CN114290715A - Rapid trial-manufacturing forming process for producing ducted propeller - Google Patents
Rapid trial-manufacturing forming process for producing ducted propeller Download PDFInfo
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- CN114290715A CN114290715A CN202210004987.9A CN202210004987A CN114290715A CN 114290715 A CN114290715 A CN 114290715A CN 202210004987 A CN202210004987 A CN 202210004987A CN 114290715 A CN114290715 A CN 114290715A
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- 238000004519 manufacturing process Methods 0.000 title claims abstract description 46
- 238000000034 method Methods 0.000 title claims abstract description 29
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 24
- 239000004917 carbon fiber Substances 0.000 claims abstract description 24
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 24
- 239000004744 fabric Substances 0.000 claims abstract description 23
- 229920006395 saturated elastomer Polymers 0.000 claims abstract description 5
- 238000007592 spray painting technique Methods 0.000 claims abstract description 5
- 239000000463 material Substances 0.000 claims description 10
- 238000000465 moulding Methods 0.000 claims description 7
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 claims description 6
- 229910052799 carbon Inorganic materials 0.000 claims description 6
- 239000003822 epoxy resin Substances 0.000 claims description 6
- 229920000647 polyepoxide Polymers 0.000 claims description 6
- 238000010438 heat treatment Methods 0.000 claims description 5
- 239000004593 Epoxy Substances 0.000 claims description 4
- 239000003795 chemical substances by application Substances 0.000 claims description 3
- 239000003292 glue Substances 0.000 claims description 3
- 230000008595 infiltration Effects 0.000 claims description 3
- 238000001764 infiltration Methods 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 4
- 238000002360 preparation method Methods 0.000 description 14
- 238000003754 machining Methods 0.000 description 5
- 239000002131 composite material Substances 0.000 description 3
- 239000000853 adhesive Substances 0.000 description 2
- 230000001070 adhesive effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000005498 polishing Methods 0.000 description 2
- 238000002791 soaking Methods 0.000 description 2
- 238000010521 absorption reaction Methods 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000011162 core material Substances 0.000 description 1
- 238000001035 drying Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 238000012216 screening Methods 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
- 238000005303 weighing Methods 0.000 description 1
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Abstract
The invention discloses a rapid trial-manufacturing forming process for producing ducted propellers. The trial-manufacture forming process comprises the following steps: s1 provides a propeller blade drawing. And S2 carving to obtain the sandwich layer, the upper template and the lower template. And S3 saturated spray painting treatment, and airing for later use. And S4, laying carbon fiber cloth to obtain an upper die body and a lower die body. S5, placing the upper die body, the lower die body and the sandwich layer in the die cavity together, and obtaining the single propeller blade after die assembly. And S6, repeating S2-S5 to obtain a plurality of propeller blades, and assembling to obtain the ducted propeller. According to the trial-manufacturing forming process, the mode of firstly carrying out single-piece manufacturing and then combining is adopted for matching trial manufacturing, the manufacturing flexibility is high, the manufacturing difficulty is greatly reduced, the manufacturing speed is effectively improved, in addition, the effect of low-cost manufacturing is achieved based on the combination of the combined manufacturing mode and the simple die, the process is suitable for short-time test use, and the problems that the manufacturing period of the test propeller is too long and the cost is too high are solved.
Description
Technical Field
The invention relates to the technical field of composite material propeller manufacturing, in particular to a rapid trial-manufacturing forming process for producing ducted propellers.
Background
The ducted propeller is a propeller system surrounded by a duct, has higher pneumatic efficiency compared with an isolated propeller, has the advantages of low pneumatic noise, high safety and the like, and is widely applied to military and civil fields such as steamships, special aircrafts, submarines and the like.
At present, two types of metal and composite materials are adopted for the ducted propeller, wherein the metal ducted propeller is high in processing cost, high in requirements on processing equipment and processing technology, high in processing difficulty and relatively heavy in weight of the whole propeller, and the carbon fiber composite material is mainly processed integrally by using a metal mold at present, so that the processing time is long, the cost is high, and the cycle cost cannot be accepted for the tested propeller.
Disclosure of Invention
On the basis, the rapid trial-manufacturing forming process for producing the ducted propeller is needed to solve the problems that the machining cost of the existing ducted propeller is high, the requirements on machining equipment and machining process are high, the machining difficulty is high, the machining time is long, and the cycle cost of the experimental propeller is high.
