CN102795338B - Micro unmanned aerial vehicle carbon fiber rotor wing and preparation method thereof - Google Patents
Micro unmanned aerial vehicle carbon fiber rotor wing and preparation method thereof Download PDFInfo
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- CN102795338B CN102795338B CN201210264340.6A CN201210264340A CN102795338B CN 102795338 B CN102795338 B CN 102795338B CN 201210264340 A CN201210264340 A CN 201210264340A CN 102795338 B CN102795338 B CN 102795338B
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- 229920000049 Carbon (fiber) Polymers 0.000 title claims abstract description 55
- 239000004917 carbon fiber Substances 0.000 title claims abstract description 55
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 title claims abstract description 55
- 238000002360 preparation method Methods 0.000 title claims abstract description 17
- 239000010410 layer Substances 0.000 claims abstract description 44
- 239000002131 composite material Substances 0.000 claims abstract description 4
- 239000004744 fabric Substances 0.000 claims description 25
- 210000002615 epidermis Anatomy 0.000 claims description 18
- 238000000465 moulding Methods 0.000 claims description 17
- 239000011229 interlayer Substances 0.000 claims description 13
- 238000000034 method Methods 0.000 claims description 13
- 229910000831 Steel Inorganic materials 0.000 claims description 4
- 239000003795 chemical substances by application Substances 0.000 claims description 4
- 229920001971 elastomer Polymers 0.000 claims description 4
- 239000000463 material Substances 0.000 claims description 4
- 229920000260 silastic Polymers 0.000 claims description 4
- 239000010959 steel Substances 0.000 claims description 4
- 238000005987 sulfurization reaction Methods 0.000 claims description 4
- YCKRFDGAMUMZLT-UHFFFAOYSA-N Fluorine atom Chemical compound [F] YCKRFDGAMUMZLT-UHFFFAOYSA-N 0.000 claims description 3
- 238000005520 cutting process Methods 0.000 claims description 3
- 238000005538 encapsulation Methods 0.000 claims description 3
- 229910052731 fluorine Inorganic materials 0.000 claims description 3
- 239000011737 fluorine Substances 0.000 claims description 3
- 239000000565 sealant Substances 0.000 claims description 3
- 238000007711 solidification Methods 0.000 claims description 3
- 230000008023 solidification Effects 0.000 claims description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 2
- -1 airfelt Substances 0.000 claims description 2
- 238000011074 autoclave method Methods 0.000 claims description 2
- 229910052799 carbon Inorganic materials 0.000 claims description 2
- 230000007423 decrease Effects 0.000 claims description 2
- 230000001815 facial effect Effects 0.000 claims description 2
- 239000000835 fiber Substances 0.000 claims description 2
- 239000007788 liquid Substances 0.000 claims description 2
- 239000004033 plastic Substances 0.000 abstract description 12
- 229920003023 plastic Polymers 0.000 abstract description 12
- 239000002344 surface layer Substances 0.000 abstract 6
- 230000003014 reinforcing effect Effects 0.000 abstract 4
- 239000004593 Epoxy Substances 0.000 description 5
- 238000011160 research Methods 0.000 description 5
- 239000011347 resin Substances 0.000 description 3
- 229920005989 resin Polymers 0.000 description 3
- 238000013461 design Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005265 energy consumption Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 229920006305 unsaturated polyester Polymers 0.000 description 2
- PRPAGESBURMWTI-UHFFFAOYSA-N [C].[F] Chemical compound [C].[F] PRPAGESBURMWTI-UHFFFAOYSA-N 0.000 description 1
- 239000002390 adhesive tape Substances 0.000 description 1
- OFCNXPDARWKPPY-UHFFFAOYSA-N allopurinol Chemical compound OC1=NC=NC2=C1C=NN2 OFCNXPDARWKPPY-UHFFFAOYSA-N 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
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- 208000020442 loss of weight Diseases 0.000 description 1
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- 239000005011 phenolic resin Substances 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
- 238000003860 storage Methods 0.000 description 1
- 230000003746 surface roughness Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
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Abstract
