CN205150216U - Unmanned aerial vehicle's foam presss from both sides core wing - Google Patents

Unmanned aerial vehicle's foam presss from both sides core wing Download PDF

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Publication number
CN205150216U
CN205150216U CN201520946193.XU CN201520946193U CN205150216U CN 205150216 U CN205150216 U CN 205150216U CN 201520946193 U CN201520946193 U CN 201520946193U CN 205150216 U CN205150216 U CN 205150216U
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China
Prior art keywords
covering
foam
aerial vehicle
unmanned aerial
spar
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CN201520946193.XU
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Chinese (zh)
Inventor
马祥森
司亮
陆方舟
黑丽洁
苗赛
王宣博
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China Aerospace Times Electronics Corp
China Academy of Aerospace Electronics Technology Co Ltd
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China Academy of Aerospace Electronics Technology Co Ltd
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Abstract

The utility model discloses an unmanned aerial vehicle's foam presss from both sides core wing, including last covering (2), lower covering (1), upper surface glued membrane (3), foam laminboard layer (4), lower surface glued membrane (5) and spar (6), go up covering (2) through upper surface glued membrane (3) and foam laminboard layer (4), spar (6) fixed connection, lower covering (1) through lower surface glued membrane (5) and foam laminboard layer (4), spar (6) fixed connection, all fills foam laminboard layer (4) under, in the cavity between covering (1) and spar (6) at last covering (2), spar (6) are fixed through splicing with foam laminboard layer (4). The utility model discloses a wing structure is simple, the light is high -efficient, can improve the structure efficiency of unmanned aerial vehicle airfoil, improves the the stiffness and the shock resistance of structure, and more easy to carry out's manufacture craft and more controllable manufacturing cost make the structure have better design nature and wholeness simultaneously.

