CN108971698A - A kind of propeller electric arc fuse increasing material manufacturing method - Google Patents
A kind of propeller electric arc fuse increasing material manufacturing method Download PDFInfo
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- CN108971698A CN108971698A CN201810972135.2A CN201810972135A CN108971698A CN 108971698 A CN108971698 A CN 108971698A CN 201810972135 A CN201810972135 A CN 201810972135A CN 108971698 A CN108971698 A CN 108971698A
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- propeller
- electric arc
- material manufacturing
- increasing material
- arc fuse
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K9/00—Arc welding or cutting
- B23K9/04—Welding for other purposes than joining, e.g. built-up welding
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K9/00—Arc welding or cutting
- B23K9/095—Monitoring or automatic control of welding parameters
Abstract
The invention belongs to propeller preparation process correlative technology fields, more particularly, to a kind of propeller electric arc fuse increasing material manufacturing method, comprising: (i) carries out targetedly subregion to propeller members and dispose, and obtains propeller hub part and blade portion；(ii) to two kinds of different pieces, path is manufactured come planning and designing based on different principles；Wherein propeller hub is planned to obtain path using planar slice and biasing filling mode, and blade is sliced and biases filling mode using cylinder and plans to obtain path；(iii) according to the different manufacture paths completed, corresponding Combined machining is carried out using electric arc fuse increasing material manufacturing technique.The invention also discloses corresponding propeller members products.Through the invention, it can not only be preferably adapted with the complex three-dimensional construction feature of propeller members, so that the precision and appearance profile of electric arc fuse increasing material manufacturing propeller control more preferably, and the dimensional accuracy of final products can be significantly improved, while greatly shortening its manufacturing cycle.
Description
Technical field
The invention belongs to propeller preparation process correlative technology fields, more particularly, to a kind of propeller electric arc fuse
Increasing material manufacturing method.
Background technique
Propeller members have critically important status in multiple fields such as the ship in China, aviation and the energy, in ship, fly
It is one of core component of dynamical system in the large scale equipments such as machine and wind-driven generator, manufacturing quality directly affects these and sets
Standby performance.Currently, the manufacture of large-size propeller relate generally to propeller three-dimensional modeling, Mold Making, material melting, casting,
Numerous techniques such as numerical control processing, and it is long, accuracy is poor, manufacturing cost is high there are the period the disadvantages of, it is difficult to ensure that the height of propeller
Precision and high performance requirements.
For constituting for the propeller members preparation casting technique of one of core procedure the most, traditionally uses and scrape
Hardened conjunction pitch plate makes mo(u)ld bottom half, and the wooden model heart or the sand mo(u)ld heart make mo(u)ld top half, but since the casting die heart makes difficulty, the period is long, size essence
Degree is difficult to ensure, it is long not only result in the propeller production cycle, it is also difficult to guarantee its dimensional accuracy and appearance profile.For this purpose, in recent years
It is made to be gradually introduced electric arc fuse increasing material manufacturing (Wire Arc Additive Manufacturing, WAAM) technology
Metal wire material is melted successively accumulation that is, using electric arc as heat source to produce workpiece by standby propeller members.It is cast with tradition
The technology of making is compared, and electric arc fuse increasing material manufacturing has in terms of equipment is not necessarily to mold, and processing flexibility degree is high, and the manufacturing cycle is short,
The characteristics of being easily achieved Digitized manufacturing.
However, further investigations have shown that, material technology production propeller is being increased in the prior art using electric arc fuse,
Manufacture path planning is commonly planar slice mode, also concentrates on the adaptive of planar slice lifting capacity to the research of microtomy
In terms of algorithm；Wherein for adaptive planar slice according to the complexity of workpiece surface, complex surface plane lifting capacity is small, simple table
Facial plane lifting capacity is big.But for the propeller with more complicated space curved surface, especially in printing propeller hub
When mutually passing through the specific regions such as place, equal thickness planar slice or the mode of adaptive planar slice no matter is taken all with blade
Appear in the case where sustained height obtains multiple tracks profile.It in this case, can the multiple starting the arc during printing blade blade root
And blow-out, to reduce the dimensional accuracy of propeller, also results in leaf since electric arc is extremely unstable in the starting the arc and blow-out
Residual stress becomes larger at root, these are all unfavorable for the use of propeller.Correspondingly, this field needs to make further research and changes
Into preferably to meet the needs of manufacturing higher quality and higher efficiency to propeller members.
