CN106275377A - The stressed-skin construction of a kind of small-sized unmanned plane and forming method thereof - Google Patents

The stressed-skin construction of a kind of small-sized unmanned plane and forming method thereof Download PDF

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Publication number
CN106275377A
CN106275377A CN201610782369.1A CN201610782369A CN106275377A CN 106275377 A CN106275377 A CN 106275377A CN 201610782369 A CN201610782369 A CN 201610782369A CN 106275377 A CN106275377 A CN 106275377A
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CN
China
Prior art keywords
stressed
pmi foam
foam core
frp panel
skin construction
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
Application number
CN201610782369.1A
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Chinese (zh)
Inventor
崔艳鸿
周烈
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Beijing Qizheng Polytron Technologies Inc A Few Dollars
Original Assignee
Beijing Qizheng Polytron Technologies Inc A Few Dollars
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Beijing Qizheng Polytron Technologies Inc A Few Dollars filed Critical Beijing Qizheng Polytron Technologies Inc A Few Dollars
Priority to CN201610782369.1A priority Critical patent/CN106275377A/en
Publication of CN106275377A publication Critical patent/CN106275377A/en
Pending legal-status Critical Current

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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
    • B64C1/12—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
    • 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
    • B29C70/40—Shaping or impregnating by compression not applied
    • B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
    • B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
    • B64U10/00—Type of UAV
    • 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
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
    • 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 stressed-skin construction and the forming method thereof of a kind of small-sized unmanned plane, wherein, stressed-skin construction integral die molding, include the most successively: outer layer the oneth FRP panel, outer layer the 2nd FRP panel, PMI foam core and internal layer FRP panel, PMI foam core by hot-forming and solidification after formed curved surface.The invention have benefit that: the stressed-skin construction of (1) present invention, it substituted for cork wood plate, fiberglass, cellular composite material with PMI foam core, not only alleviate the weight of stressed-skin construction, and add the rigidity of stressed-skin construction, be particularly suitable for small-sized unmanned plane and use；(2) PMI foam core uses stressed-skin construction hot-forming, whole to use compression molding, not only reduces cost of labor, and formed precision is high, deflection is little, concordance and the surface forming effect of molding have been effectively ensured.

