CN206648810U - A kind of fuselage stringer banjo fixing butt jointing test fixture - Google Patents
A kind of fuselage stringer banjo fixing butt jointing test fixture Download PDFInfo
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- CN206648810U CN206648810U CN201720321828.6U CN201720321828U CN206648810U CN 206648810 U CN206648810 U CN 206648810U CN 201720321828 U CN201720321828 U CN 201720321828U CN 206648810 U CN206648810 U CN 206648810U
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- clamping plate
- stringer
- test fixture
- base board
- regulating base
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Abstract
The utility model discloses a kind of fuselage stringer banjo fixing butt jointing test fixture, belongs to aircraft stringer class formation experiment field.Including first clamping plate (4), second clamping plate (5) and regulating base board (7), wherein, first clamping plate (4) includes mainboard face and the stud (41 perpendicular to the mainboard face formed in side with second clamping plate (5), 51), the mainboard face of two clamping plates is present and edge strip (2) thickness identical thickness difference under the stringer, when testpieces covering (3) is clamped by the larger clamping plate of mainboard face thickness and the regulating base board (7), gap is formed between the covering and another clamping plate, the gap can accommodate the lower edge strip (2) of the stringer.It is connected by the utility model middle clamp plate stud with stringer web, preferably eliminates the influence that additional bending moment examines area's stress distribution to experiment.Drastically increase the validity and authenticity of test data.
Description
Technical field
The utility model belongs to aircraft stringer class formation experiment field, and in particular to a kind of fuselage stringer banjo fixing butt jointing experiment
Fixture.
Background technology
Fuselage stringer class formation is one of more important structure of aircraft, and its destruction will directly affect the complete of aircraft
Property, therefore when doing stringer class formation fatigue test, therefore, to assure that examine load distribution in region basic with actual airplane in experiment
Unanimously, and to ensure to test clamping zone can not in test premature degradation.At present, fuselage stringer class formation test fixture, no
False additional stress caused by moment of flexure can be preferably avoided, causes experiment examination area's stress distribution and aircraft truth
It is inconsistent, and then there is the phenomenon of bare terminal end premature degradation, test data validity and authenticity are made a big impact.
Utility model content
In order to solve the above problems, the utility model proposes a kind of fuselage stringer banjo fixing butt jointing test fixture, can disappear
Except the untrue additional bending moment influence on stringer class formation, to improve fatigue test validity and authenticity.Clamped by the fixture
Stringer mainly include web and upper and lower edge strip, wherein edge strip extends to certain side of web respectively from the both ends of web, is formed
" 2 " font structure, as shown in Fig. 2 in addition, the fixture is also held and mounted on the covering on lower edge strip.
The utility model fuselage stringer banjo fixing butt jointing test fixture mainly includes first clamping plate, second clamping plate and regulation bottom
Plate, wherein, first clamping plate includes mainboard face and the stud perpendicular to the mainboard face formed in side with second clamping plate,
The regulating base board is arranged on the first clamping plate and the second clamping plate deviates from the side of stud, and the mainboard face of two clamping plates is deposited
With edge strip thickness identical thickness difference under the stringer, when testpieces covering is by the larger clamping plate of mainboard face thickness and the tune
When saving bottom plate clamping, gap is formed between the covering and another clamping plate, the gap can accommodate the lower edge of the stringer
Bar.
Preferably, in addition to backing plate, it is arranged on remaining after the lower edge strip of the stringer is placed in the gap
In space.
In such scheme preferably, the first clamping plate and second clamping plate are set on the one side away from regulating base board
There is step, rounding transition is arranged at the step.
In such scheme preferably, on the direction that test fixture extends to the stringer center, the regulating base board
Length be less than the length of first clamping plate or second clamping plate.
In such scheme preferably, the first clamping plate rivets with the covering, regulating base board.
In such scheme preferably, the second clamping plate rivets with edge strip, covering and regulating base board under the stringer.
