CN106275375A - Four axle unmanned plane main body and manufacture methods of integration molding - Google Patents
Four axle unmanned plane main body and manufacture methods of integration molding Download PDFInfo
- Publication number
- CN106275375A CN106275375A CN201610905159.7A CN201610905159A CN106275375A CN 106275375 A CN106275375 A CN 106275375A CN 201610905159 A CN201610905159 A CN 201610905159A CN 106275375 A CN106275375 A CN 106275375A
- Authority
- CN
- China
- Prior art keywords
- cloth
- layer
- carbon fibre
- fibre initial
- initial rinse
- 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
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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
- B64C1/061—Frames
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B38/00—Ancillary operations in connection with laminating processes
- B32B38/0004—Cutting, tearing or severing, e.g. bursting; Cutter details
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
- B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
- B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
- B32B5/26—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer another layer next to it also being fibrous or filamentary
-
- 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
- B64C1/068—Fuselage sections
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- 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
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2262/00—Composition or structural features of fibres which form a fibrous or filamentary layer or are present as additives
- B32B2262/10—Inorganic fibres
- B32B2262/106—Carbon fibres, e.g. graphite fibres
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B2605/00—Vehicles
- B32B2605/18—Aircraft
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Moulding By Coating Moulds (AREA)
- Laminated Bodies (AREA)
Abstract
The present invention relates to four axle unmanned plane main body and manufacture methods of a kind of integration molding, this four axles unmanned plane main body is formed by the first carbon fibre initial rinse layer of cloth, the second carbon fibre initial rinse layer of cloth, the first adhesive film, foam core, the second adhesive film, the first carbon fiber one-way layer of cloth, the second carbon fiber one-way layer of cloth, the 3rd carbon fibre initial rinse layer of cloth and the 4th carbon fibre initial rinse layer of cloth paving the most successively, integrally curing.Such that unmanned plane weight can be alleviated significantly, improve intensity and the levelness of unmanned plane blade of unmanned plane, it is to avoid flying for long time causes standard component to loosen, and unmanned plane overall performance is improved.
Description
Technical field
The invention belongs to unmanned air vehicle technique field, particularly to four axle unmanned plane main body and manufactures of a kind of integration molding
Method.
Background technology
At present, on market, the main body of existing four axle unmanned planes is all to use four carbon fiber square tubes or pipe, by dress
Join frame standard component (bolt, nut) to connect together.The body weight weight of existing four axle unmanned planes, causes flying of unmanned plane
Row energy consumption is higher, flight manipulation is relatively difficult, and assembles main body together and make the blade levelness of assembling be difficult to ensure that, causes
Unmanned plane all has reduction, flying for long time to be also easy to occur that assembling standard component loosens problem at flight overall performance such as handling grade,
Summary of the invention
In order to solve above-mentioned technical problem present in prior art, the invention provides a kind of integration molding, weight
Gently, flight energy consumption is low, handling good, and intensity and blade levelness are high, the four axle unmanned plane main bodys that overall performance is reliable and stable, with
And the manufacture method of this four axles unmanned plane main body.
For solving above-mentioned technical problem, the present invention adopts the following technical scheme that
Four axle unmanned plane main bodys of a kind of integration molding, by the first carbon fibre initial rinse layer of cloth, the second carbon fibre initial rinse fabric
Layer, the first adhesive film, foam core, the second adhesive film, the first carbon fiber one-way layer of cloth, the second carbon fiber one-way layer of cloth, the 3rd carbon
Fiber prepreg layer of cloth and the 4th carbon fibre initial rinse layer of cloth paving the most successively, integrally curing form.
Further, the paving direction of described first carbon fibre initial rinse layer of cloth and the second carbon fibre initial rinse layer of cloth is the most vertical
Directly, the paving direction of described 3rd carbon fibre initial rinse layer of cloth and the 4th carbon fibre initial rinse layer of cloth is mutually perpendicular to, and the first carbon is fine
The paving direction of dimension preimpregnation layer of cloth and the 4th carbon fibre initial rinse layer of cloth is consistent, the second carbon fibre initial rinse layer of cloth and the 3rd carbon fiber
The paving direction of preimpregnation layer of cloth is consistent.
Further, described first carbon fibre initial rinse layer of cloth and the 4th carbon fibre initial rinse layer of cloth all with+45 ° of direction pavings,
Described second carbon fibre initial rinse layer of cloth and the 3rd carbon fibre initial rinse layer of cloth are all with-45 ° of direction pavings.
Further, described foam core is 0.25 be spliced " flat foam core.
