CN220263058U - Embedded secondary flow system built-in aircraft wing surface - Google Patents
Embedded secondary flow system built-in aircraft wing surface Download PDFInfo
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- CN220263058U CN220263058U CN202320421523.8U CN202320421523U CN220263058U CN 220263058 U CN220263058 U CN 220263058U CN 202320421523 U CN202320421523 U CN 202320421523U CN 220263058 U CN220263058 U CN 220263058U
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- 238000005516 engineering process Methods 0.000 description 5
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- 238000004364 calculation method Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000004927 fusion Effects 0.000 description 2
- 230000017525 heat dissipation Effects 0.000 description 2
- 238000012360 testing method Methods 0.000 description 2
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Abstract
The utility model discloses a buried secondary flow system built in an airplane airfoil surface, and relates to the field of airplane components. The system consists of an airfoil body and a secondary pipeline, wherein the airfoil body is an airfoil and a part of a fuselage body which are selected and optimized according to actual flight tasks; the secondary pipeline consists of an inlet pipeline, an equal-straight measuring section and an outlet pipeline, a platy structure extending from the front side of the inlet pipeline and the rear side of the outlet pipeline is fused with the airfoil, and the curved surface of the structure is consistent with the shape of the airfoil. In addition, the main pipeline of the inlet pipeline adopts an s-bend design method, and the structural parameters of the main pipeline can be locally adjusted according to task requirements. The low-flow air on the surface of the airfoil flows out after flowing through the inlet pipeline, the equal straight section and the outlet pipeline and interacts with the air flow outside the trailing edge of the airfoil, thereby improving the local flow characteristic of the airfoil. The utility model has the advantages of low cost, good stealth property, local flow control and the like, and can be applied to unmanned planes, fighters and other airplanes to further improve the fighter/operation efficiency of the airplane.
Description
Technical Field
The utility model relates to the field of aircraft parts, in particular to a buried secondary flow system built in an aircraft airfoil.
Background
The secondary flow system refers to a small flow circulation system applied to the interior of an aircraft, and can be arranged at the positions of an air inlet system, an air exhaust system, a local part of a fuselage, an airfoil surface and the like of the aircraft for flow control, cold and heat management and energy generation of the aircraft.
Through calculation simulation and experiments, the method has the advantages that a small-flow circulation system is constructed through effective small-flow, the flow field structure and flow field parameters of the airfoil are adjusted, the aerodynamic performance, propulsion efficiency, working envelope, heat-proof capacity and the like of the aircraft are improved, and the method has a wide application prospect in the technical field of engineering.
The current minor flow system based on small flow is applied to turbines, she Shan and spray pipes in many cases, and a small flow circulation environment is built on the aircraft wing surface, and particularly, a buried minor flow system built in the aircraft wing surface is not searched in related publications.
Therefore, the embedded secondary flow system applied to the aeroplane surface has the advantages of low cost, good stealth property, obvious local flow control effect and the like, can be applied to unmanned planes, fighters and the like, and improves the fighter/operation efficiency of the aeroplane. The heat-dissipating device can be used for heat dissipation of engines and the like in the civil field; the military field can be used for unmanned aerial vehicle local flow control, engine heat dissipation and the like.
Disclosure of Invention
The utility model aims to overcome the defects in the prior art, so as to improve the aerodynamic characteristics of the part of the existing airfoil, and provides a hidden embedded secondary flow system which is built in the airfoil of an airplane by combining a CFD calculation technology, a wind tunnel test technology and a high-precision manufacturing process technology. Compared with the traditional airfoil surface without a secondary flow system, the system has the characteristics of good stealth performance, improved local flow control effect and the like, is suitable for aircrafts such as fighters, unmanned aerial vehicles and the like, and has wider application prospect.
