CN106021779A - Method for calculating bending rigidity of main box section of high-aspect-ratio wing - Google Patents
Method for calculating bending rigidity of main box section of high-aspect-ratio wing Download PDFInfo
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- CN106021779A CN106021779A CN201610374301.XA CN201610374301A CN106021779A CN 106021779 A CN106021779 A CN 106021779A CN 201610374301 A CN201610374301 A CN 201610374301A CN 106021779 A CN106021779 A CN 106021779A
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- main box
- line segment
- box section
- outer ring
- inner ring
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- G—PHYSICS
- G06—COMPUTING; CALCULATING OR COUNTING
- G06F—ELECTRIC DIGITAL DATA PROCESSING
- G06F30/00—Computer-aided design [CAD]
- G06F30/10—Geometric CAD
- G06F30/15—Vehicle, aircraft or watercraft design
Abstract
The invention relates to a method for calculating the bending rigidity of a main box section of a high-aspect-ratio wing. The method comprises the particular steps that 1, a coordinate system is constructed; 2, coordinate positions of outer ring and inner ring feature points of the cross section of the main box section are obtained; 3, a material reduction coefficient corresponding to a line segment composed of every two adjacent outer ring and inner ring feature points of the cross section of the main box section is calculated; 4, feature point line segment rigidity characteristic calculation is conducted; 5, the bending rigidity of the main box section of the high-aspect-ratio wing is obtained by summing the feature point line segment rigidities. The invention provides the method for calculating the bending rigidity of the wing main box section by means of feature point coordinates and material information, an existing method for conducting summing by means of micro-element surface inertia moments, and the calculation accuracy and efficiency are improved.
Description
Technical field
The invention belongs to aircraft structural mechanics field, particularly relate to a kind of high aspect ratio wing main box section bending
Calculating method of stiffness.
Background technology
Wing Rigidity Calculation has very important status in airplane design, and it is that tremor, pneumostatic bullet are special
The element task of industry, Wings rigidity can provide important support for airplane design exactly.
The general method by the summation of Wings main box section cross section structure infinitesimal face the moment of inertia in engineering in the past
Try to achieve；This is a kind of approximation method, and result of calculation exists error, and is difficult to consider, and then can be to aircraft
FLUTTER CALCULATION, pneumostatic bullet calculate and bring potential error, and the most this method requires that input data include knot
Structure unit dimension, adds amount of calculation.
Summary of the invention
It is an object of the invention to provide a kind of high aspect ratio wing main box section bending stiffness computational methods, in order to
Solve the problems referred to above.
For reaching above-mentioned purpose, the technical solution used in the present invention is: a kind of high aspect ratio wing main box section
Bending stiffness computational methods, predict wing main box section cross-sectional shape, firm heart position, cross section principal axis of inertia side
In, profile, the characteristic point position on Internal and external cycle and structural material elastic modulus E, calculate main box section curved
Stiffness E0I, it specifically comprises the following steps that
1.1, coordinate system Oxy set up, make zero O be positioned at firm heart position, Ox axle along principal axis of inertia to
After, Oy axle be perpendicular to Ox axially on；
1.2, wing main box Duan Weidan closed chamber thin-wall construction, single closed chamber thin-walled is from being geometrically divided into outer ring and interior
Circle, outer ring is considered as with inner ring being made up of a series of line segments being connected the most respectively, and these line segments are by feature
Point is connected and forms；Counterclockwise, the characteristic point of outer ring is calculated as W1、W2、…、Wm, m point altogether,
Its coordinate is (xW1,yW1)、(xW2,yW2)、...、(xWm,yWm), outer ring line segment can be expressed as
Wherein i=1,2,3 ..., m, and as i=m, making m+1 is 1；Counterclockwise, inner ring
Characteristic point is calculated as N1、N2、…、Nn, n point altogether, its coordinate is (xN1,yN1)、(xN2,yN2)、...、
(xNn,yNn), inner ring line segment can be expressed asWherein j=1,2,3 ..., n, and as j=n,
Making n+1 is 1；
1.3, one reference material elastic modulus E of definition0；Just it is in a counterclockwise direction, outer ring line segment
The structural material elastic modelling quantity of positive direction is EWi, inner ring line segmentThe structural material springform of negative direction
Amount is ENj, calculating material reduction factor:
1.4, counterclockwise, outer ring line segmentCharacteristic of correspondence point line segment stiffness characteristics is
Inner ring line segmentCharacteristic of correspondence point line segment stiffness characteristics is
1.5, wing main box section bending stiffness is
It is desired value.