A kind of manufacture method of four axle unmanned plane main bodys, including first on flat plate mold successively paving direction be mutually perpendicular to
The first carbon fibre initial rinse layer of cloth and the second carbon fibre initial rinse layer of cloth, paving the of then ruling on the second carbon fibre initial rinse layer of cloth
One adhesive film, is then layered on the foam core spliced on the first adhesive film, paving the second glue of subsequently ruling in foam core
Film layer, followed by paving the first carbon fiber one-way layer of cloth, the second carbon fiber one-way layer of cloth and direction successively on the second adhesive film
It is mutually perpendicular to the 3rd carbon fibre initial rinse layer of cloth and the 4th carbon fibre initial rinse layer of cloth, finally sends into curing oven in the lump with flat plate mold whole
After body curing molding, cutting forms.
It is further, described that " successively the orthogonal first carbon fibre initial rinse layer of cloth in paving direction and the second carbon fiber are pre-
Leaching layer of cloth " and " paving direction is mutually perpendicular to the 3rd carbon fibre initial rinse layer of cloth and the 4th carbon fibre initial rinse layer of cloth successively ", particularly as follows:
First first to spread with+45 ° of direction paving the first carbon fibre initial rinse layer of cloths, the 3rd carbon fibre initial rinse layer of cloths, then with-45 ° of direction pavings
Second carbon fibre initial rinse layer of cloth, the 4th carbon fibre initial rinse layer of cloth.
The invention has the beneficial effects as follows:
The present invention passes through technique scheme, can significantly alleviate unmanned plane weight, reduces flight energy consumption and improves flight
Handling, also improve intensity and the levelness of unmanned plane blade of unmanned plane, it is to avoid flying for long time causes standard component simultaneously
Loosening, unmanned plane overall performance is more stable, more reliable.
Accompanying drawing explanation
The invention will be further described with specific embodiment below in conjunction with the accompanying drawings:
Fig. 1 is the structural representation of four axle unmanned plane body embodiment of integration molding of the present invention；
Fig. 2 is the sectional structure schematic diagram of four axle unmanned plane body embodiment of integration molding of the present invention.
Detailed description of the invention
In order to make the purpose of the present invention, technical scheme and advantage clearer, below in conjunction with drawings and Examples, right
The present invention is further elaborated.Should be appreciated that specific embodiment described herein only in order to explain the present invention, not
For limiting the present invention.
As shown in Figures 1 and 2:
Embodiments providing four axle unmanned plane main bodys of a kind of integration molding, this four axles unmanned plane main body is by
One carbon fibre initial rinse layer of cloth the 2, second carbon fibre initial rinse layer of cloth the 3, first adhesive film 4, foam core the 5, second adhesive film the 6, first carbon
One-way fiber layer of cloth the 7, second carbon fiber one-way layer of cloth the 8, the 3rd carbon fibre initial rinse layer of cloth 9 and the 4th carbon fibre initial rinse layer of cloth 10 from
Under paving the most successively, integrally curing form.
Wherein, described first carbon fibre initial rinse layer of cloth 2 is mutually perpendicular to the paving direction of the second carbon fibre initial rinse layer of cloth 3,
Described 3rd carbon fibre initial rinse layer of cloth 9 is mutually perpendicular to the paving direction of the 4th carbon fibre initial rinse layer of cloth 10, and the first carbon is fine
Dimension preimpregnation layer of cloth 2 is consistent with the paving direction of the 4th carbon fibre initial rinse layer of cloth 10, the second carbon fibre initial rinse layer of cloth 3 and the 3rd carbon
The paving direction of fiber prepreg layer of cloth 9 is consistent；It is specifically as follows: described first carbon fibre initial rinse layer of cloth 2 and the 4th carbon fiber
Preimpregnation layer of cloth 10 all with+45 ° of direction pavings, described second carbon fibre initial rinse layer of cloth 3 and the 3rd carbon fibre initial rinse layer of cloth 9 all with-
45 ° of direction pavings.Described foam core 5 can be 0.25 be spliced " flat foam core, such as dotted outline region in Fig. 1, i.e. in
Maltese cross type foam core material.
