CN101653990A - Integrative solidifying and molding method of minitype unmanned aerial vehicle body and vertical fin and solidifying mold thereof - Google Patents
Integrative solidifying and molding method of minitype unmanned aerial vehicle body and vertical fin and solidifying mold thereof Download PDFInfo
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- CN101653990A CN101653990A CN200910092799A CN200910092799A CN101653990A CN 101653990 A CN101653990 A CN 101653990A CN 200910092799 A CN200910092799 A CN 200910092799A CN 200910092799 A CN200910092799 A CN 200910092799A CN 101653990 A CN101653990 A CN 101653990A
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Abstract
The invention relates to an integrative solidifying and molding mold of a minitype unmanned aerial vehicle body and a vertical fin; the mold is composed of a convex mold, a concave mold and a bolt andnut; the convex mold is a steel mod with a convex shape, which is consistent with the stream line form of the vehicle body; the concave mold which is a steel mold is formed by a left side mold pressing block and a right side mold pressing block which are connected by the bolt and nut, and the inner shape of the concave mold is consistent with the stream line form of the vehicle body. An integrative solidifying and molding method of a minitype unmanned aerial vehicle body and a vertical fin comprises three steps: 1. material preparation, the selected fiber reinforcement pre-impregnated fabricis cut into needed size; 2. the prepared material by the step one is paved on a matrix of the convex mold with one layer, and then the material is wrapped on the pre-impregnated fabric with another layer continuously, after sequential pavement is carried out, the designed paving layers are achieved, and then the convex mold is placed in the convex mold, and the bolt and nut is used for fixing alllocating pieces of axial mold assembly of the whole mold; 3. the whole mold is placed in a solidifying box and is solidified by temperature rising between 140-170 DEG C, and the mold is taken out after the temperature is naturally decreased to 60 DEG C and then is demoulded. The method realizes integrative formation of a complex structural piece.
Description
One, technical field:
The present invention relates to a kind of MAV shell streamline fuselage and vertical fin integral solidifying technology, relate in particular to integrated curing molding method of MAV fuselage and vertical fin and curing mold thereof, belong to unmanned plane manufacturing technology field.It adopts the process and the integrated jig of continuous fibre reinforcement shop layer, and emphasis has solved complex composite material structure spare integrated forming technique difficult point.
Two, background technology:
From the forties in 20th century polymer matrix composite and product forming method thereof begin one's study, along with polymer composites industrial boom and being becoming better and approaching perfection day by day, a lot of new methods constantly occur.It is very harsh that but MAV requires weight, if adopt conventional method of attachment between the parts such as fuselage and wing, is easy to cause the increase of weight on the one hand; On the other hand since in the heavy damage of composite junction the continuity of load fiber, increase thereby cause intensity to weaken with stress.Therefore be necessary that the method for inventing a kind of integrated molding solves this technical barrier.Integral solidifying technology among the present invention has adopted continuous fiber to strengthen the process and the integrated jig of body shop layer, both guaranteed the complex-curved shape need of fuselage and vertical fin, kept the continuity of fiber between fuselage and the vertical fin again, illustrated through overtesting that unidimensional product weight that this method is made is compared with conventional composite material forming method and alleviated 21%.The effectively technology that has realized complex-curved a plurality of structural member integrated moldings of this method and designing mould is for the full machine model of next step being made into one has been established technical foundation.
Three, summary of the invention:
(1) purpose: the object of the invention is at the streamline fuselage of microminiature unmanned aerial vehicle and vertical fin structure, provide integrated curing molding method of a kind of MAV fuselage and vertical fin and curing mold thereof, to solve owing to assembling brings problems such as weight increase, intensity weaken.Therefore the present invention also can be used for other complex composite material structure spare integrated forming techniques.
(2) technical scheme:
1) a kind of MAV fuselage of the present invention and the integrated curing molding mould of vertical fin, it is made up of punch, die and the bolt and nut of fixing them.
Described punch is the steel die of the convex shape consistent with designed shell streamline fuselage.
Described die is that left side mold pressing piece, right side mold pressing piece are formed by connecting by bolt and nut, the die interior shape equally with designed shell streamline fuselage and the consistent steel die of vertical fin.
Described bolt and nut is the standard product.
Left and right side mold pressing piece is provided with the through hole of a plurality of symmetries, passes through hole for bolt, implements the mold pressing procedure of the bolt tightening of section bar before curing with nut screwing clamping.The outer surface of punch, the inner surface of die are consistent with the endoporus or the inner surface of products made thereby.
