CN105923145A - Detachable leading edge structure of airplane - Google Patents
Detachable leading edge structure of airplane Download PDFInfo
- Publication number
- CN105923145A CN105923145A CN201610177947.9A CN201610177947A CN105923145A CN 105923145 A CN105923145 A CN 105923145A CN 201610177947 A CN201610177947 A CN 201610177947A CN 105923145 A CN105923145 A CN 105923145A
- Authority
- CN
- China
- Prior art keywords
- detachable
- leading edge
- rib
- eyelid covering
- canned paragraph
- 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.)
- Pending
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/28—Leading or trailing edges attached to primary structures, e.g. forming fixed slots
Abstract
The invention belongs to the field of aircraft design, and relates to a detachable leading edge structure of an airplane. The structure includes a fixed section leading edge (1) and a removable leading edge (3); the fixed section leading edge (1) includes a fixed section skin (6) and fixed ribs (7); the fixed section skin (6) is covered between two fixed ribs (7) and in riveting connection with the fixed ribs (7); the upper and lower ends of the fixed section skin (6) are in riveting connection with a beam (9); the upper and lower ends of the fixing rib (7) are connected to angle clips (8) of the beam (9); the removable leading edge (3) includes a removable skin (11), angle stiffeners (12), a stringer (13), and a detachable rib (14); the removable skin (11) covers the outer surfaces of the stringer (13) and the detachable rib (14); the inner sides of the upper and lower ends of the removable skin (11) are connected with the angle stiffeners (12); and the upper and lower ends of the removable skin (11) and the angle stiffeners (12) are in bolt connection to the beam (9).
Description
Technical field
The invention belongs to field of airplane design, relate to a kind of detachable leading edge structure of aircraft.
Background technology
Leading edge is a part for wing, is the important component part of whole wing aerodynamic profile, existing
Having Y12 type aircraft leading edge to be connected with wing-box by riveting, center off position is installed
Enging cabin.Its structure is as shown in Figure 1.
Aircraft leading edge is made up of rib, stringer and covering riveting, and after riveting, structure is non-dismountable.Before
Edge lower aerofoil sets safeguards lid, is connected with leading edge by hinge, provides operation dimension for other system
Protect space.
Because Y12 type aircraft leading edge is connected with wing-box by riveting, structure after riveting
Narrow space, can only be safeguarded by lower aerofoil lid, bring to the regular maintenance of aircraft
Inconvenience.
Summary of the invention
The purpose of the present invention: propose a kind of detachable leading edge structure of aircraft, leading edge detachable and
Easy to maintenance.
Technical scheme: a kind of detachable leading edge structure of aircraft, including:
Canned paragraph leading edge (1) and detachable leading edge (3)；
Canned paragraph leading edge (1) includes canned paragraph eyelid covering (6) and fixing rib (7), two Horse hoofs
The fixing rib (7) of shape is oppositely arranged, and canned paragraph eyelid covering (6) covers two fixing rib (7)
Between and with fixing rib (7) rivet；The two ends up and down of canned paragraph eyelid covering (6) and beam (9)
Riveting；The two ends up and down of fixing rib (7) are connected with the attachment angle (8) on beam (9)；
Detachable leading edge (3) includes detachable eyelid covering (11), angle stiffener (12), stringer
(13), detachable rib (14)；Detachable eyelid covering (11) covers in stringer (13) and removable
Unloading the outer surface of rib (14), connecting inside detachable eyelid covering (11) two ends up and down has reinforcement angle
Material (12), detachable eyelid covering (11) two ends and angle stiffener (12) up and down are screwed onto beam (9)
On；Detachable eyelid covering (11) side is screwed onto that fixing rib (7) is upper or rib (2), (4),
(5), on, described rib (2), (4), (5) are fixed on beam (9).
Offer on detachable eyelid covering (11) and safeguard lid (10).
Advantages of the present invention
The detachable leading edge of the present invention makes the readily accessible installation of structure, shortens the repair time；Leading edge
Use segment design, it is simple to change structure during structural failure, reduce maintenance cost.
Accompanying drawing illustrates:
Fig. 1 is existing Y12 type aircraft leading edge structural representation.
Fig. 2 is aircraft leading edge structural representation of the present invention.
Fig. 3 is canned paragraph leading edge structure schematic diagram in the present invention.
Fig. 4 is detachable leading edge structure schematic diagram in the present invention.
Detailed description of the invention:
Below in conjunction with the accompanying drawings the present invention is described in further detail.
A kind of detachable leading edge structure of aircraft, as in figure 2 it is shown, include:
Canned paragraph leading edge 1 and detachable leading edge 3；
Canned paragraph leading edge 1 as it is shown on figure 3, include canned paragraph eyelid covering 6 and fixing rib 7, two
Horseshoe-shaped fixing rib 7 is oppositely arranged, and canned paragraph eyelid covering 6 covers between two fixing rib 7 also
Rivet with fixing rib 7；The two ends up and down of canned paragraph eyelid covering 6 rivet with beam 9；Fixing rib 7
Two ends are connected with the attachment angle 8 on beam 9 up and down；
Detachable leading edge 3 as shown in Figure 4, including detachable eyelid covering 11, angle stiffener 12,
Stringer 13, detachable rib 14；Detachable eyelid covering 11 covers at stringer 13 and detachable rib 14
Outer surface, inside detachable eyelid covering about 11 two ends connect have angle stiffener 12, detachably
Eyelid covering about 11 two ends and angle stiffener 12 are screwed onto on beam 9；Detachable eyelid covering 11 side
Being screwed onto in fixing rib 7 or on rib 2,4,5, described rib 2,4,5 is fixed on beam 9.
