CN106184744A - A kind of manufacture method of the bionical Insect wings of light-high-strength - Google Patents
A kind of manufacture method of the bionical Insect wings of light-high-strength Download PDFInfo
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- CN106184744A CN106184744A CN201610630978.5A CN201610630978A CN106184744A CN 106184744 A CN106184744 A CN 106184744A CN 201610630978 A CN201610630978 A CN 201610630978A CN 106184744 A CN106184744 A CN 106184744A
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- carbon fiber
- wing
- support frame
- light
- strength
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C33/00—Ornithopters
- B64C33/02—Wings; Actuating mechanisms therefor
Abstract
The invention discloses the manufacture method of the bionical Insect wings of a kind of light-high-strength, wing support frame is carbon fiber, and support frame includes a main spar and three reinforcement ribs；Wing face is Mylar thin film.Its manufacturing step is: 1. stacked by two pieces of angled for machine direction unidirectional carbon prepregs and exert oneself to compress；2. on above-mentioned double-deck carbon fiber prepreg, cut wing support frame profile by cut mode, Mylar film cuts wing facial contour；3. it is uniformly coated with epoxy resin high-temp glue on carbon fiber prepreg surface；4. remove surplus carbon fiber around carbon fiber prepreg support frame, the Mylar film cut is positioned on skeleton；5. carbon fiber skeleton and Mylar film it is placed in baking box and on wing, applies weight, heating 80 minutes at 70 DEG C.The bionical wing light weight prepared based on the method, intensity is high, and this method is suitable for manufacturing Centimeter Level to grade bionic insect wing.
Description
Technical field
The present invention relates to material in the preparation process of the bionical Insect wings of a kind of light-high-strength select and processed side
Method, belongs to process engineering, materials processing technology field.
Background technology
Since 21 century, along with the development of the ambits such as micro Process, material, electronics, based on bionics principle, use micro-
The imitative insect minisize flapping wing aircraft (span is less than 5cm) of mechanical-electronic system technique is increasingly becoming the focus of research.Development elder brother
The micro flapping wing air vehicle of worm yardstick, one of which key technology is exactly the machining manufacture of bionical wing.Due to bionical wing
The wing is in high frequency amplitude at work and flutters state, this require bionical wing wing face and support frame have sufficiently high by force
Degree；Additionally, in order to improve pneumatic efficiency, it is desirable to the quality of bionical wing is the lightest, therefore, this to the selection of bionical wing and adds
Work technique proposes the highest requirement.
According to the version of bionical wing, bionical wing typically can be divided into reinforcement support frame (include main spar
And rib) and wing face.Wherein, strengthen main load part and main by weight source that support frame is bionical wing, need
Higher intensity and lighter quality；Wing face depends on support frame, bears aerodynamic loading, to requirement of strength slightly in fluttering
Low.
According to strengthening support frame and wing face whether separate machined, current existing process technology can be largely classified into two
Kind.In the first processing mode, support frame and wing, as an overall processing, directly obtain required bionical wing；The
Both, by support frame and wing face separate machined, are then combined by two kinds of mode work in-processes by bonding agent.
For the first processing mode, due to support frame and the machine-shaping simultaneously of wing face, thus both are selected
Material is the same, can be printed by 3D at present or the mode such as casting obtains, and the advantage of the method is to reappear true insecticide
The rib regularity of distribution (rib profile and thickness) of wing；Shortcoming is that support frame is integrally manufactured with wing face, available
Material is generally plastics, if wing thinner thickness, is then unsatisfactory for requirement of strength, if wing is thicker, then quality can be caused relatively big, nothing
Method takes into account high intensity and lightweight.Additionally, the method operation is complex, the requirement to equipment is higher.
For the second processing mode, due to support frame and the separate machined molding of wing face, both can want according to self
Ask independent selection.For support frame, often require that intensity is high, light weight, the most typically use carbon fibre material；For
Wing face, often requires that light weight, and flatness is good, typically selects plastic sheeting (such as Mylar film, PET film etc.).To carbon fiber and
The cutting of thin film, typically can use laser or machine cuts.The advantage of the method is to give full play to support frame and wing
The feature of airfoil material, lighter weight.But the method there is also some problems, owing to unidirectional carbon prepreg machine direction is
Single direction, and main spar and rib typically have a certain degree, if machine direction is consistent with main spar direction, although main spar
Can be strengthened, but rib direction is only kept profile by resin, so causes the support frame local strength of bionical wing very
Low, it is impossible to work under high frequency amplitude flutters state.In order to solve above-mentioned intensity deficiency problem, the most general by rib and master
Spar separate machined, main spar is all consistent with machine direction with rib direction, is then taken off by rib, splices at a certain angle
On main spar, although so solving the problem of rib insufficient strength, but also can introduce the error of splicing, being unfavorable for outside wing
Shape designs；Meanwhile, splicing causes support frame the most in one plane, is unfavorable for film laying on skeleton；In addition, spell
The intensity of contact is also required to additionally consider.On the other hand, in Laser Processing, owing to laser energy is higher, in cutting process
The epoxide-resin glue on carbon fiber prepreg surface can be partially cured, causes carbon fiber support frame can not fit completely with thin film,
Wing wing face thin film during flapping may depart from support frame.
