the exterior skin is 0.125mm, and the thickness of the PMI foams is 2mm, flexible layer of cloth 4
Thickness is 0.1mm.
The present invention has the beneficial effect that：The present invention provides a kind of Small and micro-satellite aerofoil leading edge structure and its shaping moulds
Tool, upper lower wall panels are whole binding structure, are linked together by up-front flexible layer of cloth, ensure that aerofoil leading edge during use
It is not broken, it repaves and sticks after the not upper lower wall panels pairing of the flexibility layer of cloth, but produced with the integrated molding of upper lower wall panels
Come, reduce the workload polished needed for edge patch in face of conventional flap, while reduce edge in face of conventional flap and be glued what face thickened
Weight and corresponding workload.
Description of the drawings
Fig. 1 is edge structure chart in face of conventional flap；
Fig. 2 is 1-5 aerofoil leading edge structure figures of the embodiment of the present invention；
Structure chart when Fig. 3 is the non-pairing of lower wall panels on 1-5 aerofoils of the embodiment of the present invention；
Fig. 4 is aerofoil forming die structure figure of the present invention；
Fig. 5 is aerofoil forming die structure sectional view of the present invention；
Fig. 6 mitigates groove structure figure for the aerofoil molding die back side of the present invention.
Wherein, 1 is aerofoil wainscot, and 2 be edge paving layer of cloth in face of conventional flap, and 3 be aerofoil lower wall panels, and 4 be flexible layer of cloth,
5 be aerofoil upper wall template face, and 6 be aerofoil lower wall template face.
Specific embodiment
With reference to the accompanying drawings and examples, the specific embodiment of the present invention is further elaborated.
Embodiment 1
Aerofoil leading edge structure is made of aerofoil wainscot 1, aerofoil lower wall panels 3 and centre 0.1mm thickness aramid fabric 4, aerofoil dress
It is overall structure with can be overturn before along aramid fabric medial axis；Wherein aerofoil wainscot 1,3 inner surface of aerofoil lower wall panels and
Respectively there is the carbon cloth of one layer of 0.125mm thickness in outer surface, and centre is the PMI foams of 2mm thickness.
The involved mold of manufacture is as shown in figure 4, be to combine the upper and lower siding type face of aerofoil, and wainscot is along the wing
The off-axis line of fate overturns 180 ° of expansion in front, and edge is located next to edge in face of lower wall template, mold along separation axis in face of upper wall template
For solid construction, material is aluminium alloy, during use first in a mold between axial location one layer of 0.1mm thickness of symmetrical paving aramid fiber
Cloth, repaves the carbon cloth for sticking siding and lower wall panels exterior skin 0.125mm thickness, and carbon cloth docks at medial axis position
But do not overlap, then on carbon fibre cloth layer each one layer of 2mm thickness of placed PMI foams, then each one layer of paving on foam
The carbon cloth of 0.125mm thickness is docked but is overlapped at medial axis position, and repairing type is to get to such as Fig. 3 institutes after vacuumizing curing
Show product, assembling rib, beam etc., leading edge involutory surface and other splicing face brushing adhesive, upper and lower siding pairing is glued, curing
Aerofoil as shown in Figure 2 is obtained after repairing type.
Embodiment 2
Aerofoil leading edge structure is made of aerofoil wainscot 1, aerofoil lower wall panels 3 and centre 0.1mm thickness nylon cloth 4, aerofoil dress
It is overall structure with can be overturn before along nylon cloth medial axis；Wherein aerofoil wainscot 1,3 inner surface of aerofoil lower wall panels and
Respectively there is the carbon cloth of 1 layer of 0.125mm thickness in outer surface, and centre is the PMI foams of 2mm thickness.
The involved mold of manufacture is as shown in figure 4, be to combine the upper and lower siding type face of aerofoil, and wainscot is along the wing
The off-axis line of fate overturns 180 ° of expansion in front, and wainscot leading edge is along separation axis next to lower wall panels leading edge, the design of the mold back side
To mitigate groove structure, material is steel, during use first in a mold between axial location one layer of 0.1mm thickness of symmetrical paving nylon
Cloth, repaves the carbon cloth for sticking siding and lower wall panels exterior skin 0.125mm thickness, and carbon cloth docks at medial axis position
But do not overlap, then on carbon fibre cloth layer each one layer of 2mm thickness of placed PMI foams, then each one layer of paving on foam
The carbon cloth of 0.125mm thickness is docked but is overlapped at medial axis position, and repairing type is to get to such as Fig. 3 institutes after vacuumizing curing
Show product, assembling rib, beam etc., leading edge involutory surface and other splicing face brushing adhesive, upper and lower siding pairing is glued, curing
Aerofoil as shown in Figure 2 is obtained after repairing type.