Summary of the invention
For the above shortcoming and Improvement requirement of the prior art, the present invention provides a kind of increasings of propeller electric arc fuse
Material manufacturing method, wherein by the product configurations feature and specific molding demand of propeller members itself of combining closely, to its into
The design of row specific aim subregion again, and the completely new processing road further combined using cylinder slice and plane slice process
Line executes electric arc fuse increasing material manufacturing forming process, is accordingly not only remarkably improved electric arc fuse increasing material manufacturing propeller members
Dimensional accuracy, substantially reduce its manufacturing cycle, and effectively prevent printing blade blade root when the starting the arc and blow-out phenomenon,
It is therefore particularly suitable for all kinds of propellers high-precision processing purposes for having complex space curved surfaces.
To achieve the above object, according to one aspect of the present invention, a kind of propeller electric arc fuse increasing material manufacturing is provided
Method, which is characterized in that this method includes the following steps:
(i) foundation of propeller threedimensional model and subregion
For the propeller members as object to be processed, its three-dimensional point cloud is generated, and is fitted and builds in space coordinates
Found corresponding threedimensional model；Then, it carries out targetedly subregion to this threedimensional model to dispose, wherein entire propeller hub coverlet
The each propeller blade for being solely set as first area, and being located at propeller hub side is each set to independent of each other more
A second area；
(ii) the particular path planning and designing of different subregions
For first area and multiple second areas, path is manufactured come planning and designing based on different principles: wherein for
For first area, the inside and outside contour of propeller hub is obtained by the way of planar slice first, wherein the planar slice institute
It is defined as remaining vertical plane with propeller hub axis with tangent plane, then calculates the propeller hub in the tangent plane
Inside and outside contour, then gradually biased by outer profile until Internal periphery, thus gradually the mentioning with cutting-height with the tangent plane
Rise and complete the path planning of entire propeller hub；And for multiple second areas, first using the side of cylinder slice
Each blade portion is divided into multiple profiles by formula, and wherein the cylinder is sliced cylinder section used and is defined as and the propeller
Then the coaxial cylindrical surface of propeller hub calculates the profile of the propeller blade on the cylinder section, then gradually inclined from the edge of profile
It sets until contoured interior is filled completely, thus completes institute one by one as slice height is gradually promoted with the radius on cylindrical surface
There is the path planning of propeller blade；
(iii) final molding based on electric arc fuse increasing material manufacturing
According to the manufacture path of propeller hub and blade that step (ii) is completed, using electric arc fuse increasing material manufacturing work
Skill carries out corresponding Combined machining, and then obtains required propeller members product.
As it is further preferred that gradually being biased in its outer profile until Internal periphery for the propeller hub
During, each offset is preferably set to 2.5mm.
As it is further preferred that gradually being biased at the edge of its profile until wheel for the propeller blade
During wide inside is filled completely, it is preferred to use circumferentially filling and cylinder axial direction fill mode alternately to hold to cylinder
Row: wherein circumferentially filling is defined as the point set of contoured interior according to profile circumferencial direction coordinate value consistent time the cylinder
Sequence connects, the filling mode gradually deviated then along propeller hub axis direction；And axially filling is defined as the cylinder
The point set of contoured interior is connected according to the hub axis direction consistent order of coordinate value, then along propeller hub circumferencial direction
The filling mode gradually deviated.
As it is further preferred that gradually being biased at the edge of its profile until wheel for the propeller blade
During wide inside is filled completely, each offset is preferably set to 2.5mm.
