CN105620717B - A kind of tilt rotor aircraft wing tip load diffusion structure - Google Patents
A kind of tilt rotor aircraft wing tip load diffusion structure Download PDFInfo
- Publication number
- CN105620717B CN105620717B CN201410605932.9A CN201410605932A CN105620717B CN 105620717 B CN105620717 B CN 105620717B CN 201410605932 A CN201410605932 A CN 201410605932A CN 105620717 B CN105620717 B CN 105620717B
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- Prior art keywords
- ribs
- short beam
- diffusion structure
- wing tip
- load diffusion
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Abstract
The invention discloses a kind of tilt rotor aircraft wing tip load diffusion structure, including preceding short beam (1), rear short beam (2), outer ribs (3), interior ribs (4), the preceding short beam (1), rear short beam (2), outer ribs (3), interior ribs (4) and wing cover form local closed chamber, nacelle inclining rotary mechanism can be hung, provides and supports rigidity, effectively diffusion tip concentrfated load enough so that the smooth rotation of nacelle.
Description
Technical field
The invention belongs to field of airplane structure, is related to a kind of tilt rotor aircraft wing tip load diffusion structure and its answers
Ribs.
Background technology
Tilt rotor aircraft wing, its tip hang with nacelle, rotor and related system etc., and its stress form has different from routine
Fixed wing aircraft, that is, require consideration for how the concentrfated load of wing tip being effectively diffused on the main force support structure of wing, to subtract
The construction weight of few wing, at present, this aspect is effectively studied, and the country still belongs to blank.
The content of the invention
The technical problem to be solved in the present invention is, during the structural support of solution nacelle and its inclining rotary mechanism, nacelle move
Concentrfated load diffusion problem.
A kind of tilt rotor aircraft wing tip load diffusion structure is provided for the technical solution of the present invention that solves the above problems, including
Preceding short beam, rear short beam, outer ribs, interior ribs, the preceding short beam is between two ribs close to front-axle beam position, one end
Connect and add ribs in outer ribs other end connection, the rear short beam close back rest position between two ribs, one
End connects ribs in outer ribs other end connection.The outer ribs is arranged on both ends on the outside of wing tip, connects wing respectively
Front-axle beam and the back rest, the interior ribs are arranged on the inside of wing tip, and both ends connect Front wing spar and the back rest respectively, the preceding short beam,
Short beam, outer ribs, interior ribs and wing cover form local closed chamber afterwards.
Preferably, the outer ribs has partial thickening structure inside and outside.
Preferably, the partial thickening structure of the outer ribs is positioned at the position for installing the preceding short beam and the rear short beam
Between.
Preferably, lid is provided with the local closed chamber.
The present invention is for the unique wing tip carry of tilt rotor aircraft and the concentration big load in use, brand-new design one
The local closed cell structure of kind, nacelle inclining rotary mechanism can be hung, is provided and is supported rigidity enough, effectively spreads tip concentrfated load so that
The smooth rotation of nacelle.
Brief description of the drawings
Specific embodiments of the present invention are further described in detail below in conjunction with the accompanying drawings, wherein：
Fig. 1 is load diffusion structure schematic diagram；
Fig. 2 is load diffusion structure outward appearance；
Fig. 3 is short beam structure chart；
Fig. 4 is additional reinforced rib structure figure；
Fig. 5 is interior ribs structure chart.
Embodiment
The embodiment of the present invention provides a kind of tilt rotor aircraft wing tip load diffusion structure, the load diffusion structure, installation
It is concentrfated load power transmission diffuser, transmission mechanism motion supporting assembly at wing-box wing tip position.The load diffusion structure by
Two short beams 1,2, each double-deck covering 5,6,9,10, front-axle beam 7, the back rest 8 and two neighboring ribs 3,4 assembly up and down.
Two short beams, i.e., preceding short beam 1, rear short beam 2, and be double-deck covering herein, ribs 3 two neighboring with installation position, 4, on
Lower wall panels form local closed chamber, and moment of flexure, shearing, moment of torsion caused by concentrfated load can effectively be passed to wing box primary load bearing structure by the closed chamber
On part, that is, the concentrfated load diffuser that enough rigidity is supported can be provided by being formed；Two short beams 1,2 structure types are identical, due to
With wing, so not being equivalent elements, two short beams 1,2 webs are provided with circular lightening core, and circular hole periphery is locally thicker than web
Other positions, to play lightening core booster action, using machine addition shape.
