KR20160056634A - Aerial vehicle comprising multiple rotors and frame manufacturing method thereof - Google Patents
Aerial vehicle comprising multiple rotors and frame manufacturing method thereof Download PDFInfo
- Publication number
- KR20160056634A KR20160056634A KR1020140157195A KR20140157195A KR20160056634A KR 20160056634 A KR20160056634 A KR 20160056634A KR 1020140157195 A KR1020140157195 A KR 1020140157195A KR 20140157195 A KR20140157195 A KR 20140157195A KR 20160056634 A KR20160056634 A KR 20160056634A
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- hollow
- frame
- printing
- rotor blades
- present
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C67/00—Shaping techniques not covered by groups B29C39/00 - B29C65/00, B29C70/00 or B29C73/00
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
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- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
Abstract
The present invention discloses a flight body having a plurality of rotor blades and a frame manufacturing method of the flight body. That is, the present invention provides a simple design / manufacturing method using the difference in height of a wing (or a rotor), and a frame is manufactured by filling hollow of a frame structure printed in a hollow form with a molten filament at a time, Enabling cost savings and complementing and enhancing the weak bond between layer and layer of a stacked 3D printer.
Description
BACKGROUND OF THE INVENTION 1. Field of the Invention [0001] The present invention relates to a flight body having a plurality of rotor blades and a method of manufacturing a frame of the flight body.
A 3D printer (or a three-dimensional printer) is a device that directly forms an object using 3D data of an object.
When a flying object is manufactured using the FDM (Fused Deposition Modeling) type 3D printer, the shear load is increased due to the weight of the propeller and the motor of the manufactured flying object, and a break occurs.
Further, in the case of the FDM type 3D printer, when the filaments injected first are hardened after a certain period of time and the next filaments are laminated thereon, sufficient bonding force can not be obtained.
SUMMARY OF THE INVENTION It is an object of the present invention to provide a flight body having a plurality of rotor blades providing a simple design / manufacturing method using a height difference of a blade (or a rotor), and a method of manufacturing a frame of the flight body.
Another object of the present invention is to provide a flight body having a plurality of rotor blades for filling a hollow of a frame structure printed in a hollow form with molten filaments to produce a frame, and a method for manufacturing a frame of the flight body.
According to an embodiment of the present invention, there is provided a flight body including a plurality of rotor blades, the flight body including a plurality of rotor blades, the frame comprising: a frame formed by three-dimensional printing; A plurality of rods extending from the frame and having height differences according to a placement order; And a plurality of rotor blades configured to intersect at least a part of the turning radius with respect to the plurality of rod ends, wherein the frame includes an outer region that is primarily printed to have a hollow portion, And a hollow region having a larger bonding force than the region.
As an example related to the present invention, the rod may be formed by the three-dimensional printing, and may have a larger bonding force than the other outer areas that are first printed to have hollows and other outer areas that are printed through the second printing Other hollow regions may be included.
A method of manufacturing a frame of a flying body having a plurality of rotor blades according to an embodiment of the present invention includes the steps of forming a unit frame region constituting a frame, Forming a corresponding portion having a height difference according to an arrangement order of the rotor blades; And performing a first printing so that the predetermined frame area has a hollow and performing a second printing on the hollow of the structure where the first printing is completed to fill the hollow.
In one embodiment of the present invention, first printing is performed so as to have a plurality of rods formed between the frame and the rotor blades, and secondary printing is performed on the hollows of the first- The method may further comprise the step of filling.
The present invention provides a simple designing / manufacturing method using the height difference of the wing (or rotor), thereby making it possible to miniaturize the flying body and reduce the cost.
In addition, the present invention improves the load supporting ability by filling the hollow of the frame structure printed in the hollow type with the molten filaments at one time to improve the load-supporting ability and compensates the weak bonding force between the layer and the layer of the 3D printer There is an effect to strengthen.
FIG. 1 is a block diagram showing the configuration of a flying body having a plurality of rotor blades according to an embodiment of the present invention.
2 is a flowchart illustrating a method of manufacturing a frame of a flight vehicle having a plurality of rotor blades according to an embodiment of the present invention.
3 to 6 are views showing a structure including a hollow according to an embodiment of the present invention.
FIG. 7 and FIG. 8 are diagrams showing a flying object, which is a completed three-dimensional structure according to an embodiment of the present invention.