As it is further preferred that in step (iii), the key process parameter of the electric arc fuse increasing material manufacturing technique
Including speed of welding, welding current, weldingvoltage and wire feed rate etc., and it is corresponding with selected silk material holding.
As it is further preferred that the lifting capacity of the cylinder slice remains unchanged, and its size in step (ii)
It is preferably set to equal with the reinforcement of single track stack layer.
As it is further preferred that the propeller members are for example naval vessel propelling screws.
In general, through the invention it is contemplated above technical scheme is compared with the prior art, mainly have below
Technological merit:
1, not only right by the product configurations feature for propeller members itself of combining closely and specific molding demand, the present invention
It has carried out zoning design again, it is often more important that also based on the mechanism being sliced with the shape, for propeller hub and blade point
Different section hierarchical path plannings is not introduced；Correspondingly, more actual test shows that it can be with propeller members
Complex three-dimensional construction feature is preferably adapted, and the ruler of electric arc fuse increasing material manufacturing can be significantly improved from the point of view of final products
Very little precision, while greatly shortening its manufacturing cycle；
2, the subregion and section hierarchical planning that the present invention is redesigned can preferably join electric arc increasing material manufacturing technique
Number optimizes disposition, so that each key process parameter is more accurately adapted with print area, is therefore particularly suitable for each
The complex-curved propeller members manufacturing process of class, and it is existing to effectively prevent the frequent starting the arc and blow-out when printing blade blade root
As.
Detailed description of the invention
Fig. 1 is the concrete technology flow process according to propeller electric arc fuse increasing material manufacturing process constructed by the present invention
Figure；
Fig. 2 is a preferred embodiment according to the invention, for showing propeller hub planar slice and biasing filling
Schematic illustration；
Fig. 3 is illustrated as demonstration, for being particularly shown in actual operation for propeller blade stl file
Execute the schematic illustration of local triangle's dough sheet calculating intersection point of cylinder slice and acquisition；
Fig. 4 is according to present invention propeller blade profile printing path schematic diagram obtained；
Fig. 5 a and Fig. 5 b are remarked additionally as demonstration respectively, for being particularly shown in actual operation for propeller
Blade stl file execute cylinder slice when, in fact it could happen that local triangle's dough sheet calculate intersection point special circumstances schematic diagram；
Fig. 6 is according to present invention propeller blade fill path schematic diagram obtained；
Fig. 7 is a preferred embodiment according to the invention, for being shown as present invention propeller blade obtained
Cylinder circumferentially fills schematic diagram；
Fig. 8 is a preferred embodiment according to the invention, for being shown as present invention propeller blade obtained
Cylinder radially fills schematic diagram
Specific embodiment
In order to make the objectives, technical solutions, and advantages of the present invention clearer, with reference to the accompanying drawings and embodiments, right
The present invention is further elaborated.It should be appreciated that the specific embodiments described herein are merely illustrative of the present invention, and
It is not used in the restriction present invention.As long as in addition, technical characteristic involved in the various embodiments of the present invention described below
Not constituting a conflict with each other can be combined with each other.
Fig. 1 is the overall process schematic diagram according to casting technological parameter optimization method constructed by the present invention.Such as Fig. 1 institute
Show, it is shown that according to the concrete technology flow process figure of propeller electric arc fuse increasing material manufacturing process constructed by the present invention.With
The prior art is compared, and is in place of key improvements, is studied and proposed for the construction feature of propeller complex component
Targetedly zoning design, and further just different subregions uses different layering fill path planning；Correspondingly, greatly
The actual test of amount shows that the entire machining accuracy of electric arc fuse increasing material manufacturing propeller and appearance profile is enabled to control
More preferably, adaptable in actually printing convenient for manipulation；In addition, the present invention is significantly improving the same of final products forming accuracy
When can also greatly shorten the manufacturing cycle.
Specific explanations explanation will be carried out one by one to these steps below.
Firstly, first is foundation and the partitioning step of propeller threedimensional model.