In order to achieve the above purpose, the utility model adopts the following technical scheme:
the utility model provides a buried secondary flow system which is built in an airplane airfoil, comprising an airfoil main body and a secondary flow pipeline; the airfoil body comprises an airfoil outer cover vertically arranged on the upper side of the middle part of the plane of the part of the machine body, and the airfoil outer cover comprises two airfoil side plates which are vertically and symmetrically arranged; the secondary pipeline is positioned inside the airfoil body and comprises an inlet pipeline, an equal-straight measuring section and an outlet pipeline; one end of the inlet pipeline is communicated with an inlet formed in the front edge of one airfoil side plate, the other end of the inlet pipeline is communicated with one end of the outlet pipeline through the equal-straight measuring section, and the other end of the outlet pipeline is communicated with an outlet formed in the rear edge of the same airfoil side plate.
Preferably, the airfoil shroud is removably secured to a portion of the fuselage plane.
Further, the detachable fixing is screw mounting.
Preferably, one end of the inlet pipeline connected with the inlet is provided with a positioning curved surface component, and one end of the outlet pipeline connected with the outlet is provided with a positioning curved surface component; the positioning curved surface part is of a plate-shaped structure extending outwards along the section of the pipeline and is attached to the shape of the wing surface side plate at the position.
Preferably, the inlet pipeline adopts an s-bend design method, so that the distance along the incoming flow direction is x, the cross-sectional area of the pipeline is y, and the cross-sectional area y of the pipeline changes along with the distance along the x in an s-bend trend.
Preferably, the equal-straight measuring section is a circular tube, and the length of the equal-straight measuring section is 2.5 times of the diameter of the circular section.
Preferably, the front side of the outlet pipeline is connected with the equal-straight measuring section, and the length of the outlet pipeline is twice as long as that of the equal-straight measuring section.
Preferably, the inlet duct, the iso-measuring section and the outlet duct have the same cross-sectional dimensions.
Preferably, the length ratio of the inlet pipe, the equal direct measurement section and the outlet pipe is 6:1:2.
Preferably, the airfoil of the airfoil body is a sharp leading edge airfoil which is obtained by adopting a spline curve to optimally design the leading edge on the basis of an NACA0016 airfoil.
Compared with the prior art, the utility model has the following beneficial effects:
1) The embedded secondary flow system built in the aircraft wing surface provided by the utility model constructs a small flow circulation system through effective small flow, improves the local flow field structure and flow field parameters of the wing surface, further can improve the local aerodynamic performance, propulsion efficiency, working envelope, heat-proof capacity and the like of the aircraft, and has wide application prospects in the technical field of engineering.
2) The embedded secondary flow system built in the aircraft wing surface provided by the utility model adopts an embedded design, effectively reduces the radar cross section of the wing surface, has the advantages of low cost, good stealth characteristic and the like, and further improves the fight/operation efficiency of the aircraft.
Drawings
FIG. 1 is an airfoil body structure of a buried secondary flow system;
FIG. 2 is a secondary flow conduit of the embedded secondary flow system;
FIG. 3 is an inlet pipe of a secondary pipe of a buried secondary flow system;
FIG. 4 is an isometric measurement section structure of a secondary pipeline of a buried secondary flow system;
FIG. 5 is an outlet pipe of a secondary pipe of a buried secondary flow system;
the reference numerals in the drawings are: an airfoil shroud 1, a portion of the fuselage plane 2, an inlet duct 3, an iso-measuring section 4, and an outlet duct 5.
Detailed Description
The utility model is further illustrated and described below with reference to the drawings and detailed description. The technical features of the embodiments of the utility model can be combined correspondingly on the premise of no mutual conflict.
According to the utility model, a secondary flow system applied to an aircraft is designed in a small flow circulation mode, on the premise of considering stealth characteristics, the design parameters of a secondary flow pipeline are optimized by combining a CFD computing technology, an optimal secondary flow system is determined, and the designed embedded secondary flow system is researched and verified by combining a wind tunnel test technology, so that the final embedded secondary flow system applied to the aircraft wing surface is obtained. It should be noted that the airfoil may be a wing or a tail wing, that is, the embedded secondary flow system provided by the utility model may be applied to the wing or the tail wing.
The utility model provides a buried secondary flow system built in an aircraft airfoil, which is shown in a specific figure 1 and comprises an airfoil main body and a secondary flow pipeline. The structure and connection of the components will be described in detail.
