CN109710987B - Estimation method for equivalent beam shear coefficient of single closed cell main box section of high-aspect-ratio wing - Google Patents
Estimation method for equivalent beam shear coefficient of single closed cell main box section of high-aspect-ratio wing Download PDFInfo
- Publication number
- CN109710987B CN109710987B CN201811476557.7A CN201811476557A CN109710987B CN 109710987 B CN109710987 B CN 109710987B CN 201811476557 A CN201811476557 A CN 201811476557A CN 109710987 B CN109710987 B CN 109710987B
- Authority
- CN
- China
- Prior art keywords
- calculating
- intermediate variable
- section
- main box
- box section
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- 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
Abstract
The invention belongs to the field of structural mechanics, and particularly relates to a method for estimating a shear coefficient of an equivalent beam of a single closed cell main box section of a high-aspect-ratio wing. The method for determining the shear coefficient of the equivalent beam of the main box section of the single closed cell of the high aspect ratio wing comprises the following steps: sorting the section size data; calculating the equivalent area of the main box section; calculating the size of the equivalent thin-wall rectangular hollow section of the main box section; and estimating the equivalent beam shear coefficient of the main box section of the single closed cell of the high aspect ratio wing. The invention provides a simple and efficient method for determining the shear coefficient of an equivalent beam of a main box section of a single closed cell of a high aspect ratio wing according to the size of the main box section. The method is easy to realize by a computer program, and improves the working efficiency in engineering application.
Description
Technical Field
The invention belongs to the field of structural mechanics, and particularly relates to a method for estimating a shear coefficient of an equivalent beam of a single closed cell main box section of a high-aspect-ratio wing.
Background
The wings of the modern large-scale transport plane mostly adopt high aspect ratio wings, and the main box section mostly adopts a hollow thin-wall single closed chamber form; when the flutter analysis of the wing is carried out, the flutter analysis is often simplified into a single-beam model, the influence of shearing is rarely considered in the process of simplifying the wing into the single-beam model, and larger errors are caused sometimes.
Disclosure of Invention
The purpose of the invention is: the method is suitable for engineering application and provides an estimation method for the equivalent beam shear coefficient of the main box section of the single closed cell of the high-aspect-ratio wing, so as to provide input reference for establishing a single-beam model of the high-aspect-ratio wing.
The technical solution of the invention is as follows: a method for estimating the shear coefficient of an equivalent beam of a main box section of a single closed cell of a high-aspect-ratio wing is characterized in that the shape of the section of the main box section of the wing, the position of a centroid, the direction of the main centroid of the section, the positions and the areas of a stringer and a flange strip, and the positions and the thicknesses of a skin and a web are predicted, and the shear coefficient k of the equivalent beam of the main box section is estimated x (ii) a Step of estimating main box section equivalent beam shear coefficientThe following were used:
1. establishing a coordinate system Oxy, enabling an origin of coordinates O to be located at a centroid position, enabling an Ox axis to go backwards along a main centroid axis, and enabling an Oy axis to be perpendicular to the Ox axis; the beam edge strips and the stringers are called rod elements, the rod elements are simplified into one point on the cross section, and the total number of the beam edge strips is 4; the upper long purlin is provided with N U The lower long girder is N D A total of M, and has the following relations
M＝N U +N D +4……………………………[1]The beam edge strips at the joints of the upper skins and the web plates of the back beams are arranged in the anticlockwise direction by taking the beam edge strips as the 1 st rod element, and the area of the ith rod element is S ri (i =1, \8230;, M); the skin and the beam web are called plate elements, the plate elements are simplified into a section of line on the cross section, and the skin and the beam web are divided into M sections by the plate elements; the upper skin of the section connected with the upper edge strip of the back beam is a 1 st plate element which is arranged in a counterclockwise direction, and the thickness of the j-th plate element is t pj The positions of two end points of the j-th section plate element are respectively (x) pj ,y pj ) And (x) pj+1 ,y pj+1 ) (j =1, \ 8230;, M-1), and when j = M, the positions of both end points of the M-th-stage plate member are (x) respectively pM ,y pM ) And (x) p1 ,y p1 ) Namely, the rear beam web plate is obtained;
2. the position of the middle point of the board element is calculated,
3. the cross-sectional length of the board member is calculated,
4. the area of the board element is calculated,
S pj ＝d pj t pj (j＝1,…,M)……………………………[6]
5. the total area of the board elements is calculated,
6. the intermediate variable is calculated and the intermediate variable,
7. the intermediate variable is calculated and the intermediate variable,
8. the intermediate variable is calculated and the intermediate variable,
9. calculating the total area of the rod element,
10. the total area of the cross-section is calculated,
S＝S r +S p ……………………………[13]
11. the intermediate variable is calculated and the intermediate variable,
12. calculating the size of the equivalent thin-wall rectangular hollow section,
13. the intermediate variable is calculated and the intermediate variable,
14. the intermediate variable is calculated and the intermediate variable,
Z＝12+72m+150m 2 +90m 3 +30m(1+m)n 2 ………………[17]
15. calculating the shear coefficient k of the main box section equivalent beam x ，
I.e. the final evaluated value.