For the propeller members as object to be processed, its three-dimensional point cloud is generated, and is fitted and builds in space coordinates
Found corresponding threedimensional model；Then, it carries out targetedly subregion to this threedimensional model to dispose, wherein entire propeller hub coverlet
The each propeller blade for being solely set as first area, and being located at propeller hub side is each set to independent of each other more
A second area.
More specifically, in actual operation, for example data point two-dimentional in propeller plan drawing can be converted to space
Three-dimensional point cloud file, and obtain the three-dimensional modeling of propeller to be printed.Then, the point cloud file format example of propeller data point
It is such as imported into, and the point of sustained height is fitted to spline curve and fair curve.Then, propeller data point coordinate is convertible
The point cloud file for generating propeller aperture three-dimensional feature point, is then introduced into and the point of sustained height is fitted to spline curve simultaneously
And fair curve.Finally, passing through the space curve group of different height, it can be fitted to obtain propeller blade sheet body, sheet body is sutured
Propeller blade entity is obtained later, and thus propeller three-dimension modeling is completed.
The above concrete processing procedure is known in the art, therefore details are not described herein.As crucial medical record, this hair
Region division is carried out to propeller threedimensional model in bright；Wherein propeller hub is an isolated area；Each paddle of propeller
Leaf is as an isolated area.This Regionalization basis mainly considers that the component belongs to complex space curved surfaces, by by conduct
The propeller hub of relatively easy specification curved surface is divided into isolated area, while will be provided with symmetry and curved surface complexity features
Each propeller blade is individually divided into a region, in this way can be convenient in the planning of subsequent printing path and practical print processing
When can preferably control profile characteristic, and sufficiently combined structure feature carries out the forming process of more machining accuracy.
Then, second be different subregions particular path planning and designing step.
For first area and multiple second areas, path is manufactured come planning and designing based on different principles: wherein for
For first area, the inside and outside contour of propeller hub is obtained by the way of planar slice first, wherein the planar slice institute
It is defined as remaining vertical plane with propeller hub axis with tangent plane, then calculates the propeller hub in the tangent plane
Inside and outside contour, then gradually biased by outer profile until Internal periphery, thus gradually the mentioning with cutting-height with the tangent plane
Rise and complete the path planning of entire propeller hub；And for multiple second areas, first using the side of cylinder slice
Each blade portion is divided into multiple profiles by formula, and wherein the cylinder is sliced cylinder section used and is defined as and the propeller
Then the coaxial cylindrical surface of propeller hub calculates the profile of the propeller blade on the cylinder section, then gradually inclined from the edge of profile
It sets until contoured interior is filled completely, thus completes institute one by one as slice height is gradually promoted with the radius on cylindrical surface
There is the path planning of propeller blade；
More specifically, as shown in Fig. 2, for the propeller hub for having completed subregion, in the present invention to it
The processing for carrying out planar slice, obtains propeller hub inside and outside contour.Meanwhile outer profile gradually being biased up to Internal periphery, partially
Shifting amount is preferably 2.5mm.Inside and outside contour is printed in practical print procedure first to guarantee propeller hub dimensional accuracy, then carry out again partially
Set filling.
As one of key improvements of the invention, as shown in Fig. 3 demonstration, for having completed each propeller of subregion
For blade, the processing of cylinder section is carried out to it in the present invention.
Specific section is the cylindrical surface that radius is gradually promoted with slice height as shown in Figure 3 and Figure 4, and hoisting depth is excellent
It is selected as the reinforcement of single track stack layer in the case where selected technological parameter, generally 2.0mm-3.0mm is promoted in the present embodiment
Height is 2.0mm.It is illustrated to more specifically give, present invention combination marginal data is as follows.In actual operation, cylinder
It can be intersected in slicing processes using cylinder section with model propeller stl file intermediate cam shape dough sheet to calculate profile print path
Diameter.It realizes that algorithm is specific as follows: (1) defining cylinder section.In slice program, using definition perpendicular in hub axis
O and O1 two o'clock coordinate and radius R determine cylinder section；(2) judge STL model intermediate cam shape dough sheet whether with cylinder section phase
It hands over, by all and section, there are the triangle surfaces of intersection point to be stored in a set；(3) one by one to required triangle surface set
Ask friendship.Then P point coordinate is acquired using following formula；(4) when all intersection points for finding out current cylinder section and stl file
Afterwards, it is sequentially connected in sequence to get contour edge printing path is arrived.