Description

The stressed-skin construction of a kind of small-sized unmanned plane and forming method thereof
Technical field
The present invention relates to stressed-skin construction and the forming method thereof of a kind of aircraft, be specifically related to the illiteracy of a kind of small-sized unmanned plane Skin structure and forming method thereof, belong to unmanned air vehicle technique field.
Background technology
At present, the stressed-skin construction making small-sized unmanned plane is many based on cork wood plate, fiberglass, cellular composite material.
Use these materials to make stressed-skin construction, not only need substantial amounts of manual operation, lose time, increase artificial one-tenth This, and the problems such as precision is low, deflection is big, surface effect is poor during molding, can be run into.
Additionally, the stressed-skin construction intensity being made is low, in order to reach certain wing load and safety coefficient, stressed-skin construction The weight of waste is bigger.
Summary of the invention
For solving the deficiencies in the prior art, first purpose of the present invention is to provide the eyelid covering of a kind of small-sized unmanned plane Structure, the not only weight saving of this stressed-skin construction, and also rigidity increases.
Second object of the present invention is to provide the forming method of a kind of above-mentioned stressed-skin construction, the method to be possible not only to joint About cost of labor, and can ensure that concordance and the surface forming effect of molding.
In order to realize first aim, the present invention adopts the following technical scheme that:
The stressed-skin construction of a kind of small-sized unmanned plane, it is characterised in that integral die molding, includes the most successively: Outer layer the oneth FRP panel (1), outer layer the 2nd FRP panel (2), PMI foam core (3) and internal layer FRP panel (4), wherein, front State PMI foam core (3) and pass through hot-forming, and after solidification, form curved surface.
In order to realize second target, the present invention adopts the following technical scheme that:
The forming method of the stressed-skin construction of aforesaid small-sized unmanned plane, it is characterised in that comprise the following steps:
Step1: by hot moulding mold and the common effect of hot moulding lower mold, by molded for PMI foam thermal, formed Curved surface, obtains PMI foam core (3)；
Step2: outer layer the oneth FRP panel (1) and outer layer the 2nd FRP panel (2) are placed sequentially on molding bottom die, Then epoxy resin is smeared；
Step3: PMI foam core (3) is placed on outer layer the 2nd FRP panel (2), again smears epoxy resin；
Step4: internal layer FRP panel (4) is placed on PMI foam core (3), and by under shaping upper tool and molding Mould matched moulds, carries out cured, the demoulding and get final product.
The invention have benefit that:
(1) stressed-skin construction of the present invention, it substituted for cork wood plate, fiberglass, cellular composite material with PMI foam core, Not only alleviate the weight of stressed-skin construction, and add the rigidity of stressed-skin construction, be particularly suitable for small-sized unmanned plane and use；
(2) PMI foam core uses stressed-skin construction hot-forming, whole to use compression molding, not only reduces artificial one-tenth This, and formed precision is high, deflection is little, and concordance and the surface forming effect of molding have been effectively ensured.
Accompanying drawing explanation
Fig. 1 is the schematic diagram making PMI foam core；
Fig. 2 is the schematic diagram making stressed-skin construction.
The implication of reference in figure: 1-outer layer the oneth FRP panel, 2-outer layer the 2nd FRP panel, 3-PMI foam core, 4-internal layer FRP panel, 5-hot moulding mold, 6-hot moulding lower mold, 7-molding bottom die, 8-shaping upper have.
Detailed description of the invention
Below in conjunction with the drawings and specific embodiments, the present invention made concrete introduction.
One, PMI foam core is made
With reference to Fig. 1, by hot moulding mold 5 and the common effect of hot moulding lower mold 6, by molded for PMI foam thermal, Form curved surface, obtain PMI foam core 3.
PMI foam core 3 uses hot-forming, not only reduces cost of labor, and formed precision is high, deflection is little.
PMI foam full name polymethacrylimide foam, is the foam plastics of a kind of lightweight, closed pore, high intensity, with first Base acrylic acid (MAA) and methacrylonitrile (MAN) copolymer are matrix, have good mechanical property, under equal densities, PMI The compression of foam, stretching, modulus of shearing and intensity are higher；There is higher heat-resistant deforming temperature, can reach 240 DEG C, be current The reasonable structural foamed plastic of heat resistance.PMI foam is prone to processing, and thermoforming and mechanical means can be used to be processed into respectively Plant complicated shape face.PMI foam adhesive property is good, can use epoxy resin, unsaturated polyester resin, BMI tree The adhesive such as fat, cyanate ester resin obtains good bonding interface, can be at 190 DEG C and autoclave pressure (0.35-0.75MPa) bar Realize and panel co-curing under part；Also there is superior resistance to chemical corrosion, be mainly used in outside Aero-Space, radar antenna In cover, CT medical treatment bed board, wind-powered electricity generation helicopter blade, bullet train, even construction material, it is the hardest under the most equal density conditions Structural core.
As the preferred scheme of one, the PMI foam that making PMI foam core 3 is used uses space flight level PMI bubble Foam.
Two, stressed-skin construction is made
Stressed-skin construction integral die molding, with reference to Fig. 2, includes the most successively: outer layer the oneth FRP panel 1, outer layer the Two FRP panels 2, PMI foam core 3 and internal layer FRP panel 4, concrete manufacture method is as follows:
Step1: outer layer the oneth FRP panel 1 and outer layer the 2nd FRP panel 2 are placed sequentially on molding bottom die 7, so After smear epoxy prepreg.
Step2: be placed on by PMI foam core 3 on outer layer the 2nd FRP panel 2, smears epoxy resin preimpregnation again Material.
Step3: internal layer FRP panel 4 is placed on PMI foam core 3, and by shaping upper tool 8 and molding lower mold Have 7 matched moulds, carry out cured, the demoulding and get final product.
The demoulding for convenience, can have on 8 at molding bottom die 7 and shaping upper in advance and be coated with a certain amount of releasing agent.
FRP panel full name fibre-reinforced plastics panel, is a kind of with macromolecule epoxy resin as matrix, fiberglass or Carbon fibers etc. are reinforcement, the composite made through combination process.Advantage includes: light and handy, corrosion-resistant, aging resistance, absolutely Edge.Shell and printed circuit board (PCB) mainly for the manufacture of various sports requsites, pipeline, shipbuilding, automobile and electronic product.
The stressed-skin construction of the present invention, it substituted for cork wood plate, fiberglass, cellular composite material with PMI foam core 3, no Only alleviate the weight of stressed-skin construction, and add the rigidity of stressed-skin construction, be particularly suitable for small-sized unmanned plane and use.
Additionally, due to PMI foam core 3 uses stressed-skin construction hot-forming, whole to use compression molding, so not only dropping Low cost of labor, and formed precision is high, deflection is little, and concordance and the surface forming effect of molding have been effectively ensured.
Become it should be noted that above-described embodiment limits the present invention, all employing equivalents or equivalence the most in any form The technical scheme that the mode changed is obtained, all falls within protection scope of the present invention.

Claims (3)