Description

A kind of foam core wing of SUAV (small unmanned aerial vehicle)
Technical field
The utility model relates to a kind of unmanned plane wing, particularly a kind of foam core wing of SUAV (small unmanned aerial vehicle).
Background technology
Existing unmanned plane wing adopts traditional girder structure aerofoil usually, and honeycomb sandwich construction aerofoil.Tradition beam type airfoil structure mainly carries by spar and maintains the rigidity of structure, simple and reliable for structure, but for the unmanned plane wing of small-sized thin airfoil, spar height is too small, and structural materials degree of utilization is low, and intensity and toughness characteristic is poor.Honeycomb sandwich construction aerofoil, is main load dimension shape structure with thick covering, can take into account structural stability preferably, but for SUAV (small unmanned aerial vehicle) wing, manufacture process requirement is high, the more difficult realization of structural behaviour while proof strength characteristic.
SUAV (small unmanned aerial vehicle) aerofoil many employings thin airfoil, and have stricter requirement to structural weight.Several typical structure is poor for the applicability in small-sized thin wing face, and difficulty of processing is higher, more difficult implementation structure lightweight.
Utility model content
Technical problem to be solved in the utility model is: provide that a kind of structure is simple, the foam core wing structure form being applicable to SUAV (small unmanned aerial vehicle) of efficient and light weight, the structure efficiency of SUAV (small unmanned aerial vehicle) aerofoil can be improved, improve integral rigidity and the shock resistance of structure, be easier to the manufacture craft of enforcement and more controlled manufacturing cost, make structure have better designability and globality simultaneously.
The utility model comprises following technical scheme:
A foam core wing for SUAV (small unmanned aerial vehicle), comprises covering, lower covering, upper surface glued membrane, foam sandwich laminate, lower surface glued membrane and spar; Upper covering is fixedly connected with foam sandwich laminate, spar by upper surface glued membrane, lower covering is fixedly connected with foam sandwich laminate, spar by lower surface glued membrane, whole filled and process laminboard layer in upper covering, cavity between lower covering and spar, described spar is fixed by glueing joint with foam sandwich laminate.
Described upper covering and lower covering are composite fiber laying covering, and foam sandwich laminate is closed pore rigid foamed plastic materials.
Described upper covering and lower covering are carbon fiber, aramid fiber or glass fiber material laying.
Described upper covering and lower covering are the mixing laying of carbon fiber, aramid fiber and glass fiber material.
Described upper covering and lower covering adopt aramid fiber laying, and described foam sandwich laminate is Polyurethane foam, and the material of described spar is aramid fiber.
The thickness of described upper and lower covering is 0.2mm.
Aerofoil opening portion directly processes on foam sandwich laminate, and upper and lower covering adapts to opening shape and lays.
Aerofoil blank area mounting hole is directly processed on foam sandwich laminate, and attaching parts is embedded in foam sandwich laminate.
Foam sandwich laminate is Polyurethane foam.
Spar adopts carbon fiber, aramid fiber laminate structures or strong plastic material.
The utility model compared with prior art tool has the following advantages:
The utility model adopts full chamber filled and process sandwich airfoil structure, and by filled and process material whole in the cavity between the parts such as wing cover and spar, between foam sandwich laminate and covering and other contact components, glue connects.The airfoil structure adopting full-scale foam core to support, has higher yield limit, and good impact resistance, can the conventional stall landing mode of compatible SUAV (small unmanned aerial vehicle), is particularly useful for the SUAV (small unmanned aerial vehicle) that relative thickness of airfoil is less.Foamed core more easily realizes different airfoil surface configurations, and is convenient to the setting of aerofoil opening and interface, has good designability.The parts such as upper and lower covering, foamed core and beam connect by glueing joint, and connection area is large, and structural integrity is strong.By adopting said structure, making structure of the present utility model simpler, be easy to processing, and quality and cost easily being controlled.
Accompanying drawing explanation
Fig. 1 is the first version schematic diagram of foam core wing;
Fig. 2 is aerofoil hatch frame schematic diagram;
Fig. 3 is foam core wing the second version schematic diagram;
Fig. 4 is wing lower surface mould schematic diagram;
Fig. 5 is upper surface of the airfoil mould schematic diagram.
Detailed description of the invention
Just by reference to the accompanying drawings the utility model is described further below.
As shown in Figure 1, the foam core wing of SUAV (small unmanned aerial vehicle) of the present utility model, comprises covering 2, lower covering 1, upper surface glued membrane 3, foam sandwich laminate 4, lower surface glued membrane 5 and spar 6; Upper covering 2 is fixedly connected with foam sandwich laminate 4, spar 6 by upper surface glued membrane 3, lower covering 1 is fixedly connected with foam sandwich laminate 4, spar 6 by lower surface glued membrane 5, whole filled and process laminboard layer 4 in upper covering 2, cavity between lower covering 1 and spar 6, described spar 6 is fixed by glueing joint with foam sandwich laminate 4.Aerofoil front and rear edges according to actual applying working condition, can increase to lay and strengthens laying, to strengthen front and rear edges intensity.Construction opening needed for aerofoil erecting equipment, can directly process on foam sandwich laminate, and covering fiber laying is complied with opening shape and laid.As shown in Figure 2, rudder face 22 is by being installed on the servos control in opening 21, and opening 21 is direct machine-shaping when preparing foamed core, and covering fiber laying is laid on its surface, and edge of opening can lay reinforcement laying as required.
Upper covering 2, lower covering 1 adopt the composite fiber laying covering of high specific strength, stiffness-to-density ratio, make airfoil structure have good mechanical property.Material or the mixing laying separately such as carbon fiber, glass fibre and aramid fiber can be selected, effectively can improve the intensity of structure.Fill sandwich layer and can adopt the closed pore rigid foamed plastic materials such as Polyurethane foam, connect with covering and the structural adhesion such as beam, rib, improve integral rigidity and the shock resistance of structure.
Spar 6 adopts carbon fiber, aramid fiber laminate structures or strong plastic material.Spar 6 is arranged, and concrete shape and cross section parameter design etc., can change design according to demand, or select other inner structure form.As shown in Figure 3, the another kind of version of foam core wing, it is inner adopts twin-spar construction, comprises front-axle beam 7 and the back rest 6, adopts different cross sectional shapes, and shown in its connection mode with other parts and Fig. 1, single-spar construction is identical.
This airfoil structure has good mechanical property, and structure light wt is efficient.Covering prepared by composite material and girder construction, all have good mechanical characteristic and lower density with foam-filled sandwich layer, stock utilization is higher.Be connected by upper and lower covering by foam sandwich laminate, the lower covering of tension supports the upper covering of pressurized by sandwich layer, therefore this structure has higher yield limit.Simultaneously foam sandwich laminate effectively can also improve rigidity and the impact resistance of airfoil structure, the stall land mode that compatible SUAV (small unmanned aerial vehicle) that can be good is conventional.
This airfoil structure is simple, has good fabrication properties simultaneously, and controlled tooling cost and production cycle.The preparation of foam sandwich laminate and the laying of fabric jacket easy to implement, and crudy is easily controlled, and is applicable to weight in the production of the SUAV (small unmanned aerial vehicle) of below 10kg and applicable requirements.
This airfoil structure has good designability, and the opening of aerofoil and interface can directly design for reinforcement sandwich layer, and composite fiber covering can adapt to core shape and directly lay, without the need to the Cutout reinforcement measure of complexity.Structural integrity is easy to ensure, internal reinforcing structure is connected reliably with integral structure.
Embodiment
In this embodiment, upper covering 2, lower covering 1 adopt aramid fiber laying, and foam sandwich laminate 4 adopts Polyurethane foam, spar 6 is aramid fiber, wherein descend covering 1, upper covering 2 and foam sandwich laminate 4 and spar 6, gluedd joint by glued membrane 3,5 and connect, described glued membrane is preferably epoxide-resin glue.Spar 6 is i-shaped beams.The manufacturing process of this wing is as follows:
On the lower covering die shown in Fig. 4, from pad pasting face, lower surface ground floor is that individual layer aramid fiber plants covering 1, and thickness is 0.2mm.
The second layer is lower surface glued membrane 5, for glueing joint aerofoil covering and foam sandwich laminate 4, spar 6.Foam sandwich laminate 4 is connected by glueing joint with the parts such as spar 6 grade of aerofoil inside.Foam sandwich laminate 4 (comprising internal part such as spar 6 grade) is laid on third layer, is gluedd joint by lower surface glued membrane 5 and lower covering 1.
Upper surface glued membrane 3 is laid on the 4th layer, for glueing joint foam sandwich laminate 4 and upper covering 2.
Upper covering 2 is aramid fabric preferably, is laid on layer 5, thickness 0.2mm.Gluedd joint by upper surface glued membrane 3 and foam sandwich laminate 4.
Upper surface mould as shown in Figure 5 and lower surface mould matched moulds cure under pressure shaping.
Wing lower surface airfoil shape, can be ensured by mould as shown in Figure 4, upper surface airfoil shape, relies on the foam sandwich construction of numerical control machining to ensure.
The wing manufacture of this version, realize by vacuum-bag process technique, each laying inner structures such as (wherein can first be connected by glueing joint) foam sandwich laminate 4 and spars 6 is successively laid, the pressurization of upper/lower die matched moulds, one-step solidification moulding from pad pasting face.
Described in above detailed description of the invention, be preferred version of the present utility model, not for limiting protection domain of the present utility model.
The unspecified part of the utility model belongs to general knowledge as well known to those skilled in the art.