Some special circumstances during above-mentioned calculating intersection point are further illustrated below in conjunction with figure.As shown in Figure 5 a, three
Angular dough sheet and one and only one intersection point of cylinder section；Before calculating intersection point, each vertex of triangle surface is judged
Whether the distance D to axis is equal to radius R, if one and only one vertex meets condition, this is put in deposit intersection point set.
Furthermore as shown in Figure 5 b, a line of triangle surface is on cylinder section, and the distance D on two vertex to axis is equal to if it exists
R, the then side that will possess the two vertex exclude, calculate the two other side of triangle surface and the intersection point of cylinder section and by its
It is stored in intersection point set.
Then, as shown in fig. 6, after acquiring blade contour path, the present invention " can draw net on cylindrical surface using one kind
The method of lattice " calculates scanning filling path.During calculating fill path, offset 2.5mm, that is, the side of grid
Length is 2.5mm, thus finds out the coordinate of the point set in profile on cylinder section.
As another key improvements of the invention, a preferred embodiment according to the invention, filling mode is divided into two kinds:
Cylinder circumferentially axially fill by filling and cylinder.Cylinder is circumferentially filled as shown in fig. 7, by required point set according to circumferencial direction coordinate value
It is consistent to be linked in sequence, and gradually deviate until contoured interior is filled completely.Axially filling such as Fig. 8 shows cylinder, column
Axially required point set is linked in sequence by filling according to axis direction coordinate value is consistent in face, and is gradually deviated until wheel
Wide inside is filled complete.It is further preferred that the point of fill path, which is gathered, is inwardly indented 2.5mm in contour edge, in order to
In banking process, effective overlap joint of contour layer and filled layer.Correspondingly, during actually manufacturing propeller, by adopting
With cylinder, axially circumferentially filling mode alternately is printed for filling and cylinder, with guarantee propeller members performance it is each to
The same sex.
Finally, being the final molding step based on electric arc fuse increasing material manufacturing.
The manufacture path of the propeller hub and blade completed according to above step, using electric arc fuse increasing material manufacturing technique
Corresponding Combined machining is carried out, and then obtains required propeller members product.
More specifically, the conversion that robot language can be carried out to the hierarchy slicing path, obtains robot motion
Welding instruction.Then, the robot motion is welded into instruction and imports robot controlling platform, using with propeller electric arc fuse
Increasing material manufacturing selects the corresponding technological parameter of silk material to carry out propeller processing manufacture.In the present embodiment, technological parameter used
It is preferred that being respectively welding current: 135A；Weldingvoltage: 18V；Wire feed rate: 60mm/s；Speed of welding: 8mm/s.
To sum up, it is used during path planning of the present invention and is sliced path planning mode by the curved surface of section of cylindrical surface,
It is a kind of method that path planning is carried out according to propeller members section feature itself, this method is based on profile-followed slice principle,
The dimensional accuracy of electric arc fuse increasing material manufacturing propeller members is not only increased, and greatly shortens propeller manufacture week
Phase.
As it will be easily appreciated by one skilled in the art that the foregoing is merely illustrative of the preferred embodiments of the present invention, not to
The limitation present invention, any modifications, equivalent substitutions and improvements made within the spirit and principles of the present invention should all include
Within protection scope of the present invention.
