CN110589020A - Structure and method for determining influence of surface quality defects of airplane - Google Patents
Structure and method for determining influence of surface quality defects of airplane Download PDFInfo
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- CN110589020A CN110589020A CN201910906927.4A CN201910906927A CN110589020A CN 110589020 A CN110589020 A CN 110589020A CN 201910906927 A CN201910906927 A CN 201910906927A CN 110589020 A CN110589020 A CN 110589020A
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- 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
- B64F5/60—Testing or inspecting aircraft components or systems
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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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
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- General Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The application belongs to the technical field of influence determination of surface quality defects of airplanes, and particularly relates to a structure for determining influence of surface quality defects of airplanes, which comprises the following steps: a force measurement body section, manufactured on the basis of a typical profile of an aircraft surface sensitive to mass defects; and the surface quality defect simulation assembly is arranged on the force measurement main body section to simulate the quality defect of the surface of the airplane. Furthermore, a knot method for determining the effect of surface quality defects of an aircraft is proposed, comprising: placing the structure for determining the influence of the surface quality defect of the airplane in a wind tunnel to perform a wind tunnel test to obtain a first wind tunnel test result; placing the force measurement main body section of the structure for determining the influence of the surface quality defects of the airplane in a wind tunnel for wind tunnel test to obtain a second wind tunnel test result; and comparing the first wind tunnel test result with the second wind tunnel test result to correspondingly obtain the aerodynamic influence of the surface quality defect of the airplane.
Description
Technical Field
The application belongs to the technical field of determining the influence of surface quality defects of airplanes, and particularly relates to a structure and a method for determining the influence of the surface quality defects of airplanes.
Background
The surface of the aircraft may have certain quality defects due to design and manufacture, such as steps and gaps generated on the surface, and bulges, depressions, roughness and the like generated by installing fasteners.
The method has the advantages that additional resistance can be brought by the surface quality defects of the airplane, even advance transition is caused, the influence of the surface quality defects of the airplane can be accurately determined, reference can be provided for design and improvement of the airplane, the method is mainly determined through a full-airplane or half-mold wind tunnel test at present, accurate simulation on the appearance of the aerodynamic defects of the surface quality of the airplane is difficult to achieve due to the fact that the size of the aerodynamic defects of the surface quality of the airplane is small, the influence quantity of the surface quality defects of the airplane is too small relative to the full-airplane characteristic quantity, and the influence quantity is limited by the precision of a measuring balance.
The present application is made in view of the above-mentioned drawbacks of the prior art.
Disclosure of Invention
It is an object of the present application to provide a structure and method for determining the effect of a surface quality defect in an aircraft that overcomes or mitigates at least one aspect of the disadvantages of the prior art.
The technical scheme of the application is as follows:
one aspect provides a structure for determining the effect of surface quality defects of an aircraft, comprising:
a force measurement body section, manufactured on the basis of a typical profile of an aircraft surface sensitive to mass defects;
and the surface quality defect simulation assembly is arranged on the force measurement main body section to simulate the quality defect of the surface of the airplane.
According to at least one embodiment of the present application, an aircraft surface susceptible to quality defects comprises:
the typical section of the surface of the airplane wing is the section at the average aerodynamic chord length of the airplane wing, and the section is subjected to chord-wise scaling and spanwise stretching to form an equal straight wing section which is a force measurement main body section.
According to at least one embodiment of the present application, further comprising:
one of the shape following sections is arranged on one side of the force measurement main body section in the spanwise direction and has a first distance with the force measurement main body section; the other elliptical section is arranged on the other side of the force measurement main body section, and a second distance is formed between the other elliptical section and the force measurement main body section.
According to at least one embodiment of the present application, the first pitch and the second pitch are 1 mm.
According to at least one embodiment of the present application, further comprising:
and the balance connecting joint is arranged on one side of the force measuring main body section and is used for being connected with the force measuring balance.
