CN105966596A - Thickness-variable thin-wall skin structure - Google Patents
Thickness-variable thin-wall skin structure Download PDFInfo
- Publication number
- CN105966596A CN105966596A CN201610418459.2A CN201610418459A CN105966596A CN 105966596 A CN105966596 A CN 105966596A CN 201610418459 A CN201610418459 A CN 201610418459A CN 105966596 A CN105966596 A CN 105966596A
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- CN
- China
- Prior art keywords
- skin
- stringer
- frame
- eyelid covering
- thickness
- 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
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
Abstract
The invention discloses a thickness-variable thin-wall skin structure. The structure comprises a left stringer, a front frame, a right stringer, a skin and a rear frame; multiple rows of hollowed-out groups are formed in the skin, each row of the hollowed-out groups are provided with multiple lightening holes, multiple crisscrossed fillets are formed between the adjacent hollowed-out groups and between the adjacent lightening holes, the front side and the rear side of the skin are connected with the front frame and the rear frame respectively, and the left side and the right side of the skin are connected with the left stringer and the right stringer respectively. By combining the advantages of a chemical milling structure and a skin skeleton structure, an integrated structure of which the inner skin wall is thin and the peripheral overlapping area meets the structural functionality is combined, and the structural weight is effectively reduced under the condition that the bearing capacity of the skin is guaranteed; due to the fact that the skin is integrally formed, the tool manufacturing cost is eliminated, and the assembly cycle is shortened.
Description
Technical field
The present invention relates to a kind of Varying-thickness thin-walled skin structure, be specifically related to the Varying-thickness thin-walled skin structure of a kind of aircraft.
Background technology
Along with the development of aircraft, product wants while meeting index that cube is little, lightweight construction.Eyelid covering is the important primary structure member in Flight Vehicle Structure, and it bears and Transfer of Shear and moment of torsion with shearing flow form, and eyelid covering forms wallboard together with stringer and bears the axle power that moment of flexure causes.
For metal skin, in addition to chemistry milling Varying-thickness eyelid covering, the most each block of sheet material is all equal thickness, is generally manufactured respectively with stringer by eyelid covering, then is linked together by forms such as rivetings, causes assembly period longer, and adds the weight of standard component.
Original version, for frame, the structure of beam+eyelid covering, thickness is changed uniform eyelid covering and manufactures respectively with thickness change frame greatly, re-use the structure that electron beam is integrally welded, need to rely on frock to ensure assembly precision, and length assembling/welding interval, cost are high.
Accordingly, it is desirable to provide a kind of new technical scheme solves the problems referred to above.
Summary of the invention
The technical issues that need to address of the present invention are to provide a kind of Varying-thickness thin-walled skin structure.Stressed-skin construction is carried out integrated design, improves bearing capacity, and avoid using frock assembling.
For solving the technical problem of the present invention, the technical solution used in the present invention is:
A kind of Varying-thickness thin-walled skin structure, it includes left stringer, front frame, right stringer, eyelid covering and after-frame, multiple rows of hollow out group is had inside described eyelid covering, often row's hollow out group has multiple lightening hole, it is formed with crisscross rib between adjacent hollow out group and between adjacent lightening hole, before and after described eyelid covering, both sides are connected with front frame and after-frame respectively, and the described eyelid covering left and right sides is connected with left stringer and right stringer respectively.
Beneficial effects of the present invention: by the advantage combining chemistry milling structure and frame-covering structure, it is combined into an inner skins wall thin, and around overlapping regions meets the integral structure of structural functionality, under conditions of ensureing eyelid covering bearing capacity, effectively reduce construction weight；Due to the integrated shaping of eyelid covering, therefore eliminate the cost that frock manufactures, shorten assembly period.
Accompanying drawing explanation
Fig. 1 is the structural representation of the present invention.
The most left stringer, 2. before frame, the rightest stringer, 4. eyelid covering, 41. lightening holes, 42. ribs, 5. after-frame, 6, outside frame, 7, scuncheon.
Detailed description of the invention
The invention will be further described with specific embodiment below in conjunction with the accompanying drawings.Following example are merely to illustrate the present invention, are not limited to protection scope of the present invention.
As shown in Figure 1, a kind of Varying-thickness thin-walled skin structure of the present invention, it includes left stringer 1, front frame 2, right stringer 3, eyelid covering 4 and after-frame 5, eyelid covering 4 is internal has multiple rows of hollow out group, often row's hollow out group has multiple lightening hole 41, being formed with crisscross rib 42 between adjacent hollow out group and between adjacent lightening hole 41, before and after eyelid covering 4, both sides are connected with front frame 2 and after-frame 5 respectively, and eyelid covering 4 left and right sides is connected with left stringer 1 and right stringer 3 respectively.
Left stringer 1 is relatively thick with right stringer 3, can transmit axial force, again can be as join domain, and front frame 2 is all main force support structure with after-frame 5 one, and together ensures aerodynamic configuration with eyelid covering 4.Typical case's skin thickness is thin, and inside maintains profile by crisscross rib and transmits load, structural strength, good rigidity, and lightweight；Frame (comprising front frame 2 and after-frame 5) is according to using needs, and outside frame, with eyelid covering combination, 6 ensure that aerodynamic configuration, scuncheon 7 are fitted with main force support structure, the disconnected part interior hollow out loss of weight of eyelid covering 4.Owing to the one integral piece forming technologies such as thickness changes greatly, general chemistry milling all cannot be made, by using quick shaping molding+hot investment casting forming technique, it is possible to achieve the shaping of Varying-thickness thin-walled skin structure.
