CN105966596B - A kind of Varying-thickness thin-walled skin structure - Google Patents
A kind of Varying-thickness thin-walled skin structure Download PDFInfo
- Publication number
- CN105966596B CN105966596B CN201610418459.2A CN201610418459A CN105966596B CN 105966596 B CN105966596 B CN 105966596B CN 201610418459 A CN201610418459 A CN 201610418459A CN 105966596 B CN105966596 B CN 105966596B
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- CN
- China
- Prior art keywords
- covering
- frame
- stringer
- hollow out
- out group
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- 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 kind of Varying-thickness thin-walled skin structures, it includes left stringer, front frame, right stringer, covering and after-frame, multiple rows of hollow out group is provided with inside covering, every row's hollow out group has multiple lightening holes, criss-cross rib is formed between adjacent hollow out group and between adjacent lightening hole, covering front and rear sides are connect with front frame and after-frame respectively, are connect respectively with left stringer and right stringer at left and right sides of covering.The advantages of by combining chemistry milling structure and frame-covering structure, it is thin to be combined into an inner skins wall, and surrounding overlapping regions meets the integral structure of structural functionality, construction weight is effectively reduced under conditions of guaranteeing covering bearing capacity；Since covering is integrated chemical conversion shape, the cost of tooling manufacture is eliminated, assembly period is shortened.
Description
Technical field
The present invention relates to a kind of Varying-thickness thin-walled skin structures, and in particular to a kind of Varying-thickness thin-walled skin knot of aircraft
Structure.
Background technique
With the development of aircraft, product requires small in size, lightweight construction while meeting index.Covering is flight
Important primary structure member in device structure, it is born in the form of shearing flow and Transfer of Shear and torque, and covering organizes wall-forming together with stringer
Plate bears axle power caused by moment of flexure.
For metal skin, other than chemistry milling Varying-thickness covering, general each block of plate is equal thickness, usually
Covering is manufactured respectively with stringer, then is linked together by forms such as rivetings, causes assembly period longer, and increase standard
The weight of part.
Original structure type, is frame, beam+covering structure, the uniform covering of thickness change and thickness change is big
Frame manufactures respectively, reuses the integral structure of electron beam welding, needs to guarantee by tooling assembly precision, and assembly/weldering
It is long, at high cost to connect the period.
Accordingly, it is desirable to provide a kind of new technical solution solves the above problems.
Summary of the invention
The technical problem to be solved by the invention is to provide a kind of Varying-thickness thin-walled skin structures.Stressed-skin construction is carried out one
Bodyization design, improves bearing capacity, and avoid assembling using tooling.
To solve technical problem of the invention, the technical solution adopted by the present invention is that:
A kind of Varying-thickness thin-walled skin structure, it includes left stringer, front frame, right stringer, covering and after-frame, in the covering
Portion is provided with multiple rows of hollow out group, and every row's hollow out group has multiple lightening holes, shape between adjacent hollow out group and between adjacent lightening hole
At there is criss-cross rib, the covering front and rear sides are connect with front frame and after-frame respectively, at left and right sides of the covering respectively
It is connect with left stringer and right stringer.
Beneficial effects of the present invention: by being combined into one in conjunction with the advantages of chemistry milling structure and frame-covering structure
Inner skins wall is thin, and surrounding overlapping regions meets the integral structure of structural functionality, is guaranteeing covering bearing capacity
Under the conditions of construction weight is effectively reduced；Since covering is integrated chemical conversion shape, the cost of tooling manufacture is eliminated, dress is shortened
With the period.
Detailed description of the invention
Fig. 1 is the structural diagram of the present invention.
1. left stringer, 2. front frames, 3. right stringers, 4. coverings, 41. lightening holes, 42. ribs, 5. after-frames, 6, outside frame
Side, 7, scuncheon.
Specific embodiment
The present invention will be further explained below with reference to the attached drawings and specific examples.Following embodiment is merely to illustrate this hair
It is bright, it is 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 invention, it include left stringer 1, front frame 2, right stringer 3,
Covering 4 and after-frame 5, are provided with multiple rows of hollow out group inside covering 4, and every row's hollow out group has multiple lightening holes 41, adjacent hollow out group it
Between and adjacent lightening hole 41 between be formed with criss-cross rib 42,4 front and rear sides of covering respectively with front frame 2 and after-frame 5
Connection, 4 left and right sides of covering are connect with left stringer 1 and right stringer 3 respectively.
Left stringer 1 and right stringer 3 are relatively thick, can transmit axial force and as join domain, front frame 2 and after-frame 5
It is together main force support structure, and guarantees aerodynamic configuration together with covering 4.Typical skin thickness is thin, and inside passes through criss-cross
Rib maintain shape and transmit load, structural strength, good rigidity, and light-weight；Frame (including front frame 2 and after-frame 5) basis
Using needs, 6 combine guarantee aerodynamic configuration with covering on the outside of frame, and scuncheon 7 is bonded with main force support structure, covering 4 it is non-
Hollow out loss of weight inside connecting portion.Since thickness change is big, the one integral piece such as general chemistry milling forming technology can not all be produced, and be passed through
Using Quick-forming molding+hot investment casting forming technique, the forming of Varying-thickness thin-walled skin structure may be implemented.
In conjunction with the characteristics of chemistry milling covering and metal plate riveting covering, while guaranteeing structural strength, rigidity, pass through integration
Design, frame, beam and covering is combined as a whole, since covering internal load is distributed to surrounding by the reinforcing rib of covering inner surface
Frame in, therefore covering can be thinned to 1 millimeter or less.Surrounding frame can thicken according to actual needs, bear aerodynamic loading simultaneously
As join domain.
Claims (1)
1. a kind of Varying-thickness thin-walled skin structure, it is characterised in that: it includes left stringer, front frame, right stringer, covering and after-frame,
It is provided with multiple rows of hollow out group inside the covering, every row's hollow out group has multiple lightening holes, between adjacent hollow out group and adjacent subtracts
Criss-cross rib is formed between repeated hole, the covering front and rear sides are connect with front frame and after-frame respectively, and the covering is left
Right two sides are connect with left stringer and right stringer respectively；Front frame is main force support structure together with after-frame, and frame includes front frame and after-frame,
It is combined on the outside of frame with covering, scuncheon is bonded with main force support structure.
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 CN105966596A (en) | 2016-09-28 |
| CN105966596B true 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 |
|---|---|
| CN (1) | CN105966596B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2894859A1 (en) * | 2005-12-16 | 2007-06-22 | Alcan Rhenalu Sa | SOLDER SAIL LONGERON AND METHOD OF MAKING SAME |
| US7766277B2 (en) * | 2006-01-19 | 2010-08-03 | The Boeing Company | Deformable forward pressure bulkhead for an aircraft |
| US7997529B2 (en) * | 2006-01-19 | 2011-08-16 | The Boeing Company | Compliant panel for aircraft |
| CN101214429B (en) * | 2007-12-28 | 2010-10-20 | 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 |
| 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 |
| CN105035359B (en) * | 2015-07-28 | 2017-03-08 | 中国运载火箭技术研究院 | A kind of degressive-rate composite material integral formed rudder face structure and machining method |
-
2016
- 2016-06-13 CN CN201610418459.2A patent/CN105966596B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN105966596A (en) | 2016-09-28 |
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