CN201249874Y - Wing spar topological optimization stiffened girder - Google Patents
Wing spar topological optimization stiffened girder Download PDFInfo
- Publication number
- CN201249874Y CN201249874Y CNU2008200136637U CN200820013663U CN201249874Y CN 201249874 Y CN201249874 Y CN 201249874Y CN U2008200136637 U CNU2008200136637 U CN U2008200136637U CN 200820013663 U CN200820013663 U CN 200820013663U CN 201249874 Y CN201249874 Y CN 201249874Y
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- rib
- junction
- plate muscle
- edge
- fascia
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Abstract
A wing spar topological optimization stiffened girder is characterized by comprising a stiffened girder frame 1, a fascia 2 and a fascia 3; wherein, the stiffened girder frame 1 is of a quadrilateral structure, the bottom edge of which is horizontal, the left edge of which forms a 35-50 degrees angle with the horizontal line, the upper edge of which forms a 0-10 degrees angle with the horizontal line, and the right edge of which is vertical; one end of the fascia 2 is connected with the junction of the left edge and the upper edge of the stiffened girder frame 1, and is connected with the bottom edge at an angel of 40-50 degrees; one end of the fascia 3 is connected with the junction of the upper edge and the right edge of the stiffened girder frame 1, and the other end is connected with the junction of the fascia 2 and the bottom edge. The utility model changes the traditional structure, improves the performance and can be applied to mechanics teaching experiment in university of science and engineering.
Description
Technical field
The utility model relates to mechanical field, and a kind of spar topological optimization plate muscle beam is provided especially.
Background technology
Plate muscle structure has a wide range of applications on present generation aircraft, no matter is the primary load bearing reinforced bulkhead of fuselage, or the crossbeam of aerofoil or reinforcement rib, all is comparison representative type plate muscle structures.Traditional plate muscle mount structure Heavy Weight, rigidity is little, the stress level height, fatigue life is low.
The utility model provides a kind of diplopore topological optimization plate muscle frame, adopts the main Path of Force Transfer of determining structure based on the Topology Optimization Method of sensitivity threshold value, and rib is arranged on the main Path of Force Transfer of being obtained; Then, come breadboard muscle structure, and set up corresponding finite element analysis model with plate and bar unit; At last, with the thickness of plate and the sectional area of rib is design variable, carry out full stress design and obtain final prioritization scheme, the numerical simulation result of multiple example shows: utilization this paper method is compared with traditional method based on engineering experience, under the condition of structure constant characteristic, the former design plan can alleviate structural weight and reach 5%～20%.
The utility model content
The purpose of this utility model is to overcome the deficiencies in the prior art part, and a kind of spar topological optimization plate muscle beam is provided especially.
The utility model provides a kind of spar topological optimization plate muscle beam, it is characterized in that: include plate muscle roof beam structure 1, rib 2, rib 3; Wherein plate muscle roof beam structure 1 is a quadrilateral structure, the base level, and the left side becomes 35～50 degree angles with level, and the top becomes 0～10 degree angle with level, and the right is vertical; Rib 2 one ends are connected with plate muscle roof beam structure 1 left side, junction, top, and become 40～50 degree angles to be connected with the base; Rib 3 one ends are connected with the top of plate muscle roof beam structure 1, the junction on the right, and the other end is connected with the junction on rib 2, base.
At first will curved scissors makes up the diplopore reinforced bulkhead that loads, carry out iteration according to the topological optimization flow process and draw the most reasonable distribution of cooresponding rib material, detailed process is the finite element modeling-structural analysis (ANSYS)-based on the optimization criterion-main power transmission road warp of sensitivity threshold value based on topological optimization; Determine the rib position afterwards.Conventional beam, truss girder, optimization beam performance comparison are as follows:
The structural response contrast of the beam of three kinds of versions of table 1
| Title | Maximum displacement/mm | Maximum rod stress/Kg/mm 2 | Maximum plate stress/Kg/mm 2 | Structure FEM weight/Kg |
| Conventional beam | 0.8364 | 9.396 | 6.732 | 0.836 |
| Truss girder | 0.8345 | 4.25 | / | 0.862 |
| Optimize beam | 0.8301 | 5.1 | 5.1 | 0.681 |
Advantage of the present utility model: under the condition of structure constant characteristic, present design can alleviate structural weight and reach 5%～20%.
Description of drawings
Fig. 1 is a spar topological optimization plate muscle beam;
Fig. 2 is conventional plate muscle beam;
Fig. 3 is the truss girder scheme drawing.
The specific embodiment
Embodiment 1
A kind of spar topological optimization of present embodiment plate muscle beam includes plate muscle roof beam structure 1, rib 2, rib 3; Wherein plate muscle roof beam structure 1 is a quadrilateral structure, the base level, and the left side becomes 35～50 degree angles with level, and the top becomes 0～10 degree angle with level, and the right is vertical; Rib 2 one ends are connected with plate muscle roof beam structure 1 left side, junction, top, and become 40～50 degree angles to be connected with the base; Rib 3 one ends are connected with the top of plate muscle roof beam structure 1, the junction on the right, and the other end is connected with the junction on rib 2, base.
Claims (1)
1, a kind of spar topological optimization plate muscle beam is characterized in that: include plate muscle roof beam structure (1), rib (2), rib (3); Wherein plate muscle roof beam structure (.) is a quadrilateral structure, the base level, and the left side becomes 35～50 degree angles with level, and the top becomes 0～10 degree angle with level, and the right is vertical; Rib (2) one ends are connected with plate muscle roof beam structure (1) left side, junction, top, and become 40～50 degree angles to be connected with the base; Rib (3) one ends are connected with the top of plate muscle roof beam structure (1), the junction on the right, and the other end is connected with the junction on rib (2), base.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2008200136637U CN201249874Y (en) | 2008-06-26 | 2008-06-26 | Wing spar topological optimization stiffened girder |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2008200136637U CN201249874Y (en) | 2008-06-26 | 2008-06-26 | Wing spar topological optimization stiffened girder |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201249874Y true CN201249874Y (en) | 2009-06-03 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2008200136637U Expired - Lifetime CN201249874Y (en) | 2008-06-26 | 2008-06-26 | Wing spar topological optimization stiffened girder |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201249874Y (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102944211A (en) * | 2012-11-12 | 2013-02-27 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining area of crack arrest rib of aircraft integral wing spar |
-
2008
- 2008-06-26 CN CNU2008200136637U patent/CN201249874Y/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102944211A (en) * | 2012-11-12 | 2013-02-27 | 中国航空工业集团公司西安飞机设计研究所 | Method for determining area of crack arrest rib of aircraft integral wing spar |
| CN102944211B (en) * | 2012-11-12 | 2016-03-09 | 中国航空工业集团公司西安飞机设计研究所 | A kind of defining method of whole wing spar of airplane crack arrest rib area |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20090603 |