In such scheme preferably, the stud of the first clamping plate and second clamping plate is clamping the web of the stringer
Afterwards, fixed by rivet.
In such scheme preferably, the backing plate and covering, regulating base board and with the less clamping plate of mainboard face thickness
Riveting.
It is connected by the utility model middle clamp plate stud with stringer web, preferably eliminates additional bending moment and experiment is examined
The influence of area's stress distribution, make load distribution basically identical with actual airplane；In this utility model, by adjusting bottom plate thickness
Degree, easily the load effect centre of form in experiment can be adjusted, be easy to experiment to implement；Pass through the carry out multistage machine to clamping plate
Add, make section load change more gentle, improve clamping zone fatigue behaviour.Examination is drastically increased using this utility model
Test the validity and authenticity of data.
Brief description of the drawings
Fig. 1 is the front view of a preferred embodiment of the utility model fuselage stringer banjo fixing butt jointing test fixture.
Fig. 2 is the left view of embodiment illustrated in fig. 1.
Fig. 3 is the test fixture and stringer connection diagram of a preferred embodiment of the present utility model.
Wherein, 1 is web, and 2 be lower edge strip, and 3 be covering, and 4 be first clamping plate, and 5 be second clamping plate, and 6 be backing plate, and 7 be tune
Bottom plate is saved, 8 be rivet, and 41 be stud, and 51 be stud.
Embodiment
To make the purpose, technical scheme and advantage that the utility model is implemented clearer, below in conjunction with the utility model
Accompanying drawing in embodiment, the technical scheme in the embodiment of the utility model is further described in more detail.In the accompanying drawings, from beginning
Same or similar element is represented to same or similar label eventually or there is the element of same or like function.Described reality
It is the utility model part of the embodiment to apply example, rather than whole embodiments.Below with reference to the embodiment of accompanying drawing description
It is exemplary, it is intended to for explaining the utility model, and it is not intended that to limitation of the present utility model.It is new based on this practicality
Embodiment in type, the every other implementation that those of ordinary skill in the art are obtained under the premise of creative work is not made
Example, belong to the scope of the utility model protection.Embodiment of the present utility model is described in detail below in conjunction with the accompanying drawings.
In description of the present utility model, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom " " interior ", " outer " is based on accompanying drawing institutes
The orientation or position relationship shown, it is for only for ease of description the utility model and simplifies description, rather than indicates or imply and be signified
Device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to this practicality
The limitation of novel protected scope.
The utility model proposes a kind of fuselage stringer banjo fixing butt jointing test fixture, its stringer clamped mainly includes web
With upper and lower edge strip, wherein edge strip extends to certain side of web respectively from the both ends of web, forms " 2 " font structure, such as Fig. 2
It is shown, wherein, web 1 and lower edge strip 2 are clamped, meanwhile, fixture is also held and mounted on the covering 3 of the lower bottom of edge strip 2.
The utility model fuselage stringer banjo fixing butt jointing test fixture mainly includes first clamping plate 4, second clamping plate 5 and regulation
Bottom plate 7, wherein, first clamping plate 4 and second clamping plate 5 include mainboard face and formed in side perpendicular to the mainboard face
Stud 41,51, the regulating base board 7 are arranged on the side that two clamping plates deviate from stud, and the mainboard face of two clamping plates is present and institute
Edge strip thickness identical thickness difference under stringer is stated, when testpieces covering 3 is by the larger clamping plate of mainboard face thickness and the regulation bottom
When plate 7 clamps, gap is formed between the covering 3 and another clamping plate, the gap can accommodate the lower edge strip of the stringer
2。
With reference to figure 1, label 4 is first clamping plate, and 5 be second clamping plate, and two clamping plates are stretched in side (upper side in figure)
Go out stud, first clamping plate 4 includes stud 41, and second clamping plate 5 includes stud 51, two pieces of stud alignment, for clamping above-mentioned stringer
Web 1, with reference to figure 2 and Fig. 3.In Fig. 2 or Fig. 3,3 be covering, wherein, two clamping plates clamp the web 1 of stringer jointly, and two
The mainboard face of block clamping plate clamps covering 3 and lower edge strip 2 jointly with regulating base board 7, so preferably eliminates additional bending moment to examination
The influence of examination area's stress distribution is tested, makes load distribution basically identical with actual airplane.