The invention relates to a micro unmanned aerial vehicle carbon fiber rotor wing and a preparation method thereof, belonging to the technical field of composite material structures. The rotor wing sequentially comprises a wing tip, a wing body and a wing root from two ends to middle; the wing tip sequentially comprises an upper surface layer and a lower surface layer from top to bottom; the wing body sequentially comprises an upper surface layer, a reinforcing rib, a middle layer and a lower surface layer from top to bottom; the wing root sequentially comprises an upper surface layer, a reinforcing rib, a reinforcing layer, a middle layer and a lower surface layer from top to bottom; and each reinforcing rib extends from the wing root to the critical part of the wing body and the wing tip and is narrowed gradually. Compared with a domestic plastic rotor wing with the same specification, the weight of the rotor wing provided by the invention is reduced by 65%; under unit mass, the output power of the rotor wing provided by the invention is 3.4 times that of the plastic rotor wing; under unit power consumption, the output power of the rotor wing provided by the invention is 1.3 times that of the plastic rotor wing; and under the condition of generating the same lifting power, the power consumption of the rotor wing provided by the invention is reduced by 40%, and the rotation speed is reduced by 30%. The rotor wing provided by the invention can improve the lift efficiency of an unmanned aerial vehicle under the conditions of low rotation speed and low power consumption.
Description
Technical field
The present invention relates to a kind of microminiature unmanned plane carbon fiber rotor and preparation method thereof, belong to composite structure technical field.
Background technology
People are less than 2m by the span/length conventionally, quality is called SUAV (small unmanned aerial vehicle) less than the unmanned plane of 50kg, and the unmanned plane that the span/length is less than to 1kg less than 30cm, quality is called Micro Aerial Vehicle.
In the country of Helicopter Technology prosperity, pilotless helicopter starts to have developed very early.Unmanned plane has the various fight functions that general battlefield needs, and energy scouting, supervision, flight, can give other operational weapon indicating targets, can also participate in a kind of ubiquitous countermeasure activity one electronic warfare on future battlefield.
With foresight with respect to developed country at unmanned plane field of research, China starts late in the research in this field.Due to China in the research in unmanned plane field always in following state, tachnical storage deficiency, drops into strength little, superior consciousness is also nowhere near, cause Research Group small in domestic this field at present, let alone large-scale industrialization.
The performance objective of rotor is high lift, low resistance.The rotary wing performance of microminiature unmanned plane requires than the height of big payload helicopter.Because microminiature cyclogyro must strictly limit its size.Due to Airflow Environment difference, the method for research big payload helicopter rotary wing performance can not be applicable to microminiature unmanned plane rotor completely.So design has increased greatly once the difficulty of secondary microminiature unmanned plane rotor.
The Design and manufacture of rotor is the gordian technique of microminiature unmanned plane.In order to solve the vibration problem in when rotation, rotor does gently and firm, and the waving of rotor, shimmy and torsional stiffness reduce gradually from wing root to wing tip, so wing tip is flexible larger than wing root.Be model of an airplane plastics rotor used and the rotor of domestic microminiature unmanned plane adopts, select that its quality of plastics rotor is large, lift is low; Under unit power consumption, horsepower output is little, in the situation that voyage is long, highly high, can not meet flight requirement.
Summary of the invention
The object of the invention is in order to propose a kind of microminiature unmanned plane carbon fiber rotor and preparation method thereof, this rotor quality is little, rigidity is high, intensity is high, anti-flutter is good, fatigue resistance is good; Under unit power consumption, horsepower output is large.
The object of the invention is to be achieved through the following technical solutions.
