CN106828967A - Full-height foaming structure multi-rotor unmanned aerial vehicle manufacture method - Google Patents
Full-height foaming structure multi-rotor unmanned aerial vehicle manufacture method Download PDFInfo
- Publication number
- CN106828967A CN106828967A CN201611250999.0A CN201611250999A CN106828967A CN 106828967 A CN106828967 A CN 106828967A CN 201611250999 A CN201611250999 A CN 201611250999A CN 106828967 A CN106828967 A CN 106828967A
- Authority
- CN
- China
- Prior art keywords
- aerial vehicle
- unmanned aerial
- rotor unmanned
- foam core
- full
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
- 238000000034 method Methods 0.000 title claims abstract description 21
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 15
- 238000005187 foaming Methods 0.000 title claims abstract description 14
- 239000006260 foam Substances 0.000 claims abstract description 23
- 239000004033 plastic Substances 0.000 claims abstract description 13
- 229920007790 polymethacrylimide foam Polymers 0.000 claims abstract description 11
- 239000002131 composite material Substances 0.000 claims abstract description 8
- 239000003365 glass fiber Substances 0.000 claims abstract description 8
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 7
- 239000004917 carbon fiber Substances 0.000 claims abstract description 7
- 239000011229 interlayer Substances 0.000 claims abstract description 7
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 7
- 239000011162 core material Substances 0.000 claims description 24
- 239000004744 fabric Substances 0.000 claims description 15
- 239000011521 glass Substances 0.000 claims description 11
- 239000011347 resin Substances 0.000 claims description 9
- 229920005989 resin Polymers 0.000 claims description 9
- 238000012545 processing Methods 0.000 claims description 7
- 238000013461 design Methods 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 6
- 238000007493 shaping process Methods 0.000 claims description 5
- 239000004593 Epoxy Substances 0.000 claims description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 3
- 229910052799 carbon Inorganic materials 0.000 claims description 3
- 239000002184 metal Substances 0.000 claims description 3
- 238000007592 spray painting technique Methods 0.000 claims description 3
- 238000002560 therapeutic procedure Methods 0.000 claims description 3
- 238000001746 injection moulding Methods 0.000 claims description 2
- 238000005498 polishing Methods 0.000 claims description 2
- 230000002787 reinforcement Effects 0.000 claims description 2
- 238000007711 solidification Methods 0.000 claims description 2
- 230000008023 solidification Effects 0.000 claims description 2
- 238000010276 construction Methods 0.000 abstract description 9
- 239000003822 epoxy resin Substances 0.000 abstract description 5
- 229920000647 polyepoxide Polymers 0.000 abstract description 5
- 238000010586 diagram Methods 0.000 description 4
- 239000002253 acid Substances 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 150000003949 imides Chemical class 0.000 description 2
- 238000000465 moulding Methods 0.000 description 2
- 239000004677 Nylon Substances 0.000 description 1
- 150000001336 alkenes Chemical class 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 239000000835 fiber Substances 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 229920001778 nylon Polymers 0.000 description 1
- 238000010422 painting Methods 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
-
- 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
- B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
- B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
- B29C65/52—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by the way of applying the adhesive
- B29C65/54—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding characterised by the way of applying the adhesive between pre-assembled parts
-
- 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
- B29C69/00—Combinations of shaping techniques not provided for in a single one of main groups B29C39/00 - B29C67/00, e.g. associations of moulding and joining techniques; Apparatus therefore
- B29C69/02—Combinations of shaping techniques not provided for in a single one of main groups B29C39/00 - B29C67/00, e.g. associations of moulding and joining techniques; Apparatus therefore of moulding techniques only
-
- 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
- B29C70/305—Spray-up of reinforcing fibres with or without matrix to form a non-coherent mat in or on a mould
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/061—Frames
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2079/00—Use of polymers having nitrogen, with or without oxygen or carbon only, in the main chain, not provided for in groups B29K2061/00 - B29K2077/00, as moulding material
- B29K2079/08—PI, i.e. polyimides or derivatives thereof
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3076—Aircrafts
-
- 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 discloses a kind of full-height foaming structure multi-rotor unmanned aerial vehicle and its manufacture method.The body of unmanned plane is made of integrally formed mode, and the body includes composite material skin, foam core interlayer and plastic frame body skeleton, and composite material skin wraps foam core interlayer by way of being glued and plastic frame body skeleton forms the body.The present invention links together the PMI foams of low-density with good stiffness with the carbon fiber and glass fiber reinforced epoxy resin covering of intensity by the upper and lower matched moulds of mould, forms a kind of multi-rotor unmanned aerial vehicle housing construction with superperformance and more complicated outward appearance.Flight provides help during boat long for electronic multi-rotor unmanned aerial vehicle extension big load.
