CN209192202U - A kind of truss rib structure transporting airfoil - Google Patents
A kind of truss rib structure transporting airfoil Download PDFInfo
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- CN209192202U CN209192202U CN201821559550.7U CN201821559550U CN209192202U CN 209192202 U CN209192202 U CN 209192202U CN 201821559550 U CN201821559550 U CN 201821559550U CN 209192202 U CN209192202 U CN 209192202U
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- rib structure
- edge strip
- beam splice
- airfoil
- upper edge
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Abstract
The utility model belongs to large and medium-sized transporter rib structure design field, and in particular to a kind of truss rib structure for transporting airfoil.Situations such as large and medium-sized common rib structure of transporter is all made of edge strip, rib web up and down and reinforces pillar construction, the too low buckling of rib structure rigidity is be easy to cause to increase.After the utility model carries out topological optimization to the common rib structure of large and medium-sized transporter, a kind of truss rib structure for transporting airfoil is proposed.The structure is mounted between spar by lateral preceding beam splice and rear beam splice, upper edge strip is connected between preceding beam splice and the end of rear beam splice, lower edge strip is connected between preceding beam splice and the end of rear beam splice, is connected with several T profiles or angle section between upper edge strip and lower edge strip.After the utility model truss rib structure form, intensity is held essentially constant, and rigidity is slightly promoted, and the weight of entire rib structure reduces 31.5%.
Description
Technical field
The utility model belongs to large and medium-sized transporter rib structure design field, and in particular to a kind of transport airfoil
Truss rib structure.
Background technique
Currently, all having carried out a large amount of scientific research both at home and abroad, it comprises sizes for the optimization design of aircaft configuration
Optimization, parameter optimization and structural Topology Optimization etc..But its optimum results mostly be integrally formed and irregular structure type,
This is unfavorable for engineer application in practice.Former rib structure stress form is complicated and process and assemble is difficult.Meanwhile because frequent in wing
Additional equipment and task system, when installation, need guiding through rib position, therefore opening and reinforcement need to be carried out to rib web, this increases machine
The security risk of wing structure also further improves difficulty of construction simultaneously.
As shown in Figure 1, the large and medium-sized common rib structure of transporter is all made of edge strip, rib web up and down and reinforces column
Structure.When carrying out loss of weight design to it, mostly using rib web be open method, due to aircraft design at the beginning of just it is right
The intensity of housing construction is controlled with rigidity, so change nargin is little when carrying out loss of weight design to rib structure, and
Situations such as be easy to causeing the too low buckling of rib structure rigidity to increase.Meanwhile most research achievement, be also all it is Utopian not
Regular texture can not be applied in Practical Project at all.
Utility model content
After the utility model carries out topological optimization to the common rib structure of large and medium-sized transporter, a kind of transport airfoil is proposed
Truss rib structure.
A kind of truss rib structure transporting airfoil, the structure are mounted on the wing by lateral preceding beam splice and rear beam splice
Between beam, upper edge strip is connected between preceding beam splice and the end of rear beam splice, and beam splice and the back rest connect before lower edge strip is connected to
Between the end of head, several T profiles or angle section are connected between upper edge strip and lower edge strip.
Form is connect with upper edge strip and lower edge strip by being inclined cross that overlapped for the T profile or angle section.
The T profile or angle section and upper edge strip or lower edge strip constitute triangular frame structure.
The truss rib structure is suitable for outer wing, horizontal tail or the vertical fin of large and medium-sized transporter.
The utility model has the advantages that
A can carry out effective loss of weight to the common rib of large and medium-sized transporter；
B does not damage the rigidity and intensity of rib structure, it might even be possible to carry out limited reinforcement to rigidity, the intensity of structure；
C is convenient for engineering construction；
D can reduce aircraft manufacturing cost；
E is convenient for the later maintenance of aircraft.
Detailed description of the invention
Fig. 1 is certain medium transport aircraft rib structure form；
Fig. 2 is the schematic diagram of the utility model truss rib structure.
Specific embodiment
A kind of truss rib structure transporting airfoil, the structure are mounted on by lateral preceding beam splice 3 and rear beam splice 4
Between spar, upper edge strip 1 is connected between preceding beam splice 3 and the end of rear beam splice 4,3 He of beam splice before lower edge strip 2 is connected to
Afterwards between the end of beam splice 4, several T profiles or angle section 5 are connected between upper edge strip 1 and lower edge strip 2.
Form is connect with upper edge strip 1 and lower edge strip 2 by being inclined cross that overlapped for the T profile or angle section 5.The T profile
Or angle section 5 constitutes triangular frame structure with upper edge strip 1 or lower edge strip 2.
The truss rib structure is suitable for outer wing, horizontal tail or the vertical fin of large and medium-sized transporter.
After the utility model truss rib structure form, intensity is held essentially constant, and rigidity is slightly promoted, entire rib knot
The weight of structure reduces 31.5%.
Claims (3)
1. a kind of truss rib structure for transporting airfoil, it is characterised in that: the structure passes through lateral preceding beam splice (3) and the back rest
Connector (4) is mounted between spar, and upper edge strip (1) is connected between preceding beam splice (3) and the end of rear beam splice (4), lower edge
Item (2) is connected between preceding beam splice (3) and the end of rear beam splice (4), is connected between upper edge strip (1) and lower edge strip (2)
There are several T profiles or angle section (5).
2. truss rib structure according to claim 1, it is characterised in that: the T profile or angle section (5) are taken by being inclined cross
The form connect is connect with upper edge strip (1) and lower edge strip (2).
3. truss rib structure according to claim 2, it is characterised in that: the T profile or angle section (5) and upper edge strip
(1) or lower edge strip (2) constitutes triangular frame structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821559550.7U CN209192202U (en) | 2018-09-25 | 2018-09-25 | A kind of truss rib structure transporting airfoil |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821559550.7U CN209192202U (en) | 2018-09-25 | 2018-09-25 | A kind of truss rib structure transporting airfoil |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209192202U true CN209192202U (en) | 2019-08-02 |
Family
ID=67406590
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821559550.7U Active CN209192202U (en) | 2018-09-25 | 2018-09-25 | A kind of truss rib structure transporting airfoil |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209192202U (en) |
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2018
- 2018-09-25 CN CN201821559550.7U patent/CN209192202U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address | ||
| CP03 | Change of name, title or address |
Address after: 723213 Liulin Town, Chenggu County, Hanzhong City, Shaanxi Province Patentee after: Shaanxi Aircraft Industry Co.,Ltd. Address before: 723213 box 34, Hanzhong City, Shaanxi Province Patentee before: Shaanxi Aircraft INDUSTRY(GROUP) Co.,Ltd. |