A kind of microminiature unmanned plane carbon fiber rotor of the present invention, this rotor is followed successively by wing tip, wing body and wing root from both ends to the middle;
Wing tip is followed successively by upper epidermis and lower top layer from top to bottom;
Wing body is followed successively by upper epidermis, reinforced rib, interlayer and lower top layer from top to bottom;
Wing root is followed successively by upper epidermis, reinforced rib, enhancement Layer, interlayer and lower top layer from top to bottom;
Above-mentioned upper epidermis adopts 45 ° of carbon fiber plains cloth;
Above-mentioned lower top layer adopts 45 ° of carbon fiber plains cloth; Upper epidermis and lower top layer are symmetrical ply sequence;
Above-mentioned reinforced rib is extended to the critical place of wing body and wing tip by wing root, and narrows gradually; Reinforced rib adopts high modulus carbon fiber or high-strength carbon fiber, and ply sequence is 0
n; If reinforced rib is many, the axis of every reinforced rib all overlaps, and different reinforced rib width is from the bottom to top staged and successively decreases;
Above-mentioned interlayer is more than 1 layer, adopts carbon fibre fabric or carbon fiber one-way band;
Above-mentioned enhancement Layer adopts carbon fiber plain cloth, is more than 1 layer, and ply sequence is (0/90)
n.
The preparation method of a kind of microminiature unmanned plane carbon fiber rotor of the present invention, the concrete steps of the method are:
The first step, makes reinforced rib
Adopt high modulus carbon fiber prepreg or high-strength carbon fiber prepreg, according to 0
nmode laying, adopt vacuum bag molding or autoclave method curing molding, then reach the oad of setting by machine up;
Second step, makes mould
Mould is made up of three parts, is respectively rigid die, preform soft mode and large deformation rate silaatic soft mode; Rigid die is wherein formpiston, and material can be steel or composite material, and rigid die comprises base and boss, and base is a platform, and the appearance profile of boss is consistent with the appearance profile of rotor, and the upper surface shape face of boss is consistent with the shape face of rotor; Preform soft mode is rubber soft mode, and its cavity shape and boss surrounding shape are coincide, and its height is higher than boss vertex 6～8mm; Large deformation rate silaatic soft mode is sheet silaatic soft mode, and its deformation rate is greater than 300%, thickness 3-5mm, and its profile is consistent with the upper surface shape face of boss;
The 3rd step, laying
45 ° of carbon fiber plain cloth prepregs on top layer under the rigid die surface of release agent application first spreads, paving is covered the reinforced rib described in enhancement Layer and the first step at interlayer, wing root position successively again, finally spread 45 ° of carbon fiber plain cloth prepregs on top layer, upper epidermis and lower top layer are symmetrical laying, obtain laying thing;
The 4th step, mould assembling, encapsulation
Surrounding in rigid die is placed preform soft mode, at the laying thing surface coverage large deformation rate silaatic soft mode described in the 3rd step, is then sealed to a vacuum bag with ventilative fluorine cloth, airfelt, sealant tape and vacuum bag film;
The 5th step, curing molding
Vacuum bag described in the 4th step is put into autoclave, curing molding.
In described the 5th step, the condition of curing molding decides according to preparing prepreg resin used, and resin can be the one in epoxy resin, unsaturated polyester (UP), phenol resin, but is not limited to this three kinds of resins.
Beneficial effect
Compared with the domestic plastics rotor of same size, carbon fiber rotor loss of weight 65% of the present invention; Under unit mass, the horsepower output of carbon fiber rotor of the present invention is 3.4 times of plastics rotor; Under unit power consumption, horsepower output is 1.3 times of plastics rotor; Producing same lift in the situation that, carbon fiber rotor of the present invention is low in energy consumption 40%, rotating speed is low by 30%.
Carbon fiber gyroplane rotate speed of the present invention is low, low in energy consumption, thereby has greatly improved the efficiency of unmanned plane lift system.
Brief description of the drawings
Fig. 1 is the rotor structure schematic diagram that removes top layer in embodiment 1;
Fig. 2 is the A-A cutaway view in Fig. 1;
Fig. 3 is the B-B cutaway view in Fig. 1;
Fig. 4 is the C-C cutaway view in Fig. 1;
Fig. 5 is the structural representation of rigid die in embodiment 1;
Wherein, 1-base, 2-boss, 3-enhancement Layer, 4-reinforced rib, 5-upper epidermis, 6-interlayer, top layer under 7-.