Description
Technical field
The present invention relates to a kind of full-height foaming structure multi-rotor unmanned aerial vehicle manufacture method, by the polymethyl of low-density
Acid imide foam and the carbon fiber and glass fiber reinforced epoxy resin covering with good stiffness and intensity, it is upper and lower by mould
Matched moulds links together, and forms a kind of multi-rotor unmanned aerial vehicle housing construction and its manufacture with superperformance and more complicated outward appearance
Method.
Background technology
With the development of electronic technology, the control of multi-rotor aerocraft is allowed to become simple, multi-rotor unmanned aerial vehicle is huge with its
Advantage, wide application prospect, make one of study hotspot of unmanned plane industry in recent years.
Multi-rotor unmanned aerial vehicle has very big advantage compared with fixed-wing unmanned plane on flying method and site requirements.
Many rotors can realize that VTOL and fixed point are spiraled, and this is that fixed-wing unmanned plane is difficult to, while many rotors are to flight
The requirement in space is harsh not as fixed-wing, adapts to be flown in relatively small space.Multi-rotor unmanned aerial vehicle is now used for oil and patrols
Line, power-line patrolling, forest fire protection, ground mapping etc..
Multi-rotor unmanned aerial vehicle is to drive propeller rotation to provide lift by multiple motors, real so as to overcome self gravitation
Existing unmanned plane during flying.Therefore this aircraft utilizes rudder face weave control aspect without image of Buddha fixed wing aircraft, consumes electricity
It is more that the increase of battery capacity also brings the rising of battery weight, it is necessary to high capacity cell meets flight needs, weight,
During boat, structural strength three mutually restrict, now in order to optimize the design of aircraft, it is ensured that body in-flight possesses foot in boat long
Enough intensity, while body will have enough rigidity, the vibrations for preventing motor rotating band from coming make housing construction that obvious deformation to occur,
In the case where above-mentioned condition is met, construction weight will control minimum.
The content of the invention
It is an object of the invention to provide a kind of many rotor housing constructions that can effectively solve the above problems.
The structure is by the polymethacrylimide foam of low-density and the carbon fiber and glass with good stiffness and intensity
Glass fiber reinforced epoxy resin covering, is linked together by the upper and lower matched moulds of mould, forms a kind of with superperformance and more multiple
The multi-rotor unmanned aerial vehicle housing construction of miscellaneous outward appearance.Flight provides help during boat long for electronic multi-rotor unmanned aerial vehicle extension big load.
The body of full-height foaming structure multi-rotor unmanned aerial vehicle of the invention is made of integrally formed mode, the machine
Body includes composite material skin, foam core interlayer and plastic frame body skeleton, and composite material skin is wrapped up by way of being glued
Firmly foam core interlayer and plastic frame body skeleton form the body.
The manufacture method of full-height foaming structure multi-rotor unmanned aerial vehicle of the invention, it is characterised in that：Including：Step one,
According to product design and the multiple Split molds of cavity body structure design processing；Step 2, using machining center coordinate Split mold add
Work polymethacrylimide foam core body, plastic frame body is made using Cutter Body Processing with Machining Center or the mode of injection moulding；Step
Rapid three, respectively on split metal die, carbon fiber and glass fabric the enhancing ring of split are prepared using wet therapy forming process
Epoxy resin-based composite covering；Step 4, by resin uniform application in foam core surface and internal cavity, adopted in mould
The method being glued with matched moulds links together polymethacrylimide foam core body, plastic frame body and split covering；Step
5th, many rotations of carbon fiber and glass fiber reinforcement covering full-height polymethacrylimide foam sandwich are obtained after solidifying
Wing body.
It is preferred that the Split mold includes mold, lower mould and rear mold, the inner chamber of the mold is on unmanned plane
The shape of half portion profile, the inner chamber of the lower mould is the shape of unmanned plane lower half profile, at the rear mold lumen centers
It is provided with intermediate cylinder, the shape for being shaped as coordinating body inner chamber of the intermediate host.
