CN109625316B - Method for measuring inner side hinge moment of control surface of wing with super-large aspect ratio - Google Patents
Method for measuring inner side hinge moment of control surface of wing with super-large aspect ratio Download PDFInfo
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- CN109625316B CN109625316B CN201811355604.2A CN201811355604A CN109625316B CN 109625316 B CN109625316 B CN 109625316B CN 201811355604 A CN201811355604 A CN 201811355604A CN 109625316 B CN109625316 B CN 109625316B
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- 238000000034 method Methods 0.000 title claims abstract description 19
- 238000012360 testing method Methods 0.000 claims abstract description 8
- 230000003068 static effect Effects 0.000 claims description 6
- 238000004364 calculation method Methods 0.000 description 3
- 238000005259 measurement Methods 0.000 description 2
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- 238000005452 bending Methods 0.000 description 1
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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
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- B64F5/60—Testing or inspecting aircraft components or systems
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Abstract
The application provides a method for measuring the inboard hinge moment of a wing control surface with an ultra-large aspect ratio, which comprises the following steps: acquiring first pressure coefficient distribution along the course direction of the outermost side of the control surface on the inner side of the untruncated wing; acquiring a second pressure coefficient distribution along the course direction at the outermost side of the control surface at the inner side of the wing with a cut-off preset length; determining the length of the wing according to the first pressure coefficient distribution and the second pressure coefficient distribution; and carrying out wind tunnel test on the wing with the determined length, and measuring the hinge moment of the inner side of the control surface of the wing.
Description
Technical Field
The application relates to the field of aerodynamic layout, and particularly provides a method for measuring the inner side hinge moment of a control surface of a wing with an ultra-large aspect ratio.
Background
With the increasing demand of individuals, society and the like on the flight of the aircraft during the flight, in order to achieve higher aerodynamic efficiency, the aspect ratio of the aircraft is increased, so that the aircraft with the ultra-large aspect ratio is one of the important directions of the current development. At present, the hinge moment is obtained in two ways, one is a special wind tunnel test, and the other is CFD simulation calculation. However, the wing with the extra large aspect ratio can cause larger bending moment than that of a common airplane with a medium and small aspect ratio due to overlong spanwise length in a high-speed wind tunnel test, so that larger elastic deformation is caused, and the excessive deformation of the wing can generate larger influence on the measurement accuracy of the current hinge moment measurement balance, even influence the normal use of the balance, so that accurate test data can not be obtained easily, and even normal test cannot be performed. In the CFD calculation, because the control surface is usually positioned at the trailing edge, the flow near the control surface is very complex, particularly, the control surface is easy to generate detached vortex after deflection, and meanwhile, serious airflow separation exists, so that the CFD calculation is difficult to accurately simulate so as to obtain an accurate hinge moment value.
Disclosure of Invention
In order to solve at least one of the above technical problems, the present application provides a method for measuring an inboard hinge moment of a control surface of an airfoil with an ultra-large aspect ratio, including: acquiring first pressure coefficient distribution along the course direction of the outermost side of the control surface on the inner side of the untruncated wing; acquiring a second pressure coefficient distribution along the course direction at the outermost side of the control surface at the inner side of the wing with a cut-off preset length; determining the length of the wing according to the first pressure coefficient distribution and the second pressure coefficient distribution; and performing wind tunnel test on the wing with the determined length, and measuring the inner side hinge moment of the wing control surface.
According to at least one embodiment of the application, acquiring a first pressure coefficient distribution of the outermost forward direction of the inner control surface of the untruncated wing comprises: and acquiring the pressure distribution of the outermost side of the control surface at the inner side of the untruncated wing along the heading direction, and carrying out non-dimensionalization on the pressure distribution to obtain a first pressure coefficient distribution.
According to at least one embodiment of the application, acquiring a second pressure coefficient distribution of the outermost forward course direction of the wing inner side control surface with a preset length cut off comprises the following steps: and acquiring the pressure distribution of the outermost side of the control surface at the inner side of the wing with the cut-off preset length along the heading direction, and carrying out non-dimensionalization on the pressure distribution to obtain a second pressure coefficient distribution.