Detailed description of the invention
Below in conjunction with drawings and Examples, the invention will be further described.
Embodiment
A kind of microminiature unmanned plane carbon fiber rotor, as shown in Figure 1; This rotor is followed successively by wing tip, wing body and wing root from both ends to the middle; The total length of this rotor is 410mm, starts at as initial point from the center of rotor, is negative in the left side of initial point, is just on the right side of initial point, and from-45 to+45 is wing root, from-190 to-45 and+45 to+190 be wing body, other parts are wing tip;
Wing tip is followed successively by upper epidermis 5 and lower top layer 7 from top to bottom; As shown in Figure 2;
Wing body is followed successively by upper epidermis 5, reinforced rib 4, interlayer 6 and lower top layer 7 from top to bottom; As shown in Figure 3;
Wing root is followed successively by upper epidermis 5, reinforced rib 4, enhancement Layer 3, interlayer 6 and lower top layer 7 from top to bottom; As shown in Figure 4;
Above-mentioned upper epidermis 5 adopts 45 ° of carbon fiber plains cloth;
Above-mentioned lower top layer 7 adopts 45 ° of carbon fiber plains cloth; Upper epidermis 5 and lower top layer 7 are symmetrical ply sequence;
Above-mentioned reinforced rib 4 from-20 to-190 narrows gradually and narrows gradually from+20 to+190; Reinforced rib 4 adopts high modulus carbon fiber, and ply sequence is 0
2; Totally four of reinforced ribs 4, wherein have two left sides that are distributed in rotor, become up and down and distribute, and the width of upper strata reinforced rib is less than the width of lower floor's reinforced rib; Two other is distributed in the right side of rotor, with two, left side reinforced rib symmetry; The dead in line of upper strata and lower floor's reinforced rib;
Above-mentioned interlayer 6 is 1 layer, adopts carbon fiber plain cloth;
Above-mentioned enhancement Layer 3 is 2 layers, adopts carbon fiber plain cloth, and ply sequence is (0/90)
2.
A preparation method for microminiature unmanned plane carbon fiber rotor, the concrete steps of the method are:
The first step, makes reinforced rib
Adopt high modulus carbon fiber/epoxy prepreg, according to 0
2mode laying, adopt vacuum bag molding curing molding, then reach the oad of reinforced rib by machine up; The condition of vacuum bag molding curing molding is: degree of vacuum is-0.1MPa that temperature is 165 DEG C ± 5 DEG C; The length of reinforced rib is 170mm, and lower floor's reinforced rib width is reduced to gradually and is not more than 0.1mm from the 10mm of one end, and upper strata reinforced rib width is reduced to gradually and is not more than 0.1mm from the 5mm of one end;
Second step, makes mould
Mould is made up of three parts, is respectively rigid die, preform soft mode and large deformation rate silaatic soft mode; Rigid die is wherein formpiston, and material is steel, and rigid die comprises base 1 and boss 2, and as shown in Figure 5, base 1 is a platform, and the appearance profile of boss 2 is consistent with the appearance profile of rotor, and the upper surface shape face of boss 2 is consistent with the shape face of rotor.The surface roughness Ra of rigid die upper surface should be not more than 1.6; Material is No. 45 steel, and after modifier treatment, hardness should be in the scope of HRC27～32;
