CN114560063A - Gyroid structure-based aircraft base with noise elimination performance and manufacturing method thereof - Google Patents
Gyroid structure-based aircraft base with noise elimination performance and manufacturing method thereof Download PDFInfo
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- CN114560063A CN114560063A CN202210186642.XA CN202210186642A CN114560063A CN 114560063 A CN114560063 A CN 114560063A CN 202210186642 A CN202210186642 A CN 202210186642A CN 114560063 A CN114560063 A CN 114560063A
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- gyroid
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63G—OFFENSIVE OR DEFENSIVE ARRANGEMENTS ON VESSELS; MINE-LAYING; MINE-SWEEPING; SUBMARINES; AIRCRAFT CARRIERS
- B63G8/00—Underwater vessels, e.g. submarines; Equipment specially adapted therefor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B63—SHIPS OR OTHER WATERBORNE VESSELS; RELATED EQUIPMENT
- B63B—SHIPS OR OTHER WATERBORNE VESSELS; EQUIPMENT FOR SHIPPING
- B63B3/00—Hulls characterised by their structure or component parts
- B63B3/13—Hulls built to withstand hydrostatic pressure when fully submerged, e.g. submarine hulls
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
The invention discloses a Gyroid structure-based aircraft base with silencing performance, which is wholly or partially made of a Gyroid minimum curved surface structure; the Gyroid tiny curved surface structure comprises a plurality of Gyroid tiny curved surface unit cells which are arrayed in a three-dimensional space and connected with each other; the Gyroid tiny curved surface has the advantages of zero average curvature of the surface, no distortion, no sharp edge and good mechanical property, and meanwhile, the structure has long fatigue life, a complex topological structure and a large specific surface area, and can effectively absorb vibration noise generated by an aircraft and reduce the dead weight of the base.
Description
Technical Field
The invention relates to the technical field of material structures and underwater vehicles, in particular to a vehicle base with silencing performance and based on a Gyroid structure and a manufacturing method thereof.
Background
In the present day that marine industry is rapidly developed and the sea defense consciousness of all countries in the world is continuously strengthened, all countries strive to improve the concealment of the underwater vehicle, reduce noise, compress volume and improve sound stealth performance, and the submarine design is a revolution. The extremely small curved surface has wide application prospect in the industries of aerospace, petrochemical engineering, machinery, medical treatment and the like due to the inherent excellent properties of the extremely small curved surface, such as ultra-light weight, high strength, energy absorption, heat transfer and permeation and the like. The structure of the extremely small curved surface can realize parametric modeling, the porosity of the structure can be regulated and controlled by changing structural parameters, the same configuration has different mechanical properties under different porosities, and the mechanical parameter values are reduced along with the increase of the porosity. Wherein, the Gyroid structure (G) has complex internal topology and good mechanical property.
Disclosure of Invention
The object of the present invention is therefore to make available a porous design of the base of an existing aircraft, the walls of which are designed to be porous while at the same time satisfying the sealing and load-bearing properties of the base. The characteristics of a complex internal topological structure and a large specific surface area of the G curved surface are utilized to realize the functions of silencing and absorbing energy to a great extent for transmitting sound waves inside the base of the aircraft.
The invention relates to a Gyroid structure-based aircraft base with silencing performance, which comprises a base and a top cover; the base and the top cover are both made of Gyroid minimum curved surface structures; the Gyroid minimum-curved-surface structure comprises a plurality of Gyroid minimum-curved-surface unit cells which are arrayed in a three-dimensional space and connected with one another.
Further, the Gyroid minimum curved surface structure is distributed inside the wall thickness of the base of the aircraft.
Further, the porosity of the Gyroid tiny curved surface structure in the top cover is larger than that of the Gyroid tiny curved surface structure in the base.
The invention relates to a method for manufacturing said aircraft base, characterized in that it comprises the following steps:
s1. drawing Gyroid minimal surface unit cells;
s2, thickening the drawn minimum curved surface to form a lamellar Gyroid minimum curved surface unit cell;
s3., arraying the obtained sheet-shaped extremely-small-curved-surface Gyroid unit cells to form an extremely-small-curved-surface Gyroid structure, and embedding the formed extremely-small-curved-surface Gyroid structure into the side wall of the base of the aircraft;
s5. the aircraft base is obtained by integral processing based on 3D printing.
Further, in step s1, Gyroid minimal surface unit cell models with different pore sizes are built by the following generations:
Y＝cos(ωx)sin(ωy)+cos(ωy)sin(ωz)+cos(ωz)sin(ωx)-t；
the porosity of the structure is obtained by changing the t value in the formula.
Further, when a Gyroid minimum surface unit cell model of the top cover is established, the value of the parameter t is 0.6; and when a Gyroid minimum-surface single-cell model of the base is established, the value of the parameter t is 0.4.
Further, when a Gyroid minimum-curved-surface single-cell model of the top cover is established, the height coefficient value is 0.5-1.5; and when a Gyroid minimum-surface single-cell model of the base is established, the height coefficient is 1-2.
Further, in step s5, printing is performed by using the SLM process, with the process parameters of 275W laser power, 1250mm/s scanning speed, 0.13mm scanning pitch, and 30 μm layer thickness.
The invention has the beneficial effects that: the aircraft base is designed by adopting a gyroid (G) minimum curved surface structure, the structure has the advantages of zero average curvature of the surface, no distortion, no sharp edge and better mechanical property, and meanwhile, the structure has long fatigue life, complex topological structure and large specific surface area, and can effectively absorb vibration noise generated by an aircraft and reduce the dead weight of the base.