It is preferred that in the step 3, thickness 0.048mm, the dry cloth of density 48g/m2 glass fibres are laid in into split pattern first
On the whole inner surface of tool, uniformly exhaustively brushed on glass fabric with hairbrush epoxy resin-impregnated, be impregnated with glass cloth
Then Split mold after the completion of laying is sent into curing oven by resin to being fitted on Split mold completely, solid under the conditions of 60 DEG C
Change 3 hours, then the 3K carbon cloths of laying density 200g/m2 and solidified on glass fabric using same gimmick, be made
Split covering.
It is preferred that plastic frame body is configured on the corresponding position of foam core then uniform on the surface and inner chamber of foam core
Resin is spread in painting, is filled between each Split mold, and the Split mold matched moulds with split covering is pressurizeed using instrument, and
It is put into baking oven and solidifies 3 hours under the conditions of 60 DEG C, is made body.
It is preferred that the step of also including to body polishing flash after shaping depanning and beautification spray painting.
It is preferred that the polymethacrylimide foam core body is to be processed into PMI blank materials by using machining center
Type, from foam core material density in 40kg/m3 or so.
The present invention combines the low material of strength high density, not only increases the intensity of unmanned plane housing construction, also mitigates
Construction weight, while also having certain complicated moulding.
Brief description of the drawings
Fig. 1 is the mould schematic diagram of body production of the present invention.
Fig. 2 is mold schematic diagram in the present invention.
Fig. 3 is the wet therapy forming process schematic diagram of covering in the present invention.
Fig. 4 is foam core and plastic frame body cooperation schematic diagram in the present invention.
Fig. 5 is shaping body structural representation in the present invention.
Specific embodiment
Below in conjunction with accompanying drawing, the production specific embodiment to the housing construction in the present invention elaborates.
A kind of manufacture of full-height foaming structure multi-rotor unmanned aerial vehicle body in the present invention, it is comprised the following steps：
1) mould processing
Use metal material processing mold 1, lower mould 2, rear mold 3.The mould of making should have case hardness very high
And surface quality, while adapting to temperature change.
2) foam core and plastic frame body are processed
According to multi-rotor unmanned aerial vehicle appearance structure and cavity body structure, using density in 40kg/m3 or so PMI (poly- methyl-props
Alkene acid imide foam) processing foam core 4, process framework 5 and framework 6 using nylon material.
3) preparation of body covering
As shown in figure 3, it is as follows to prepare multiple material covering：Respectively in mold 1, lower mould 2, rear mold 3, according to design drawing
Paper requirement wet placement fiber cloth laying, split metal pattern is laid in by thickness 0.048mm, the dry cloth of density 48g/m2 glass fibres
On tool, uniformly exhaustively brushed on glass fabric with hairbrush epoxy resin-impregnated, glass cloth is impregnated with resin to pasting completely
Close on mould.To be overlapped using cloth at complicated shape, laying will be finally laid to die joint；Basic resin system is from high
The epoxy-resin systems of toughness.Enter curing oven after the completion of laying, solidify 3 hours under the conditions of 60 DEG C.The same hand on mould again
The 3K carbon cloths of method laying density 200g/m2 simultaneously solidify.Prepare the upper and lower covering of body, in chamber and the covering of rear portion.
4) matched moulds is glued draft machine body structure
As shown in figure 4, framework 5 and framework 6 are individually placed on the corresponding position of foam core 3, then by PMI foam cores
The cavity at 4 rear portions is enclosed within the rectangle cylinder of rear mold 3.The resin on uniform application in foam core 4, together with rear mold 3 one
With being placed on lower mould 2, it is harmonious with mold 1 after positioning, until each mating surface of mould is adjacent to.Framework 5 and framework 6 are conducive to
Produce body equipment compartment and battery compartment opening at it is attractive in appearance, while to formed opening at have strengthen effect.
5) curing molding
Mould after matched moulds is pressurizeed using instrument, and is put into baking oven.Insert the interior solidification 3 under the conditions of 60 DEG C of baking oven small
When, polish off flash after shaping depanning carries out beautification spray painting again, just obtains this foam-filled multi-rotor unmanned aerial vehicle body, such as
Shown in accompanying drawing 5.