Generally speaking, the processing method of existing bionical wing, according to overall processing mode, it is difficult to take into account high intensity with light
Quality two aspect；Use carbon fiber and thin film separate machined mode, although high intensity and lightweight can be met to a certain extent
Amount, but in technique, have a lot of details existing defects, reliability is the best, and is not suitable for the situation of complicated support frame.
Summary of the invention
The technical problem to be solved in the present invention is: for existing bionic insect wing processing present in problem, it is provided that one
The manufacture method of kind of the bionical Insect wings of light-high-strength, it is to avoid high intensity and lightweight in the overall processing of support frame wing face
The problem that amount can not be taken into account, solve employing carbon fiber and thin film separate machined in local strength low, need splicing and laminating degree
Bad problem, it is adaptable to Centimeter Level is to the preparation of grade bionic insect wing.
The present invention solves the technical scheme of above-mentioned technical problem employing: the system of the bionical Insect wings of a kind of light-high-strength
Making method, its manufacturing step includes:
Step (1), two pieces of angled for machine direction unidirectional carbon prepregs are stacked and exert oneself compress, its
In, one layer of carbon fiber machine direction is spar direction, and another layer of carbon fiber direction is rib direction；
Step (2), design wing support frame profile and wing facial contour, by cut mode in above-mentioned double-layer carbon
Cut wing support frame profile on fiber prepreg material, Mylar film cuts wing facial contour；
Step (3), it is uniformly coated with epoxy resin high-temp glue on carbon fiber prepreg surface；
Surplus carbon fiber around step (4), removal carbon fiber prepreg support frame, is positioned over the Mylar film cut
On skeleton, light compression set position；
Step (5), carbon fiber skeleton and Mylar film are placed in baking box and on wing apply weight, at 70 DEG C heat
80 minutes, support frame was integrated with wing face film bond after cooling, thus obtained designed bionic insect wing.
Further, described carbon fiber is unidirectional carbon prepreg, and in prepreg, the content ratio of fiber is 40-
70%, the thickness of monolayer carbon fiber prepreg is 20-100 μm.
Further, described double-layer carbon fiberoptic fiber direction superposition at a certain angle, angulation value size is 30-
70 °, determine according to the design of wing main spar with rib.
Further, described double-deck carbon fiber prepreg stacked system, the carbon fiber number of plies is not limited to 2 layers, superimposed layer
Number is more than or equal to 2 layers.
Further, described multilayer material stacked system, in addition to ground floor is carbon fiber, it is fine that remainder layer is not limited to carbon
Dimension material, it is possible to select plastic sheeting or metallic film.
Further, described carbon fiber prepreg, need to be at one layer of epoxy of surface uniform application after cut
Resin glue, glue thickness 10-50 μm.
Further, described wing face material therefor is plastic sheeting, selects Mylar film, PET film or PP film, thin film
Thickness is 1 μm-10 μm.
Further, described carbon fiber skeleton and Mylar thin film need to carry out heat treatment under an increased pressure, and temperature is
60-90 DEG C, the time is 80min-120min, and pressurize 1000-5000Pa.
By Theoretical Calculation and experimental test, when the thickness of monolayer carbon fiber is 20-100 μm, and film thickness is 1-10 μm,
The a length of 10-20mm of wing, wing width is 5-14mm, and heat time heating time is 80min-120min, and heating-up temperature is 60-80 DEG C,
When ambient pressure is 1000-5000Pa, use the energy of the bionic insect wing prepared by manufacture method described in foregoing invention simultaneously
Obtain lightweight and the advantage of high intensity.
Present invention advantage compared with prior art is:
(1) the invention provides the manufacture of the bionical Insect wings of light-high-strength that a kind of operation is simple, manufacturing cycle is short
Method, the method combines the mapping of computer machinery, is suitable for the Insect wings of multiple topological form, can be according to carbon fiber THICKNESS CONTROL
The hard and soft of wing, the suitability is wide；The method uses cut carbon fiber prepreg, it is not necessary to complicated machinery cutting processing, greatly
Improving greatly work efficiency, cutting process is to carbon fiber prepreg mechanical active force, it is ensured that machining accuracy.
(2) manufacture method of the bionic insect wing that the present invention proposes selects carbon fiber as support frame, selects Mylar
Thin film, as wing face, gives full play to the feature performance benefit of material.Wherein carbon fiber strength is high, light weight, and Mylar film thickness is little,
Flatness is good；Avoiding wing support frame consistent with wing airfoil material with skeleton in the overall processing of wing face, high intensity is with light
The problem that quality cannot be taken into account.
