CN112550679B - Micro-nano resistance reduction structure for high-altitude high-speed environment - Google Patents
Micro-nano resistance reduction structure for high-altitude high-speed environment Download PDFInfo
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- CN112550679B CN112550679B CN202011505408.6A CN202011505408A CN112550679B CN 112550679 B CN112550679 B CN 112550679B CN 202011505408 A CN202011505408 A CN 202011505408A CN 112550679 B CN112550679 B CN 112550679B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
- B64C21/02—Influencing air flow over aircraft surfaces by affecting boundary layer flow by use of slot, ducts, porous areas or the like
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C21/00—Influencing air flow over aircraft surfaces by affecting boundary layer flow
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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
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
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Abstract
The invention provides a micro-nano resistance reducing structure for a high-altitude high-speed environment, which comprises a groove arranged on the outer surface of an aircraft, wherein the groove is in a long strip shape, the cross section of the groove is in an isosceles triangle shape, the vertex angle of the cross section of the groove is positioned at the bottom of the groove, the length of the bottom edge of the cross section of the groove is 150nm-200nm, the groove and high-speed airflow form a certain angle, a plurality of grooves are arranged on the outer surface of the aircraft at equal intervals along the direction vertical to the length of the groove, a separating strip is formed between any two adjacent grooves, the length direction of the separating strip is parallel to the length direction of the groove, the cross section of the separating strip is in the isosceles triangle shape, and the vertex angle of the cross section of the separating strip is positioned at the top end of the separating strip. The viscous drag reduction device is beneficial to reducing the viscous drag near the boundary layer of the near wall surface, further is beneficial to reducing the frictional resistance of high-speed gas to an aircraft, and has the advantages of simple structure, reliable work and good drag reduction effect.
Description
Technical Field
The invention relates to the technical field of object surface drag reduction design, in particular to a micro-nano drag reduction structure for a high-altitude high-speed environment.
Background
With the development of aerospace technology, the research and development and design technology of aircrafts is more and more mature.
At present, a plurality of aircrafts operating at high altitude exist in the market, and when the aircrafts fly at high altitude at high speed, the aircrafts can be subjected to large air resistance, so that the range and the speed of the aircrafts are influenced.
The prior publication No. CN105644770B discloses a shark skin-imitated drag reduction wing, a speed sensor is arranged on the surface of a fuselage, a skin layer is attached to the surface of the wing, a group of arc-shaped raised ribs are arranged on the surface of the skin layer, and a groove is formed between every two adjacent raised ribs. According to the resistance reduction method of the sharkskin-imitated resistance reduction wing, if the resistance measured by the speed sensor is too large, the skin layer is heated to be heated, and a sharkskin-imitated rib structure is formed by means of the tensile force of the variable trailing edge wing or the variable chord degree wing.
The inventor considers that the damping device in the prior art has a complex structure and poor damping effect, and has a place to be improved.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a micro-nano resistance reduction structure for a high-altitude high-speed environment.
The micro-nano resistance reducing structure for the high-altitude high-speed environment comprises a groove formed in the outer surface of an aircraft, the groove is long in strip shape, the cross section of the groove is in an isosceles triangle shape, the vertex angle of the cross section of the groove is located at the bottom of the groove, the length of the bottom side of the cross section of the groove is 150nm-200nm, the groove and high-speed airflow form a certain angle, the groove is formed in the outer surface of the aircraft at equal intervals in the direction perpendicular to the length of the groove, a plurality of separating strips are formed between any two adjacent grooves, the length direction of each separating strip is parallel to the length direction of the groove, the cross section of each separating strip is in the isosceles triangle shape, and the vertex angle of the cross section of each separating strip is located at the top end of the separating strip.
Preferably, the length direction of the groove is perpendicular to the flow direction of the high-speed airflow.
Preferably, the ratio of the base to the height of the cross section of the groove is in the range of 0.5 to 1.
Preferably, the angle of the apex angle of the groove cross-section ranges between 50 degrees and 70 degrees.
Preferably, the groove is formed by etching the outer surface of the aircraft by a laser micro-nano manufacturing technology.
Preferably, still including setting up the wind-guiding inclined plane at aircraft surface, the wind-guiding inclined plane is located the air inlet side of slot, and the wind-guiding inclined plane is kept away from the one side of slot to its one side slope that is close to the slot upwards sets up.
Preferably, the flying height of the aircraft is higher than 50 kilometers, and the flying speed of the aircraft is higher than Mach 3.