The invention has the advantages that: the method for estimating the equivalent beam shear coefficient of the main box section of the single closed cell of the high-aspect-ratio wing is suitable for engineering application, is easy to realize by a computer program, and improves the working efficiency.
Drawings
FIG. 1 is a schematic cross-sectional view of a single closed cell main box section of a high aspect ratio wing;
fig. 2 is an equivalent thin-walled rectangular hollow section.
Detailed Description
The present invention is described in further detail below. Referring to fig. 1, fig. 1 is a schematic cross-sectional view of a single closed cell main box section of a high aspect ratio wing; in the figure, the origin of coordinates O is positioned at the centroid position, the axis of Ox is backward along the main inertia axis, and the axis of Oy is vertical to the axis of Ox; A. b is upper skin and lower skin, C and D are front beam web and back beam web, E is beam edge strip, F is stringer, stringer is connected under upper skin and lower skinOn the upper side, 5 stringers are respectively connected with the upper skin and the lower skin in the figure, and 2 stringers are schematically marked; the stringers and the edge strips are called rod elements, there being a total of M, each rod element having a cross-sectional area S ri (i =1, \8230;, M); the skins and the webs are called plate elements, the plate elements divide the skins and the webs into M sections, and each section of the plate element has a length d j Thickness t j ，(j＝1,…,M)；
FIG. 2 is an equivalent thin-wall rectangular hollow section, where h is the equivalent section height, b is the equivalent section inside width, and t is sk Is the equivalent thickness of the upper and lower skins, t sp Is the front and rear web equivalent thickness.
A method for estimating the shear coefficient of the equivalent beam of a main box section of a single closed cell of a high-aspect-ratio wing includes predicting the shape of the section of the main box section of the wing, the position of a centroid, the direction of the main centroid of the section, the positions and areas of stringers and edge strips, and the positions and thicknesses of skins and webs, and estimating the shear coefficient k of the equivalent beam of the main box section x (ii) a The steps of estimating the shear coefficient of the main box section equivalent beam are as follows:
1. establishing a coordinate system Oxy, wherein a coordinate origin O is positioned at a centroid position, an axis of Ox is backward along a main centroid, and an axis of Oy is vertical to the axis of Ox; the beam edge strips and the stringers are called rod elements, the rod elements are simplified into one point on the cross section, and the total number of the beam edge strips is 4; the upper long purlin is provided with N U The lower long girder is N D A total of M, and has the following relations
M＝N U +N D +4……………………………[1]The beam flange strips at the joints of the upper skin and the back beam web are made to be the 1 st rod element which is arranged in a counterclockwise direction, and the area of the ith rod element is S ri (i =1, \8230;, M); the skin and the beam web are called plate elements, the plate elements are simplified into a section of line on the cross section, and the skin and the beam web are divided into M sections by the plate elements; the upper skin of the section connected with the upper edge strip of the back beam is a 1 st plate element which is arranged in a counterclockwise direction, and the thickness of the j-th plate element is t pj The positions of two end points of the jth plate element are respectively (x) pj ,y pj ) And (x) pj+1 ,y pj+1 ) (j =1, \ 8230;, M-1), and when j = M, the positions of both end points of the M-th-segment plate member are respectively setIs (x) pM ,y pM ) And (x) p1 ,y p1 ) Namely, the rear beam web plate is obtained;
2. calculating the position of the middle point of the board element,
3. the cross-sectional length of the plate member is calculated,
4. the area of the board element is calculated,
S pj ＝d pj t pj (j＝1,…,M)……………………………[6]
5. the total area of the board elements is calculated,
6. the intermediate variable is calculated and the intermediate variable,
7. the intermediate variable is calculated and the intermediate variable,
8. the intermediate variable is calculated and the intermediate variable,
9. calculating the total area of the rod elements,
10. the total area of the cross-section is calculated,
S＝S r +S p ……………………………[13]
11. calculating the middle variable of the equivalent thin-wall rectangular hollow section,
12. calculating the size of the equivalent thin-wall rectangular hollow section,
13. the intermediate variable is calculated and the intermediate variable,
14. the intermediate variable is calculated and the intermediate variable,
15. calculating the shear coefficient k of the main box section equivalent beam x ，
I.e. the final evaluated value.
