CN205366051U

CN205366051U - Carbon fiber small aircraft

Info

Publication number: CN205366051U
Application number: CN201521134607.5U
Authority: CN
Inventors: 罗世彬; 赵贺; 吴雷
Original assignee: Hunan Airtops Intelligent Technology Co Ltd
Current assignee: Hunan Airtops Intelligent Technology Co Ltd
Priority date: 2015-12-30
Filing date: 2015-12-30
Publication date: 2016-07-06
Anticipated expiration: 2025-12-30

Abstract

The utility model discloses a carbon fiber small aircraft, two wings including fuselage and symmetrical arrangement, fuselage and wing integrated into one piece, two the wing all is the triangle wing section, and the trailing edge department of wing all is equipped with convex fin, every all be equipped with a screw power assembly on the fin, the edge of wing and fin has all covered carbon fiber prepreg layer and epoxy layer, be equipped with control assembly on the fuselage. This carbon fiber small aircraft simple structure, fundamentally solve carbon fiber small aircraft edge sharpness, burr, easily cut the problem of hand, and are difficult for the layering, drop, are able to bear or endure to hit, in addition, these goods still have the advantage that deformation shrinkage is little, dimensional stability good, hardness is high, the pliability is good.

Description

Carbon fiber small aircraft

Technical field

This utility model relates to small aircraft field, particularly to a kind of carbon fiber small aircraft.

Background technology

Appearance along with carbon fiber " paper helicopter "; fuselage and wing profile also become more and more attractive in appearance; but owing to " paper helicopter " fuselage and wing thickness are very thin; and the intensity of carbon fiber own, rigidity and toughness are higher; therefore; " paper helicopter " edge would generally ratio sharp, this obviously give operator safety cause certain potential safety hazard.Generally, the problem of sharp for part edge, jagged, oarsman, usual means are exactly at part edge road fillet, but owing to " paper helicopter " edge thickness only has 0.3mm, rounding is also unrealistic.

Easily hurt, scratch measure that the problem of operator adopts usually after the burr of manufacturing process sand papering part edge for " paper helicopter " edge in the market, one layer of varnish of surface spraying, but part edge is due to thinner thickness when spraying paint, edge as depicted be cannot adhere to effective enamelled coating (after spraying paint, the enamelled coating on edge due to adhesive force relatively low and very easily fall paint).This way is not in the problem fundamentally solving sharp edges；Further, if aircraft utilization process occurs that shock falls the problem such as burr, overlap that can cause when painting, it is more easy to the hidden danger that oarsman occurs.

Utility model content

Based on this, this utility model provides the carbon fiber small aircraft of a kind of anti-cutting hands.

The concrete technical scheme solving above-mentioned technical problem is as follows:

A kind of carbon fiber small aircraft, including fuselage and two wings being arranged symmetrically with, described fuselage and wing are one-body molded, two described wings are all in triangle aerofoil profile, the trailing edge place of wing is equipped with the empennage of protrusion, being equipped with a propeller power assembly on each described empennage, the edge of described wing and empennage is all covered with the carbon fibre initial rinse bed of material and epoxy resin layer, and described fuselage is provided with control assembly.

As further improvement of the utility model, the number of plies of the described carbon fibre initial rinse bed of material and epoxy resin layer is multiple, and one_to_one corresponding, and wing innermost layer is the carbon fibre initial rinse bed of material, and from innermost layer outward, epoxy resin layer and the carbon fibre initial rinse bed of material successively cover mutually.

As further improvement of the utility model, the width of the described carbon fiber preadmission bed of material is 10mm-15mm.

As further improvement of the utility model, between described carbon fiber prepreg slice width degree, carbon fibre initial rinse thickness of feed layer, epoxy resin layer thickness, ratio is 10-15:0.2:0.5.

As further improvement of the utility model, described wing outermost layer is coated with skin of paint.

As further improvement of the utility model, between the thickness of described skin of paint and the carbon fibre initial rinse bed of material, ratio is 2:1.

Carbon fiber small aircraft described in the utility model has the following advantages and beneficial effect:

(1) this utility model simple in construction, fundamentally solves carbon fiber small aircraft sharp edges, burr, easily cuts the problem of hands, and be not easily layered, come off, crashworthiness；The advantage that deformation retract is little, good stability of the dimension, hardness high it addition, these goods also have, pliability is good.

(2) this utility model is by laying the carbon fibre initial rinse bed of material in wing edge, add the thickness at edge on the one hand, namely the strength and stiffness at wing edge are added, use continuous fiber layer cladding wing edge on the other hand, avoid the exposed of carbon fiber, not cracky when making small aircraft occur to clash in flight drop event, is not easy to scratch operator simultaneously；It is coated with epoxy resin layer afterwards so that the wing edge of the prepreg of coated mistake, by one layer of continuous print resin-coating, forms fillet, further functions as the effect of cut-protection after solidification；This is owing to containing active epoxide group in the strand of epoxy resin, this group may be located at molecule chain end, centre or structure in the form of a ring, and this makes epoxy resin can form the insoluble high polymer with tridimensional network with the firming agent generation cross-linking reaction of multiple types；So the epoxy resin after solidifying has excellent adhesion strength with the carbon fibre initial rinse bed of material；Also have, in the curing process, due to capillary effect, resin shrinkage, it is coated on wing edge and forms similar drop-shaped " resin mass ", namely wing edge will by not havinging wedge angle, right angle after solidifying, but small round corner, and deformation retract is little, product size good stability, hardness is high, and pliability is good.

(3) making of this utility model wing is simple, convenient, it is not necessary to wing edge is done substantial amounts of polishing, only need to be coated with.