Claims (7)
1. a kind of full-height foaming structure multi-rotor unmanned aerial vehicle, it is characterised in that its body is made of integrally formed mode,
The body includes composite material skin, foam core interlayer and plastic frame body skeleton, the side that composite material skin passes through splicing
Formula wraps foam core interlayer and plastic frame body skeleton forms the body.
2. the manufacture method of the full-height foaming structure multi-rotor unmanned aerial vehicle described in a kind of claim 1, it is characterised in that：Bag
Include：
Step one, according to product design and the cavity body structure design multiple Split molds of processing；
Step 2, using machining center coordinate Split mold process polymethacrylimide foam core body, using machining center
The mode of processing or injection moulding makes plastic frame body；
Step 3, respectively on split metal die, the carbon fiber and glass fabric of split are prepared using wet therapy forming process
Reinforced epoxy based composites covering；
Step 4, by resin uniform application in foam core surface and internal cavity, the method being glued using matched moulds in mould
Polymethacrylimide foam core body, plastic frame body and split covering are linked together；
Carbon fiber and glass fiber reinforcement covering full-height polymethacrylimide foam interlayer knot are obtained after step 5, solidification
Many rotor bodies of structure.
3. the manufacture method of full-height foaming structure multi-rotor unmanned aerial vehicle according to claim 2, it is characterised in that：It is described
Split mold includes mold, lower mould and rear mold, and the inner chamber of the mold is the shape of unmanned plane first half profile, institute
The inner chamber for stating lower mould is the shape of unmanned plane lower half profile, is provided with intermediate cylinder at the rear mold lumen centers, institute
State the shape for being shaped as coordinating body inner chamber of intermediate host.
4. the manufacture method of the full-height foaming structure multi-rotor unmanned aerial vehicle according to Claims 2 or 3, its spy's levies
In：In the step 3, thickness 0.048mm, the dry cloth of density 48g/m2 glass fibres are laid in the whole of Split mold first
On inner surface, uniformly exhaustively brushed on glass fabric with hairbrush epoxy resin-impregnated, glass cloth is impregnated with resin to complete
It is fitted on Split mold entirely, the Split mold after the completion of laying is then sent into curing oven, solidifies 3 hours under the conditions of 60 DEG C,
Then the 3K carbon cloths of laying density 200g/m2 and solidified on glass fabric using same gimmick, be made split covering.
5. the manufacture method of full-height foaming structure multi-rotor unmanned aerial vehicle according to claim 2, it is characterised in that：Will modeling
Material frame body is configured on the corresponding position of foam core, then the resin on the surface of foam core and inner chamber uniform application, filling
Between each Split mold, the Split mold matched moulds with split covering is pressurizeed using instrument, and be put into baking oven at 60 DEG C
Under the conditions of solidify 3 hours, be made body.
6. the manufacture method of full-height foaming structure multi-rotor unmanned aerial vehicle according to claim 2, levying for its spy be：Also
The step of including to body polishing flash after shaping depanning and beautification spray painting.