Claims (6)
1. a kind of propeller electric arc fuse increasing material manufacturing method, which is characterized in that this method includes the following steps:
(i) foundation of propeller threedimensional model and subregion
For the propeller members as object to be processed, its three-dimensional point cloud is generated, and the fitting foundation pair in space coordinates
The threedimensional model answered；Then, it carries out targetedly subregion to this threedimensional model to dispose, wherein entire propeller hub is individually set
The each propeller blade for being set to first area, and being located at propeller hub side is each set to independent of each other multiple the
Two regions；
(ii) the particular path planning and designing of different subregions
For first area and multiple second areas, path is manufactured come planning and designing based on different principles: wherein for first
For region, the inside and outside contour of propeller hub is obtained by the way of planar slice first, is wherein cut used in the planar slice
Plane is defined as remaining vertical plane with propeller hub axis, then calculates in the tangent plane inside and outside propeller hub
Profile, then gradually biased by outer profile until Internal periphery, thus with the tangent plane with the gradually promotion of cutting-height and
Complete the path planning of entire propeller hub；And for multiple second areas, it will first by the way of cylinder slice
Each blade portion is divided into multiple profiles, and wherein the cylinder is sliced cylinder section used and is defined as and the propeller hub
Then coaxial cylindrical surface calculates the profile of the propeller blade on the cylinder section, then gradually bias directly from the edge of profile
It is filled completely to contoured interior, thus completes all spiral shells one by one as slice height is gradually promoted with the radius on cylindrical surface
Revolve the path planning of paddle blade；
(iii) final molding based on electric arc fuse increasing material manufacturing
According to the manufacture path of propeller hub and blade that step (ii) is completed, using electric arc fuse increasing material manufacturing technique into
The corresponding Combined machining of row, and then obtain required propeller members product.
2. a kind of propeller electric arc fuse increasing material manufacturing method as described in claim 1, which is characterized in that for the spiral
For paddle propeller hub, during its outer profile is gradually biased up to Internal periphery, each offset is preferably set to 2.5mm.
3. a kind of propeller electric arc fuse increasing material manufacturing method as claimed in claim 1 or 2, which is characterized in that for described
For propeller blade, during the edge of its profile gradually biases and is filled complete until contoured interior, it is preferred to use
Circumferentially axially filling mode alternately executes cylinder for filling and cylinder: wherein the cylinder circumferentially filling be defined as by
The point set of contoured interior is connected according to the consistent order of profile circumferencial direction coordinate value, then along propeller hub axis direction by
The filling mode gradually deviated；And axially filling is defined as sitting the point set of contoured interior according to hub axis direction the cylinder
The consistent order of scale value connects, the filling mode gradually deviated then along propeller hub circumferencial direction.
4. a kind of propeller electric arc fuse increasing material manufacturing method as claimed in any one of claims 1-3, which is characterized in that right
For the propeller blade, during the edge of its profile gradually biases and is filled complete until contoured interior, often
Secondary offset is preferably set to 2.5mm.
5. a kind of propeller electric arc fuse increasing material manufacturing method as described in claim 1-4 any one, which is characterized in that
In step (iii), the key process parameter of the electric arc fuse increasing material manufacturing technique includes speed of welding, welding current, welding
Voltage and wire feed rate etc., and it is corresponding with selected silk material holding.
6. a kind of propeller members product uses the electric arc fuse increasing material manufacturing side as described in claim 1-5 any one
Method and be made.