Embodiment 3
Aerofoil leading edge structure is made of aerofoil wainscot 1, aerofoil lower wall panels 3 and centre 0.1mm thickness aramid fabric 4, aerofoil dress
It is overall structure with can be overturn before along aramid fabric medial axis；Wherein aerofoil wainscot 1,3 inner surface of aerofoil lower wall panels and
Respectively there is the glass fabric of one layer of 0.125mm thickness in outer surface, and centre is the PMI foams of 2mm thickness.
The involved mold of manufacture is as shown in figure 4, be to combine the upper and lower siding type face of aerofoil, and wainscot is along the wing
The off-axis line of fate overturns 180 ° of expansion in front, and edge is located next to edge in face of lower wall template, mold along separation axis in face of upper wall template
For solid construction, material is aluminium alloy, during use first in a mold between axial location one layer of 0.1mm thickness of symmetrical paving aramid fiber
Cloth repaves the glass fabric for sticking siding and lower wall panels exterior skin 0.125mm thickness, and glass fabric is at medial axis position
Docking but do not overlap, then on fiberglass cloth each one layer of 2mm thickness of placed PMI foams, then each paving one on foam
The glass fabric of layer 0.125mm thickness, docks but is overlapped at medial axis position, and repairing type is to get to such as after vacuumizing curing
Product shown in Fig. 3, assembling rib, beam etc., leading edge involutory surface and other splicing face brushing adhesive, upper and lower siding pairing is glued,
Aerofoil as shown in Figure 2 is obtained after curing repairing type.
Embodiment 4
Aerofoil leading edge structure is made of aerofoil wainscot 1, aerofoil lower wall panels 3 and centre 0.1mm thickness aramid fabric 4, aerofoil dress
It is overall structure with can be overturn before along aramid fabric medial axis；Wherein aerofoil wainscot 1,3 inner surface of aerofoil lower wall panels and
Respectively there is the glass fabric of one layer of 0.125mm thickness in outer surface, and centre is the PMI foams of 2mm thickness.
The involved mold of manufacture is as shown in figure 4, be to combine the upper and lower siding type face of aerofoil, and wainscot is along the wing
The off-axis line of fate overturns 180 ° of expansion in front, and edge is located next to edge in face of lower wall template, mold along separation axis in face of upper wall template
For solid construction, material is aluminium alloy, during use first in a mold between one layer of 0.1mm thickness of the symmetrical paving of axial location polyester fibre
Wei Bu repaves the glass fabric for sticking siding and lower wall panels exterior skin 0.125mm thickness, and glass fabric is in medial axis position
Place's docking but do not overlap, then on fiberglass cloth each one layer of 2mm thickness of placed PMI foams, then each paving on foam
The glass fabric of one layer of 0.125mm thickness, at medial axis position dock but overlap, vacuumize curing after repairing type to get to
Product as shown in Figure 3, assembling rib, beam etc., leading edge involutory surface and other splicing face brushing adhesive, by upper and lower siding to rubber alloy
It connects, aerofoil as shown in Figure 2 is obtained after curing repairing type.
Embodiment 5
Aerofoil leading edge structure is made of aerofoil wainscot 1, aerofoil lower wall panels 3 and centre 0.1mm thickness aramid fabric 4, aerofoil dress
It is overall structure with can be overturn before along aramid fabric medial axis；Wherein aerofoil wainscot 1,3 inner surface of aerofoil lower wall panels and
Respectively there is the glass fabric of one layer of 0.125mm thickness in outer surface, and centre is the PMI foams of 2mm thickness.
The involved mold of manufacture is as shown in figure 4, be to combine the upper and lower siding type face of aerofoil, and wainscot is along the wing
The off-axis line of fate overturns 180 ° of expansion in front, and edge is located next to edge in face of lower wall template, mold along separation axis in face of upper wall template
For solid construction, material is aluminium alloy, during use first in a mold between axial location one layer of 0.1mm thickness of symmetrical paving polyethylene
Fiber cloth repaves the glass fabric for sticking siding and lower wall panels exterior skin 0.125mm thickness, and glass fabric is in medial axis position
The place of putting docks but does not overlap, then on fiberglass cloth each one layer of 2mm thickness of placed PMI foams, then respectively spread on foam
Paste one layer of 0.125mm thickness glass fabric, at medial axis position dock but overlap, vacuumize cure after repairing type to get
To product as shown in Figure 3, assembling rib, beam etc., leading edge involutory surface and other splicing face brushing adhesive, by upper and lower siding pairing
It is glued, aerofoil as shown in Figure 2 is obtained after curing repairing type.
Embodiment 6
Aerofoil leading edge structure is made of aerofoil wainscot 1, aerofoil lower wall panels 3 and centre 0.1mm thickness aramid fabric 4, aerofoil dress
It is overall structure with can be overturn before along aramid fabric medial axis；Wherein aerofoil wainscot 1,3 inner surface of aerofoil lower wall panels and
Respectively there is the glass fabric of one layer of 0.125mm thickness in outer surface, and centre is the PMI foams of 2mm thickness.