The principle of the invention is as follows: the method for estimating the shear coefficient of the equivalent beam of the main box section of the single closed cell of the high-aspect-ratio wing suitable for engineering application and used for airplane design is obtained through geometric equivalence, only the geometric dimension of the cross section needs to be input, the method is easy to realize by using a computer program, and the working efficiency is improved.
Examples
For the method, an embodiment is given; table 1 shows the number of upper and lower stringers and the total number of bar elements;
TABLE 1 variable number of rod elements
| N U | N D | M |
| 5 | 5 | 14 |
Table 2 gives the bar element areas;
TABLE 2 area of bar elements
Table 3 gives the geometrical parameters of the plate elements;
TABLE 3 plate element geometry
Table 4 gives the area parameters of the plate element and the bar element;
TABLE 4 area parameters
| S p | S px | S py | S r | S |
| mm 2 | mm 2 | mm 2 | mm 2 | mm 2 |
| 3507.2 | 3068.1 | 439.1 | 970.1 | 4477.3 |
Table 5 gives the geometric parameters of the equivalent thin-walled rectangular hollow section;
TABLE 5 geometric parameters of equivalent thin-wall rectangular hollow section
| y pu | y pd | x pf | x pb | L x | L y | t sk | t sp | b | h |
| mm | mm | mm | mm | mm | mm | mm | mm | mm | mm |
| 112.4 | -100.8 | -462.2 | 444.1 | 906.3 | 213.2 | 1.7 | 1.0 | 905.3 | 214.9 |
Table 6 gives some intermediate parameters and the shear coefficient of the main box section equivalent beam;
table 6 partial intermediate parameters and shear coefficient of main box section equivalent beam
Claims (1)
1. A method for estimating the shear coefficient of an equivalent beam of a main box section of a single closed cell of a high-aspect-ratio wing is characterized by comprising the following steps:
(1) Establishing a coordinate system Oxy, wherein the origin of coordinates O is positioned at the centroid position, the axis of Ox is backward along the main centroid, and the axis of Oy is vertical to the axis of Ox; the beam edge strips and the stringers are called rod elements, the rod elements are simplified into one point on the cross section, and the total number of the beam edge strips is 4; the upper long purlin is provided with N U The lower long girder is N D A total of M, and has the following relations
M＝N U +N D +4……………………………[1]The beam flange strips at the joints of the upper skin and the back beam web are made to be the 1 st rod element which is arranged in a counterclockwise direction, and the area of the ith rod element is S ri (i =1, \8230;, M); the skins and webs are referred to as plate elements, which are reduced to a line segment in cross-section, the bar elements linking the skins and websThe plate is divided into M sections; the upper skin of the section connected with the upper edge strip of the back beam is a 1 st plate element which is arranged in a counterclockwise direction, and the thickness of the j-th plate element is t pj The positions of two end points of the jth plate element are respectively (x) pj ,y pj ) And (x) pj+1 ,y pj+1 ) (j =1, \ 8230;, M-1), and when j = M, the positions of both end points of the M-th-stage plate member are (x) respectively pM ,y pM ) And (x) p1 ,y p1 ) Namely, the rear beam web plate is obtained;
(2) Calculating the position of the middle point of the board element,
(3) Calculating the cross-sectional length of the board member,
(4) Calculating the area of the board element,
S pj ＝d pj t pj (j＝1,…,M)……………………………[6]
(5) Calculating the total area of the board elements,
(6) And calculating the intermediate variable of the intermediate variable,
(7) And calculating the intermediate variable of the intermediate variable,
(8) And calculating the intermediate variable of the intermediate variable,
(9) Calculating the total area of the rod elements,
(10) Calculating the total area of the cross section,
S＝S r +S p ……………………………[13]
(11) And calculating the intermediate variable of the intermediate variable,
(12) Calculating the size of the equivalent thin-wall rectangular hollow section,
(13) And calculating the intermediate variable of the intermediate variable,
(14) And calculating the intermediate variable of the intermediate variable,
Z＝12+72m+150m 2 +90m 3 +30m(1+m)n 2 ………………[17]
(15) Calculating the shear coefficient k of the main box section equivalent beam x ，