The method for making of preform soft mode is: sulphurated siliastic is not cut into small pieces, be centered around the surrounding of rigid die boss 2, height is higher than rigid die vertex 8mm, then put into autoclave and make its sulfuration, rubber soft mode outer rim after sulfuration is concordant with the outer rim of rigid die base 1, and the outside surrounding of inner chamber and rigid die boss 2 fits; The effect of preform soft mode has two: the one, make the unitary mould profile rule after assembling, and conveniently encapsulate and vacuumize; The 2nd, can effectively stop in solidification process glue excessive;
The method for making of large deformation rate silaatic soft mode is: by the SILASTIC T-4 host of bi-component liquid state and SILASTIC T-4 curing agent, after mixing at 100: 10 according to mass ratio, be cast into flat soft mode, thickness is 5mm, then according to the upper surface shape facial contour cutting soft mode of boss 2; Its deformation rate is 400%, and in rotor solidification process, this soft mode can be fitted well with the laying thing surface of rotor curved surface, thereby realizes the evenly object of pressurization;
The 3rd step, laying
Paste die face paving following table floor height strength carbon fiber plain cloth/epoxy prepreg at the upper surface of rigid die that applies F-57NC fluorine carbon mold release, ply sequence is (± 45), the warp thread direction of fabric and rotor be axially 45 °; Repave interlayer: 1 floor height strength carbon fiber plain cloth/epoxy prepreg, ply sequence is (0/90), the warp thread direction of fabric and rotor is axial consistent; Then at wing root region paving enhancement Layer: 2 floor height strength carbon fiber plain cloth/epoxy prepregs, ply sequence is (0/90)
2; Respectively spread 2 reinforced ribs that prepared on left side, the right side of rotor respectively again, the length direction of reinforced rib is axial consistent with rotor, and the reinforced rib on left side, right side is symmetrical; Finally spread top layer: high-strength carbon fiber plain cloth/epoxy prepreg, ply sequence is (± 45), is symmetrical laying with lower top layer;
Along the outer rim of rigid die boss 2, cutting prepreg, makes its profile consistent with boss 2 outer rims of rigid die;
The 4th step, mould assembling, encapsulation
In the prepreg outside of laying, it is the surrounding of rigid die boss 2, suit preform soft mode, the upper surface of its lower surface and rigid die base 1 is fitted, cover ready large deformation rate silaatic soft mode at the upper surface of laying thing subsequently, finally, with adhesive tape, three part moulds are fixed together;
In the coated ventilative fluorine cloth of outside face, the airfelt of mould, then use Feng Chengyi vacuum bag of sealant tape and vacuum bag film;
The 5th step, curing molding
Vacuum bag described in the 4th step is put into autoclave, curing molding, the condition of curing molding is 165 DEG C ± 5 DEG C of temperature, external pressure 0.2MPa, by rotor curing molding.
The carbon fiber rotor chord 410mm of preparation according to the method described above, quality is 13g, under the condition of same size, has alleviated 65% than the quality of plastics rotor; And its appearance is bright and clean, attractive in appearance, confirm through Ultrasonic Nondestructive, inner without layering, be mingled with, the defect such as hole.
In the lift testing experiment of rotor, in the time that rotating speed is 2490r/min, the lift of generation is 406g, and power consumption is 44.9w.Compared with plastics rotor, under unit mass, the power of carbon fiber rotor output is 3.4 times of plastics rotor; Under unit power consumption, the horsepower output of carbon fiber rotor is 1.3 times of plastics rotor.