When outer ribs 3 in this programme connects, the web place of thickening of outer ribs 3 is bolted tip carry,
Outer ribs 3 is bolted with short beam, and the outer web of ribs 3 outside short beam join domain with needing local reinforcement, to play
To the humidification of rib web, the outer integrated machine addition shape of ribs 3.When interior ribs 4 in this programme connects, interior ribs 4
It is bolted with short beam, interior ribs 4 outside short beam join domain with needing local reinforcement, to play the enhancing to rib web
Effect, integrated machine addition shape.
The described two short beams of this programme are integrated machine add-on type, and edge strip takes I-shaped formula, preferable top airfoil two
Layer covering 9,10 is provided with maintenance lid 11, and lid 11 is outer layer covering 9, and it is connected by plate nut with internal layer covering 10.
Claims (4)
1. a kind of tilt rotor aircraft wing tip load diffusion structure, it is characterised in that including preceding short beam (1), rear short beam (2), outer
Ribs (3), interior ribs (4), the preceding short beam (1) are outer close to front-axle beam position, one end connection between two ribs
Ribs (4) in the connection of ribs (3) other end, the rear short beam (2) close back rest position between two ribs, one
End connects ribs (4) in outer ribs (3) other end connection；The outer ribs (3) is arranged on both ends on the outside of wing tip, respectively
Front wing spar and the back rest are connected, the interior ribs (4) is arranged on the inside of wing tip, and both ends connect Front wing spar and the back rest respectively,
The preceding short beam (1), rear short beam (2), outer ribs (3), interior ribs (4) and wing cover form local closed chamber.
2. load diffusion structure according to claim 1, it is characterised in that the outer ribs (3) has inside and outside
There is partial thickening structure.
3. load diffusion structure according to claim 2, it is characterised in that the partial thickening knot of the outer ribs (3)
Structure is between the position for installing the preceding short beam (1) and the rear short beam (2).
4. load diffusion structure according to claim 1, it is characterised in that lid is provided with the local closed chamber
(11)。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410605932.9A CN105620717B (en) | 2014-10-31 | 2014-10-31 | A kind of tilt rotor aircraft wing tip load diffusion structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410605932.9A CN105620717B (en) | 2014-10-31 | 2014-10-31 | A kind of tilt rotor aircraft wing tip load diffusion structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105620717A CN105620717A (en) | 2016-06-01 |
| CN105620717B true CN105620717B (en) | 2018-03-02 |
Family
ID=56036149
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410605932.9A Active CN105620717B (en) | 2014-10-31 | 2014-10-31 | A kind of tilt rotor aircraft wing tip load diffusion structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105620717B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110539874B (en) * | 2019-09-19 | 2023-04-07 | 中国航空工业集团公司西安飞机设计研究所 | Wing mounting structure of tilt rotor aircraft |
Family Cites Families (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| BRPI0419051A (en) * | 2004-09-30 | 2007-12-11 | Bell Helicopter Textron Inc | compact tiltrotor tower conversion actuation system |
| KR100555176B1 (en) * | 2004-12-31 | 2006-03-03 | 한국항공우주연구원 | A tilt-rotor aircraft |
| US7721995B2 (en) * | 2006-12-13 | 2010-05-25 | The Boeing Company | Rib support for wing panels |
| ES2799904T3 (en) * | 2012-10-03 | 2020-12-22 | Airbus Operations Sl | End hull of a horizontal bearing surface |
| CN203612194U (en) * | 2013-08-23 | 2014-05-28 | 中国航空工业集团公司西安飞机设计研究所 | Concentrated-load force-transferring diffusion piece in box section of wing box |
| CN203612195U (en) * | 2013-09-10 | 2014-05-28 | 中国航空工业集团公司西安飞机设计研究所 | Diffusion structure of concentrated loads between wing ribs |
-
2014
- 2014-10-31 CN CN201410605932.9A patent/CN105620717B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN105620717A (en) | 2016-06-01 |
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