2) a kind of MAV fuselage of the present invention and the integrated curing molding method of vertical fin, these method concrete steps are as follows:
Step 1: get the raw materials ready, with the pre-impregnated fabric of selected fibre reinforcement, tailor required size, this is of a size of shell fairing fuselage and the vertical fin outer surface coats two-layer at least above size;
Step 2: lay composite fortifying fibre layer, brushing on the punch carcass of releasing agent, select the pre-impregnated fabric of fortifying fibre for use, with getting the raw materials ready that step 1 makes, after at first spreading one deck on the carcass of punch, continue to coat the pre-impregnated fabric of another layer again, successively behind the lay, reach and put into die after the number of plies of layer is spread in design, the keeper of each axial matched moulds of a whole set of mould is fixed with bolt and nut;
Step 3: curing molding, material and the mould of finishing the compression molding operation are put into the heating cure of curing case; Or the pre-impregnated fabric of the fibre reinforcement of normal temperature cure matrix finished the material of shop layer mold pressing and mould tightening mould in uncured 20 minutes of matrix, and place the demoulding again after 24 hours at normal temperatures, reached maximum intensity in 72 hours;
Wherein, the pre-impregnated fabric of the fibre reinforcement described in the step 1 is meant the two-way woven cloth of carbon fiber (plain weave or twill), the two-way woven cloth of aramid fiber, the two-way shuffling cloth of carbon fiber/aramid fiber.
Wherein, the releasing agent described in the step 2 is meant liquid carbon fibrous composite releasing agent, NT-200 model.
Wherein, material described in the step 3 and mould are put into and are solidified the case heating cure, and its heating cure temperature is 140-170 degree centigrade.
3) advantage and effect: a kind of MAV fuselage of the present invention and integrated curing molding method of vertical fin and curing mold thereof, its advantage is
A. light more strong, epoxy resin-base 140C of the present invention ° molded curing shaped article and hand are stuck with paste the ratio of product aspect weight that vacuumizes the back curing molding and are: 0.79: 1.
B. one piece heat cure moulding.This covering covered fiber strengthens body and spreads the mechanical property that the process of layer has improved shell streamline fuselage and vertical fin greatly, has realized that the seamless non-bolt of fuselage and vertical fin is connected.
C. applicability is more extensive, and multiaxis is fit to make the complicated connector of other aircraft to the process of location integrated molding mould.
Four, description of drawings:
Fig. 1 is the schematic diagram of multiaxis to jig punch and die.
Fig. 2 is the schematic diagram of multiaxis to jig left side mold pressing piece and right side mold pressing piece.
Fig. 3 is integrated fuselage and vertical fin schematic diagram after the moulding.
Symbol description is as follows among the figure:
1 punch; 2 dies; 3 left side mold pressing pieces; 4 right side mold pressing pieces; 5 bolt and nuts.
Five, the specific embodiment:
1) see Fig. 1, Fig. 2, a kind of MAV fuselage of the present invention and the integrated curing molding mould of vertical fin, it is made up of punch 1, die 2 and the bolt and nut 5 of fixing them.
Described punch 1 is the steel die with the streamlined consistent convex shape of designed fuselage.
Described die 2 is that left side mold pressing piece 3, right side mold pressing piece 4 are formed by connecting by bolt and nut 5, the die interior shape equally with the streamlined consistent steel die of designed fuselage.
Described bolt and nut 5 is the standard product.
Left and right side mold pressing piece 3,4 is provided with the through hole of a plurality of symmetries, passes through hole for bolt, implements the mold pressing procedure of the bolt tightening of section bar before curing with nut screwing clamping.The inner surface of the outer surface of punch 1, die 2 is consistent with the endoporus of products made thereby or inner surface.
2) a kind of MAV fuselage of the present invention and the integrated curing molding method of vertical fin, these method concrete steps are as follows:
Step 1: get the raw materials ready, with the pre-impregnated fabric of selected fibre reinforcement, tailor required size, this is of a size of shell fairing fuselage and the vertical fin outer surface coats two-layer at least above size;
Step 2: lay composite fortifying fibre layer, brushing on the formpiston carcass of releasing agent, select the pre-impregnated fabric of fortifying fibre for use, with getting the raw materials ready that step 1 makes, after at first spreading one deck on the carcass of punch, continue to coat the pre-impregnated fabric of another layer again, successively behind the lay, reach and put into mould after the number of plies of layer is spread in design, the keeper of each axial matched moulds of mould is fixed with bolt;
Step 3: curing molding, material and the mould of finishing the compression molding operation are put into the heating system curing of solidifying the case heating cure or conduction oil being inputed to mould with the petroleum pipeline of the outer heat source case of mould; Or the pre-impregnated fabric of the fibre reinforcement of normal temperature cure matrix finished the material of shop layer mold pressing and mould tightening mould in uncured 20 minutes of matrix, and place the demoulding again after 24 hours at normal temperatures, reached maximum intensity in 72 hours;
The technical process of heating cure is as follows:
Be raised to 140-170 ℃ half an hour, constant temperature one hour cools to 60 ℃ of demouldings naturally;
Perhaps tightening mould demoulding after 24 hours in uncured 20 minutes of matrix.