According to at least one embodiment of the present application, a surface quality defect simulation assembly includes:
the first front edge cover plate covers the front end of the force measuring body section, and the surface of the first front edge cover plate is provided with a plurality of recesses so as to simulate the recesses of fasteners.
According to at least one embodiment of the present application, a surface quality defect simulation assembly includes:
the second front edge cover plate covers the front end of the force measuring main body section;
and the strip-shaped cover plates are arranged on the surface of the second front edge cover plate along the chord direction so as to simulate steps.
In accordance with at least one embodiment of the present application, among the plurality of strip-shaped cover plates,
at least part of the strip-shaped cover plate is provided with a convex front edge and/or a concave rear edge so as to simulate a reverse airflow step;
at least part of the front edge of the strip-shaped cover plate is sunken and/or the rear edge of the strip-shaped cover plate is raised so as to simulate a downstream step;
at least part of the strip-shaped cover plate is provided with strip-shaped grooves along the airflow direction so as to simulate gaps.
According to at least one embodiment of the present application, a surface quality defect simulation assembly includes:
the third front edge cover plate covers the front end of the force measuring main body section;
and the columnar rough belt is attached to the surface of the third front edge cover plate so as to simulate the protrusion of the fastener.
Another aspect provides a method for determining the effect of surface quality defects of an aircraft, comprising the steps of:
placing any structure for determining the influence of the surface quality defect of the airplane into a wind tunnel to perform a wind tunnel test to obtain a first wind tunnel test result;
placing the force measurement main body section of any structure for determining the influence of the surface quality defects of the airplane in a wind tunnel for wind tunnel test to obtain a second wind tunnel test result;
and comparing the first wind tunnel test result with the second wind tunnel test result to correspondingly obtain the aerodynamic influence of the surface quality defect of the airplane.
Drawings
FIG. 1 is a schematic structural view of a first leading edge cover plate provided by an embodiment of the present application;
FIG. 2 is a schematic structural diagram of a first leading edge cover plate covering the front end of a measurement main body segment according to an embodiment of the present application;
FIG. 3 is a schematic structural view of a second leading edge panel provided in accordance with an embodiment of the present application;
FIG. 4 is a schematic structural diagram of a second leading edge cover plate covering the front end of a measurement main body segment according to an embodiment of the present application;
wherein:
1-measuring a main body segment; 2-a first leading edge cover plate; 3-a second leading edge cover plate; 4-strip cover plate.
Detailed Description
The present application will be described in further detail with reference to the following drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the relevant application and are not limiting of the application. It should be noted that, for convenience of description, only the portions related to the present application are shown in the drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
It should be noted that in the description of the present application, the terms of direction or positional relationship indicated by the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. are based on the directions or positional relationships shown in the drawings, which are merely for convenience of description, and do not indicate or imply that the device or element must have a specific orientation, be constructed and operated in a specific orientation, and thus, should not be construed as limiting the present application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
Furthermore, it should be noted that, in the description of the present application, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as being fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood by those skilled in the art as the case may be.
The present application is described in further detail below with reference to fig. 1 to 4.
One aspect provides a structure for determining the effect of surface quality defects of an aircraft, comprising:
a force measurement body section 1, manufactured on the basis of a typical profile of an aircraft surface sensitive to mass defects;
and the surface quality defect simulation assembly is arranged on the force measurement main body section 1 to simulate the quality defect of the surface of the airplane.
For the structure for determining the influence of the surface quality defect of the aircraft disclosed in the above embodiment, those skilled in the art can understand that the force measurement main body section 1 is manufactured based on a typical profile of an aircraft surface sensitive to the quality defect, the mass volume is relatively small, and a surface quality defect simulation assembly for simulating the quality defect of the aircraft surface is arranged on the force measurement main body section, so that a small-caliber wind tunnel can be selected for local test, the test cost is saved, and a large-scale simulation can be performed on various aircraft surface quality defects, so that a relatively accurate test result can be obtained.