The airfoil body is an airfoil and part of a body selected and optimized according to actual flight tasks, and comprises an airfoil outer cover 1 and a part of a body plane 2, wherein the airfoil outer cover 1 is vertically arranged on the upper side of the middle part of the body plane 2. In this embodiment, the airfoil shroud 1 is removably secured to a portion of the fuselage planar surface 2, for example, by screw mounting. The airfoil cover 1 comprises two airfoil side plates which are vertically and symmetrically distributed, and the two airfoil side plates and a part of the plane 2 of the machine body jointly enclose a relatively closed space structure. According to the utility model, the secondary pipeline is arranged in the airfoil body, so that the radar cross section of the airfoil can be reduced, and the stealth characteristic is improved. In this embodiment, the airfoil of the airfoil body is a tip leading edge airfoil obtained by optimally designing the leading edge with spline curves on the basis of the NACA0016 airfoil.
As shown in FIG. 2, the secondary flow duct is located inside the airfoil body and mainly comprises an inlet duct 3, an equal direct measurement section 4 and an outlet duct 5. One end of the inlet duct 3 communicates with the inlet, which is provided in the leading edge of one airfoil side plate, and the inlet duct 3 communicates with the outside through the inlet. The other end of the inlet pipeline 3 is communicated with one end of the equal-straight measuring section 4, the other end of the equal-straight measuring section 4 is communicated with one end of the outlet pipeline 5, the other end of the outlet pipeline 5 is communicated with an outlet, the outlet is arranged at the rear edge of the airfoil side plate which is the same as the inlet, and the outlet pipeline 5 is communicated with the outside through the outlet. That is, the inlet duct 3 is located near the front edge of the airfoil shroud 1, the outlet duct 5 is located near the rear edge of the airfoil shroud 1, and the constant velocity measurement section 4 is a member connecting the inlet duct 3 and the outlet duct 5, and the constant velocity measurement section 4 is disposed entirely inside the airfoil body. In this embodiment, the inlet pipe 3, the equal-straight measuring section 4 and the outlet pipe 5 may be all configured as circular pipes with the same cross-sectional dimensions, and the length ratio of the inlet pipe 3, the equal-straight measuring section 4 and the outlet pipe 5 is preferably 6:1:2..
As shown in fig. 3 and 5, the end of the inlet pipe 3 connected to the inlet is provided with a positioning curved surface member, and the end of the outlet pipe 5 connected to the outlet is also provided with a positioning curved surface member. The positioning curved surface part is of a plate-shaped structure extending outwards along the section of the pipeline and is attached to the shape of the wing surface side plate at the position.
In this embodiment, as shown in fig. 3, the inlet pipe 3 of the secondary pipe is shown, and the front curved surface is a positioning curved surface, and the curved surface is in fusion design with the airfoil surface and is consistent with the airfoil surface. In installation, the inlet duct 3 is placed into the airfoil interior from below the airfoil, corresponding to the recess near the airfoil leading edge; the inlet pipeline 3 is designed according to s-bend, namely the cross-section area of the inlet pipeline changes along with the distance of the incoming flow direction of the inlet pipeline in an s-bend trend, and the structural parameters of the inlet pipeline can be locally adjusted according to task requirements.
In this embodiment, as shown in fig. 4, an equal-straight measuring section 4 structure of the secondary flow pipeline is shown, the measuring section is connected with the inlet pipeline 3 and the outlet pipeline 5, and the length of the measuring section is 2.5 times of the diameter of the circular section, so as to measure parameters such as the total pressure recovery coefficient, the total pressure distortion, the temperature and the like of the secondary flow pipeline.
In this embodiment, as shown in fig. 5, the structure of the equal outlet pipeline 5 of the secondary pipeline is shown, and the front side plate sheet structure is a positioning curved surface part, and the curved surface part is in fusion design with the airfoil surface and is consistent with the shape of the side plate of the airfoil surface and the shape of the groove. In actual installation, the outlet pipe 5 is placed into the airfoil from below the airfoil, the front side is in installation connection with the iso-measuring section 4, and the locating curved surface of the rear side is installed corresponding to the groove near the trailing edge of the airfoil. The front side of the outlet pipe 5 is connected with the equal-straight measuring section 4, and the length of the outlet pipe is twice the length of the equal-straight measuring section.