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110802302A (en) * | 2019-10-18 | 2020-02-18 | 华中科技大学 | Arc fuse wire additive manufacturing method of multidirectional steel node |
| CN111890061A (en) * | 2020-07-31 | 2020-11-06 | 华中科技大学 | High-precision arc fuse additive manufacturing method for aircraft transition end frame and product thereof |
| CN112157213A (en) * | 2020-08-31 | 2021-01-01 | 镇江同舟螺旋桨有限公司 | 3D printing manufacturing method of fiber reinforced composite propeller for ship |
| CN112214906A (en) * | 2020-10-22 | 2021-01-12 | 华中科技大学 | Filling track planning method based on principal component analysis |
| CN112659122A (en) * | 2020-12-10 | 2021-04-16 | 江苏科技大学 | Propeller cleaning path planning method and cleaning robot using same |
| CN113042858A (en) * | 2021-04-02 | 2021-06-29 | 华东理工大学 | Adaptive parameter-adaptive arc additive manufacturing method and system |
| CN114036595A (en) * | 2021-09-30 | 2022-02-11 | 北京空间机电研究所 | Tool rapid modeling method for spacecraft composite material honeycomb sandwich structure plate |
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Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1476956A (en) * | 2003-04-30 | 2004-02-25 | 华中科技大学 | Quick manufacture method and its equipment |
| CN103949646A (en) * | 2014-05-19 | 2014-07-30 | 北京航空航天大学 | Preparation method for Nb-Si base ultra-temperature alloy turbine vane |
| TW201529286A (en) * | 2013-07-10 | 2015-08-01 | 松下電器產業股份有限公司 | Method for manufacturing three-dimensional modeled object |
| CN105252774A (en) * | 2015-11-19 | 2016-01-20 | 吴江中瑞机电科技有限公司 | Generating method for multiple contour scanning paths for additive manufacturing |
| CN105643053A (en) * | 2016-03-04 | 2016-06-08 | 贵州师范大学 | Consumable electrode gas shielded arc deposition three-dimensional printing method |
| CN106166599A (en) * | 2016-07-20 | 2016-11-30 | 珠海市和裕丰船舶设备有限公司 | A kind of 3D prints the method manufacturing propeller |
| CN106200559A (en) * | 2016-07-11 | 2016-12-07 | 湖南大学 | A kind of rapid generation printing section for 3d |
-
2018
- 2018-08-24 CN CN201810972135.2A patent/CN108971698B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1476956A (en) * | 2003-04-30 | 2004-02-25 | 华中科技大学 | Quick manufacture method and its equipment |
| TW201529286A (en) * | 2013-07-10 | 2015-08-01 | 松下電器產業股份有限公司 | Method for manufacturing three-dimensional modeled object |
| CN103949646A (en) * | 2014-05-19 | 2014-07-30 | 北京航空航天大学 | Preparation method for Nb-Si base ultra-temperature alloy turbine vane |
| CN105252774A (en) * | 2015-11-19 | 2016-01-20 | 吴江中瑞机电科技有限公司 | Generating method for multiple contour scanning paths for additive manufacturing |
| CN105643053A (en) * | 2016-03-04 | 2016-06-08 | 贵州师范大学 | Consumable electrode gas shielded arc deposition three-dimensional printing method |
| CN106200559A (en) * | 2016-07-11 | 2016-12-07 | 湖南大学 | A kind of rapid generation printing section for 3d |
| CN106166599A (en) * | 2016-07-20 | 2016-11-30 | 珠海市和裕丰船舶设备有限公司 | A kind of 3D prints the method manufacturing propeller |
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110802302A (en) * | 2019-10-18 | 2020-02-18 | 华中科技大学 | Arc fuse wire additive manufacturing method of multidirectional steel node |
| CN111890061A (en) * | 2020-07-31 | 2020-11-06 | 华中科技大学 | High-precision arc fuse additive manufacturing method for aircraft transition end frame and product thereof |
| CN112157213A (en) * | 2020-08-31 | 2021-01-01 | 镇江同舟螺旋桨有限公司 | 3D printing manufacturing method of fiber reinforced composite propeller for ship |
| CN112214906A (en) * | 2020-10-22 | 2021-01-12 | 华中科技大学 | Filling track planning method based on principal component analysis |
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| CN113042858B (en) * | 2021-04-02 | 2022-02-22 | 华东理工大学 | Adaptive parameter-adaptive arc additive manufacturing method and system |
| CN114036595A (en) * | 2021-09-30 | 2022-02-11 | 北京空间机电研究所 | Tool rapid modeling method for spacecraft composite material honeycomb sandwich structure plate |
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