In some alternative embodiments, the aircraft surface susceptible to quality defects comprises:
the typical section of the surface of the airplane wing is the section at the average aerodynamic chord length of the airplane wing, and the section is subjected to chord-wise scaling and spanwise stretching to form an equal straight wing section which is a force measuring main body section 1.
In some optional embodiments, further comprising:
one of the two shape following sections is arranged on one side of the force measurement main body section 1 in the spanwise direction and has a first distance with the force measurement main body section 1; the other elliptical section is arranged on the other side of the force measuring body section 1, and a second distance is formed between the other elliptical section and the force measuring body section 1 so as to reduce the interference of the end face of the force measuring body section 1.
In some alternative embodiments, the first and second spacings are 1 mm.
In some optional embodiments, further comprising:
and the balance connecting joint is arranged on one side of the force measuring body section 1 and is used for being connected with a force measuring balance, and the measuring range of the force measuring balance is matched with the influence quantity of each plane surface quality defect.
In some alternative embodiments, the surface quality defect simulation assembly comprises:
the first front edge cover plate 2 covers the front end of the force measuring body section, and the surface of the first front edge cover plate is provided with a plurality of recesses so as to simulate fastener recesses.
In some alternative embodiments, the surface quality defect simulation assembly comprises:
the second front edge cover plate 3 covers the front end of the force measuring main body section 1;
and a plurality of strip-shaped cover plates 4 are arranged on the surface of the second front edge cover plate 3 along the chord direction to simulate steps.
In some alternative embodiments, the number of strip-shaped cover plates 4,
the front edge of at least part of the strip-shaped cover plate 4 is convex and/or the rear edge of the cover plate is concave so as to simulate a reverse airflow step;
the front edge of at least part of the strip-shaped cover plate 4 is sunken and/or the rear edge is raised so as to simulate a downstream step;
at least part of the strip-shaped cover plate 4 is provided with strip-shaped grooves along the airflow direction so as to simulate gaps.
In some alternative embodiments, the surface quality defect simulation assembly comprises:
the third front edge cover plate covers the front end of the force measuring main body section 1;
and the columnar rough belt is attached to the surface of the third front edge cover plate so as to simulate the protrusion of the fastener.
As will be understood by the person skilled in the art with respect to the first 2, second 3 and third leading edge cover plates provided in the above embodiments, these three leading edge cover plates are not provided on the force-measuring body segment 1 at the same time, but are covered at a certain moment on the front end of the force-measuring body segment 1 for the corresponding measurement of a corresponding surface quality defect.
Another aspect provides a method for determining the effect of surface quality defects of an aircraft, comprising the steps of:
placing any structure for determining the influence of the surface quality defect of the airplane into a wind tunnel to perform a wind tunnel test to obtain a first wind tunnel test result;
placing the force measurement main body section 1 of any structure for determining the influence of the surface quality defects of the airplane in a wind tunnel for wind tunnel test to obtain a second wind tunnel test result;
and comparing the first wind tunnel test result and the second wind tunnel test result to correspondingly obtain the aerodynamic influence of the surface quality defects of the airplanes, namely comparing the wind tunnel test result with the quality defects on the surface of the airplane with the wind tunnel test result without the quality defects on the surface of the airplane, so that the influence quantity of the surface quality defects of each airplane can be determined.
So far, the technical solutions of the present application have been described in connection with the preferred embodiments shown in the drawings, but it is easily understood by those skilled in the art that the scope of the present application is obviously not limited to these specific embodiments. Equivalent changes or substitutions of related technical features can be made by those skilled in the art without departing from the principle of the present application, and the technical scheme after the changes or substitutions will fall into the protection scope of the present application.
Claims (10)
1. A structure for determining the effect of surface quality defects of an aircraft, comprising:
a force-measuring body section (1) which is produced on the basis of a typical profile of an aircraft surface sensitive to mass defects;
the surface quality defect simulation assembly is arranged on the force measurement main body section (1) to simulate the quality defect of the surface of the airplane.