I.e. the final evaluated value.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811476557.7A CN109710987B (en) | 2018-12-04 | 2018-12-04 | Estimation method for equivalent beam shear coefficient of single closed cell main box section of high-aspect-ratio wing |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811476557.7A CN109710987B (en) | 2018-12-04 | 2018-12-04 | Estimation method for equivalent beam shear coefficient of single closed cell main box section of high-aspect-ratio wing |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109710987A CN109710987A (en) | 2019-05-03 |
| CN109710987B true CN109710987B (en) | 2022-11-22 |
Family
ID=66255423
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811476557.7A Active CN109710987B (en) | 2018-12-04 | 2018-12-04 | Estimation method for equivalent beam shear coefficient of single closed cell main box section of high-aspect-ratio wing |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109710987B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111143944B (en) * | 2019-12-25 | 2023-09-05 | 中国航空工业集团公司西安飞机设计研究所 | Wing beam rigidity configuration method of double-beam wing |
| CN113051696B (en) * | 2019-12-26 | 2022-09-20 | 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 single closed cell box section in airplane structure |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105197253B (en) * | 2015-08-14 | 2017-12-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of wing Material Stiffened Panel margin of safety computational methods |
| CN106021779B (en) * | 2016-05-31 | 2019-04-23 | 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 bending stiffness calculation method of high aspect ratio wing |
| CN106156449B (en) * | 2016-08-31 | 2019-05-10 | 中航沈飞民用飞机有限责任公司 | A kind of composite wing siding optimum design method |
-
2018
- 2018-12-04 CN CN201811476557.7A patent/CN109710987B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN109710987A (en) | 2019-05-03 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109710987B (en) | Estimation method for equivalent beam shear coefficient of single closed cell main box section of high-aspect-ratio wing | |
| CN109711048B (en) | Wing design method considering aerodynamic and structural multi-type design variables | |
| CN102446241B (en) | Wing surface structural rigidity simulation method | |
| US20080208540A1 (en) | Method for designing a composite material part with a curved surface | |
| CN103754386B (en) | A kind of wing spar method for determining position | |
| CN107463746A (en) | Fuselage bulkhead circumference stress computational methods under a kind of airtight load | |
| CN111914351B (en) | Method for calculating overall stability of reinforced wallboard of fuselage structure | |
| CN113886967A (en) | Multi-cruise-condition aeroelasticity optimization method for large aircraft wing | |
| CN108563916B (en) | Initial size optimization design method for thin-wall structure of aircraft wing fuselage | |
| CN104699873B (en) | A kind of aircraft target ship hatch frame numerical analysis method | |
| CN110334364B (en) | Composite structural strength checking system | |
| CN102663165B (en) | Preparation method of upper tool post of cold-rolled flying shear | |
| CN115092414B (en) | Annular quantity control airfoil pneumatic and electromagnetic stealth combined optimization method | |
| CN113051696B (en) | Method for calculating shear coefficient of single closed cell box section in airplane structure | |
| Raveh | Maneuver load analysis of overdetermined trim systems | |
| Yadlin et al. | Icing simulation research supporting the ice-accretion testing of large-scale swept-wing models | |
| Ciliberti et al. | A new approach in aircraft vertical tailplane design | |
| CN112949127A (en) | Interference trailing edge structure of leading-edge slat and design method of interference amount of interference trailing edge structure | |
| Kirz | Surrogate-Based Low-Boom Low-Drag Nose Design for the JAXA S4 Supersonic Airliner | |
| Arsenyeva et al. | Efficient and adaptive parametric modeling for shape optimization of a wingbox | |
| CN112362290A (en) | Method for rapidly analyzing influence of thickness tolerance of wing on resistance coefficient | |
| CN113591284B (en) | Analytic method for analyzing delamination and expansion of simple woven composite material | |
| Atkin | Laminar flow control: Leap or creep? | |
| CN106021665B (en) | The multiple batches of aerodynamic data method for quick predicting of hypersonic aircraft | |
| CN110555227A (en) | Multilayer optimization design method for reconfigurable structure |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |