CN209513479U - A kind of shear fatigue test part - Google Patents
A kind of shear fatigue test part Download PDFInfo
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- CN209513479U CN209513479U CN201822110300.1U CN201822110300U CN209513479U CN 209513479 U CN209513479 U CN 209513479U CN 201822110300 U CN201822110300 U CN 201822110300U CN 209513479 U CN209513479 U CN 209513479U
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Abstract
The utility model category aircraft fatigue strength test field, it is related to a kind of shear fatigue test part, the testpieces includes testpieces examination section (1-1), stringer and covering linkage section (1-2) and testpieces changeover portion (1-3), gripping section (1-4) is the extended segment of testpieces changeover portion (1-3), it is connected when for testing with fixture, the thickness of testpieces examination section (1-1) is identical as the actual (real) thickness of aircraft real structure；Stringer is connect by rivet with examination section (1-1) with covering linkage section (1-2), gripping section (1-4) to examination section (1-1) equal thickness transition.The testpieces can be realized load center overtesting part examination section centroid, it avoids testpieces from being bent, is not necessarily to the anti-bending fixture of additional designs, so that it may it is genuine and believable to reach test result, the purpose for reducing empirical risk simultaneously, avoids unnecessary human and material resources resources loss.
Description
Technical field
The utility model category aircraft fatigue strength test field, is related to a kind of shear fatigue test part.
Background technique
The static(al) shearing test part design of similar fuselage skin is had conducted extensive research both at home and abroad, is had accumulated certain
Experience, but it is seldom for the research of metal material shear fatigue test part design.Shear fatigue test design is unreasonable, will lead to
Load transmission is uneven, and fatigue rupture easily occurs in advance in non-examination section, causes finally to lose test meaning.Therefore it must inhale
It takes previous testpieces design experiences to give a lesson to, designs a kind of testpieces for examining section Jing Guo two-sided milling, so that examination is crossed at load center
Part examination section centroid is tested, avoids testpieces from being bent, is not necessarily to the anti-bending fixture of additional designs, so that it may it is true to reach test result
Believable purpose.
Shear fatigue test research was seldom in the past, and corresponding testpieces design lacks experience.The testpieces designed,
It is excessively heavy due to there is the testpieces that the problems such as eccentric causes testpieces either to design in non-examination section premature degradation,
Cause the loss on man power and material.Testpieces optimization design how is carried out, guarantees that load center overtesting part examines section
Centroid avoids testpieces from being bent, to reach reduction empirical risk, reduces experimentation cost, these are to experimental design personnel
It is all particularly important for examination personnel with holding.
Summary of the invention
Goal of the invention: proposing a kind of shear fatigue test part, to guarantee that load center overtesting part examines section centroid, keeps away
Exempt from testpieces to be bent.
Technical solution: a kind of shear fatigue test part, including testpieces examination section (1-1), stringer and covering linkage section (1-
2) with testpieces changeover portion (1-3), gripping section (1-4) is the extended segment of testpieces changeover portion (1-3), when for testing and is pressed from both sides
Tool is connected, and the thickness of testpieces examination section (1-1) is identical as the actual (real) thickness of aircraft real structure；Stringer is connect with covering
Section (1-2) is connect by rivet with examination section (1-1), gripping section (1-4) to examination section (1-1) equal thickness transition.The testpieces
It can be realized load center overtesting part examination section centroid, avoid testpieces from being bent, be not necessarily to the anti-bending fixture of additional designs,
It just can reach that test result is genuine and believable, while reducing the purpose of empirical risk, avoid unnecessary human and material resources resource damage
It loses.
Advantageous effects: using the utility model proposes testpieces, examination is true, facilitates fixture to clamp, avoids trying
It tests part to be bent, without increasing anti-bending fixture, experimentation cost can be reduced, avoid unnecessary human and material resources resources loss.
Detailed description of the invention
Fig. 1 is the utility model testpieces front schematic view,
Fig. 2 is the utility model testpieces schematic rear view；
Number explanation: 1-1 examines section, 1-2 stringer and covering linkage section, 1-3 changeover portion, 1-4 gripping section, 1-5 diagonal segments.