During the manufacture of four axle unmanned plane main bodys of the present invention, first on flat plate mold, successively paving direction is mutually perpendicular to
The first carbon fibre initial rinse layer of cloth 2 and the second carbon fibre initial rinse layer of cloth 3 (such as: preferably first first to spread with+45 ° of direction pavings the
One carbon fibre initial rinse layer of cloth 2, then with-45 ° of direction paving the second carbon fibre initial rinse layer of cloths 3), then at the second carbon fibre initial rinse
Paving the first adhesive film 4 of ruling on layer of cloth 3 (is i.e. accurately positioned the first glue by line on the second carbon fibre initial rinse layer of cloth 3
The paving angles and positions of film layer 4), then the foam core 5 spliced is layered on the first adhesive film 4, subsequently in foam core 5
Upper line paving the second adhesive film 6 (i.e. by line in foam core 5 be accurately positioned the second adhesive film 6 paving angle and
Position), followed by paving the first carbon fiber one-way layer of cloth the 7, second carbon fiber one-way layer of cloth 8 and successively on the second adhesive film 6
Direction is mutually perpendicular to the 3rd carbon fibre initial rinse layer of cloth 9 and the 4th carbon fibre initial rinse layer of cloth 10 (such as: preferably first first to spread with+45 °
Direction paving the 3rd carbon fibre initial rinse layer of cloth 9, then with-45 ° of direction paving the 4th carbon fibre initial rinse layer of cloths 10), last and flat board
Mould cuts after sending into curing oven integral solidifying in the lump and forms.
So, four axle unmanned plane main bodys of integration molding of the present invention not only significantly reduce unmanned plane weight (with
Conventional metal frames compares the weight that can reduce by about 15～25%), effectively reduce the flight energy consumption of unmanned plane and improve flight behaviour
Control property, the intensity also improving unmanned plane (such as uses intersection ± 45 ° paving the first carbon fibre initial rinse layer of cloth 2 and the second carbon fine
Dimension preimpregnation layer of cloth 3, described 3rd carbon fibre initial rinse layer of cloth 9 and the 4th carbon fibre initial rinse layer of cloth 10, make four axle unmanned plane main bodys whole
Body structural strength symmetrical equilibrium) and unmanned plane blade levelness (integration molding can design at the beginning of be ensured that by frock
Levelness rather than the traditional installation and debugging of four axles ensure levelness), it is to avoid flying for long time causes standard component pine
Dynamic, unmanned plane overall performance is more stable, more reliable.
The above is the preferred embodiment of the present invention, it is noted that for those skilled in the art
For, under the premise without departing from the principles of the invention, it is also possible to make some improvements and modifications, these improvements and modifications are also considered as
Protection scope of the present invention.
Claims (6)
1. four axle unmanned plane main bodys of an integration molding, it is characterised in that: this four axle unmanned plane main body (1) is fine by the first carbon
Dimension preimpregnation layer of cloth (2), the second carbon fibre initial rinse layer of cloth (3), the first adhesive film (4), foam core (5), the second adhesive film (6), the
One carbon fiber one-way layer of cloth (7), the second carbon fiber one-way layer of cloth (8), the 3rd carbon fibre initial rinse layer of cloth (9) and the 4th carbon fiber are pre-
Leaching layer of cloth (10) paving the most successively, integrally curing form.
Four axle unmanned plane main bodys of integration molding the most according to claim 1, it is characterised in that: described first carbon fiber is pre-
Leaching layer of cloth (2) is mutually perpendicular to the paving direction of the second carbon fibre initial rinse layer of cloth (3), described 3rd carbon fibre initial rinse layer of cloth (9)
It is mutually perpendicular to the paving direction of the 4th carbon fibre initial rinse layer of cloth (10), and the first carbon fibre initial rinse layer of cloth (2) and the 4th carbon
The paving direction of fiber prepreg layer of cloth (10) is consistent, the second carbon fibre initial rinse layer of cloth (3) and the 3rd carbon fibre initial rinse layer of cloth (9)
Paving direction consistent.
Four axle unmanned plane main bodys of integration molding the most according to claim 2, it is characterised in that: described first carbon fiber is pre-
Leaching layer of cloth (2) and the 4th carbon fibre initial rinse layer of cloth (10) all with+45 ° of direction pavings, described second carbon fibre initial rinse layer of cloth (3) and
3rd carbon fibre initial rinse layer of cloth (9) is all with-45 ° of direction pavings.
Four axle unmanned plane main bodys of integration molding the most according to claim 3, it is characterised in that: described foam core (5) is
0.25 " the flat foam core being spliced.
5. the manufacture method of an axle unmanned plane main body, it is characterised in that: include first priority paving side on flat plate mold
To orthogonal first carbon fibre initial rinse layer of cloth (2) and the second carbon fibre initial rinse layer of cloth (3), then at the second carbon fibre initial rinse
Layer of cloth (3) upper line paving the first adhesive film (4), is then layered on the foam core (5) spliced on the first adhesive film (4), then
Then in foam core (5) upper line paving the second adhesive film (6), followed by paving the first carbon successively on the second adhesive film (6)
One-way fiber layer of cloth (7), the second carbon fiber one-way layer of cloth (8) and direction are mutually perpendicular to the 3rd carbon fibre initial rinse layer of cloth (9) and the
Four carbon fibre initial rinse layer of cloths (10), cut after finally sending into curing oven integral solidifying in the lump with flat plate mold and form.
