CN101665152B - Quick detachable combined cover cap capable of bearing stress - Google Patents
Quick detachable combined cover cap capable of bearing stress Download PDFInfo
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- CN101665152B CN101665152B CN2009101861276A CN200910186127A CN101665152B CN 101665152 B CN101665152 B CN 101665152B CN 2009101861276 A CN2009101861276 A CN 2009101861276A CN 200910186127 A CN200910186127 A CN 200910186127A CN 101665152 B CN101665152 B CN 101665152B
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- cover cap
- flap
- normal stress
- quick
- quick detachable
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Abstract
The invention relates to the improvement of an aircraft cover cap, in particular to a quick detachable combined cover cap capable of bearing stress. The cover cap comprises a positive stress bearing cover cap and a quick detachable cover cap, and is characterized in that the quick detachable cover cap is installed at the opening in the positive stress bearing cover cap; the shape of the quick detachable cover cap is matched with that of the opening installed in the positive stress bearing cover cap, and the quick detachable cover cap is connected with the positive stress bearing cover cap through a hinge and a bearing lock at the opening of the positive stress bearing cover cap so as to cover the opening in the positive stress bearing cover cap. The adoption of the combined cover cap form of the positive stress bearing cover cap and the quick detachable cover cap guarantees the structural strength need and the maintainability need of the aircraft and facilitates the installation and maintenance of the aircraft, without affecting the structural weight of the aircraft.
Description
Technical field
The present invention relates to the improvement of aircraft port cover structure, particularly a kind of quick detachable combined cover cap capable of bearing stress.
Background technology
On the aircraft physical construction owing to install and safeguard when needing the big flap of design quick-release non-bearing flap is arranged usually and hold two kinds of normal stress flaps.Usually select quick-release non-bearing flap for use in the open area by actual conditions at the equipment region that needs are often safeguarded, in order not influence power transmission, usually can only be by actual conditions with holding the reservation of normal stress member and strengthening a mouthful mount structure in the open area, so just, can influence path, and structural weight is increased; Equipment region needing periodical maintenance but often not overhauling is designed to flap to hold the normal stress flap usually, when safeguarding, needs the whole normal stress flap that holds is taken off, and needs the time longer, and influence is maintainable.When in needing the periodical maintenance equipment region equipment that will often overhaul being arranged simultaneously, adopt usually and hold normal stress flap form, so each maintenance all must be opened the whole normal stress flap that holds, the lengthening repair time, increase work capacity when overhauling, and influence the maintainability of equipment.
Summary of the invention
The objective of the invention is to, install on physical construction and safeguard when needing the big flap of design, flap is designed to hold the combination flap of normal stress flap and quick-release flap, so neither influence power transmission, also guaranteed path, the while can be satisfied maintainable requirement.
Technical scheme of the present invention is, a kind of quick detachable combined cover cap capable of bearing stress, by holding the normal stress flap and the quick-release flap is formed, holding normal stress flap outer is connected with aircraft skin with bolt by plate nut, hold and be provided with rectangle, circle, square or oval-shaped opening in the normal stress flap, it is characterized in that, the opening part that holds in the normal stress flap is equipped with the quick-release flap, the profile of quick-release flap with hold the opening shape that is provided with in the normal stress flap and match, and by hinge and bearing lock with hold the normal stress flap and be connected.
Advantage of the present invention is that the combination flap form that normal stress flap and quick-release flap are held in employing needs aircaft configuration intensity and maintainability need be guaranteed, and has made things convenient for aircraft in installation and maintenance, does not also influence the structural weight of aircraft.
Description of drawings
Fig. 1 is a structural representation of the present invention.
Fig. 2 is that the A-A of Fig. 1 is to cutaway view.
The specific embodiment
The invention will be further described below in conjunction with accompanying drawing, referring to accompanying drawing 1,2, a kind of quick detachable combined cover cap capable of bearing stress, by holding normal stress flap 1 and quick-release flap 2 is formed, holding normal stress flap 1 outer is connected with aircraft skin with bolt 6 by plate nut 3, hold in the normal stress flap 1 and be provided with rectangle, circular, square or oval-shaped opening, it is characterized in that, the opening part that holds in the normal stress flap 1 is equipped with quick-release flap 2, the profile of quick-release flap 2 with hold the opening shape that is provided with in the normal stress flap 1 and match, and by hinge 5 and bearing lock 4 with hold normal stress flap 1 and be connected, quick-release flap 2 is covered holds normal stress flap 1 inner opening.