Claims (10)

1. the foam core wing of a SUAV (small unmanned aerial vehicle), it is characterized in that, comprise covering (2), lower covering (1), upper surface glued membrane (3), foam sandwich laminate (4), lower surface glued membrane (5) and spar (6); Upper covering (2) is fixedly connected with foam sandwich laminate (4), spar (6) by upper surface glued membrane (3), lower covering (1) is fixedly connected with foam sandwich laminate (4), spar (6) by lower surface glued membrane (5), whole filled and process laminboard layer (4) in upper covering (2), cavity between lower covering (1) and spar (6), described spar (6) is fixed by glueing joint with foam sandwich laminate (4).
2. the foam core wing of SUAV (small unmanned aerial vehicle) as claimed in claim 1, it is characterized in that: described upper covering and lower covering are composite fiber laying covering, foam sandwich laminate (4) is closed pore rigid foamed plastic materials.
3. the foam core wing of SUAV (small unmanned aerial vehicle) as claimed in claim 1, is characterized in that: described upper covering and lower covering are carbon fiber, aramid fiber or glass fiber material laying.
4. the foam core wing of SUAV (small unmanned aerial vehicle) as claimed in claim 1, is characterized in that: described upper covering and lower covering are the mixing laying of carbon fiber, aramid fiber and glass fiber material.
5. the foam core wing of SUAV (small unmanned aerial vehicle) as claimed in claim 1, it is characterized in that: described upper covering and lower covering adopt aramid fiber laying, described foam sandwich laminate (4) is Polyurethane foam, and the material of described spar (6) is aramid fiber.
6. the foam core wing of SUAV (small unmanned aerial vehicle) as claimed in claim 4, is characterized in that: the thickness of described upper and lower covering is 0.2mm.
7. the foam core wing of SUAV (small unmanned aerial vehicle) as claimed in claim 1, is characterized in that: aerofoil opening portion is directly in the upper processing of foam sandwich laminate (4), and upper and lower covering adapts to opening shape and lays.
8. the foam core wing of SUAV (small unmanned aerial vehicle) as claimed in claim 1, is characterized in that: aerofoil blank area mounting hole is directly in the upper processing of foam sandwich laminate (4), and attaching parts is embedded in foam sandwich laminate (4).
9. the foam core wing of SUAV (small unmanned aerial vehicle) as claimed in claim 1, is characterized in that: foam sandwich laminate (4) is Polyurethane foam.
10. the foam core wing of SUAV (small unmanned aerial vehicle) as claimed in claim 1, is characterized in that: spar (6) adopts carbon fiber, aramid fiber laminate structures or strong plastic material.
CN201520946193.XU 2015-11-24 2015-11-24 Unmanned aerial vehicle's foam presss from both sides core wing Active CN205150216U (en)