Compared with the prior art, the invention has the following beneficial effects:
1. according to the invention, the outer surface of the aircraft is provided with the plurality of grooves, the length directions of the grooves are mutually vertical to the length direction of the high-speed airflow, the cross sections of the grooves are isosceles triangles, the length of the bottom edge of the cross section of each groove is 150-200 nm, and the ratio of the bottom edge to the height of each triangle is 0.5-1, so that when the high-speed airflow flows through the micro-nano structure, the speed and pressure pulsation of the gas in the micro-nano structure on the surface of the aircraft can be reduced, thereby being beneficial to reducing the viscous resistance near a wall surface boundary layer, further being beneficial to reducing the friction resistance of the high-speed gas to the aircraft, and having the advantages of simple structure, reliable work and good resistance reduction effect.
2. According to the invention, the two adjacent grooves are separated by the separating strip with the isosceles triangle-shaped cross section, and the vertex angle of the cross section of the separating strip is positioned at one end of the separating strip, which is far away from the bottom of the groove, so that the separating effect is achieved on the two adjacent grooves, the density of the grooves is improved, and the resistance reducing effect is improved.
3. The ratio range of the bottom edge to the height of the cross section of the groove is set to be 0.5-1, so that the separation position of laminar flow of the outer surface of the aircraft can be delayed, and the frictional resistance of the outer surface of the aircraft can be reduced.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a main view of the whole micro-nano resistance reduction structure mainly embodied by the invention;
fig. 2 is a schematic side view of the whole micro-nano drag reduction structure mainly embodied by the invention.
Description of the drawings: 1. a trench; 2. an air guide inclined plane; 3. a dividing strip.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the invention.
As shown in fig. 1, the micro-nano resistance-reducing structure for high-altitude and high-speed environments provided by the invention comprises a groove 1 etched on the outer surface of an aircraft by a laser micro-nano manufacturing technology, and further comprises an air guide inclined plane 2 integrally formed on the outer surface of the aircraft, wherein the air guide inclined plane 2 is positioned on the air inlet side of the groove 1. The flying height of the aircraft is higher than 50 kilometers, and the flying speed of the aircraft is higher than Mach 3.
As shown in fig. 1, the shape of the groove 1 is a long strip, and the length direction of the groove 1 is perpendicular to the flow direction of the high-speed airflow. The cross section of the groove 1 is an isosceles triangle, and the vertex angle of the cross section of the groove 1 is positioned at the bottom of the groove 1. The apex angle of the cross section of the groove 1 ranges between 50 degrees and 70 degrees, and the apex angle of the cross section of the groove 1 is preferably 60 degrees. The length of the bottom side of the cross section of the groove 1 is between 150nm and 200nm, and the ratio of the bottom side of the cross section of the groove 1 to the height is in the range of 0.5 to 1.
When the high-speed airflow flows through the groove 1, the speed and the pressure pulsation of the gas in the micro-nano structure on the outer surface of the aircraft can be reduced, so that the viscous resistance near a boundary layer of the outer surface of the aircraft, which is close to a wall surface, is reduced, the separation position of laminar flow on the outer surface of the aircraft is delayed, and the frictional resistance of the air is reduced.
Further, the length dimension and the height dimension of the bottom side of the cross section of the groove 1 are selected to be different according to different air flow speeds on the surface of the object, so that the frictional resistance of the aircraft can be reduced.
The grooves 1 are arranged on the outer surface of the aircraft at equal intervals along the flow direction of high-speed airflow, and the separating strips 3 are integrally formed between any two adjacent grooves 1, and because the structure and the connection mode of any separating strip 3 are the same, a group of separating strips 3 is taken as an example for explanation. The length direction of the division bar 3 is parallel to the length direction of the groove 1, the cross section of the division bar 3 is an isosceles triangle, and the vertex angle of the cross section of the division bar 3 is located at one end of the division bar 3 far away from the bottom of the groove 1. The separation of two adjacent grooves 1 by the dividing strip 3 increases the density of the grooves 1 per unit area, thereby reducing the air resistance to which the aircraft is subjected.
As shown in fig. 2, the length direction of the air guiding inclined plane 2 is parallel to the length direction of the groove 1, the air guiding inclined plane 2 is arranged obliquely upward from one side of the air guiding inclined plane away from the groove 1 to one side of the air guiding inclined plane close to the groove 1, and high-speed air flows into the groove 1 through the air guiding inclined plane 2.