In the one side (bottom side in Fig. 1, Fig. 2) away from stud, first clamping plate 4 has different height from second clamping plate 5
Degree, thickness difference is formed, with reference to figure 2, the thickness of first clamping plate 4 is more than the thickness of second clamping plate 5, so that when the lower edge strip 2 of stringer
During positioned at the lower section of second clamping plate 5, there is identical level height with first clamping plate, afterwards, in first clamping plate 4 and lower edge strip 2
Lower section installation and adjustment bottom plate 7 and covering 3 when, can ensure that regulating base board 7 (actual contact be covering 3) is total to second clamping plate 5
With the lower edge strip 2 for clamping stringer.
In the present embodiment, in addition to backing plate 6, it is arranged on and is remained after the lower edge strip 2 of the stringer is placed in the gap
In remaining space.With reference to figure 2, the lower bolster limited width of stringer, can only fill between being formed by second clamping plate 5 and covering 3
A part for gap, and another part then needs to use the backing plate 6 of suitable thickness to fill.
In the present embodiment, the first clamping plate 4 and second clamping plate 5 are provided with platform on the one side away from regulating base board
Rank, rounding transition is arranged at the step.With reference to figure 1, transition shoulder is three layers, and one layer of the leftmost side is gripping section, is used for
Test fixture clamps, and two sections of thickness that clamping plate extends to the right taper into, and uses rounding transition, more by being carried out to clamping plate
Level machine adds, and makes section load change more gentle, improves clamping zone fatigue behaviour.
In the present embodiment, on the direction that test fixture extends to the stringer center, the length of the regulating base board 7 is small
In first clamping plate 4 or the length of second clamping plate 5.With reference to figure 1, the length of regulating base board 7 is less than the length of second clamping plate 5, that is, schemes
Show the lower right-hand side of middle backing plate 6 without regulating base board, the design is in order to avoid section load is mutated, and makes to act at stringer section
Load change it is more gentle.
In the present embodiment, the test fixture also includes some rivets 8, and all fixed forms are riveting, including described
First clamping plate 4 and covering 3, regulating base board 7 (are riveted to one by first clamping plate 4 and the riveting of the covering 3, regulating base board 7 jointly
Rise, similar description is equivalent below)；The second clamping plate 5 rivets with edge strip 2, covering 3 and regulating base board 7 under the stringer；It is described
The stud of first clamping plate 4 and second clamping plate 5 is fixed after the web 1 of the stringer is clamped by rivet；And work as institute
When stating test fixture includes backing plate 6, the backing plate 6 is with setting regulating base board 7 thereunder, covering 3 and being disposed thereon
The less clamping plate of mainboard face thickness (second clamping plate 5 in Fig. 2) riveting of side.
It is further to note that in the utility model, can be easily to examination by adjusting the thickness of regulating base board 7
Test the middle load effect centre of form to be adjusted, be easy to experiment to implement.Test load passes through frictional force transmission between fixture and chuck.It is tired
Labor result of the test shows：This utility model significantly improves the validity and authenticity of test data.
It is connected by the utility model middle clamp plate stud with stringer web, preferably eliminates additional bending moment and experiment is examined
The influence of area's stress distribution, make load distribution basically identical with actual airplane；In this utility model, by adjusting bottom plate thickness
Degree, easily the load effect centre of form in experiment can be adjusted, be easy to experiment to implement；Pass through the carry out multistage machine to clamping plate
Add, make section load change more gentle, improve clamping zone fatigue behaviour.Examination is drastically increased using this utility model
Test the validity and authenticity of data.