According to at least one embodiment of the application, the pressure profile is:
wherein, CpFor pressure distribution, P is the local static pressure, P0The far-front incoming static pressure is ρ, the far-front incoming density is ρ, and the far-front incoming velocity is V.
According to at least one embodiment of the present application, determining a length of the airfoil from the first pressure coefficient profile and the second pressure coefficient profile comprises: acquiring the absolute value of the difference value of the pressure coefficients at the same position on the outermost side of the wing inner control surface which is not cut off and the outermost side of the wing inner control surface which is cut off by a preset length; and if the absolute value is equal to a preset threshold value, determining the length of the wing with the cut-off preset length as the length of the wing.
The method for measuring the hinge moment on the inner side of the control surface of the wing with the ultra-large aspect ratio can accurately obtain the numerical value of the hinge moment.
Drawings
FIG. 1 is a schematic flow chart of a method for measuring the inner side hinge moment of the control surface of the wing with the ultra-large aspect ratio according to the embodiment of the application;
FIG. 2 is a pressure coefficient distribution diagram of the outermost forward direction of the inner control surface of the untruncated wing according to the embodiment of the present application.
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.
Fig. 1 shows a flow chart of a method for measuring an inboard hinge moment of a control surface of an ultra-large aspect ratio wing provided by an embodiment of the application.
As shown in fig. 1, the method for measuring the inboard hinge moment of the control surface of the wing with the ultra-large aspect ratio comprises the following steps:
step 101, taking a first pressure coefficient distribution along the direction of the outermost side of the control surface on the inner side of the untruncated wing.
The first pressure coefficient distribution is obtained by obtaining the pressure distribution along the outermost side of the inner control surface of the untruncated wing along the heading direction and carrying out non-dimensionalization on the pressure distribution, so that the first pressure coefficient distribution is obtained.
Alternatively, the non-truncated pressure distribution along the outermost lateral direction of the inner control surface of the wing may be non-dimensionalized according to a general non-dimensionalization formula, so as to obtain the first pressure coefficient distribution.
As an alternative embodiment, the pressure profile is:
wherein, CpFor pressure distribution, P is the local static pressure, P0The far-front incoming static pressure is ρ, the far-front incoming density is ρ, and the far-front incoming velocity is V.
In one example, referring to FIG. 2, FIG. 2 shows an untruncated airfoil inboard rudder surface outermost forward pressure coefficient profile.
And 102, acquiring a second pressure coefficient distribution of the outermost side of the control surface at the inner side of the wing with a cut-off preset length along the heading direction.
The method for obtaining the second pressure coefficient distribution is the same as the method for obtaining the first pressure coefficient, and is not described herein again.
And 103, determining the length of the wing according to the first pressure coefficient distribution and the second pressure coefficient distribution.
Specifically, the absolute value of the difference value of the pressure coefficients at the same position on the outermost side of the wing inner control surface which is not cut off and the outermost side of the wing inner control surface which is cut off by a preset length is obtained; and if the absolute value is equal to the preset threshold value, determining the length of the wing with the cut-off preset length as the length of the wing.
In an example, if the required precision is high, the value of the preset threshold may be set to be small, for example, 0.003.
In another example, if the required precision is low, the value of the preset threshold may be set to be large, for example, 0.01.
It should be noted that when the length of the intercepted wing is shorter, the airflow flow difference is smaller, and therefore, the difference of the pressure coefficients calculated twice is not large; when the length of the intercepted wing is longer, the airflow flow difference is larger, so that the difference of the calculated pressure coefficients at the two sides is larger;
at this time, the absolute values of the differences of the pressure coefficients of the corresponding positions calculated twice may be averaged.
And 104, performing a wind tunnel test on the wing with the determined length, and measuring the hinge moment of the inner side of the control surface of the wing.
By the method for measuring the hinge moment on the inner side of the control surface of the wing with the ultra-large aspect ratio, the numerical value of the hinge moment can be accurately obtained.