2. The structure for determining aircraft surface quality defect effects of claim 1,
the aircraft surface sensitive to quality defects comprises:
the typical section of the surface of the airplane wing is the section at the average aerodynamic chord length of the airplane wing, and the section is subjected to chord-wise scaling and spanwise stretching to form an equal straight wing section which is the force measuring main body section (1).
3. The structure for determining the effect of surface quality defects of an aircraft according to claim 2,
further comprising:
one of the shape following sections is arranged on one side of the force measurement main body section (1) in the spanwise direction, and a first distance is reserved between the shape following section and the force measurement main body section (1); the other elliptical section is arranged on the other side of the force measuring body section (1) and has a second distance with the force measuring body section (1).
4. The structure for determining aircraft surface quality defect effects of claim 3,
the first distance and the second distance are 1 mm.
5. The structure for determining the effect of surface quality defects of an aircraft according to claim 2,
further comprising:
and the balance connecting joint is arranged on one side of the force measurement main body section (1) and is used for being connected with a force measurement balance.
6. The structure for determining the effect of surface quality defects of an aircraft according to claim 2,
the surface quality defect simulation assembly comprises:
a first leading edge cover plate (2) covering the front end of the dynamometric body segment, the surface of which has a plurality of recesses to simulate fastener recesses.
7. The structure for determining the effect of surface quality defects of an aircraft according to claim 2,
the surface quality defect simulation assembly comprises:
the second front edge cover plate (3) covers the front end of the force measuring main body section (1);
and the strip-shaped cover plates (4) are arranged on the surface of the second front edge cover plate (3) along the chord direction to simulate steps.
8. The structure for determining aircraft surface quality defect effects of claim 7,
among a plurality of said strip-shaped cover plates (4),
at least part of the front edge of the strip-shaped cover plate (4) is convex and/or the rear edge of the strip-shaped cover plate is concave so as to simulate a counter airflow step;
at least part of the front edge of the strip-shaped cover plate (4) is sunken and/or the rear edge of the strip-shaped cover plate is raised so as to simulate a downstream step;
at least part of the strip-shaped cover plate (4) is provided with a strip-shaped groove along the airflow direction so as to simulate a gap.
9. The structure for determining the effect of surface quality defects of an aircraft as recited in claim 2,
the surface quality defect simulation assembly comprises:
the third front edge cover plate is covered at the front end of the force measuring main body section (1);
and the columnar rough belt is attached to the surface of the third front edge cover plate so as to simulate the protrusion of a fastener.
10. A method for determining the effect of surface quality defects of an aircraft, comprising the steps of:
placing the structure for determining the influence of the surface quality defects of the aircraft according to any one of claims 1 to 9 in a wind tunnel for a wind tunnel test to obtain a first wind tunnel test result;
placing the force measuring body section (1) of the structure for determining the influence of the surface quality defects of the aircraft according to any one of claims 1 to 9 in a wind tunnel for a wind tunnel test to obtain a second wind tunnel test result;
and comparing the first wind tunnel test result with the second wind tunnel test result to correspondingly obtain the aerodynamic influence of the surface quality defect of the airplane.
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| CN201910906927.4A CN110589020B (en) | 2019-09-24 | 2019-09-24 | Structure and method for determining influence of surface quality defects of airplane |
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| CN201910906927.4A CN110589020B (en) | 2019-09-24 | 2019-09-24 | Structure and method for determining influence of surface quality defects of airplane |
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| CN110589020B CN110589020B (en) | 2023-03-14 |
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Cited By (1)
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| CN114537642A (en) * | 2022-03-11 | 2022-05-27 | 西北工业大学 | Continuous deformation mixed scaling airfoil structure for wind tunnel test |
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| CN110589020B (en) | 2023-03-14 |
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