A kind of MAV fuselage of the present invention and the integrated curing molding method of vertical fin, these method concrete steps are as follows: select for use the 1K carbon fiber to strengthen the pre-impregnated fabric of the two-way braiding of body, with the epoxy resin is matrix, multiaxis is made shell streamline fuselage and vertical fin overall structure to the process of location integrated molding.
Step 1: the two-way cloth of carbon fiber that is soaked with epoxide-resin glue is cut into the above length of an outer surface girth with punch;
Step 2: cut out the two-way woven cloth of length carbon fiber that has more than outer surface girth of punch and be coated on punch carcass last layer, adopt two pre-impregnated fabrics of fibre reinforcement jointly as the laminated material of fuselage and vertical fin, put into mould, each mold pressing piece is fixed with bolt;
Step 3: put into and solidify case, be warmed up to 140 ℃ half an hour, constant temperature solidified in one hour, cooled to 60 ℃ in case naturally, took out and solidified case, the demoulding.
A kind of MAV fuselage of the present invention and the integrated curing molding method of vertical fin, these method concrete steps are as follows:
Selecting two-way volume cloth of aramid fiber and phenolic resin for use is matrix, adopts the process of multiaxis to the location integrated molding, makes shell streamline fuselage and vertical fin overall structure.
Step 1: the two-way cloth of carbon fiber that is soaked with epoxide-resin glue is cut into the above length of an outer surface girth with punch;
Step 2: cut out the two-way woven cloth of length carbon fiber that has more than outer surface girth of punch and be coated on punch carcass last layer, adopt two pre-impregnated fabrics of fibre reinforcement jointly as the laminated material of fuselage and vertical fin, put into mould, each mold pressing piece is fixed with bolt;
Step 3: put into and solidify case, be warmed up to 140 ℃ half an hour, constant temperature solidified in one hour, cooled to 60 ℃ in case naturally, took out and solidified case, the demoulding.
Above-mentioned two examples all are the lay-up process methods of making thin-wall section, make heavy wall section bar and heavy wall auricle as need, only need employed material all is cut into the length of the required outer perisphere of punch, after coating shop one deck on the punch, renew (successively coat) behind the another kind of material in shop, put into mould, with bolt with about the mould, left and right sides module is fastening gets final product.
The laminated material of section bar of the present invention, can make up arbitrarily with carbon cloth, the two-way woven cloth of aramid fiber, the two-way shuffling cloth of carbon fiber/aramid fiber, in with a kind of product, can use a kind of in the above-mentioned material, also can use in the above-mentioned material two or more.
Claims (7)
1, the integrated curing molding mould of a kind of MAV fuselage and vertical fin is characterized in that: this mould is made up of punch, die and the bolt and nut of fixing them;
Described punch is the steel die of the convex shape consistent with designed shell streamline fuselage;
Described die is that left side mold pressing piece, right side mold pressing piece are formed by connecting by bolt and nut, the die interior shape equally with designed shell streamline fuselage and the consistent steel die of vertical fin;
Described bolt and nut is the standard product;
Left and right side mold pressing piece is provided with the through hole of a plurality of symmetries, passes through hole for bolt, implements the mold pressing procedure of the bolt tightening of section bar before curing with nut screwing clamping; The outer surface of punch, the inner surface of die are consistent with the endoporus and the inner surface of products made thereby.
2, the integrated curing molding method of a kind of MAV fuselage and vertical fin, it is characterized in that: these method concrete steps are as follows:
Step 1: get the raw materials ready, with the pre-impregnated fabric of selected fibre reinforcement, tailor required size, this is of a size of the shell streamline fuselage and the vertical fin outer surface coats two-layer at least above size;
Step 2: lay composite fortifying fibre layer, brushing on the punch carcass of releasing agent, select the pre-impregnated fabric of fortifying fibre for use, with getting the raw materials ready that step 1 makes, after at first spreading one deck on the carcass of punch, continue to coat the pre-impregnated fabric of another layer again, successively behind the lay, reach and put into die after the number of plies of layer is spread in design, the keeper of each axial matched moulds of a whole set of mould is fixed with bolt and nut;
Step 3: curing molding, material and the mould of finishing the compression molding operation are put into the heating cure of curing case.
3, a kind of MAV fuselage according to claim 2 and the integrated curing molding method of vertical fin, it is characterized in that: the pre-impregnated fabric of the fibre reinforcement described in the step 1 is meant plain weave and the two-way woven cloth of twill carbon fiber.
4, a kind of MAV fuselage according to claim 2 and the integrated curing molding method of vertical fin, it is characterized in that: the pre-impregnated fabric of the fibre reinforcement described in the step 1 is meant the two-way woven cloth of aramid fiber.