In practical application, the low-flow air on the surface of the airfoil of the system flows out after flowing through the inlet pipeline, the equal-direct measuring section and the outlet pipeline and interacts with the air flow outside the trailing edge of the airfoil, so that the local flow characteristic of the airfoil is improved. The utility model has the advantages of low cost, good stealth property, local flow control and the like, and can be applied to unmanned planes, fighters and other airplanes to further improve the fighter/operation efficiency of the airplane.
The above embodiment is only a preferred embodiment of the present utility model, but it is not intended to limit the present utility model. Various changes and modifications may be made by one of ordinary skill in the pertinent art without departing from the spirit and scope of the present utility model. Therefore, all the technical schemes obtained by adopting the equivalent substitution or equivalent transformation are within the protection scope of the utility model.
Claims (8)
1. A buried secondary flow system built into an aircraft airfoil, comprising an airfoil body and a secondary flow duct; the airfoil body comprises an airfoil outer cover (1) vertically arranged on the upper side of the middle part of a part of the plane (2) of the machine body, and the airfoil outer cover (1) comprises two airfoil side plates which are vertically and symmetrically arranged; the secondary pipeline is positioned inside the airfoil body and comprises an inlet pipeline (3), an equal-straight measuring section (4) and an outlet pipeline (5); one end of the inlet pipeline (3) is communicated with an inlet formed in the front edge of one airfoil side plate, the other end of the inlet pipeline is communicated with one end of the outlet pipeline (5) through the equal-straight measuring section (4), and the other end of the outlet pipeline (5) is communicated with an outlet formed in the rear edge of the same airfoil side plate.
2. A buried secondary flow system built-in to an aircraft airfoil according to claim 1, characterised in that the airfoil shroud (1) is detachably fastened to a part of the fuselage plane (2).
3. The embedded secondary flow system of claim 2, wherein the removable fixture is a screw mount.
4. A buried secondary flow system built-in to an aircraft airfoil according to claim 1, wherein the inlet duct (3) is provided with a locating curved surface member at one end connected to the inlet and at one end connected to the outlet duct (5); the positioning curved surface part is of a plate-shaped structure extending outwards along the section of the pipeline and is attached to the shape of the wing surface side plate at the position.
5. A buried secondary flow system built-in to an aircraft airfoil according to claim 1, characterized in that said iso-measuring section (4) is a circular tube with a circular cross-sectional diameter of 2.5 times its length.
6. A buried secondary flow system built-in to an aircraft airfoil according to claim 1, characterised in that the front side of the outlet duct (5) is connected to an equal direct measurement section (4) of a length twice the length of the equal direct measurement section (4).
7. A buried secondary flow system built-in to an aircraft airfoil according to claim 1, characterized in that the inlet duct (3), the iso-measuring section (4) and the outlet duct (5) have the same cross-sectional dimensions.
8. A buried secondary flow system built-in to an aircraft airfoil according to claim 1, characterized in that the length ratio of the inlet duct (3), the iso-measuring section (4) and the outlet duct (5) is 6:1:2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320421523.8U CN220263058U (en) | 2023-03-08 | 2023-03-08 | Embedded secondary flow system built-in aircraft wing surface |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320421523.8U CN220263058U (en) | 2023-03-08 | 2023-03-08 | Embedded secondary flow system built-in aircraft wing surface |
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| Publication Number | Publication Date |
|---|---|
| CN220263058U true CN220263058U (en) | 2023-12-29 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202320421523.8U Active CN220263058U (en) | 2023-03-08 | 2023-03-08 | Embedded secondary flow system built-in aircraft wing surface |
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| CN (1) | CN220263058U (en) |
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- 2023-03-08 CN CN202320421523.8U patent/CN220263058U/en active Active
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