A kind of high aspect ratio wing main box section bending stiffness computational methods of the present invention improve the bending of main box section
Rigidity Calculation precision, decreases the requirement to input data, easily realizes with computer program, improve
Work efficiency.
Accompanying drawing explanation
Accompanying drawing herein is merged in description and constitutes the part of this specification, it is shown that meet this
Bright embodiment, and for explaining the principle of the present invention together with description.
Fig. 1 is the wing main box section schematic cross-section of one embodiment of the invention；
Fig. 2 is the preferable wing main box section schematic cross-section of one embodiment of the invention.
Detailed description of the invention
Clearer, below in conjunction with the present invention for the purpose making the present invention implement, technical scheme and advantage
Accompanying drawing in embodiment, is further described in more detail the technical scheme in the embodiment of the present invention.Attached
In figure, the most same or similar label represents same or similar element or has same or like
The element of function.Described embodiment is a part of embodiment of the present invention rather than whole embodiments.
The embodiment described below with reference to accompanying drawing is exemplary type, it is intended to be used for explaining the present invention, and can not
It is interpreted as limitation of the present invention.Based on the embodiment in the present invention, those of ordinary skill in the art are not having
Have and make the every other embodiment obtained under creation type work premise, broadly fall into the model of present invention protection
Enclose.Below in conjunction with the accompanying drawings embodiments of the invention are described in detail.
In describing the invention, it is to be understood that term " " center ", " longitudinally ", " laterally ",
"front", "rear", "left", "right", " vertically ", " level ", " top ", " end ",
The orientation of the instruction such as " interior ", " outward " or position relationship are to close based on orientation shown in the drawings or position
System, be for only for ease of describe the present invention and simplify describe rather than instruction or hint indication device or
Element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to this
The restriction of invention protection domain.
Being illustrated in figure 1 the wing main box section schematic cross-section of the present invention, in figure, zero O is positioned at just
Heart position, Ox axle along principal axis of inertia backward, Oy axle be perpendicular to Ox axially on；Thin-wall construction outer ring feature
Point is W1、W2、...、Wm, thin-wall construction inner ring characteristic point is N1、N2、...、Nn。
If Fig. 2 is preferable wing main box section schematic cross-section, Internal and external cycle all has 4 characteristic points, outer ring width
1000mm, high 400mm, walled thickness is 2mm.
In order to verify the high aspect ratio wing of the present invention main box section bending stiffness method, provide a kind of shape here
The desired section that shape rule is symmetrical, as in figure 2 it is shown, and structural material the most constant, its elastic modelling quantity
E=72000MPa, the bending stiffness of this structure can be calculated by analytic method, the most also be given
Traditional infinitesimal face the moment of inertia summation result of calculation is as a comparison, choosing unit dimension is 8mm4；Calculate
Result is as shown in table 1, from result it will be seen that the result of the inventive method is consistent with analytic method result,
Traditional infinitesimal face the moment of inertia summation then have certain error, and this error also can be along with cross section shape
Choosing of the change of shape, the change of material and unit dimension changes and changes.
Table 1 flexural rigidity of section EIxUnit: Nm2
A kind of high aspect ratio wing main box section bending stiffness computational methods of the present invention improve the bending of main box section
Rigidity Calculation precision, decreases the requirement to input data, easily realizes with computer program, improve
Work efficiency.
The above, the only optimum detailed description of the invention of the present invention, but protection scope of the present invention is not
Being confined to this, any those familiar with the art, can in the technical scope that the invention discloses
The change readily occurred in or replacement, all should contain within protection scope of the present invention.Therefore, the present invention
Protection domain should be as the criterion with described scope of the claims.