Offer on detachable eyelid covering 11 and safeguard lid 10.
This time invention for carrying out segment design by leading edge, and it is mainly characterized by:
1, Y12F leading edge is the aluminium alloy structure of band eyelid covering, rib and stringer；
2, the mode that leading edge uses two sections of canned paragraph leading edges to combine with three sections of detachable leading edges is entered
Row connects；
3, fixing leading edge is connected with front-axle beam by rib, and detachable leading edge uses screw and without riveting torr
Crab bolt is connected with front-axle beam；
4, have lid in detachable leading edge, be used for dismantling ice set conduit at front separation and connect；
5, stringer breach processed on rib, it is ensured that the seriality of stringer；
6, eyelid covering uses chemical-milled structure；
7, detachable leading edge can meet structure interchangeability.
Claims (2)
1. the detachable leading edge structure of aircraft, it is characterised in that including:
Canned paragraph leading edge (1) and detachable leading edge (3)；
Canned paragraph leading edge (1) includes canned paragraph eyelid covering (6) and fixing rib (7), two Horse hoofs
The fixing rib (7) of shape is oppositely arranged, and canned paragraph eyelid covering (6) covers two fixing rib (7)
Between and with fixing rib (7) rivet；The two ends up and down of canned paragraph eyelid covering (6) and beam (9)
Riveting；The two ends up and down of fixing rib (7) are connected with the attachment angle (8) on beam (9)；
Detachable leading edge (3) includes detachable eyelid covering (11), angle stiffener (12), stringer
(13), detachable rib (14)；Detachable eyelid covering (11) covers in stringer (13) and removable
Unloading the outer surface of rib (14), connecting inside detachable eyelid covering (11) two ends up and down has reinforcement angle
Material (12), detachable eyelid covering (11) two ends and angle stiffener (12) up and down are screwed onto beam (9)
On；Detachable eyelid covering (11) side is screwed onto that fixing rib (7) is upper or rib (2), (4),
(5), on, described rib (2), (4), (5) are fixed on beam (9).
2. a kind of detachable leading edge structure of aircraft as claimed in claim 1, it is characterised in that
Offer on detachable eyelid covering (11) and safeguard lid (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610177947.9A CN105923145A (en) | 2016-03-25 | 2016-03-25 | Detachable leading edge structure of airplane |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610177947.9A CN105923145A (en) | 2016-03-25 | 2016-03-25 | Detachable leading edge structure of airplane |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN105923145A true CN105923145A (en) | 2016-09-07 |
Family
ID=56840362
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610177947.9A Pending CN105923145A (en) | 2016-03-25 | 2016-03-25 | Detachable leading edge structure of airplane |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105923145A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112407236A (en) * | 2020-10-27 | 2021-02-26 | 成都飞机工业（集团）有限责任公司 | Honeycomb sandwich graphene stealth front edge and processing method thereof |
| CN112798211A (en) * | 2020-12-29 | 2021-05-14 | 中国航空工业集团公司西安飞机设计研究所 | Equivalent clamping device for bird impact resistance test |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009112641A1 (en) * | 2008-03-13 | 2009-09-17 | Patria Aerostructures Oy | Leading edge element of aircraft, method for manufacturing one, wing and stabilizer |
| CN102390520A (en) * | 2011-09-29 | 2012-03-28 | 西北工业大学 | Empennage capable of improving bird strike resistance of airplane |
| CN103754353A (en) * | 2013-12-09 | 2014-04-30 | 中国航空工业集团公司西安飞机设计研究所 | Composite material elevator |
| CN204250357U (en) * | 2014-10-11 | 2015-04-08 | 中国航空工业集团公司西安飞机设计研究所 | A kind of anti-bird of aircraft leading edge arranging inside panel hits structure |
| CN105253305A (en) * | 2015-10-10 | 2016-01-20 | 南京航空航天大学 | Leading-edge detachable type experiment wing structure based on piezoelectric deicing system |
-
2016
- 2016-03-25 CN CN201610177947.9A patent/CN105923145A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009112641A1 (en) * | 2008-03-13 | 2009-09-17 | Patria Aerostructures Oy | Leading edge element of aircraft, method for manufacturing one, wing and stabilizer |
| CN102390520A (en) * | 2011-09-29 | 2012-03-28 | 西北工业大学 | Empennage capable of improving bird strike resistance of airplane |
| CN103754353A (en) * | 2013-12-09 | 2014-04-30 | 中国航空工业集团公司西安飞机设计研究所 | Composite material elevator |
| CN204250357U (en) * | 2014-10-11 | 2015-04-08 | 中国航空工业集团公司西安飞机设计研究所 | A kind of anti-bird of aircraft leading edge arranging inside panel hits structure |
| CN105253305A (en) * | 2015-10-10 | 2016-01-20 | 南京航空航天大学 | Leading-edge detachable type experiment wing structure based on piezoelectric deicing system |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112407236A (en) * | 2020-10-27 | 2021-02-26 | 成都飞机工业（集团）有限责任公司 | Honeycomb sandwich graphene stealth front edge and processing method thereof |
| CN112798211A (en) * | 2020-12-29 | 2021-05-14 | 中国航空工业集团公司西安飞机设计研究所 | Equivalent clamping device for bird impact resistance test |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20160907 |
|
| WD01 | Invention patent application deemed withdrawn after publication |