7. the manufacture method of full-height foaming structure multi-rotor unmanned aerial vehicle according to claim 2, levying for its spy be：Institute
It is by polymethacrylimide foam blank material machine-shaping, from foam core material by using machining center to state foam core
Density in 40kg/m3 or so.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611250999.0A CN106828967A (en) | 2016-12-29 | 2016-12-29 | Full-height foaming structure multi-rotor unmanned aerial vehicle manufacture method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201611250999.0A CN106828967A (en) | 2016-12-29 | 2016-12-29 | Full-height foaming structure multi-rotor unmanned aerial vehicle manufacture method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106828967A true CN106828967A (en) | 2017-06-13 |
Family
ID=59115126
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201611250999.0A Pending CN106828967A (en) | 2016-12-29 | 2016-12-29 | Full-height foaming structure multi-rotor unmanned aerial vehicle manufacture method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106828967A (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108248824A (en) * | 2017-12-29 | 2018-07-06 | 南京航空航天大学 | A kind of Small and micro-satellite aerofoil leading edge structure, molding die and preparation method thereof |
| CN108284631A (en) * | 2017-12-20 | 2018-07-17 | 东汉太阳能无人机技术有限公司 | A kind of unmanned plane rotor edge bonding method |
| CN108407331A (en) * | 2018-03-05 | 2018-08-17 | 成都凯迪精工科技有限责任公司 | A kind of small drone answers material rear body manufacturing method |
| CN108945416A (en) * | 2018-06-28 | 2018-12-07 | 中国直升机设计研究所 | Exoskeletal fuselage aircraft and airframe structure design method with duct lifting body |
| WO2018232712A1 (en) * | 2017-06-22 | 2018-12-27 | 深圳市大疆创新科技有限公司 | Method for manufacturing foamed material element, foamed material element and fixed-wing unmanned aerial vehicle |
| CN109366812A (en) * | 2018-11-28 | 2019-02-22 | 北京航空航天大学 | It is a kind of for processing the mold of seriation aircraft fuselage shell |
| CN109747181A (en) * | 2019-03-04 | 2019-05-14 | 保定国奥新能源工程材料科技有限责任公司 | The manufacturing method of duct |
| CN112519266A (en) * | 2019-09-17 | 2021-03-19 | 顺丰科技有限公司 | Unmanned aerial vehicle wing forming method |
| CN113619155A (en) * | 2021-08-04 | 2021-11-09 | 陕西天翌天线股份有限公司 | Integral co-curing forming die and method for unmanned aerial vehicle body and rotor wing rod |
| CN114274543A (en) * | 2021-12-15 | 2022-04-05 | 成都飞机工业（集团）有限责任公司 | Reinforced skin positioning and forming method |
| CN114476060A (en) * | 2020-10-27 | 2022-05-13 | 株式会社石川能源研究 | Flying device |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100129589A1 (en) * | 2008-11-25 | 2010-05-27 | Senibi Simon D | Reinforced foam-filled composite stringer |
| CN204623822U (en) * | 2015-04-23 | 2015-09-09 | 杨涛 | A kind of composite structure for unmanned plane and adopt many rotor wing unmanned aerial vehicles of this structure |
| CN105398582A (en) * | 2015-11-13 | 2016-03-16 | 中国人民解放军国防科学技术大学 | Skin, bulkhead integrated unmanned aerial vehicle body and manufacturing method of bulkhead integrated unmanned aerial vehicle body |
| 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 |
| US20160257427A1 (en) * | 2015-03-04 | 2016-09-08 | The Boeing Company | Co-curing process for the joining of composite structures |
| CN106182801A (en) * | 2016-07-15 | 2016-12-07 | 西北工业大学 | A kind of aircraft foam core filled composite material rudder face forming method |
-
2016
- 2016-12-29 CN CN201611250999.0A patent/CN106828967A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20100129589A1 (en) * | 2008-11-25 | 2010-05-27 | Senibi Simon D | Reinforced foam-filled composite stringer |
| US20160257427A1 (en) * | 2015-03-04 | 2016-09-08 | The Boeing Company | Co-curing process for the joining of composite structures |
| CN204623822U (en) * | 2015-04-23 | 2015-09-09 | 杨涛 | A kind of composite structure for unmanned plane and adopt many rotor wing unmanned aerial vehicles of this structure |
| CN105398582A (en) * | 2015-11-13 | 2016-03-16 | 中国人民解放军国防科学技术大学 | Skin, bulkhead integrated unmanned aerial vehicle body and manufacturing method of bulkhead integrated unmanned aerial vehicle body |
| 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 |
| CN106182801A (en) * | 2016-07-15 | 2016-12-07 | 西北工业大学 | A kind of aircraft foam core filled composite material rudder face forming method |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2018232712A1 (en) * | 2017-06-22 | 2018-12-27 | 深圳市大疆创新科技有限公司 | Method for manufacturing foamed material element, foamed material element and fixed-wing unmanned aerial vehicle |