The manufacture method of four axle unmanned plane main bodys the most according to claim 5, it is characterised in that: described " successively paving direction
Orthogonal first carbon fibre initial rinse layer of cloth (2) and the second carbon fibre initial rinse layer of cloth (3) " and " paving direction is the most vertical successively
Straight 3rd carbon fibre initial rinse layer of cloth (9) and the 4th carbon fibre initial rinse layer of cloth (10) ", particularly as follows: first first to spread with+45 ° of direction pavings
Paste the first carbon fibre initial rinse layer of cloth (2), the 3rd carbon fibre initial rinse layer of cloth (9), then with-45 ° of direction paving second carbon fibre initial rinses
Layer of cloth (3), the 4th carbon fibre initial rinse layer of cloth (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610905159.7A CN106275375A (en) | 2016-10-17 | 2016-10-17 | Four axle unmanned plane main body and manufacture methods of integration molding |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610905159.7A CN106275375A (en) | 2016-10-17 | 2016-10-17 | Four axle unmanned plane main body and manufacture methods of integration molding |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106275375A true CN106275375A (en) | 2017-01-04 |
Family
ID=57718881
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610905159.7A Pending CN106275375A (en) | 2016-10-17 | 2016-10-17 | Four axle unmanned plane main body and manufacture methods of integration molding |
Country Status (1)
| Country | Link |
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| CN (1) | CN106275375A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828865A (en) * | 2017-03-01 | 2017-06-13 | 山东长空雁航空科技有限责任公司 | Crossbeam and its forming method on fuselage |
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| CN104192292A (en) * | 2014-09-17 | 2014-12-10 | 中航通飞华南飞机工业有限公司 | Composite integral co-curing aircraft body and processing method |
| WO2015016518A1 (en) * | 2013-07-30 | 2015-02-05 | (주)엘지하우시스 | Continuous fiber reinforced resin composite material and molded article thereof |
| CN104723631A (en) * | 2013-12-23 | 2015-06-24 | 上海杰事杰新材料(集团)股份有限公司 | Carbon fiber composite material product and production method |
| JP2015214027A (en) * | 2013-02-28 | 2015-12-03 | ザ・ボーイング・カンパニーＴｈｅＢｏｅｉｎｇ Ｃｏｍｐａｎｙ | Composite laminated plate having reduced crossply angle |
| 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 |
| CN105563851A (en) * | 2016-02-04 | 2016-05-11 | 上海晋飞新材料科技有限公司 | Moulding process for fuselage of UAV (Unmanned Aerial Vehicle) |
| CN206125395U (en) * | 2016-10-17 | 2017-04-26 | 中航通飞华南飞机工业有限公司 | Fashioned four -axis unmanned aerial vehicle main part of wholeization |
-
2016
- 2016-10-17 CN CN201610905159.7A patent/CN106275375A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101219587A (en) * | 2007-12-28 | 2008-07-16 | 同济大学 | Composite stressed-skin construction for fuselage and technique of preparing the same |
| JP2015214027A (en) * | 2013-02-28 | 2015-12-03 | ザ・ボーイング・カンパニーＴｈｅＢｏｅｉｎｇ Ｃｏｍｐａｎｙ | Composite laminated plate having reduced crossply angle |
| WO2015016518A1 (en) * | 2013-07-30 | 2015-02-05 | (주)엘지하우시스 | Continuous fiber reinforced resin composite material and molded article thereof |
| CN104723631A (en) * | 2013-12-23 | 2015-06-24 | 上海杰事杰新材料(集团)股份有限公司 | Carbon fiber composite material product and production method |
| CN104192292A (en) * | 2014-09-17 | 2014-12-10 | 中航通飞华南飞机工业有限公司 | Composite integral co-curing aircraft body and processing method |
| 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 |
| CN105563851A (en) * | 2016-02-04 | 2016-05-11 | 上海晋飞新材料科技有限公司 | Moulding process for fuselage of UAV (Unmanned Aerial Vehicle) |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106828865A (en) * | 2017-03-01 | 2017-06-13 | 山东长空雁航空科技有限责任公司 | Crossbeam and its forming method on fuselage |
| CN106828865B (en) * | 2017-03-01 | 2019-04-02 | 山东长空雁航空科技有限责任公司 | Crossbeam and its forming method on fuselage |
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| PB01 | Publication | ||
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| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170104 |