CN202518458U - Stiffened wallboard fatigue test transition section - Google Patents
Stiffened wallboard fatigue test transition section Download PDFInfo
- Publication number
- CN202518458U CN202518458U CN2011201383120U CN201120138312U CN202518458U CN 202518458 U CN202518458 U CN 202518458U CN 2011201383120 U CN2011201383120 U CN 2011201383120U CN 201120138312 U CN201120138312 U CN 201120138312U CN 202518458 U CN202518458 U CN 202518458U
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- band plate
- transition section
- band board
- wedge
- fatigue test
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- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The utility model discloses a stiffened wallboard fatigue test transition section which belongs to the technical field of fatigue tests and relates to a stiffened wallboard fatigue test technology. The stiffened wallboard fatigue test transition section consists of a wedge-shaped band board (1), a reinforcing band board (2), a reinforcing band board (3), a skin (4) on a test piece and a long truss (5), wherein the wedge-shaped band board (1) is embedded between the long truss (5) and the skin (4); and the upper surface of an equal-thickness end of the wedge-shaped band board (1) and the lower surface of the skin (4) are respectively clamped by the reinforcing band board (2) and the reinforcing band board (3). Through the wedge-shaped band board embedded in the transition section, transfer optimization design is carried out on a transition area, so that the even loading of the skin and the long truss is realized and the eccentricity of loading is directly eliminated; and at the same time, the transition section is fully reinforced by the wedge-shaped band board and the reinforcing boards, so that the problem that the transition section cracks due to large stress gradient is avoided. The transition section can be applied to various wall plate fatigue tests, is easy for implementation and has generality.
Description
Technical field
The utility model belongs to the fatigue test technical field, relates to a kind of reinforcement wallboard fatigue test technology.
Background technology
Fuselage wallboard level fatigue test is an important Test item in the airframe development, and wherein the design of test article transition phase is the necessary condition that warranty test carries out smoothly.Existing testing technique general end covering 4 local delamination that adopt when the test article transition phase designs are thickeied; Perhaps band plate 2 and the mode of strengthening band plate 3 are strengthened in local increase on end covering 4; This transition phase design can not solve the long purlin of fuselage, covering stand under load problem of non-uniform, and the off-centre of loading also needs to adjust through jig Design in addition in test.Test results shows, the stress on the free edge strip in long purlin, same cross section is merely the about 1/3 of covering stress, causes the distortion of test results; Present according to statistics similar test has 90% owing to the transition phase early damage, and causing the test progress to be delayed with experimentation cost increases.
The utility model content
The purpose of the utility model is: a kind of new fuselage wallboard test article transition phase structure is provided; It can overcome the drawback of prior art, transition region has been carried out passing carried optimal design, makes the test article covering even with long purlin stand under load; Eliminate loading off-centre, prevent transition region destruction ahead of time.
The technical scheme of the utility model is: a kind of reinforcement wallboard fatigue test transition phase; It is characterized in that; By wedge shape band plate 1, reinforcement band plate 2, reinforcement band plate 3; And the covering on the test article 4, long purlin 5 form, and between long purlin 5 and covering 4, embeds wedge shape band plate 1, at wedge shape band plate 1 equal thickness, one end upper surface and covering 4 lower surfaces respectively with strengthening band plate 2, strengthening band plate 3 clampings.
Said reinforcement band plate 2, the connection mode of strengthening band plate 3 and wedge shape band plate 1 and covering 4 adopt bolted connection.
The beneficial effect of the utility model is: through the wedge shape band plate that embeds in the transition phase design, transition region has been carried out passing a year optimal design, realized that covering is even with long purlin stand under load, directly eliminated the off-centre that loads; Utilize wedge shape band plate and brace panel that transition phase is fully strengthened simultaneously, avoided transition phase to have the big and problem of crack initiation of stress gradient.This transition phase design can be used for various wallboard class fatigue tests, and is easy to implement, has commonality.