It is noted that the technical terms used in the present invention are used only to describe specific embodiments and are not intended to limit the present invention. In addition, the technical terms used in the present invention should be construed in a sense generally understood by a person having ordinary skill in the art to which the present invention belongs, unless otherwise defined in the present invention, Should not be construed to mean, or be interpreted in an excessively reduced sense. In addition, when a technical term used in the present invention is an erroneous technical term that does not accurately express the concept of the present invention, it should be understood that technical terms that can be understood by a person skilled in the art can be properly understood. In addition, the general terms used in the present invention should be interpreted according to a predefined or prior context, and should not be construed as being excessively reduced.
Furthermore, the singular expressions used in the present invention include plural expressions unless the context clearly dictates otherwise. The term "comprising" or "comprising" or the like in the present invention should not be construed as necessarily including the various elements or steps described in the invention, Or may further include additional components or steps.
Furthermore, terms including ordinals such as first, second, etc. used in the present invention can be used to describe elements, but the elements should not be limited by terms. Terms are used only for the purpose of distinguishing one component from another. For example, without departing from the scope of the present invention, the first component may be referred to as a second component, and similarly, the second component may also be referred to as a first component.
Hereinafter, exemplary embodiments of the present invention will be described in detail with reference to the accompanying drawings, wherein like reference numerals refer to like or similar elements throughout the several views, and redundant description thereof will be omitted.
In the following description, well-known functions or constructions are not described in detail since they would obscure the invention in unnecessary detail. It is to be noted that the accompanying drawings are only for the purpose of facilitating understanding of the present invention, and should not be construed as limiting the scope of the present invention with reference to the accompanying drawings.
1 is a block diagram showing a configuration of a flying body 10 having a plurality of rotor blades according to an embodiment of the present invention.
As shown in FIG. 1, a flying body 10 having a plurality of rotor blades is composed of a
Although the
The
In addition, the
That is, the
In addition, the
That is, the
The
Further, the
That is, the
In addition, the
That is, the
The rotor 300 is a structure that constitutes the air vehicle 10.
In addition, the rotor 300 is printed through the three-dimensional printer so as to include the hollow.
That is, the rotor blade 300 is formed in an outer region (or a second outer region) to be primarily printed so as to have a hollow.
In addition, the rotor 300 including the hollow core is subjected to a secondary printing process to fill the hollow through the dimension printer to form the finished rotor 300.
That is, the rotor 300 including the hollow is filled with the hollow through the filament through the secondary printing to form a hollow region (or a second hollow region) having a larger coupling force than the primary printed region.
The thickness of the first printed
Further, the filament used in the secondary printing according to the embodiment of the present invention may use the same filament as the filament used in the primary printing.
Further, the filament used in the secondary printing according to the embodiment of the present invention may use a filament having relatively higher strength than the filament used in the primary printing.
In addition, the
At this time, the plurality of
Thus, a simple design / manufacturing method using the difference in height of the blade (or rotor) can be provided.
In this way, the hollow of the frame structure printed in a hollow form can be filled with molten filaments at one time to produce a frame.
Hereinafter, a method of manufacturing a multi-rotor type air vehicle according to the present invention will be described in detail with reference to FIGS. 1 to 8. FIG.
2 is a flowchart illustrating a method of manufacturing a frame of a flight vehicle having a plurality of rotor blades according to an embodiment of the present invention.
First, primary printing is performed on each structure included in the three-dimensional structure based on three-dimensional data of a three-dimensional structure previously designed through a three-dimensional printer. Here, each structure to be printed first includes a hollow.
That is, through the three-dimensional printer, primary printing is performed on each of a plurality of rotors including a hollow, a plurality of rods including a hollow, and one or more frames including a hollow constituting the three-dimensional structure. At this time, the thickness of the at least one frame, the plurality of rotor blades, and the plurality of rods generated through the primary printing can be set to various thicknesses according to the designer's design. Further, in addition to the frame, the rod, and the rotor, additional components (not shown) for the air vehicle may further be printed.
For example, an arm including a hollow and a body (or frame) including the hollow are firstly printed through the three-dimensional printer (S210).
Thereafter, through the three-dimensional printer, secondary printing is performed on the hollow of the structure subjected to the primary printing with the same filament used in the primary printing.
That is, through the three-dimensional printer, the filaments are used to fill the cavity with respect to a plurality of the rotors including one or more frames including the completed first-printed hollow, a plurality of rods including the hollow, Car print is performed. At this time, the three-dimensional printer performs secondary printing in which the filaments are injected into the hollow formed in the frame, the rod, and the rotor blade, respectively, at one time.
For example, as shown in FIGS. 3 to 6, through the three-dimensional printer, the arm and the body including the hollow are filled with the same filament using the same filament used in forming the arm and the body, And the body is formed (S220).