A rapid trial-manufacturing forming process for producing ducted propellers comprises the following steps:
s1, providing a propeller blade drawing paper;
the propeller blade comprises a sandwich layer, two groups of carbon fiber cloth, an upper template and a lower template, wherein the two groups of carbon fiber cloth are positioned at two corresponding sides of the sandwich layer;
s2, sequentially carving to obtain a sandwich layer, an upper template and a lower template based on the propeller blade drawing;
s3, carrying out saturated spray painting treatment on the upper template and the lower template in sequence, and airing for later use;
s4, infiltrating carbon fiber cloth with a curing material, and then respectively paving the carbon fiber cloth on the upper template and the lower template which are processed by the S3 to obtain an upper die body and a lower die body;
s5, placing the upper die body, the lower die body and the sandwich layer into the die cavity together according to the sequence of the propeller blade drawing, and heating and curing after die assembly to obtain a single propeller blade;
s6, repeating S2-S5 to obtain a plurality of propeller blades, and selecting a plurality of groups of propeller blades with similar weights to assemble to obtain the ducted propeller.
Above-mentioned trial-manufacturing forming process adopts the mode of single chip preparation earlier + back combination to cooperate the trial-manufacturing, and the flexibility ratio of preparation is high and compare in whole processing, and the preparation degree of difficulty greatly reduces to effectively promoted preparation speed, in addition, based on combination preparation mode and simple and easy mould cooperation, reached the effect of low-cost preparation, be applicable to the experimental use of short time, solved experimental propeller preparation cycle overlength and the too high problem of cost.
In one embodiment, the upper template and the lower template both adopt epoxy boards, and are located at positions corresponding to one sides of the carbon fiber cloth, which face away from the sandwich layer.
Further, the upper template is positioned above the lower template;
the sandwich layer is made of PVC or PMI, and is fixedly arranged between the two groups of carbon fiber cloth.
And furthermore, the upper template and the lower template are fixedly connected with the corresponding carbon fiber cloth.
In one embodiment, the epoxy resin and curing agent are mixed in a ratio of 1: 1 to obtain the curing material.
In one embodiment, in S5, the upper mold body, the lower mold body, and the sandwich layer are placed together in a cavity, and 3 to 5 strands of epoxy resin carbon filaments are added to the edges for infiltration.
Further, after the soaking, the upper die body and the lower die body are fixed in a matched mode through a clamping flange and the like and are solidified, and the edge opening is polished after the solidification is finished, so that the single propeller blade is obtained.
And further, the curing treatment temperature is 70-90 ℃, and the curing time is 3.5-4.5 h.
In one embodiment, in S6, the propeller blades are weighed using a high precision gram scale, and an appropriate number of propeller blades of similar weight are screened out.
In one embodiment, in the assembling process, two pieces of 1mm carbon plates are carved and bonded with structural adhesive at the root of the propeller blade.
Compared with the prior art, the invention has the beneficial effects that:
according to the trial-manufacturing forming process, the mode of firstly carrying out single-piece manufacturing and then combining is adopted for matching trial manufacturing, the manufacturing flexibility is high, the manufacturing difficulty is greatly reduced compared with the integral processing, the manufacturing speed is effectively increased, in addition, the effect of low-cost manufacturing is achieved based on the combination manufacturing mode and the simple die, the trial-manufacturing forming process is suitable for short-time test use, and the problems that the manufacturing period of the test propeller is too long and the cost is too high are solved.
Drawings
Fig. 1 is a schematic diagram of a propeller blade drawing sheet provided in embodiment 1 of the present invention.
Description of the main elements
1. A sandwich layer; 2. carbon fiber cloth; 3. mounting a template; 4. and a lower template.
The present invention is described in further detail with reference to the drawings and the detailed description.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings.
Example 1
The embodiment provides a rapid trial-manufacturing forming process for producing ducted propellers, which comprises the following steps of:
s1 provides a propeller blade drawing.
Referring to fig. 1, fig. 1 is a schematic diagram of a drawing of a propeller blade according to the present embodiment, which is designed by a designer. As can be seen from the observation and analysis of the figure 1, the propeller blade comprises a sandwich layer 1, two groups of carbon fiber cloth 2 positioned at two corresponding sides of the sandwich layer 1, an upper template 3 and a lower template 4. The upper template 3 and the lower template 4 both adopt epoxy boards, and the epoxy boards are density boards, so that the high-speed engraving machine has the advantages of high engraving speed and low cost. The upper template 3 and the lower template 4 are both positioned at the position corresponding to one side of the carbon fiber cloth 2 back to the sandwich layer 1. The upper template 3 is positioned above the lower template 4. The sandwich layer 1 is made of PMI materials, and the sandwich layer 1 is fixedly arranged between the two groups of carbon fiber cloth 2. In this embodiment, the sandwich layer 1 is made of PMI material, and PMI (polymethacrylimide) is used as a core material to simplify the process, shorten the flow, and solve the problems of easy moisture absorption and easy debonding of the conventional material, and in other embodiments, the sandwich layer 1 made of PVC material may also be used. The upper template 3 and the lower template 4 are both fixedly connected with the corresponding carbon fiber cloth 2.