| CN108284631A (en) * | 2017-12-20 | 2018-07-17 | 东汉太阳能无人机技术有限公司 | A kind of unmanned plane rotor edge bonding method |
| CN108248824A (en) * | 2017-12-29 | 2018-07-06 | 南京航空航天大学 | A kind of Small and micro-satellite aerofoil leading edge structure, molding die and preparation method thereof |
| CN108407331A (en) * | 2018-03-05 | 2018-08-17 | 成都凯迪精工科技有限责任公司 | A kind of small drone answers material rear body manufacturing method |
| CN108945416A (en) * | 2018-06-28 | 2018-12-07 | 中国直升机设计研究所 | Exoskeletal fuselage aircraft and airframe structure design method with duct lifting body |
| CN109366812B (en) * | 2018-11-28 | 2020-07-03 | 北京航空航天大学 | Mold for processing serialized aircraft fuselage shell |
| CN109366812A (en) * | 2018-11-28 | 2019-02-22 | 北京航空航天大学 | It is a kind of for processing the mold of seriation aircraft fuselage shell |
| CN109747181A (en) * | 2019-03-04 | 2019-05-14 | 保定国奥新能源工程材料科技有限责任公司 | The manufacturing method of duct |
| CN112519266A (en) * | 2019-09-17 | 2021-03-19 | 顺丰科技有限公司 | Unmanned aerial vehicle wing forming method |
| CN114476060A (en) * | 2020-10-27 | 2022-05-13 | 株式会社石川能源研究 | Flying device |
| CN113619155A (en) * | 2021-08-04 | 2021-11-09 | 陕西天翌天线股份有限公司 | Integral co-curing forming die and method for unmanned aerial vehicle body and rotor wing rod |
| CN113619155B (en) * | 2021-08-04 | 2023-08-22 | 陕西天翌科技股份有限公司 | Integral co-curing forming die and method for unmanned aerial vehicle body and rotor wing rod |
| CN114274543A (en) * | 2021-12-15 | 2022-04-05 | 成都飞机工业（集团）有限责任公司 | Reinforced skin positioning and forming method |
| CN114274543B (en) * | 2021-12-15 | 2023-01-10 | 成都飞机工业（集团）有限责任公司 | Reinforced skin positioning and forming method |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106828967A (en) | Full-height foaming structure multi-rotor unmanned aerial vehicle manufacture method | |
| CN205150216U (en) | Unmanned aerial vehicle's foam presss from both sides core wing | |
| CN103407175B (en) | A kind of integral forming method of fiber-reinforced resin matrix compound material wing box | |
| CN107738457A (en) | A kind of integrated forming technique of unmanned aerial vehicle body | |
| CN105904740B (en) | A kind of integral manufacturing method of composite material light continuous fiber grid | |
| CN104626605B (en) | Composite material wing integral molding technological method and composite material wing integral molding tool | |
| CN102795338B (en) | Micro unmanned aerial vehicle carbon fiber rotor wing and preparation method thereof | |
| CN105416567A (en) | Skin, unmanned aerial vehicle wing, manufacturing method of unmanned aerial vehicle wing, empennage and manufacturing method of empennage | |
| CN103909658B (en) | Composite material connecting skirt forming method and mold and inner rubber core mold forming mold | |
| CN103507941B (en) | Composite hat stiffener, composite hat-stiffened pressure webs, and methods of making the same | |
| CN105216345B (en) | RTM global formation orthogonal stiffenerses structure member (cover)s and its manufacture method | |
| CN105555510A (en) | Method of forming a composite member and assembly therefor | |
| CN110193956A (en) | A kind of small drone composite material vertical tail moulding technique | |
| CN109562578A (en) | The manufacturing method of composite material structure and composite material structure | |
| CN105270612A (en) | Unmanned aerial vehicle body | |
| CN110193957A (en) | A kind of small drone composite aileron moulding technique | |
| CN108891040A (en) | A kind of small and medium size unmanned aerial vehicles composite horizontal empennage manufacturing method | |
| CN110356018A (en) | A kind of unmanned plane integrated machine head-shield co-curing manufacture mold and process | |
| CN109016562A (en) | A kind of preparation method of winglet | |
| CN110510145A (en) | Three beam type composite wing overall structures of one kind and its moulding technique | |
| CN106426987B (en) | A kind of monolithic molding airfoil structure manufacturing process | |
| CN105881922A (en) | Novel high-impacting-resistance type unmanned aerial vehicle airframe structure | |
| CN106584881A (en) | Hollow cap-shaped *-shaped reinforced all-carbon fibre structure and preparation method thereof | |
| CN108146652A (en) | A kind of aspect ratio is more than 9 times of rudder face manufacturing method | |
| CN103057128A (en) | Automatic heating and pressurization production process for composite material specially used for small-sized unmanned plane |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170613 |