Feature in conjunction with chemistry milling eyelid covering Yu metal plate riveting eyelid covering, while ensureing structural strength, rigidity, pass through integrated design, frame, beam are combined as a whole with eyelid covering, owing to eyelid covering internal load is distributed in the frame of surrounding by the reinforcement of eyelid covering inner surface, therefore eyelid covering can be thinned to less than 1 millimeter.Around frame can thicken according to actual needs, bears aerodynamic loading and as join domain.
Claims (1)
1. a Varying-thickness thin-walled skin structure, it is characterized in that: it includes left stringer, front frame, right stringer, eyelid covering and after-frame, multiple rows of hollow out group is had inside described eyelid covering, often row's hollow out group has multiple lightening hole, it is formed with crisscross rib between adjacent hollow out group and between adjacent lightening hole, before and after described eyelid covering, both sides are connected with front frame and after-frame respectively, and the described eyelid covering left and right sides is connected with left stringer and right stringer respectively.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610418459.2A CN105966596B (en) | 2016-06-13 | 2016-06-13 | A kind of Varying-thickness thin-walled skin structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610418459.2A CN105966596B (en) | 2016-06-13 | 2016-06-13 | A kind of Varying-thickness thin-walled skin structure |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105966596A true CN105966596A (en) | 2016-09-28 |
| CN105966596B CN105966596B (en) | 2019-03-29 |
Family
ID=57020993
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610418459.2A Active CN105966596B (en) | 2016-06-13 | 2016-06-13 | A kind of Varying-thickness thin-walled skin structure |
Country Status (1)
| Country | Link |
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| CN (1) | CN105966596B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107023419A (en) * | 2017-05-03 | 2017-08-08 | 湖北航天技术研究院总体设计所 | A kind of Solid Rocket Motor combustion chamber housing lightweight joint |
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| US20070164152A1 (en) * | 2006-01-19 | 2007-07-19 | The Boeing Company | Deformable forward pressure bulkhead for an aircraft |
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| US20080265094A1 (en) * | 2005-12-16 | 2008-10-30 | Airbus Uk Limited | Structural Element and Method of Manufacture |
| CN101342941A (en) * | 2008-08-21 | 2009-01-14 | 马献林 | Disposal solidifying and molding method for fuselage ring and outer panel skin |
| CN101596933A (en) * | 2009-07-06 | 2009-12-09 | 北京航空航天大学 | A kind of based on crash-worthiness design-calculated civil aircraft fuselage bottom structure |
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| CN201745741U (en) * | 2010-07-20 | 2011-02-16 | 中国航空工业集团公司西安飞机设计研究所 | Overall thin-walled structure of composite machine body |
| CN102407936A (en) * | 2011-09-06 | 2012-04-11 | 苏氏工业科学技术（北京）有限公司 | Integral keel and skin composite self-propelled equipment capsule structure |
| CN103770929A (en) * | 2014-02-11 | 2014-05-07 | 中航飞机股份有限公司西安飞机分公司 | Integral aircraft panel structure with reinforcing grid ribs |
| CN105035359A (en) * | 2015-07-28 | 2015-11-11 | 中国运载火箭技术研究院 | Composite material integrated control surface structure with progressive decrease in rigidity and processing method thereof |
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2016
- 2016-06-13 CN CN201610418459.2A patent/CN105966596B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20080265094A1 (en) * | 2005-12-16 | 2008-10-30 | Airbus Uk Limited | Structural Element and Method of Manufacture |
| US20070164152A1 (en) * | 2006-01-19 | 2007-07-19 | The Boeing Company | Deformable forward pressure bulkhead for an aircraft |
| CN101687540A (en) * | 2007-03-06 | 2010-03-31 | 波音公司 | The compliant panel that is used for aircraft |
| CN101214429A (en) * | 2007-12-28 | 2008-07-09 | 卢铭津 | Aircraft casing and shaping technique thereof |
| CN101342941A (en) * | 2008-08-21 | 2009-01-14 | 马献林 | Disposal solidifying and molding method for fuselage ring and outer panel skin |
| CN101596933A (en) * | 2009-07-06 | 2009-12-09 | 北京航空航天大学 | A kind of based on crash-worthiness design-calculated civil aircraft fuselage bottom structure |
| CN201745741U (en) * | 2010-07-20 | 2011-02-16 | 中国航空工业集团公司西安飞机设计研究所 | Overall thin-walled structure of composite machine body |
| CN102407936A (en) * | 2011-09-06 | 2012-04-11 | 苏氏工业科学技术（北京）有限公司 | Integral keel and skin composite self-propelled equipment capsule structure |
| CN103770929A (en) * | 2014-02-11 | 2014-05-07 | 中航飞机股份有限公司西安飞机分公司 | Integral aircraft panel structure with reinforcing grid ribs |
| CN105035359A (en) * | 2015-07-28 | 2015-11-11 | 中国运载火箭技术研究院 | Composite material integrated control surface structure with progressive decrease in rigidity and processing method thereof |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107023419A (en) * | 2017-05-03 | 2017-08-08 | 湖北航天技术研究院总体设计所 | A kind of Solid Rocket Motor combustion chamber housing lightweight joint |
| CN107023419B (en) * | 2017-05-03 | 2019-05-03 | 湖北航天技术研究院总体设计所 | A kind of Solid Rocket Motor combustion chamber shell lightweight connector |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105966596B (en) | 2019-03-29 |
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