And S2, sequentially carving to obtain the sandwich layer 1, the upper template 3 and the lower template 4 based on the propeller blade drawing.
The sandwich layer 1, the upper template 3 and the lower template 4 are obtained by engraving through an engraving machine, and the upper template 3 and the lower template 4 form a double-pressure die with an upper structure and a lower structure to flexibly manufacture propeller blades.
And S3, carrying out saturated spray painting treatment on the upper template 3 and the lower template 4 in sequence, and airing for later use.
And carrying out saturated spray painting on the upper template 3 and the lower template 4 which are carved in the S2, simply polishing after drying, and smearing the surface with No. 8 wax to facilitate subsequent demoulding treatment.
S4, soaking the carbon fiber cloth 2 with a curing material, and then respectively paving the carbon fiber cloth on the upper template 3 and the lower template 4 which are processed by the S3 to obtain an upper die body and a lower die body.
Epoxy resin and curing agent the ratio of 1: 1 to obtain the curing material. The carbon fiber cloth 2 is slightly larger than the cavity when being paved on the upper template 3. The carbon fiber cloth 2 is smaller than the cavity when being paved on the lower template 4, and is used as reinforcement from the root of the oar to one third of the cavity.
And S5, placing the upper die body, the lower die body and the sandwich layer 1 into the die cavity together according to the sequence of the propeller blade drawing, and heating and curing after die assembly to obtain the single propeller blade.
The upper die body, the lower die body and the sandwich layer 1 are placed in the die cavity together, 4 strands of epoxy resin glue carbon wires are added at the edge to be infiltrated, then a clamping flange and the like are used between the upper die body and the lower die body to carry out die assembly fixation and placed between heating rooms to be treated for 4 hours for curing at the temperature of 80 ℃, and the edge is polished after curing is completed to obtain the single propeller blade.
S6, repeating S2-S5 to obtain a plurality of propeller blades, and selecting a plurality of groups of propeller blades with similar weights to assemble to obtain the ducted propeller.
And repeating the manufacturing steps to obtain a plurality of ducted propeller blades, weighing the propeller blades by using a high-precision gram scale, screening proper number of propeller blades with similar weight (within 0.1g difference), simply polishing, and matching and assembling to obtain the ducted propeller. In the assembling process, the root of the propeller blade is adhered by carving two 1mm carbon plates and adding structural adhesive, and after the propeller blade is assembled, the propeller blade is placed in a heating room and cured for 4 hours at 80 ℃ to obtain the ducted propeller.
In summary, the trial-manufacture molding process of the embodiment has the following advantages compared with the current propeller production: the trial-manufacturing forming process of this embodiment adopts the mode of earlier monolithic preparation + back combination to cooperate the trial-manufacturing, and the flexibility ratio of preparation is high and compare in whole processing, and the preparation degree of difficulty greatly reduces to effectively promoted preparation speed, in addition, cooperatees with simple and easy mould based on combination preparation mode, has reached the effect of low-cost preparation, is applicable to the experimental use of short time, has solved experimental propeller preparation cycle overlength and the too high problem of cost.
For the naming of each component referred to, the function described in the specification is used as the standard for naming, but is not limited by the specific term used in the present invention, and those skilled in the art can also select other terms to describe each component name of the present invention.
Claims (10)
1. A rapid trial-manufacturing forming process for producing ducted propellers is characterized by comprising the following steps:
s1, providing a propeller blade drawing paper;
the propeller blade comprises a sandwich layer (1), two groups of carbon fiber cloth (2) positioned at two corresponding sides of the sandwich layer (1), an upper template (3) and a lower template (4);
s2, sequentially carving to obtain a sandwich layer (1), an upper template (3) and a lower template (4) based on the propeller blade drawing;
s3, carrying out saturated spray painting treatment on the upper template (3) and the lower template (4) in sequence, and airing for later use;
s4, infiltrating the carbon fiber cloth (2) with a curing material, and then respectively paving the carbon fiber cloth on the upper template (3) and the lower template (4) which are processed by the S3 to obtain an upper mold body and a lower mold body;
s5, placing the upper die body, the lower die body and the sandwich layer (1) into a die cavity together according to the sequence of the propeller blade drawing, and heating and curing after die assembly to obtain a single propeller blade;
s6, repeating S2-S5 to obtain a plurality of propeller blades, and selecting a plurality of groups of propeller blades with similar weights to assemble to obtain the ducted propeller.