It is last it is to be noted that：Above example is only to illustrate the technical solution of the utility model, rather than it is limited
System.Although the utility model is described in detail with reference to the foregoing embodiments, one of ordinary skill in the art should manage
Solution：It can still be modified to the technical scheme described in foregoing embodiments, or which part technical characteristic is entered
Row equivalent substitution；And these modifications or replacement, the essence of appropriate technical solution is departed from various embodiments of the utility model
The spirit and scope of technical scheme.
Claims (8)
- A kind of 1. fuselage stringer banjo fixing butt jointing test fixture, it is characterised in that：Mainly include first clamping plate (4), second clamping plate (5) And regulating base board (7), wherein, first clamping plate (4) includes mainboard face with second clamping plate (5) and formed in side vertical Stud (41,51) in the mainboard face, the regulating base board (7) is arranged on the first clamping plate and the second clamping plate deviates from The side of stud, the mainboard faces of two clamping plates exist with edge strip (2) thickness identical thickness difference under the stringer, when testpieces covers When skin (3) is clamped by the larger clamping plate of mainboard face thickness and the regulating base board (7), the covering (3) and another clamping plate it Between form gap, the gap can accommodate the lower edge strip (2) of the stringer.
- 2. fuselage stringer banjo fixing butt jointing test fixture as claimed in claim 1, it is characterised in that：Also include backing plate (6), set After the lower edge strip (2) of the stringer is placed in the gap in remaining space.
- 3. fuselage stringer banjo fixing butt jointing test fixture as claimed in claim 1, it is characterised in that：The first clamping plate (4) and Second clamping plate (5) is provided with step on the one side away from regulating base board (7), and rounding transition is arranged at the step.
- 4. fuselage stringer banjo fixing butt jointing test fixture as claimed in claim 1, it is characterised in that：In test fixture to the length On the direction of purlin center extension, the length of the regulating base board (7) is less than the length of first clamping plate (4) or second clamping plate (5).
- 5. fuselage stringer banjo fixing butt jointing test fixture as claimed in claim 1, it is characterised in that：The first clamping plate (4) with The covering (3) and regulating base board (7) riveting.
- 6. fuselage stringer banjo fixing butt jointing test fixture as claimed in claim 1, it is characterised in that：The second clamping plate (5) with Edge strip (2), covering (3) and regulating base board (7) riveting under the stringer.
- 7. fuselage stringer banjo fixing butt jointing test fixture as claimed in claim 1, it is characterised in that：The first clamping plate (4) with The stud of second clamping plate (5) is fixed after the web (1) of the stringer is clamped by rivet.
- 8. fuselage stringer banjo fixing butt jointing test fixture as claimed in claim 2, it is characterised in that：The backing plate (6) and covering (3), regulating base board (7) and clamping plate less with mainboard face thickness riveting.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720321828.6U CN206648810U (en) | 2017-03-30 | 2017-03-30 | A kind of fuselage stringer banjo fixing butt jointing test fixture |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720321828.6U CN206648810U (en) | 2017-03-30 | 2017-03-30 | A kind of fuselage stringer banjo fixing butt jointing test fixture |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206648810U true CN206648810U (en) | 2017-11-17 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720321828.6U Active CN206648810U (en) | 2017-03-30 | 2017-03-30 | A kind of fuselage stringer banjo fixing butt jointing test fixture |
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| CN (1) | CN206648810U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109178340A (en) * | 2018-08-24 | 2019-01-11 | 中国飞机强度研究所 | A kind of wing body docking siding and its test method for fatigue test |
| CN110091978A (en) * | 2019-04-12 | 2019-08-06 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of stringer banjo fixing butt jointing, wing upper wall board connecting structure and aircraft |
-
2017
- 2017-03-30 CN CN201720321828.6U patent/CN206648810U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109178340A (en) * | 2018-08-24 | 2019-01-11 | 中国飞机强度研究所 | A kind of wing body docking siding and its test method for fatigue test |
| CN110091978A (en) * | 2019-04-12 | 2019-08-06 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of stringer banjo fixing butt jointing, wing upper wall board connecting structure and aircraft |
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