Claims (1)
1. high aspect ratio wing main box section bending stiffness computational methods, it is characterised in that precognition wing
Characteristic point on Internal and external cycle in main box section cross-sectional shape, firm heart position, principal axis of inertia direction, cross section, profile
Position and structural material elastic modulus E, calculate main box section bending stiffness E0I, it specifically comprises the following steps that
1.1, coordinate system Oxy set up, make zero O be positioned at firm heart position, Ox axle along principal axis of inertia to
After, Oy axle be perpendicular to Ox axially on；
1.2, wing main box Duan Weidan closed chamber thin-wall construction, single closed chamber thin-walled is from being geometrically divided into outer ring and interior
Circle, outer ring is considered as with inner ring being made up of a series of line segments being connected the most respectively, and these line segments are by feature
Point is connected and forms；Counterclockwise, the characteristic point of outer ring is calculated as W1、W2、…、Wm, m point altogether,
Its coordinate is (xW1,yW1)、(xW2,yW2)、...、(xWm,yWm), outer ring line segment can be expressed as
Wherein i=1,2,3 ..., m, and as i=m, making m+1 is 1；Counterclockwise, inner ring
Characteristic point is calculated as N1、N2、…、Nn, n point altogether, its coordinate is (xN1,yN1)、(xN2,yN2)、...、
(xNn,yNn), inner ring line segment can be expressed asWherein j=1,2,3 ..., n, and as j=n,
Making n+1 is 1；
1.3, one reference material elastic modulus E of definition0；Just it is in a counterclockwise direction, outer ring line segment
The structural material elastic modelling quantity of positive direction is EWi, inner ring line segmentThe structural material springform of negative direction
Amount is ENj, calculating material reduction factor:
1.4, counterclockwise, outer ring line segmentCharacteristic of correspondence point line segment stiffness characteristics is
Inner ring line segmentCharacteristic of correspondence point line segment stiffness characteristics is
1.5, wing main box section bending stiffness is
It is desired value.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201610374301.XA CN106021779B (en) | 2016-05-31 | 2016-05-31 | A kind of main box section bending stiffness calculation method of high aspect ratio wing |
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| CN201610374301.XA CN106021779B (en) | 2016-05-31 | 2016-05-31 | A kind of main box section bending stiffness calculation method of high aspect ratio wing |
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| CN106021779A true CN106021779A (en) | 2016-10-12 |
| CN106021779B CN106021779B (en) | 2019-04-23 |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107515088A (en) * | 2017-08-04 | 2017-12-26 | 中国航空工业集团公司西安飞机设计研究所 | A kind of model test part design method of the main box section bending stiffness test of metal wings |
| CN109710987A (en) * | 2018-12-04 | 2019-05-03 | 中国航空工业集团公司西安飞机设计研究所 | A kind of main box section Equivalent Beam shearing factor evaluation method of high aspect ratio wing list closed chamber |
| CN113051696A (en) * | 2019-12-26 | 2021-06-29 | 中国航空工业集团公司西安飞机设计研究所 | Method for calculating shear coefficient of box section of single closed chamber in aircraft structure |
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| US20140061385A1 (en) * | 2012-08-28 | 2014-03-06 | The Boeing Company | Bonded Composite Aircraft Wing |
| CN104978485A (en) * | 2015-06-23 | 2015-10-14 | 中国航空工业集团公司西安飞机设计研究所 | Method for calculating wing bending rigidity of high-aspect-ratio aircraft |
| CN105109705A (en) * | 2015-08-03 | 2015-12-02 | 江西洪都航空工业集团有限责任公司 | Method for calculating rigidity of aircraft airfoil surface structure |
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2016
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20140061385A1 (en) * | 2012-08-28 | 2014-03-06 | The Boeing Company | Bonded Composite Aircraft Wing |
| CN104978485A (en) * | 2015-06-23 | 2015-10-14 | 中国航空工业集团公司西安飞机设计研究所 | Method for calculating wing bending rigidity of high-aspect-ratio aircraft |
| CN105109705A (en) * | 2015-08-03 | 2015-12-02 | 江西洪都航空工业集团有限责任公司 | Method for calculating rigidity of aircraft airfoil surface structure |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107515088A (en) * | 2017-08-04 | 2017-12-26 | 中国航空工业集团公司西安飞机设计研究所 | A kind of model test part design method of the main box section bending stiffness test of metal wings |
| CN109710987A (en) * | 2018-12-04 | 2019-05-03 | 中国航空工业集团公司西安飞机设计研究所 | A kind of main box section Equivalent Beam shearing factor evaluation method of high aspect ratio wing list closed chamber |
| CN113051696A (en) * | 2019-12-26 | 2021-06-29 | 中国航空工业集团公司西安飞机设计研究所 | Method for calculating shear coefficient of box section of single closed chamber in aircraft structure |
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| CN106021779B (en) | 2019-04-23 |
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