Specific embodiment
Referring to attached drawing 1,2, a kind of shear fatigue test part, including testpieces examination section 1-1, stringer and covering linkage section 1-
2 and testpieces changeover portion 1-3, gripping section 1-4 be the extended segment of testpieces changeover portion 1-3, be connected when for testing with fixture, institute
The thickness for stating testpieces examination section 1-1 is identical as the actual (real) thickness of aircraft real structure；Stringer and covering linkage section 1-2 pass through riveting
Nail is connect with examination section 1-1, clamping 1-4 to examination section 1-1 equal thickness transition.
On the basis of above-mentioned testpieces, it is provided with bolt hole on gripping section 1-4, in order to fixture clamping.
On the basis of above-mentioned testpieces, testpieces changeover portion 1-3 further includes diagonal segments 1-5, is cut using Rouno Cormer Pregrinding Wheel
It cuts, facilitates the clamping of fatigue test piece and test fixture.
On the basis of above-mentioned testpieces, gripping section 1-4 to examination section 1-1 equal thickness transition, it is ensured that shear fatigue
Under the premise of test gripping section and changeover portion stress distribution are uniform, experimentation cost is reduced.
On the basis of above-mentioned testpieces, gradually milling is true to aircraft using two-sided milling mode by testpieces examination section 1-1
The actual (real) thickness of real structure is identical.
Claims (4)
1. a kind of shear fatigue test part, including testpieces examination section (1-1), stringer and covering linkage section (1-2) and testpieces
Changeover portion (1-3), it is characterised in that: gripping section (1-4) is the extended segment of testpieces changeover portion (1-3), when for testing and is pressed from both sides
Tool is connected, and the thickness of testpieces examination section (1-1) is identical as the actual (real) thickness of aircraft real structure；Stringer is connect with covering
Section (1-2) is connect by rivet with examination section (1-1), gripping section (1-4) to examination section (1-1) equal thickness transition.
2. a kind of shear fatigue test part according to claim 1, it is characterised in that: be provided on gripping section (1-4)
Bolt hole.
3. a kind of shear fatigue test part according to claim 1, it is characterised in that: testpieces changeover portion (1-3) also wraps
Diagonal segments (1-5) is included, is cut using Rouno Cormer Pregrinding Wheel.
4. a kind of shear fatigue test part according to claim 1, it is characterised in that: testpieces examines section (1-1) to use
The actual (real) thickness of two-sided milling mode gradually milling to aircraft real structure is identical.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822110300.1U CN209513479U (en) | 2018-12-14 | 2018-12-14 | A kind of shear fatigue test part |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201822110300.1U CN209513479U (en) | 2018-12-14 | 2018-12-14 | A kind of shear fatigue test part |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209513479U true CN209513479U (en) | 2019-10-18 |
Family
ID=68195197
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201822110300.1U Active CN209513479U (en) | 2018-12-14 | 2018-12-14 | A kind of shear fatigue test part |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209513479U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111122316A (en) * | 2019-12-13 | 2020-05-08 | 中国航空工业集团公司西安飞机设计研究所 | Device for eliminating residual stress of aviation metal part and examining aging performance |
| CN111122315A (en) * | 2019-12-13 | 2020-05-08 | 中国航空工业集团公司西安飞机设计研究所 | Aging performance assessment method for eliminating residual stress of aviation metal part |
-
2018
- 2018-12-14 CN CN201822110300.1U patent/CN209513479U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111122316A (en) * | 2019-12-13 | 2020-05-08 | 中国航空工业集团公司西安飞机设计研究所 | Device for eliminating residual stress of aviation metal part and examining aging performance |
| CN111122315A (en) * | 2019-12-13 | 2020-05-08 | 中国航空工业集团公司西安飞机设计研究所 | Aging performance assessment method for eliminating residual stress of aviation metal part |
| CN111122316B (en) * | 2019-12-13 | 2022-11-18 | 中国航空工业集团公司西安飞机设计研究所 | Device for eliminating residual stress of aviation metal part and examining aging performance |
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