The involved mold of manufacture is as shown in figure 4, be to combine the upper and lower siding type face of aerofoil, and wainscot is along the wing
The off-axis line of fate overturns 180 ° of expansion in front, and edge is located next to edge in face of lower wall template, mold along separation axis in face of upper wall template
For solid construction, material is aluminium alloy, and when use first sticks siding and the glass of lower wall panels exterior skin 0.125mm thickness on mold upper berth
Glass fiber cloth, glass fabric are docked at medial axis position but are not overlapped, then in glass fabric medial axis position pair
Claim the PMI foams of the aramid fabric, then each one layer of 2mm thickness of placed of one layer of 0.1mm thickness of paving, then each one layer of paving on foam
The glass fabric of 0.125mm thickness is docked but is overlapped at medial axis position, and repairing type is assembled after vacuumizing curing, will be upper and lower
Siding pairing is glued, and aerofoil leading edge structure is obtained after curing repairing type.
The above is only the preferred embodiment of the present invention, it should be pointed out that for those skilled in the art
For, various improvements and modifications may be made without departing from the principle of the present invention, these improvements and modifications should also regard
For protection scope of the present invention.
Claims (9)
1. a kind of Small and micro-satellite aerofoil leading edge structure, which is characterized in that including aerofoil wainscot (1), aerofoil lower wall panels
(3), flexible layer of cloth (4)；Aerofoil wainscot (1) leading edge is located next to aerofoil lower wall panels (3) leading edge, aerofoil wainscot (1) and aerofoil
Lower wall panels (3) are whole binding structure, are linked together by flexible layer of cloth (4), during without being made into complete aerofoil, aerofoil wainscot
(1) it can be overturn with aerofoil lower wall panels (3) along the axis of leading edge flexibility layer of cloth (4), flexible layer of cloth (4) is and aerofoil wainscot
(1) and aerofoil lower wall panels (3) are integrally formed manufacture.
2. Small and micro-satellite aerofoil leading edge structure according to claim 1, which is characterized in that flexible layer of cloth (4) is located at
The inner or outer side of aerofoil wainscot (1) and aerofoil lower wall panels (3) exterior skin.
3. Small and micro-satellite aerofoil leading edge structure according to claim 1 or 2, which is characterized in that flexible layer of cloth (4) is
Aryl fiber cloth, nylon fiber cloth, polyester fiber cloth or polyvinyl fibre cloth.
4. a kind of Small and micro-satellite aerofoil leading edge structure molding die, which is characterized in that mold includes aerofoil upper wall template face
(5) and lower wall template face (6), upper wall template face (5) overturns 180 ° and along aerofoil leading edge separation shaft along aerofoil leading edge separation axis
Line is located next to lower wall template face (6).
5. Small and micro-satellite aerofoil leading edge structure molding die according to claim 4, which is characterized in that the mold is real
Core structure or the back side is mitigate groove structure.
6. a kind of Small and micro-satellite aerofoil leading edge structure preparation method, which is characterized in that include the following steps：
(1) in a mold between the symmetrical paving flexibility layer of cloth (4) of axial location and aerofoil wainscot (1), aerofoil lower wall panels (3) cover outside
Skin carbon cloth or glass fabric；
(2) each one layer of PMI foam of placed again, then each one layer of carbon cloth of paving or glass fabric on PMI foams, in
Between docking but do not overlap at axial location；
(3) repairing type is assembled after vacuumizing curing, and upper and lower siding pairing is glued, and aerofoil leading edge structure is obtained after curing repairing type.
7. Small and micro-satellite aerofoil leading edge structure preparation method according to claim 6, which is characterized in that flexible layer of cloth
(4) on the outside of the exterior skin when, the step (1) for first in a mold between the symmetrical paving flexibility layer of cloth of axial location
(4), then on flexible layer of cloth (4) paving exterior skin, the exterior skin are docked at medial axis position but are not overlapped.
8. Small and micro-satellite aerofoil leading edge structure preparation method according to claim 6, which is characterized in that flexible layer of cloth
(4) on the inside of the exterior skin when, the step (1) is the paving exterior skin first on mold, and the exterior skin is in centre
It docks but does not overlap, then the medial axis positional symmetry paving flexibility layer of cloth (4) on exterior skin at axial location.
9. Small and micro-satellite aerofoil leading edge structure preparation method according to claim 6, which is characterized in that the outer illiteracy
The thickness of skin is 0.125mm, and the thickness of the PMI foams is 2mm, and the thickness of flexible layer of cloth (4) is 0.1mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| 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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| Publication Number | Publication Date |
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| CN108248824A true CN108248824A (en) | 2018-07-06 |
| CN108248824B CN108248824B (en) | 2021-12-21 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112173160A (en) * | 2019-07-02 | 2021-01-05 | 宁波海曙昱图航空科技有限公司 | Forming process and clamping tool for wings and empennage of unmanned aerial vehicle |
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