Claims (9)
1. a preparation method for microminiature unmanned plane carbon fiber rotor, this rotor is followed successively by wing tip, wing body and wing root from both ends to the middle;
Wing tip is followed successively by upper epidermis and lower top layer from top to bottom;
Wing body is followed successively by upper epidermis, reinforced rib, interlayer and lower top layer from top to bottom;
Wing root is followed successively by upper epidermis, reinforced rib, enhancement Layer, interlayer and lower top layer from top to bottom;
Upper epidermis and lower top layer are symmetrical ply sequence;
Reinforced rib is extended to the critical place of wing body and wing tip by wing root, and narrows gradually;
The concrete steps that it is characterized in that the method are:
The first step, makes reinforced rib
Adopt high modulus carbon fiber prepreg or high-strength carbon fiber prepreg, according to the mode laying of 0n, adopt vacuum bag molding or autoclave method curing molding, then reach the oad of setting by machine up;
Second step, makes mould
Mould is made up of three parts, is respectively rigid die, preform soft mode and large deformation rate silaatic soft mode; Rigid die is wherein formpiston, material is steel or composite material, rigid die comprises base (1) and boss (2), base (1) is a platform, the appearance profile of boss (2) is consistent with the appearance profile of rotor, and the upper surface shape face of boss (2) is consistent with the shape face of rotor; Preform soft mode is rubber soft mode, and its cavity shape and boss (2) surrounding shape is coincide, and its height is higher than boss (2) vertex 6～8mm; Large deformation rate silaatic soft mode is sheet silaatic soft mode, and its deformation rate is greater than 300%, thickness 3-5mm, and its profile is consistent with the upper surface shape face of boss (2);
The 3rd step, laying
45 ° of carbon fiber plain cloth prepregs on top layer under the rigid die surface of release agent application first spreads, paving is covered the reinforced rib described in enhancement Layer and the first step at interlayer, wing root position successively again, finally spread 45 ° of carbon fiber plain cloth prepregs on top layer, upper epidermis and lower top layer are symmetrical laying, obtain laying thing;
The 4th step, mould assembling, encapsulation
Surrounding in rigid die is placed preform soft mode, at the laying thing surface coverage large deformation rate silaatic soft mode described in the 3rd step, is then sealed to a vacuum bag with ventilative fluorine cloth, airfelt, sealant tape and vacuum bag film;
The 5th step, curing molding
Vacuum bag described in the 4th step is put into autoclave, curing molding.
2. the preparation method of a kind of microminiature unmanned plane carbon fiber rotor according to claim 1, it is characterized in that: the method for making of preform soft mode is: sulphurated siliastic is not cut into small pieces, be centered around the surrounding of rigid die boss (2), height is higher than rigid die vertex 6～8mm, then put into autoclave and make its sulfuration, rubber soft mode outer rim after sulfuration is concordant with the outer rim of rigid die base (1), and the outside surrounding of inner chamber and rigid die boss (2) fits.
3. the preparation method of a kind of microminiature unmanned plane carbon fiber rotor according to claim 1, it is characterized in that: the method for making of large deformation rate silaatic soft mode is: by the SILASTIC T-4 host of bi-component liquid state and SILASTIC T-4 curing agent, after mixing at 100: 10 according to mass ratio, be cast into flat soft mode, thickness is 3-5mm, then according to the upper surface shape facial contour cutting soft mode of boss (2); Its deformation rate is for being greater than 300%, and in rotor solidification process, fit in the laying thing surface of this soft mode and rotor curved surface.
4. the preparation method of a kind of microminiature unmanned plane carbon fiber rotor according to claim 1, is characterized in that: upper epidermis adopts 45 ° of carbon fiber plains cloth.
5. the preparation method of a kind of microminiature unmanned plane carbon fiber rotor according to claim 1, is characterized in that: lower top layer adopts 45 ° of carbon fiber plains cloth.
6. the preparation method of a kind of microminiature unmanned plane carbon fiber rotor according to claim 1, is characterized in that: reinforced rib adopts high modulus carbon fiber or high-strength carbon fiber, and ply sequence is 0
n, reinforced rib is more than 1.
7. the preparation method of a kind of microminiature unmanned plane carbon fiber rotor according to claim 6, is characterized in that: when reinforced rib is greater than 1, and the dead in line of upper strata and lower floor's reinforced rib, different reinforced rib width is from the bottom to top staged and successively decreases.
8. the preparation method of a kind of microminiature unmanned plane carbon fiber rotor according to claim 1, is characterized in that: interlayer is more than 1 layer, adopts carbon fibre fabric or carbon fiber one-way band.
9. the preparation method of a kind of microminiature unmanned plane carbon fiber rotor according to claim 1, is characterized in that: enhancement Layer adopts carbon fiber plain cloth, is more than 1 layer, and ply sequence is (0/90)
n.
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