Description of drawings:
Fig. 1: the structural front view of reinforcement wallboard test article transition phase
Fig. 2: the structure birds-eye view of reinforcement wallboard test article transition phase
1-wedge shape band plate
2-reinforcement band plate
3-reinforcement band plate
4-covering
5-long purlin
6-bolt hole
The specific embodiment
A kind of reinforcement wallboard fatigue test test article transition phase; It is characterized in that; By wedge shape band plate 1, reinforcement band plate 2, reinforcement band plate 3; And the covering on the test article 4, long purlin 5 form, and between long purlin 5 and covering 4, embeds wedge shape band plate 1, at wedge shape band plate 1 equal thickness, one end upper surface and covering 4 lower surfaces respectively with strengthening band plate 2, strengthening band plate 3 clampings.
Said reinforcement band plate 2, strengthen band plate 3 and wedge shape band plate 1 and covering 4
Claims (2)
1. reinforcement wallboard fatigue test transition phase; It is characterized in that; By wedge shape band plate (1), reinforcement band plate (2), reinforcement band plate (3); And the covering on the test article (4), long purlin (5) form, and between long purlin (5) and covering (4), embeds wedge shape band plate (1), at wedge shape band plate (1) equal thickness one end upper surface and covering (4) lower surface respectively with strengthening band plate (2), reinforcement band plate (3) clamping.
2. reinforcement wallboard fatigue test transition phase according to claim 1 is characterized in that, said reinforcement band plate (2), reinforcement band plate (3) adopt bolted connection with the connection mode of wedge shape band plate (1) and covering (4).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011201383120U CN202518458U (en) | 2011-05-04 | 2011-05-04 | Stiffened wallboard fatigue test transition section |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011201383120U CN202518458U (en) | 2011-05-04 | 2011-05-04 | Stiffened wallboard fatigue test transition section |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202518458U true CN202518458U (en) | 2012-11-07 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011201383120U Expired - Lifetime CN202518458U (en) | 2011-05-04 | 2011-05-04 | Stiffened wallboard fatigue test transition section |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202518458U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104002989A (en) * | 2014-05-08 | 2014-08-27 | 中航飞机股份有限公司西安飞机分公司 | Method for preventing installation curved surface of organic glass observation window of airplane from cracking |
| CN106202693A (en) * | 2016-07-06 | 2016-12-07 | 厦门大学 | A kind of Material Stiffened Panel structure anti-vibration fatigue optimization method based on parametric modeling |
| CN108163226A (en) * | 2017-11-29 | 2018-06-15 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft nose landing gear outer barrel strut connector launch fatigue test method |
| CN108163225A (en) * | 2017-11-29 | 2018-06-15 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft nose landing gear outer barrel suspension joint launch fatigue test method |
| CN110654569A (en) * | 2019-09-29 | 2020-01-07 | 中国直升机设计研究所 | Load simulation simplification method for helicopter tail section fatigue test |
-
2011
- 2011-05-04 CN CN2011201383120U patent/CN202518458U/en not_active Expired - Lifetime
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104002989A (en) * | 2014-05-08 | 2014-08-27 | 中航飞机股份有限公司西安飞机分公司 | Method for preventing installation curved surface of organic glass observation window of airplane from cracking |
| CN106202693A (en) * | 2016-07-06 | 2016-12-07 | 厦门大学 | A kind of Material Stiffened Panel structure anti-vibration fatigue optimization method based on parametric modeling |
| CN106202693B (en) * | 2016-07-06 | 2019-03-22 | 厦门大学 | A kind of Material Stiffened Panel structure anti-vibration fatigue optimization method based on parametric modeling |
| CN108163226A (en) * | 2017-11-29 | 2018-06-15 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft nose landing gear outer barrel strut connector launch fatigue test method |
| CN108163225A (en) * | 2017-11-29 | 2018-06-15 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of aircraft nose landing gear outer barrel suspension joint launch fatigue test method |
| CN110654569A (en) * | 2019-09-29 | 2020-01-07 | 中国直升机设计研究所 | Load simulation simplification method for helicopter tail section fatigue test |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20121107 |