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Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN106043666A (en) * 2016-08-24 2016-10-26 广州朱雀航空科技有限公司 Wing of unmanned plane
CN106275386A (en) * 2016-09-05 2017-01-04 锋源创新科技成都有限公司 A kind of wing, the manufacture method of wing and unmanned plane
WO2018032723A1 (en) * 2016-08-16 2018-02-22 前海星航(深圳)科技有限公司 Unmanned aerial vehicle, tool for molding housing of unmanned aerial vehicle, and molding process
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
CN108116656A (en) * 2017-12-20 2018-06-05 广东翼景信息科技有限公司 A kind of solar energy unmanned plane
CN108995246A (en) * 2018-06-20 2018-12-14 西北工业大学 A kind of small-sized wing integrally forming mould and forming method based on VARTM
CN109229335A (en) * 2018-08-06 2019-01-18 中国航空工业集团公司沈阳飞机设计研究所 A kind of integrally formed part of light high-stiffness composite material wing fence
CN109470089A (en) * 2018-11-23 2019-03-15 江西洪都航空工业集团有限责任公司 A kind of short beam sandwich mini-bomb wing structure
CN109591329A (en) * 2018-10-25 2019-04-09 江苏恒神股份有限公司 A kind of carbon fiber full-height foam core filled composite material rudder face structure and preparation method thereof
CN110510145A (en) * 2019-08-30 2019-11-29 中国民用航空飞行学院 Three beam type composite wing overall structures of one kind and its moulding technique
CN110815862A (en) * 2019-10-12 2020-02-21 哈尔滨飞机工业集团有限责任公司 Laying method of full-height foam sandwich airfoil surface layer
CN110978567A (en) * 2019-12-17 2020-04-10 航天特种材料及工艺技术研究所 Structure function integrated composite material wing and integral forming method thereof

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2018032723A1 (en) * 2016-08-16 2018-02-22 前海星航(深圳)科技有限公司 Unmanned aerial vehicle, tool for molding housing of unmanned aerial vehicle, and molding process
CN106043666A (en) * 2016-08-24 2016-10-26 广州朱雀航空科技有限公司 Wing of unmanned plane
CN106275386A (en) * 2016-09-05 2017-01-04 锋源创新科技成都有限公司 A kind of wing, the manufacture method of wing and unmanned plane
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
CN108116656A (en) * 2017-12-20 2018-06-05 广东翼景信息科技有限公司 A kind of solar energy unmanned plane
CN108995246A (en) * 2018-06-20 2018-12-14 西北工业大学 A kind of small-sized wing integrally forming mould and forming method based on VARTM
CN109229335A (en) * 2018-08-06 2019-01-18 中国航空工业集团公司沈阳飞机设计研究所 A kind of integrally formed part of light high-stiffness composite material wing fence
CN109591329A (en) * 2018-10-25 2019-04-09 江苏恒神股份有限公司 A kind of carbon fiber full-height foam core filled composite material rudder face structure and preparation method thereof
CN109470089A (en) * 2018-11-23 2019-03-15 江西洪都航空工业集团有限责任公司 A kind of short beam sandwich mini-bomb wing structure
CN109470089B (en) * 2018-11-23 2021-08-20 江西洪都航空工业集团有限责任公司 Small-size bullet wing structure of short beam core
CN110510145A (en) * 2019-08-30 2019-11-29 中国民用航空飞行学院 Three beam type composite wing overall structures of one kind and its moulding technique
CN110815862A (en) * 2019-10-12 2020-02-21 哈尔滨飞机工业集团有限责任公司 Laying method of full-height foam sandwich airfoil surface layer
CN110978567A (en) * 2019-12-17 2020-04-10 航天特种材料及工艺技术研究所 Structure function integrated composite material wing and integral forming method thereof

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