CN109625312A - Aircaft configuration covering injury repair device - Google Patents
Aircaft configuration covering injury repair device Download PDFInfo
- Publication number
- CN109625312A CN109625312A CN201811437132.5A CN201811437132A CN109625312A CN 109625312 A CN109625312 A CN 109625312A CN 201811437132 A CN201811437132 A CN 201811437132A CN 109625312 A CN109625312 A CN 109625312A
- Authority
- CN
- China
- Prior art keywords
- covering
- aircaft configuration
- self
- injury repair
- profile
- 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.)
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/40—Maintaining or repairing aircraft
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Bridges Or Land Bridges (AREA)
Abstract
This application discloses a kind of aircaft configuration covering injury repair devices, for repairing to the damage covering being attached by dormant bolt and self-locking nut with profile；Aircaft configuration covering injury repair device includes: stiffening plate, is laid on the one side backwards to profile of covering；It makes washer by oneself, is arranged in the taper nail hole formed on covering, and outer contour shape is adapted with the cone-shaped nail hole shape；Lengthened bolt is threadedly coupled after sequentially passing through stiffening plate, self-control washer and profile with self-locking nut.The aircaft configuration covering injury repair device of the application, is able to suppress further expanding for damage, meets intensity requirement, guarantee aircraft using safe；Also, the aircaft configuration covering injury repair device of the application is easy to operate, and outfield is implementable, and the repair cycle is short, can be effectively reduced human cost, the lash-up recovering suitable for the certain crucial primary structure member damages of outfield aircraft.
Description
Technical field
The application belongs to Aircraft Structure Maintenance device field, in particular to a kind of aircaft configuration covering injury repair device.
Background technique
In the use process of aircraft, certain components can generate damage due to fatigue, corrosion or exotic shock etc.,
The lighter damage in part can be implemented to repair after aircraft enters system shop, but the damage for influencing aircraft function needs outside
Enforcing remedies is repaired at once for field.
When repairing for the component with countersunk head nail hole in the past, increase by one piece of connector in the outside of damaged member,
Conical nail hole is filled with special countersunk head washer.It, need to be according to injury repair scheme since special countersunk head washer is not belonging to standard component
Drawing production, the production cycle is longer, it is difficult to meet the requirement of outfield rapid rush-repair.Such as damaged structure without countersunk head nail hole
Filling, will have a direct impact on the intensity of component, causes security risk.
Summary of the invention
At least one in order to solve the above-mentioned technical problem, this application provides a kind of aircaft configuration covering injury repair dresses
It sets.
This application discloses a kind of aircaft configuration covering injury repair devices, are used for by dormant bolt and self-locking nut
The damage covering being attached with profile is repaired, and the aircaft configuration covering injury repair device includes:
Stiffening plate is laid on the one side backwards to the profile of the covering；
It makes washer by oneself, is arranged in the taper nail hole formed on the covering, and outer contour shape and the taper nail hole
Shape is adapted；
Lengthened bolt is threadedly coupled after sequentially passing through the stiffening plate, self-control washer and profile with self-locking nut.
According at least one embodiment of the application, in the Lengthened bolt being located on the outside of the stiffening plate and it is located at institute
The outer surface for stating the self-locking nut on the outside of profile is provided with corrosion-inhibiting coating.
According at least one embodiment of the application, the corrosion-inhibiting coating is TB06-9 priming paint.
At least there are following advantageous effects in the application:
The aircaft configuration covering injury repair device of the application, is able to suppress further expanding for damage, meets intensity and want
Ask, guarantee aircraft using safe；Also, the aircaft configuration covering injury repair device of the application is easy to operate, and outfield can be real
It applies, the repair cycle is short, can be effectively reduced human cost, and the emergency suitable for the certain crucial primary structure member damages of outfield aircraft is repaired
It is multiple.
Detailed description of the invention
Fig. 1 is certain structural member original state type of attachment schematic diagram；
Fig. 2 is the standard component schematic diagram connected with Mr. Yu's structural member；
Fig. 3 is self-control countersunk head washer process schematic cross-sectional view；
Fig. 4 is self-control countersunk head washer schematic cross-sectional view；
Fig. 5 is that certain damaged structure repairs schematic diagram.