(3) manufacture method of the bionic insect wing that the present invention proposes uses the side of the angled superposition of double-layer carbon fiber
Formula, main spar and rib direction are distributed with reinforcement carbon fiber, it is not necessary to individually cutting main spar and rib carry out concatenation again,
So substantially increase work efficiency and machining accuracy, it is adaptable to complicated wing supporting construction；Owing to not having splice point, wing props up
Support bone frame flatness is good, in conjunction with gluing after cut and supercharging heating operation, it is ensured that support frame and wing face thin film
Laminating degree.
Accompanying drawing explanation
Fig. 1 is the process chart of embodiment of the present invention；
Fig. 2 is carbon fiber superposition and the support frame design diagram of embodiment of the present invention；
Fig. 3 is the epoxy coating schematic diagram of embodiment of the present invention.
Detailed description of the invention
Below in conjunction with the accompanying drawings and detailed description of the invention further illustrates the present invention.
As it is shown in figure 1, the present invention provides a reality of manufacture method based on the bionical Insect wings of a kind of light-high-strength
Executing example, this technological process includes:
1. two pieces of angled for machine direction unidirectional carbon prepregs are stacked and exert oneself to compress, wherein, one layer
Carbon fiber machine direction is spar direction, and another layer of carbon fiber direction is that (in the present embodiment, monolayer carbon fiber is pre-in rib direction
Leaching material thickness is 30 μm, and in prepreg, the content of carbon fiber is 48%, and two-layer carbon fiber prepreg fiber becomes 60 ° of angles to stack pressure
Tightly)；
2. using mechanical drawing, design wing support frame profile and wing facial contour, by cut mode upper
State and cut wing support frame profile on double-deck carbon fiber prepreg, Mylar film cuts wing facial contour (the present embodiment
In, wing skeleton includes main spar one, rib 3, and main spar width is 0.5mm, and rib width is 0.24mm, main spar with
Rib direction becomes 60 ° of angles；Mylar thin film is selected in wing face, and film thickness is 2.5 μm, and wing design length is 15mm, width
For 7mm)；
3. through cutting carbon fiber prepreg surface be uniformly coated with epoxy resin high-temp glue (in the present embodiment, ring
The composition proportion of epoxy resins high-temp glue is 3:1, and the room temperature primary solidification time is 25min)；
4. remove surplus carbon fiber around carbon fiber prepreg support frame, the Mylar film cut is positioned over support rib
On frame, light compression set position (in the present embodiment, around support frame, surplus carbon fiber tweezers are rejected)；
5. carbon fiber skeleton and Mylar film it is placed in baking box and on wing, applies weight, heating 80 minutes at 70 DEG C,
Support frame is integrated with wing face film bond after cooling, thus obtains designed bionic insect wing (the present embodiment
In son, heating-up temperature is set to 70 DEG C, is set to 80min heat time heating time, support frame and thin film apply weight, and after conversion, weight is executed
The pressure added is 2000Pa).
The manufacture method of the bionical Insect wings of a kind of light-high-strength of the present invention, strengthens and epoxy based on carbon fiber one-way
The principle that resin at high temperature hardens, concrete principle is described below: unidirectional carbon prepreg is epoxy resin and carbon fiber wire
Coalition, wherein, epoxy resin is matrix, and carbon fiber wire is reinforcement material.At normal temperatures, carbon fiber prepreg quality is relatively
Soft, owing to all there is epoxide-resin glue on carbon fiber prepreg two sides, therefore can stack angled for two-layer carbon fiber prepreg also
Compressing, under the bonding of epoxide-resin glue, two-layer carbon fiber can be snug against together.When fine at carbon by cut mode
When cutting support frame on dimension prepreg, owing to laser beam energy is higher, can form localized hyperthermia at incision, carbon fiber is pre-
The epoxy resin meeting partially hardened on leaching material surface, is unfavorable for that next step is film adhered with wing face, in order to solve this problem, needs
To increase on prepreg surface and to be coated with one layer of epoxide-resin glue, to guarantee the laminating of next step and wing face thin film after dicing.Wait to prop up
After support bone frame is film adhered with wing face, being placed under high-temperature and high-pressure conditions, epoxide-resin glue all solidifies, thin film and support
Skeleton tightly bonds together, and the most i.e. can get the bionic insect wing of light-high-strength.
Fig. 2 is that the sub-carbon fiber prepreg of embodiment illustrated in fig. 1 stacks and support frame design diagram.Wherein, a is epoxy
Resin bed, b is carbon fiber layer, and c is main spar in support frame, and d is reinforcement rib in support frame.Two-layer carbon fiber prepreg
As shown by arrows, both become 60 ° of angles to machine direction, and main spar becomes 60 ° of angles as rib.