Quick detachable combined cover cap capable of bearing stress is located at airframe, need install and maintenance place at airframe, be designed to hold the combination flap of normal stress flap 1 and quick-release flap 2, holding normal stress flap 1 outer is connected with aircraft skin with bolt 6 by plate nut 3, the opening part that holds in the normal stress flap 1 is equipped with quick-release flap 2, hinge 5 and bearing lock 4 be riveted on respectively the interior edge of holding normal stress flap 1 and with quick-release flap 2 cooresponding outers on, quick-release flap 2 is covered holds normal stress flap 1 inner opening.Hold normal stress flap 1 and can be system and install path is provided, flap 2 can be system maintenance path is provided.
The present invention is designed to hold the combination flap of normal stress flap and quick-release flap with the airframe flap, has made things convenient for aircraft in installation and maintenance, does not also influence the structural weight of aircraft.
Claims (1)
1. quick detachable combined cover cap capable of bearing stress, by holding normal stress flap [1] and quick-release flap [2] is formed, holding normal stress flap [1] outer is connected with aircraft skin with bolt [6] by plate nut [3], hold and be provided with rectangle, circle, square or oval-shaped opening in the normal stress flap [1], it is characterized in that, the opening part that holds in the normal stress flap [1] is equipped with quick-release flap [2], the profile of quick-release flap [2] with hold the opening shape that is provided with in the normal stress flap [1] and match, and by hinge [5] and bearing lock [4] with hold normal stress flap [1] and be connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009101861276A CN101665152B (en) | 2009-09-29 | 2009-09-29 | Quick detachable combined cover cap capable of bearing stress |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2009101861276A CN101665152B (en) | 2009-09-29 | 2009-09-29 | Quick detachable combined cover cap capable of bearing stress |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101665152A CN101665152A (en) | 2010-03-10 |
| CN101665152B true CN101665152B (en) | 2011-06-29 |
Family
ID=41801971
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2009101861276A Active CN101665152B (en) | 2009-09-29 | 2009-09-29 | Quick detachable combined cover cap capable of bearing stress |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101665152B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104477369A (en) * | 2014-11-27 | 2015-04-01 | 江西洪都航空工业集团有限责任公司 | Novel folding wall plate structure |
| CN105620558A (en) * | 2015-12-18 | 2016-06-01 | 重庆长安工业(集团)有限责任公司 | Cabin door quick opening mechanism for armored vehicle |
| CN106184702A (en) * | 2016-09-23 | 2016-12-07 | 江西洪都航空工业集团有限责任公司 | Waterproof quick-release combination lid |
| CN107054617A (en) * | 2016-12-26 | 2017-08-18 | 中国航空工业集团公司西安飞机设计研究所 | A kind of aircraft maintenance lid |
| CN109606615A (en) * | 2018-11-07 | 2019-04-12 | 中国航空工业集团公司西安飞机设计研究所 | A kind of compound lid of aircraft |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0563540A1 (en) * | 1992-03-28 | 1993-10-06 | DaimlerChrysler Aerospace Airbus Gesellschaft mit beschränkter Haftung | Protective plate for a door threshold |
| DE102006040383A1 (en) * | 2006-08-29 | 2008-03-13 | Airbus Deutschland Gmbh | Deflector trap for rainwater or de-icing fluid retracts into recess above fuselage entry door |
| CN100420607C (en) * | 2007-04-23 | 2008-09-24 | 江西洪都航空工业集团有限责任公司 | Airplane fuselage frame |
| CN101519119A (en) * | 2009-03-13 | 2009-09-02 | 贵州航天精工制造有限公司 | Fast-disassembly method of aeroplane access cover and bearing lock |
| CN201530472U (en) * | 2009-09-29 | 2010-07-21 | 江西洪都航空工业集团有限责任公司 | Force bearing rapid combined mouth cover |
-
2009
- 2009-09-29 CN CN2009101861276A patent/CN101665152B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0563540A1 (en) * | 1992-03-28 | 1993-10-06 | DaimlerChrysler Aerospace Airbus Gesellschaft mit beschränkter Haftung | Protective plate for a door threshold |
| DE102006040383A1 (en) * | 2006-08-29 | 2008-03-13 | Airbus Deutschland Gmbh | Deflector trap for rainwater or de-icing fluid retracts into recess above fuselage entry door |
| CN100420607C (en) * | 2007-04-23 | 2008-09-24 | 江西洪都航空工业集团有限责任公司 | Airplane fuselage frame |
| CN101519119A (en) * | 2009-03-13 | 2009-09-02 | 贵州航天精工制造有限公司 | Fast-disassembly method of aeroplane access cover and bearing lock |
| CN201530472U (en) * | 2009-09-29 | 2010-07-21 | 江西洪都航空工业集团有限责任公司 | Force bearing rapid combined mouth cover |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101665152A (en) | 2010-03-10 |
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