5, a kind of MAV fuselage according to claim 2 and the integrated curing molding method of vertical fin, it is characterized in that: the pre-impregnated fabric of the fibre reinforcement described in the step 1 is meant the two-way shuffling cloth of carbon fiber/aramid fiber.
6, a kind of MAV fuselage according to claim 2 and the integrated curing molding method of vertical fin is characterized in that: the releasing agent described in the step 2 is meant that model is the liquid carbon fibrous composite releasing agent of NT-200.
7, a kind of MAV fuselage according to claim 2 and the integrated curing molding method of vertical fin is characterized in that: material described in the step 3 and mould are put into and are solidified the case heating cure, and its heating cure temperature is 140-170 degree centigrade.
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| CN200910092799A CN101653990A (en) | 2009-09-25 | 2009-09-25 | Integrative solidifying and molding method of minitype unmanned aerial vehicle body and vertical fin and solidifying mold thereof |
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| CN103661916A (en) * | 2013-12-13 | 2014-03-26 | 南京航空航天大学 | Integral structure of unmanned aerial vehicle with pod and parachute bay and manufacture die thereof |
| CN104260372A (en) * | 2014-08-01 | 2015-01-07 | 昆山翔鸿无人飞行器有限公司 | Method for manufacturing fuselage of unmanned aerial vehicle |
| WO2015109700A1 (en) * | 2014-01-24 | 2015-07-30 | 深圳一电科技有限公司 | Unmanned aerial vehicle, unmanned aerial vehicle body, and manufacturing method therefor |
| CN105270612A (en) * | 2015-10-23 | 2016-01-27 | 精功（绍兴）复合材料技术研发有限公司 | Unmanned aerial vehicle body |
| CN106042240A (en) * | 2016-08-16 | 2016-10-26 | 前海星航（深圳）科技有限公司 | Forming die of unmanned aerial vehicle housing |
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| WO2018133177A1 (en) * | 2017-01-22 | 2018-07-26 | 厦门市豪尔新材料股份有限公司 | Application of hsm process in wing moulding and method for moulding wing |
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| CN113619155A (en) * | 2021-08-04 | 2021-11-09 | 陕西天翌天线股份有限公司 | Integral co-curing forming die and method for unmanned aerial vehicle body and rotor wing rod |
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| CN103661916A (en) * | 2013-12-13 | 2014-03-26 | 南京航空航天大学 | Integral structure of unmanned aerial vehicle with pod and parachute bay and manufacture die thereof |
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| WO2015109700A1 (en) * | 2014-01-24 | 2015-07-30 | 深圳一电科技有限公司 | Unmanned aerial vehicle, unmanned aerial vehicle body, and manufacturing method therefor |
| CN104260372A (en) * | 2014-08-01 | 2015-01-07 | 昆山翔鸿无人飞行器有限公司 | Method for manufacturing fuselage of unmanned aerial vehicle |
| CN105270612B (en) * | 2015-10-23 | 2018-09-07 | 精功（绍兴）复合材料技术研发有限公司 | A kind of unmanned plane body and its manufacturing method |
| CN105270612A (en) * | 2015-10-23 | 2016-01-27 | 精功（绍兴）复合材料技术研发有限公司 | Unmanned aerial vehicle body |
| CN109415006A (en) * | 2016-04-29 | 2019-03-01 | 巴斯夫东亚地区总部有限公司 | The method for being used to form vehicle enhancing component |
| CN106042240A (en) * | 2016-08-16 | 2016-10-26 | 前海星航（深圳）科技有限公司 | Forming die of unmanned aerial vehicle housing |
| CN106239813A (en) * | 2016-08-16 | 2016-12-21 | 前海星航（深圳）科技有限公司 | A kind of moulding process of unmanned plane shell |
| CN106741823A (en) * | 2016-12-30 | 2017-05-31 | 易瓦特科技股份公司 | Unmanned plane body prepared by composite and preparation method thereof |
| CN106741823B (en) * | 2016-12-30 | 2019-11-15 | 易瓦特科技股份公司 | By the unmanned plane body and preparation method thereof of composite material preparation |
| WO2018133177A1 (en) * | 2017-01-22 | 2018-07-26 | 厦门市豪尔新材料股份有限公司 | Application of hsm process in wing moulding and method for moulding wing |
| CN108407331A (en) * | 2018-03-05 | 2018-08-17 | 成都凯迪精工科技有限责任公司 | A kind of small drone answers material rear body manufacturing method |
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| CN113619155A (en) * | 2021-08-04 | 2021-11-09 | 陕西天翌天线股份有限公司 | Integral co-curing forming die and method for unmanned aerial vehicle body and rotor wing rod |
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Open date: 20100224 |