2. The rapid trial-manufacturing forming process for producing the ducted propeller as claimed in claim 1, wherein the upper template (3) and the lower template (4) both adopt epoxy plates, and the upper template (3) and the lower template (4) are both located at positions corresponding to one sides of the carbon fiber cloth (2) back to the sandwich layer (1).
3. The rapid trial-manufacturing molding process for producing the ducted propeller as claimed in claim 2, wherein the upper template (3) is located above the lower template (4);
the sandwich layer (1) is made of PVC or PMI, and the sandwich layer (1) is fixedly arranged between the two groups of carbon fiber cloth (2).
4. The rapid trial-manufacturing forming process for producing the ducted propeller as claimed in claim 3, wherein the upper template (3) and the lower template (4) are both fixedly connected with the corresponding carbon fiber cloth (2).
5. The rapid trial-manufacturing molding process for producing the ducted propeller according to claim 1, wherein the epoxy resin and the curing agent are mixed according to a ratio of 1: 1 to obtain the curing material.
6. The rapid trial-manufacturing molding process for producing the ducted propeller as claimed in claim 1, wherein in S5, the upper mold body, the lower mold body and the sandwich layer (1) are placed in a cavity together, and 3-5 strands of epoxy resin glue carbon filaments are added at the edges for infiltration.
7. The rapid trial-manufacturing molding process for producing the ducted propeller as claimed in claim 6, wherein after the infiltration, the upper mold body and the lower mold body are fixed and cured by using a snap and the like, and after the curing is completed, the edge opening is polished to obtain the single propeller blade.
8. The rapid trial-manufacturing forming process for producing the ducted propeller as claimed in claim 7, wherein the curing treatment temperature is 70-90 ℃ and the curing time is 3.5-4.5 hours.
9. The rapid trial-manufacturing molding process for producing the ducted propeller as claimed in claim 1, wherein in S6, the propeller blades are weighed by using a high-precision gram scale, and a proper number of propeller blades with similar weight are screened out.
10. The rapid trial-manufacturing molding process for producing the ducted propeller according to claim 1, wherein in the assembling process, the root of the propeller blade is bonded by carving two 1mm carbon plates and adding structural glue.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210004987.9A CN114290715A (en) | 2022-01-05 | 2022-01-05 | Rapid trial-manufacturing forming process for producing ducted propeller |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210004987.9A CN114290715A (en) | 2022-01-05 | 2022-01-05 | Rapid trial-manufacturing forming process for producing ducted propeller |
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| CN101704300A (en) * | 2009-11-12 | 2010-05-12 | 江苏九鼎新材料股份有限公司 | Integral one-step molding technique of wind power blade |
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| CN109849365A (en) * | 2019-03-04 | 2019-06-07 | 保定国奥新能源工程材料科技有限责任公司 | The manufacturing method of propeller blade |
| CN110371265A (en) * | 2019-07-09 | 2019-10-25 | 宁波梦浪户外用品有限公司 | A kind of plastics surfing paddle board and its manufacturing method |
| CN113232834A (en) * | 2021-05-10 | 2021-08-10 | 西北工业大学 | Near space double-web-plate hollow composite material propeller structure and manufacturing method thereof |
-
2022
- 2022-01-05 CN CN202210004987.9A patent/CN114290715A/en active Pending
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101704300A (en) * | 2009-11-12 | 2010-05-12 | 江苏九鼎新材料股份有限公司 | Integral one-step molding technique of wind power blade |
| CN103935042A (en) * | 2013-01-23 | 2014-07-23 | 佛山市安尔康姆航拍科技有限公司 | Manufacturing method for hollow rotor of unmanned aerial vehicle and hollow rotor |
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| CN105128876A (en) * | 2015-09-14 | 2015-12-09 | 西南交通大学 | Carbon fiber composite vehicle body and manufacturing method thereof |
| CN106275377A (en) * | 2016-08-30 | 2017-01-04 | 北京奇正数元科技股份有限公司 | The stressed-skin construction of a kind of small-sized unmanned plane and forming method thereof |
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