The preferred embodiment is as follows:
based on the description, the micro-nano resistance reducing structure is suitable to be arranged on a nose cone, a wing, a front edge of a control surface, a fuselage and other flat areas of the aircraft, so that the influence of air resistance and aerodynamic heat on the aircraft can be reduced.
The working principle is as follows:
in the work, the staff receives the manufacturing technology through laser and receives a little and etches certain quantity's slot 1 at the suitable position of aircraft surface, the aircraft carries out high-speed flight in the high altitude, high-speed air current flows through the guide inclined plane earlier and flows through vertically slot 1 with it again, more according to the not unidimensional slot 1 cross section base length and the height that different flow rates set up, aircraft surface laminar flow's separation position has been postponed, and the velocity of flow and the pressure pulsation of the gas of slot 1 of flowing through all can reduce, thereby the viscidity resistance near the aircraft wall boundary layer has been reduced, thereby help reducing the air friction resistance and the pneumatic heat's that the aircraft received influence.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (3)
1. The micro-nano resistance-reducing structure for the high-altitude high-speed environment is characterized by comprising a groove (1) formed in the outer surface of an aircraft, wherein the groove (1) is in a long strip shape, the cross section of the groove (1) is in an isosceles triangle shape, the vertex angles of the cross section of the groove (1) are located at the bottom of the groove (1), the length of the bottom side of the cross section of the groove (1) is 150-200 nm, the groove (1) and high-speed airflow form a certain angle, the groove (1) is formed in the outer surface of the aircraft in a manner of being equally spaced in the direction perpendicular to the length of the groove (1), a partition strip (3) is formed between any two adjacent grooves (1), the length direction of each partition strip (3) is parallel to the length direction of the groove (1), the cross section of each partition strip (3) is in an isosceles triangle shape, and the vertex angles of the cross section of each partition strip (3) are located at the top end of each partition strip (3);
the ratio of the bottom edge to the height of the cross section of the groove (1) ranges from 0.5 to 1;
the angle range of the top angle of the cross section of the groove (1) is 50-70 degrees;
the air guide structure is characterized by further comprising an air guide inclined plane (2) arranged on the outer surface of the aircraft, wherein the air guide inclined plane (2) is located on the air inlet side of the groove (1), and the air guide inclined plane (2) is obliquely and upwards arranged from one side, far away from the groove (1), of the air guide inclined plane to one side, close to the groove (1), of the air guide inclined plane;
the flying height of the aircraft is higher than 50 kilometers, and the flying speed of the aircraft is higher than Mach 3.
2. The micro-nano drag reduction structure for the high-altitude high-speed environment according to claim 1, wherein the length direction of the groove (1) is perpendicular to the flow direction of the high-speed airflow.
3. The micro-nano drag reduction structure for the high-altitude high-speed environment according to claim 1, wherein the groove (1) is formed by etching on the outer surface of an aircraft by a laser micro-nano manufacturing technology.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011505408.6A CN112550679B (en) | 2020-12-18 | 2020-12-18 | Micro-nano resistance reduction structure for high-altitude high-speed environment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011505408.6A CN112550679B (en) | 2020-12-18 | 2020-12-18 | Micro-nano resistance reduction structure for high-altitude high-speed environment |
Publications (2)
| Publication Number | Publication Date |
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| CN112550679A CN112550679A (en) | 2021-03-26 |
| CN112550679B true CN112550679B (en) | 2023-04-07 |
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| CN202011505408.6A Active CN112550679B (en) | 2020-12-18 | 2020-12-18 | Micro-nano resistance reduction structure for high-altitude high-speed environment |
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Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6345791B1 (en) * | 2000-04-13 | 2002-02-12 | Lockheed Martin Corporation | Streamwise variable height riblets for reducing skin friction drag of surfaces |
| US20160243586A1 (en) * | 2014-08-01 | 2016-08-25 | The Boeing Company | Drag reduction riblets integrated in a paint layer |
| CN108357665B (en) * | 2017-12-29 | 2021-03-23 | 西北工业大学 | Sand ridge simulating pneumatic resistance reducing fractal micro-nano structure |
| CN209814265U (en) * | 2019-01-24 | 2019-12-20 | 深圳大学 | Unmanned aerial vehicle rotor with micro-structure drag reduction film |
| CN111611661B (en) * | 2020-05-26 | 2023-04-25 | 北京航空航天大学 | Transverse V-groove structure based on stable vortex string drag reduction and application thereof |
| CN112027051A (en) * | 2020-09-15 | 2020-12-04 | 中国商用飞机有限责任公司 | Film drag reduction mechanism suitable for aircraft fuselage |
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