Specific embodiment
To keep the purposes, technical schemes and advantages of the application implementation clearer, below in conjunction in the embodiment of the present application
Attached drawing, technical solutions in the embodiments of the present application is further described in more detail.In the accompanying drawings, identical from beginning to end or class
As label indicate same or similar element or element with the same or similar functions.Described embodiment is the application
A part of the embodiment, instead of all the embodiments.The embodiments described below with reference to the accompanying drawings are exemplary, it is intended to use
In explanation the application, and it should not be understood as the limitation to the application.Based on the embodiment in the application, ordinary skill people
Member's every other embodiment obtained without creative efforts, shall fall in the protection scope of this application.Under
Face is described in detail embodiments herein in conjunction with attached drawing.
In the description of the present application, it is to be understood that term " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or positional relationship of the instructions such as "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outside" is based on attached drawing institute
The orientation or positional relationship shown is merely for convenience of description the application and simplifies description, rather than the dress of indication or suggestion meaning
It sets or element must have a particular orientation, be constructed and operated in a specific orientation, therefore should not be understood as protecting the application
The limitation of range.
1 to Fig. 5 the application aircaft configuration covering injury repair device is described in further details with reference to the accompanying drawing.
This application discloses a kind of aircaft configuration covering injury repair devices, are used for by dormant bolt 3 and self-locking spiral shell
The damage covering 1 that mother 4 is attached with profile 2 is repaired；Wherein, aircaft configuration covering injury repair device may include packet
Include stiffening plate 7, self-control washer 6 and Lengthened bolt 8.
Stiffening plate 7 is laid on the one side backwards to profile 2 of covering 1；The cone formed on covering 1 is arranged in self-control washer 6
In staple hole, and outer contour shape is adapted with cone-shaped nail hole shape；Lengthened bolt 8 sequentially passes through stiffening plate 7, self-control washer 6
And it is threadedly coupled after profile 2 with self-locking nut 4.
It is possible to further the self-locking nut 4 being located at the Lengthened bolt 8 in 7 outside of stiffening plate and positioned at 2 outside of profile
Outer surface be provided with corrosion-inhibiting coating 9；In the present embodiment, preferably corrosion-inhibiting coating 9 is TB06-9 priming paint.
The use process of the application aircaft configuration covering injury repair device is described below:
As shown in Figure 1, being the original state type of attachment of certain structural skin 1 and profile 2, wherein covering 1 and profile 2
Connection uses dormant bolt 3 and self-locking nut 4.After covering 1 damages, according to equal strength and etc. rigidity principle, Ying Meng
The outside of skin increases by one piece of stiffening plate 7, repairs to damage location.
It will appear the nail hole of taper after dormant bolt 3 is removed, on the outside of covering, when injury repair needs to fill out the nail hole
It fills, to guarantee the continuity of load transmission, avoids the occurrence of stress concentration.Since the head of dormant bolt 3, according to schematic diagram 3,
Self-control washer 6 is made with drill bit 5.Self-control washer 6 is put into the taper nail hole of covering 1, then with Lengthened bolt 8 and self-locking nut
4 connect stiffening plate 7 with covering 1, profile 2.Finally, can be in the Lengthened bolt 8 in 7 outside of stiffening plate and outside profile 2
The outer surface of the self-locking nut 4 of side is provided with corrosion-inhibiting coating 9.
The aircaft configuration covering injury repair device of the application, is able to suppress further expanding for damage, meets intensity and want
Ask, guarantee aircraft using safe；Also, the aircaft configuration covering injury repair device of the application is easy to operate, and outfield can be real
It applies, the repair cycle is short, can be effectively reduced human cost, and the emergency suitable for the certain crucial primary structure member damages of outfield aircraft is repaired
It is multiple.
The above, the only specific embodiment of the application, but the protection scope of the application is not limited thereto, it is any
Within the technical scope of the present application, any changes or substitutions that can be easily thought of by those familiar with the art, all answers
Cover within the scope of protection of this application.Therefore, the protection scope of the application should be with the scope of protection of the claims
It is quasi-.