Fig. 3 is the epoxy coating schematic diagram of embodiment illustrated in fig. 1.Wherein, e is newly-increased epoxy resin figure layer, treats
Carbon fiber prepreg is after cut, and the former epoxy resin of prepreg surface portion has cured, and is coated with one layer so that increase
New epoxy resin, increases and removes carbon fiber structural unnecessary around support frame by tweezers after being coated with, discharge support frame.
What the present invention did not elaborated belongs to techniques well known.
The above, be only embodiments of the invention, the present invention not make any pro forma restriction, every foundation
Any simple modification, equivalent variations and the modification that above example is done by the principle of the invention and technical spirit, all still falls within
Within the scope of technical solution of the present invention, therefore protection scope of the present invention is when being as the criterion with claims.
Claims (8)
1. the manufacture method of the bionical Insect wings of light-high-strength, it is characterised in that: comprise the steps:
Step (1), two pieces of angled for machine direction unidirectional carbon prepregs are stacked and exert oneself compress, wherein, one
Layer carbon fiber machine direction is spar direction, and another layer of carbon fiber direction is rib direction；
Step (2), design wing support frame profile and wing facial contour, by cut mode at above-mentioned double-layer carbon fiber
Cut wing support frame profile on prepreg, Mylar film cuts wing facial contour；
Step (3), it is uniformly coated with epoxy resin high-temp glue on carbon fiber prepreg surface；
Surplus carbon fiber around step (4), removal carbon fiber prepreg support frame, is positioned over skeleton by the Mylar film cut
On, light compression set position；
Step (5), carbon fiber skeleton and Mylar film are placed in baking box and on wing apply weight, at 70 DEG C heat 80 points
Clock, support frame is integrated with wing face film bond after cooling, thus obtains designed bionic insect wing.
The manufacture method of the bionical Insect wings of light-high-strength the most according to claim 1, it is characterised in that: described carbon
Fiber is unidirectional carbon prepreg, and in prepreg, the content ratio of fiber is 40-70%, the thickness of monolayer carbon fiber prepreg
For 20-100 μm.
The manufacture method of the bionical Insect wings of light-high-strength the most according to claim 1, it is characterised in that: described is double
Layer carbon fiber machine direction superposition at a certain angle, angulation value size is 30-70 °, according to wing main spar and rib
Design determines.
The manufacture method of the bionical Insect wings of light-high-strength the most according to claim 1, it is characterised in that: described is double
Layer carbon fiber prepreg stacked system, the carbon fiber number of plies is not limited to 2 layers, and the superposition number of plies is more than or equal to 2 layers.
The manufacture method of the bionical Insect wings of light-high-strength the most according to claim 1, it is characterised in that: described many
Layer material stacked system, in addition to ground floor is carbon fiber, remainder layer is not limited to carbon fibre material, it is possible to select plastic sheeting or gold
Belong to thin film.
The manufacture method of the bionical Insect wings of light-high-strength the most according to claim 1, it is characterised in that: described carbon is fine
Dimension prepreg, need to be at one layer of epoxide-resin glue of surface uniform application after cut, glue thickness 10-50 μm.
The manufacture method of the bionical Insect wings of light-high-strength the most according to claim 1, it is characterised in that: described wing
Face material therefor is plastic sheeting, selects Mylar film, and PET film or PP film, film thickness is 1 μm-10 μm.
The manufacture method of the bionical Insect wings of light-high-strength the most according to claim 1, it is characterised in that: described carbon is fine
Dimension skeleton need to carry out heat treatment under an increased pressure with Mylar thin film, and temperature is 60-90 DEG C, and the time is 80min-120min, adds
Pressure 1000-5000Pa.
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| CN201610630978.5A CN106184744B (en) | 2016-08-04 | 2016-08-04 | A kind of manufacturing method of the bionical Insect wings of light-high-strength |
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| CN201610630978.5A CN106184744B (en) | 2016-08-04 | 2016-08-04 | A kind of manufacturing method of the bionical Insect wings of light-high-strength |
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| CN109353497A (en) * | 2018-12-04 | 2019-02-19 | 南京航空航天大学 | Can VTOL flapping wing aircraft wing |
| CN110205682A (en) * | 2019-06-21 | 2019-09-06 | 河北普兴电子科技股份有限公司 | A kind of method of attaching of silicon carbide seed |
| CN112004744A (en) * | 2017-09-27 | 2020-11-27 | Gkn航空服务有限公司 | Box rib |
| CN114537703A (en) * | 2021-12-07 | 2022-05-27 | 北京航空航天大学 | Machining device and manufacturing method for wing of miniature flapping-wing aircraft |
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|---|---|
| CN106184744B (en) | 2018-06-26 |
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