Drawings
The technical scheme of the invention is further explained by combining the drawings and the embodiment as follows:
FIG. 1 is a schematic structural view of a vehicle base;
fig. 2 is a schematic distribution diagram of the extremely small curved structures in the base of the vehicle (the cross-sectional line area in the diagram is the distribution area of the extremely small curved structures).
Detailed Description
The aircraft base with the silencing performance based on the Gyroid structure comprises a base and a top cover; the base and the top cover are both made of Gyroid minimum curved surface structures; the Gyroid minimum-curved-surface structure comprises a plurality of Gyroid minimum-curved-surface unit cells which are arrayed in a three-dimensional space and connected with one another. The Gyroid tiny curved surface structure is distributed inside the wall thickness of the base of the aircraft.
The porosity of the Gyroid minimum curved surface structure in the top cover is larger than that of the Gyroid minimum curved surface structure in the base.
A method for manufacturing the aircraft base of the present embodiment is characterized by comprising the following steps:
s1. drawing Gyroid minimal surface unit cells;
s2, thickening the drawn minimum curved surface to form a lamellar Gyroid minimum curved surface unit cell;
s3., arraying the obtained sheet-shaped extremely-small-curved-surface Gyroid unit cells to form an extremely-small-curved-surface Gyroid structure, and embedding the formed extremely-small-curved-surface Gyroid structure into the side wall of the base of the aircraft;
s5. the aircraft base is obtained by integral processing based on 3D printing.
In step s1, Gyroid minimal surface unit cell models with different pore sizes are built by the following generations:
Y＝cos(ωx)sin(ωy)+cos(ωy)sin(ωz)+cos(ωz)sin(ωx)-t；
the porosity of the structure is obtained by changing the t value in the formula.
When a Gyroid minimum surface unit cell model of the top cover is established, the value of the parameter t is 0.6; and when a Gyroid minimum-surface single-cell model of the base is established, the value of the parameter t is 0.4.
When a Gyroid minimum-surface single-cell model of the top cover is established, the height coefficient is 0.5-1.5; and when a Gyroid minimum-surface single-cell model of the base is established, the height coefficient is 1-2.
By changing the coefficient value of the height parameter k of the unit cell structure, a height model with different bearing capacities is obtained. The height coefficient of the top cover is 0.5-1.5, and the height coefficient of the base is 1-2. The higher the coefficient the stronger the load bearing capacity.
In step s5, printing is performed by SLM process, wherein the process parameters are 275W of laser power, 1250mm/s of scanning speed, 0.13mm of scanning distance and 30 μm of layer thickness.
Finally, the above embodiments are only for illustrating the technical solutions of the present invention and not for limiting, although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that modifications or equivalent substitutions may be made to the technical solutions of the present invention without departing from the spirit and scope of the technical solutions of the present invention, and all of them should be covered in the claims of the present invention.
Claims (8)
1. A Gyroid structure-based aircraft base with sound attenuation performance is characterized in that: comprises a base and a top cover; the base and the top cover are both made of Gyroid minimum curved surface structures; the Gyroid minimum-curved-surface structure comprises a plurality of Gyroid minimum-curved-surface unit cells which are arrayed in a three-dimensional space and connected with one another.
2. The vehicle base of claim 1, wherein: the Gyroid tiny curved surface structure is distributed inside the wall thickness of the base of the aircraft.
3. The vehicle base of claim 1, wherein: the porosity of the Gyroid minimum curved surface structure in the top cover is larger than that of the Gyroid minimum curved surface structure in the base.
4. A method for manufacturing an aircraft base according to any one of claims 1-3, characterized in that it comprises the following steps:
s1. drawing Gyroid minimal surface unit cells;
s2, thickening the drawn minimum curved surface to form a lamellar Gyroid minimum curved surface unit cell;
s3., arraying the obtained sheet-shaped extremely-small-curved-surface Gyroid unit cells to form an extremely-small-curved-surface Gyroid structure, and embedding the formed extremely-small-curved-surface Gyroid structure into the side wall of the base of the aircraft;
s5. the aircraft base is obtained by integral processing based on 3D printing.
5. The method for manufacturing an aircraft base according to claim 4, wherein: in step s1, Gyroid minimal surface unit cell models with different pore sizes are built by the following generations:
Y＝cos(ωx)sin(ωy)+cos(ωy)sin(ωz)+cos(ωz)sin(ωx)-t；
the porosity of the structure is obtained by changing the t value in the formula.
6. The method for manufacturing an aircraft base according to claim 5, wherein: when a Gyroid minimum-surface single-cell model of the top cover is established, the value of the parameter t is 0.6; and when a Gyroid minimum-surface single-cell model of the base is established, the value of the parameter t is 0.4.
7. The method for manufacturing an aircraft base according to claim 5, wherein: when a Gyroid minimum-surface single-cell model of the top cover is established, the height coefficient is 0.5-1.5; and when a Gyroid minimum-surface single-cell model of the base is established, the height coefficient is 1-2.
8. The method for manufacturing a base for an aircraft according to claim 4, characterized in that: in step s5, printing is performed by SLM process, wherein the process parameters are 275W of laser power, 1250mm/s of scanning speed, 0.13mm of scanning distance and 30 μm of layer thickness.
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2022
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