Claims (3)
1. a kind of aircaft configuration covering injury repair device is used for by dormant bolt (3) and self-locking nut (4) and profile
(2) the damage covering (1) being attached is repaired, which is characterized in that the aircaft configuration covering injury repair device includes:
Stiffening plate (7) is laid on the one side backwards to the profile (2) of the covering (1)；
It makes by oneself washer (6), is arranged in the taper nail hole formed on the covering (1), and outer contour shape and the cone-shaped nail
Hole shape is adapted；
Lengthened bolt (8), sequentially pass through the stiffening plate (7), self-control washer (6) and profile (2) afterwards with self-locking nut (4) spiral shell
Line connection.
2. aircaft configuration covering injury repair device according to claim 1, which is characterized in that be located at the stiffening plate
(7) outer surface of Lengthened bolt (8) and the self-locking nut (4) being located on the outside of the profile (2) on the outside of is provided with anti-corrosion painting
Layer (9).
3. aircaft configuration covering injury repair device according to claim 1, which is characterized in that the corrosion-inhibiting coating (9)
For TB06-9 priming paint.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811437132.5A CN109625312A (en) | 2018-11-28 | 2018-11-28 | Aircaft configuration covering injury repair device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811437132.5A CN109625312A (en) | 2018-11-28 | 2018-11-28 | Aircaft configuration covering injury repair device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109625312A true CN109625312A (en) | 2019-04-16 |
Family
ID=66069872
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811437132.5A Pending CN109625312A (en) | 2018-11-28 | 2018-11-28 | Aircaft configuration covering injury repair device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109625312A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112693622A (en) * | 2020-12-29 | 2021-04-23 | 中国航空工业集团公司西安飞机设计研究所 | Method for repairing airplane wing surface by pulling out nails and loosening |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101561459A (en) * | 2009-06-04 | 2009-10-21 | 中国航空工业集团公司西安飞机设计研究所 | Damage-tolerance testing method for lower wall panel of airplane outboard wing |
| CN203265702U (en) * | 2013-05-20 | 2013-11-06 | 山东太古飞机工程有限公司 | Skin repairing gasket batch production tool for Boeing 737 series aircrafts |
| CN103950553A (en) * | 2014-04-25 | 2014-07-30 | 哈尔滨飞机工业集团有限责任公司 | Method for repairing countersunk crossed nest |
| CN106628240A (en) * | 2016-12-14 | 2017-05-10 | 中航通飞研究院有限公司 | Repairing method of airplane composite material foam interlayer structure |
| CN207292476U (en) * | 2017-08-25 | 2018-05-01 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of reinforced structure for being used to repair high power-driven plane horizontal tail siding |
-
2018
- 2018-11-28 CN CN201811437132.5A patent/CN109625312A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101561459A (en) * | 2009-06-04 | 2009-10-21 | 中国航空工业集团公司西安飞机设计研究所 | Damage-tolerance testing method for lower wall panel of airplane outboard wing |
| CN203265702U (en) * | 2013-05-20 | 2013-11-06 | 山东太古飞机工程有限公司 | Skin repairing gasket batch production tool for Boeing 737 series aircrafts |
| CN103950553A (en) * | 2014-04-25 | 2014-07-30 | 哈尔滨飞机工业集团有限责任公司 | Method for repairing countersunk crossed nest |
| CN106628240A (en) * | 2016-12-14 | 2017-05-10 | 中航通飞研究院有限公司 | Repairing method of airplane composite material foam interlayer structure |
| CN207292476U (en) * | 2017-08-25 | 2018-05-01 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of reinforced structure for being used to repair high power-driven plane horizontal tail siding |
Non-Patent Citations (1)
| Title |
|---|
| 王国庆: "民用飞机蒙皮损伤修理研究", 《科技视界》 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112693622A (en) * | 2020-12-29 | 2021-04-23 | 中国航空工业集团公司西安飞机设计研究所 | Method for repairing airplane wing surface by pulling out nails and loosening |
| CN112693622B (en) * | 2020-12-29 | 2023-09-05 | 中国航空工业集团公司西安飞机设计研究所 | Method for repairing aircraft wing surface screw-pulling loosening |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20190416 |
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| RJ01 | Rejection of invention patent application after publication |