Accompanying drawing explanation

Fig. 1 is the structural representation of this utility model carbon fiber small aircraft.

Fig. 2 is the cross-sectional edge view of A wing in Fig. 1.

Description of reference numerals

1, fuselage；2, wing；3, propeller power assembly；4, assembly is controlled；5, the carbon fibre initial rinse bed of material；6, epoxy resin layer；7, skin of paint；8, empennage.

Detailed description of the invention

Below with reference to specific embodiment, this utility model is described further.

Referring to Fig. 1-Fig. 2, a kind of carbon fiber small aircraft, including fuselage 1 and two wings 2 being arranged symmetrically with, described fuselage 1 and wing 2 are one-body molded, two described wings 2 are all in triangle aerofoil profile, and the trailing edge place of wing 2 is equipped with the empennage 8 of protrusion, and each described empennage 8 is equipped with a propeller power assembly 3, the edges cover of described wing 2 and empennage 8 has the carbon fibre initial rinse bed of material 5 and epoxy resin layer 6, described fuselage 1 to be provided with control assembly 4.The number of plies of the described carbon fibre initial rinse bed of material 5 and epoxy resin layer 6 is 1 layer (can be also multilamellar in other specific embodiments), and one_to_one corresponding, wing 2 innermost layer is the carbon fibre initial rinse bed of material 5, and from innermost layer outward, epoxy resin layer 6 and the carbon fibre initial rinse bed of material 5 successively cover mutually.This utility model simple in construction, fundamentally solves carbon fiber small aircraft sharp edges, burr, easily cuts the problem of hands, and be not easily layered, come off, crashworthiness；The advantage that deformation retract is little, good stability of the dimension, hardness high it addition, these goods also have, pliability is good；The carbon fibre initial rinse bed of material 5 is laid in wing 2 edge, add the thickness at edge on the one hand, namely the strength and stiffness at wing 2 edge are added, use continuous fiber layer cladding wing 2 edge on the other hand, avoid the exposed of carbon fiber, not cracky when making small aircraft occur to clash in flight drop event, is not easy to scratch operator simultaneously；It is coated with epoxy resin layer 6 afterwards so that wing 2 edge of the prepreg of coated mistake, by one layer of continuous print resin-coating, forms fillet, further functions as the effect of cut-protection after solidification；This is owing to containing active epoxide group in the strand of epoxy resin, this group may be located at molecule chain end, centre or structure in the form of a ring, and this makes epoxy resin can be formed with the firming agent generation cross-linking reaction of multiple types insoluble to have the cancellated high polymer of three-dimensional；So the epoxy resin after solidifying has excellent adhesion strength with the carbon fibre initial rinse bed of material 5；Also have, in the curing process, due to capillary effect, resin shrinkage, it is coated on wing edge and forms similar drop-shaped " resin mass ", namely wing edge will by not havinging wedge angle, right angle after solidifying, but small round corner, and deformation retract is little, product size good stability, hardness is high, and pliability is good.

Further, the width of the described carbon fiber preadmission bed of material 5 is 10-15mm；This width range edge Varying-thickness region transfers is mild, and stress distribution is uniform, is unlikely to occur that bigger stress is concentrated.

Further, the described carbon fibre initial rinse bed of material 5 width, the carbon fibre initial rinse bed of material 5 thickness, between epoxy resin layer 6 thickness than being 10-15:0.2:0.5.This ratio is more uniform, is all unlikely to the lofty especially of transition opening up thickness direction backward；During structural member Varying-thickness, redistributing of stress can be caused relative to slab construction, and lofty Varying-thickness point very easily occurs that stress is concentrated, and cause local stress to destroy.

Further, described wing outermost layer is coated with skin of paint 7.

Further, between described skin of paint 7 and the thickness of the carbon fibre initial rinse bed of material 5, ratio is 2:1.

Below being only preferred implementation of the present utility model, protection domain of the present utility model is not limited merely to above-described embodiment, and all technical schemes belonged under this utility model thinking belong to protection domain of the present utility model.It should be pointed out that, for those skilled in the art, without departing from the some improvements and modifications under this utility model principle premise, should be regarded as protection domain of the present utility model.

Claims

1. a carbon fiber small aircraft, it is characterized in that, including fuselage and two wings being arranged symmetrically with, described fuselage and wing are one-body molded, two described wings are all in triangle aerofoil profile, and the trailing edge place of wing is equipped with the empennage of protrusion, and each described empennage is equipped with a propeller power assembly, the edge of described wing and empennage is all covered with the carbon fibre initial rinse bed of material and epoxy resin layer, and described fuselage is provided with control assembly.

2. carbon fiber small aircraft according to claim 1, it is characterized in that, the number of plies of the described carbon fibre initial rinse bed of material and epoxy resin layer is multiple, and one_to_one corresponding, wing innermost layer is the carbon fibre initial rinse bed of material, from innermost layer outward, epoxy resin layer and the carbon fibre initial rinse bed of material successively cover mutually.

3. carbon fiber small aircraft according to claim 1 and 2, it is characterised in that the width of the described carbon fiber preadmission bed of material is 10mm-15mm.

4. carbon fiber small aircraft according to claim 3, it is characterised in that between described carbon fiber prepreg slice width degree, carbon fibre initial rinse thickness of feed layer, epoxy resin layer thickness, ratio is 10-15:0.2:0.5.

5. carbon fiber small aircraft according to claim 4, it is characterised in that described wing outermost layer is coated with skin of paint.

6. carbon fiber small aircraft according to claim 5, it is characterised in that between the thickness of described skin of paint and the carbon fibre initial rinse bed of material, ratio is 2:1.