Thereafter, the secondary printed structure is joined to form a three-dimensional structure. Here, the plurality of rods extend from the frame and are formed to have different height differences according to the arrangement order. Further, the plurality of rotor blades are configured (or formed) such that the turning radii at least partially intersect the plurality of rod ends.
For example, as shown in FIGS. 7 and 8, the arm and the body are combined to form a completed body (500) (S230).
As described above, the embodiment of the present invention provides a simple design / manufacturing method using the height difference of the wing (or rotor), thereby enabling downsizing of the flying body and cost reduction.
As described above, in the embodiment of the present invention, the hollow of the frame structure printed in the hollow form is filled with molten filaments at one time to manufacture a frame, thereby improving the load supporting ability, And the weak bonding force between the layers can be complemented and strengthened.
It will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the spirit or essential characteristics thereof. Therefore, the embodiments disclosed in the present invention are intended to illustrate rather than limit the scope of the present invention, and the scope of the technical idea of the present invention is not limited by these embodiments. The scope of protection of the present invention should be construed according to the following claims, and all technical ideas within the scope of equivalents should be construed as falling within the scope of the present invention.
The present invention provides a simple design / manufacturing method using a height difference of a wing (or a rotor), and enables a miniaturization of a flying body by manufacturing a frame by filling hollows of a frame structure printed in a hollow form with molten filaments And it can be widely used in the field of three-dimensional printer and the field of flight by complementing and reinforcing the weak bonding force between the layer and the layer of the layered 3D printer.
Claims (4)
A frame formed through three-dimensional printing;
A plurality of rods extending from the frame and having height differences according to a placement order; And
And a plurality of rotor blades configured to cross at least a part of the turning radius with respect to the plurality of rod ends,
Wherein the frame has a plurality of rotor blades including an outer region that is primarily printed with a hollow and a hollow region that has a greater bonding force than the outer region printed through the secondary printing.
The above-
A plurality of hollow regions formed through the three-dimensional printing and having a larger bonding force than the other outer regions printed by the primary printing through the secondary printing; A flying body equipped with a rotor blade.
Forming a unit frame region constituting a frame, wherein a portion corresponding to a region where a plurality of rotor blades are to be formed has a height difference according to an arrangement order of the rotor blades; And
Performing a first printing operation on the predetermined frame area so as to have a hollow and performing a second printing operation on the hollow of the first printing completed structure to fill the hollow, Way.
Performing a first printing operation so as to have a plurality of rods formed between the frame and the rotor blade with a hollow and performing a second printing operation on the hollow of the rod where the first printing operation is completed to fill the hollow Wherein the plurality of rotor blades are rotatably mounted on the frame.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| KR1020140157195A KR20160056634A (en) | 2014-11-12 | 2014-11-12 | Aerial vehicle comprising multiple rotors and frame manufacturing method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| KR1020140157195A KR20160056634A (en) | 2014-11-12 | 2014-11-12 | Aerial vehicle comprising multiple rotors and frame manufacturing method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| KR20160056634A true KR20160056634A (en) | 2016-05-20 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| KR1020140157195A KR20160056634A (en) | 2014-11-12 | 2014-11-12 | Aerial vehicle comprising multiple rotors and frame manufacturing method thereof |
Country Status (1)
| Country | Link |
|---|---|
| KR (1) | KR20160056634A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9884663B2 (en) | 2014-05-16 | 2018-02-06 | Divergent Technologies, Inc. | Modular formed nodes for vehicle chassis and their methods of use |
| US9975179B2 (en) | 2014-07-02 | 2018-05-22 | Divergent Technologies, Inc. | Systems and methods for fabricating joint members |
| US10960929B2 (en) | 2014-07-02 | 2021-03-30 | Divergent Technologies, Inc. | Systems and methods for vehicle subassembly and fabrication |
-
2014
- 2014-11-12 KR KR1020140157195A patent/KR20160056634A/en not_active Application Discontinuation
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9884663B2 (en) | 2014-05-16 | 2018-02-06 | Divergent Technologies, Inc. | Modular formed nodes for vehicle chassis and their methods of use |
| US10668965B2 (en) | 2014-05-16 | 2020-06-02 | Divergent Technologies, Inc. | Nodes with integrated adhesive ports and channels for construction of complex structures |
| US9975179B2 (en) | 2014-07-02 | 2018-05-22 | Divergent Technologies, Inc. | Systems and methods for fabricating joint members |
| US10960929B2 (en) | 2014-07-02 | 2021-03-30 | Divergent Technologies, Inc. | Systems and methods for vehicle subassembly and fabrication |
| US10960468B2 (en) | 2014-07-02 | 2021-03-30 | Divergent Technologies, Inc. | Stress-based method for optimization of joint members within a complex structure |
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