1. the stressed-skin construction of a small-sized unmanned plane, it is characterised in that integral die molding, includes the most successively: outer Layer the oneth FRP panel (1), outer layer the 2nd FRP panel (2), PMI foam core (3) and internal layer FRP panel (4), wherein, described PMI foam core (3) is by hot-forming, and forms curved surface after solidification.
2. the forming method of the stressed-skin construction of the small-sized unmanned plane described in claim 1, it is characterised in that include following step Rapid:
Step1: by hot moulding mold and the common effect of hot moulding lower mold, by molded for PMI foam thermal, form song Face, obtains PMI foam core (3)；
Step2: outer layer the oneth FRP panel (1) and outer layer the 2nd FRP panel (2) are placed sequentially on molding bottom die, then Smear epoxy resin；
Step3: PMI foam core (3) is placed on outer layer the 2nd FRP panel (2), again smears epoxy resin；
Step4: internal layer FRP panel (4) is placed on PMI foam core (3), and by shaping upper tool and molding bottom die Matched moulds, carries out cured, the demoulding and get final product.
Forming method the most according to claim 2, it is characterised in that have the most all with shaping upper on described molding bottom die Scribble releasing agent.
CN201610782369.1A 2016-08-30 2016-08-30 The stressed-skin construction of a kind of small-sized unmanned plane and forming method thereof Pending CN106275377A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
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Application Number Priority Date Filing Date Title
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Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106848501A (en) * 2017-01-13 2017-06-13 武汉理工大学 A kind of frequency selects composite material sandwich structure
CN107972843A (en) * 2017-11-09 2018-05-01 中国运载火箭技术研究院 A kind of lightweight, high maintainable unmanned plane composite structure system
CN107984771A (en) * 2017-12-14 2018-05-04 上海晋飞碳纤科技股份有限公司 One kind can heat CT bed boards and its manufacture craft
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
CN109747722A (en) * 2017-11-03 2019-05-14 江苏越科新材料有限公司 A kind of Lightweight carriage plate and preparation method thereof
GB2575633A (en) * 2018-07-16 2020-01-22 Bae Systems Plc Wing structure
CN112406140A (en) * 2020-09-14 2021-02-26 航天特种材料及工艺技术研究所 Molding method of die-pressing heat setting type polyurethane foam
CN113928552A (en) * 2021-11-19 2022-01-14 中国直升机设计研究所 Helicopter bearingless rotor oversleeve with light weight
CN114290715A (en) * 2022-01-05 2022-04-08 河北福莱卡航空科技有限公司 Rapid trial-manufacturing forming process for producing ducted propeller

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN201755923U (en) * 2009-12-22 2011-03-09 上海磁浮交通发展有限公司 Composite board with multi-layer sandwich structure
CN102958662A (en) * 2010-07-30 2013-03-06 赢创工业集团股份有限公司 In-mould-foaming process using foamable medium with outer layers, and plastics moulding obtainable therefrom
US20150174798A1 (en) * 2012-07-24 2015-06-25 Cornelia Zimmermann Novel shaping process for pmi foam materials and/or composite components produced therefrom
CN105416567A (en) * 2015-11-13 2016-03-23 中国人民解放军国防科学技术大学 Skin, unmanned aerial vehicle wing, manufacturing method of unmanned aerial vehicle wing, empennage and manufacturing method of empennage
CN206012939U (en) * 2016-08-30 2017-03-15 北京奇正数元科技股份有限公司 A kind of stressed-skin construction of small-sized unmanned plane

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN201755923U (en) * 2009-12-22 2011-03-09 上海磁浮交通发展有限公司 Composite board with multi-layer sandwich structure
CN102958662A (en) * 2010-07-30 2013-03-06 赢创工业集团股份有限公司 In-mould-foaming process using foamable medium with outer layers, and plastics moulding obtainable therefrom
US20150174798A1 (en) * 2012-07-24 2015-06-25 Cornelia Zimmermann Novel shaping process for pmi foam materials and/or composite components produced therefrom
CN105416567A (en) * 2015-11-13 2016-03-23 中国人民解放军国防科学技术大学 Skin, unmanned aerial vehicle wing, manufacturing method of unmanned aerial vehicle wing, empennage and manufacturing method of empennage
CN206012939U (en) * 2016-08-30 2017-03-15 北京奇正数元科技股份有限公司 A kind of stressed-skin construction of small-sized unmanned plane

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106848501A (en) * 2017-01-13 2017-06-13 武汉理工大学 A kind of frequency selects composite material sandwich structure
CN106848501B (en) * 2017-01-13 2019-10-01 武汉理工大学 A kind of frequency selection composite material sandwich structure
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
CN109747722A (en) * 2017-11-03 2019-05-14 江苏越科新材料有限公司 A kind of Lightweight carriage plate and preparation method thereof
CN107972843A (en) * 2017-11-09 2018-05-01 中国运载火箭技术研究院 A kind of lightweight, high maintainable unmanned plane composite structure system
CN107984771A (en) * 2017-12-14 2018-05-04 上海晋飞碳纤科技股份有限公司 One kind can heat CT bed boards and its manufacture craft
GB2575633A (en) * 2018-07-16 2020-01-22 Bae Systems Plc Wing structure
GB2575633B (en) * 2018-07-16 2022-06-01 Bae Systems Plc Wing structure
CN112406140A (en) * 2020-09-14 2021-02-26 航天特种材料及工艺技术研究所 Molding method of die-pressing heat setting type polyurethane foam
CN112406140B (en) * 2020-09-14 2022-09-23 航天特种材料及工艺技术研究所 Molding method of die-pressing heat setting type polyurethane foam
CN113928552A (en) * 2021-11-19 2022-01-14 中国直升机设计研究所 Helicopter bearingless rotor oversleeve with light weight
CN113928552B (en) * 2021-11-19 2023-04-28 中国直升机设计研究所 Lightweight bearingless rotor sleeve of helicopter
CN114290715A (en) * 2022-01-05 2022-04-08 河北福莱卡航空科技有限公司 Rapid trial-manufacturing forming process for producing ducted propeller

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Application publication date: 20170104