As described above, only the specific embodiments of the present application are provided, and it can be clearly understood by those skilled in the art that, for convenience and brevity of description, the specific working processes of the system, the module and the unit described above may refer to the corresponding processes in the foregoing method embodiments, and are not described herein again. It should be understood that the scope of the present application is not limited thereto, and any person skilled in the art can easily conceive various equivalent modifications or substitutions within the technical scope of the present application, and these modifications or substitutions should be covered within the scope of the present application.
Claims (4)
1. A method for measuring the inboard hinge moment of an ultra-large aspect ratio wing control surface is characterized by comprising the following steps:
acquiring first pressure coefficient distribution along the course direction of the outermost side of the control surface on the inner side of the untruncated wing;
acquiring a second pressure coefficient distribution along the course direction at the outermost side of the control surface at the inner side of the wing with a cut-off preset length;
determining the length of the wing according to the first pressure coefficient distribution and the second pressure coefficient distribution;
determining a length of the airfoil from the first pressure coefficient profile and the second pressure coefficient profile, comprising:
acquiring the absolute value of the difference value of the pressure coefficients at the same position on the outermost side of the wing inner control surface which is not cut off and the outermost side of the wing inner control surface which is cut off by a preset length;
if the absolute value is equal to a preset threshold value, determining the length of the wing with the cut-off preset length as the length of the wing;
and carrying out wind tunnel test on the wing with the determined length, and measuring the hinge moment of the inner side of the control surface of the wing.
2. The method for measuring the inboard hinge moment of the control surface of the wing with the extra-high aspect ratio as claimed in claim 1, wherein the step of obtaining the first pressure coefficient distribution of the outermost forward direction of the inboard control surface of the wing without the interruption comprises the following steps:
and acquiring the pressure distribution of the outermost side of the control surface at the inner side of the untruncated wing along the heading direction, and carrying out non-dimensionalization on the pressure distribution to obtain a first pressure coefficient distribution.
3. The method for measuring the inboard hinged moment of the control surface of the wing with the extra-large aspect ratio as claimed in claim 2, wherein the step of obtaining the second pressure coefficient distribution of the outermost side of the inboard control surface of the wing with the preset length cut off along the course direction comprises the following steps:
and acquiring the pressure distribution of the outermost side of the control surface at the inner side of the wing with the cut-off preset length along the heading direction, and carrying out non-dimensionalization on the pressure distribution to obtain a second pressure coefficient distribution.
4. The method for measuring the inboard hinge moment of the control surface of the wing with the ultra-high aspect ratio as claimed in claim 2 or 3, wherein the pressure coefficient is as follows:
wherein,
in order to be the pressure coefficient,
in order to be the local static pressure,
in order to achieve the static pressure of the incoming flow far ahead,
the density of the incoming flow far from the front,
is the far-ahead incoming flow velocity.
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| CN110909416B (en) * | 2019-09-17 | 2021-09-07 | 成都飞机工业（集团）有限责任公司 | Symmetric maneuvering load reduction method for composite control surface unmanned aerial vehicle |
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| CN104554705A (en) * | 2014-11-19 | 2015-04-29 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for reducing steering surface hinge moment of general-purpose airplane |
| CN106840593A (en) * | 2017-03-02 | 2017-06-13 | 中国航天空气动力技术研究院 | A kind of measurement apparatus and method for measuring blended configuration's vehicle rudder hinge moment |
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| CN101508338A (en) * | 2009-03-31 | 2009-08-19 | 北京航空航天大学 | Plasma gurney flap |
| US9297719B2 (en) * | 2013-04-26 | 2016-03-29 | Honda Patents & Technologies North America, Llc | Flight control system loading test apparatus and method |
| CN106586020B (en) * | 2016-11-24 | 2019-04-23 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of wing rudder face method for arranging |
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| CN104554705A (en) * | 2014-11-19 | 2015-04-29 | 中国航空工业集团公司沈阳飞机设计研究所 | Method for reducing steering surface hinge moment of general-purpose airplane |
| CN106840593A (en) * | 2017-03-02 | 2017-06-13 | 中国航天空气动力技术研究院 | A kind of measurement apparatus and method for measuring blended configuration's vehicle rudder hinge moment |
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