CN205679383U - A kind of aircraft stringer wallboard tension test part - Google Patents
A kind of aircraft stringer wallboard tension test part Download PDFInfo
- Publication number
- CN205679383U CN205679383U CN201620514970.8U CN201620514970U CN205679383U CN 205679383 U CN205679383 U CN 205679383U CN 201620514970 U CN201620514970 U CN 201620514970U CN 205679383 U CN205679383 U CN 205679383U
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- wallboard
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- 238000005452 bending Methods 0.000 claims abstract description 3
- 238000009864 tensile test Methods 0.000 claims description 26
- 230000007704 transition Effects 0.000 claims description 13
- 238000009434 installation Methods 0.000 description 4
- 210000001503 joint Anatomy 0.000 description 3
- 230000007812 deficiency Effects 0.000 description 1
- 230000007246 mechanism Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
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- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The utility model discloses a kind of aircraft stringer wallboard tension test part.Described aircraft stringer wallboard tension test part includes wallboard and stringer；Being provided with test gripping section on one side of wallboard, test accommodates section and is used for accommodating for test fixture, and this side being provided with test gripping section is referred to as first side, and another side relative with this side is referred to as second side；The thickness of test gripping section is more than the thickness of described other positions of wallboard, and from the position, boundary of test gripping section and first side, to second side direction, extension forms boss to the trend that test gripping section tapers into thickness；Stringer is arranged on the face being provided with boss of wallboard, and stringer includes wallboard section and boss section, and wallboard section is arranged on wallboard, and boss section is that the bending of wallboard section extends, and boss section is arranged on boss.Use this structure, ensure that the load of loading end carries out transmitting load by stringer, thus solve the problem that stringer of the prior art does not transmit load substantially.
Description
Technical Field
The utility model relates to an aircraft structural strength tests technical field, especially relates to a long purlin wallboard tensile test spare of aircraft.
Background
In an airplane structural strength test, test planning and design are needed to be carried out on important connecting structures such as circumferential skin butt joint of a fuselage, butt joint of rib edge strips of upper and lower wing panels, and stringer butt joint of wall panels.
The transition section problem for the test pieces was involved in both of these tests, with the key core being 2 points: 1. the problem of how to evenly transmit the load of the loading end to the stringer and the wallboard is solved, and the stress of the stringer and the wallboard at the equal straight section is ensured to be consistent; 2. the thickness of the loading section is reasonably designed, and the centroid of the loading section is consistent with that of the long-purlin wallboard of the test section.
In the transition section of the stringer wallboard test piece in the prior art, the load of a loading end is often directly transferred from a skin, and the phenomenon that the stringer does not transfer the load basically causes test failure.
Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.
SUMMERY OF THE UTILITY MODEL
It is an object of the present invention to provide an aircraft stringer panel tensile test article that overcomes or at least alleviates at least one of the above-mentioned deficiencies in the prior art.
To achieve the above objects, the present invention provides an aircraft stringer web tensile test article, comprising a web and a stringer; the wall plate comprises a wall plate, a test clamping section and a second side edge, wherein the test clamping section is arranged on one side edge of the wall plate, the test clamping section is used for clamping a test fixture, the side edge provided with the test clamping section is called a first side edge, and the other side edge opposite to the side edge is called a second side edge; the thickness of the test clamping section is larger than that of other positions of the wallboard, and the test clamping section extends towards the direction of the second side edge from the junction position of the test clamping section and the first side edge in a trend of gradually reducing the thickness to form a boss; the minimum thickness of the boss is equal to the thickness of the wall plate; the stringer sets up on the face that is provided with the boss of wallboard, the stringer includes wallboard section and boss section, the wallboard section sets up on the wallboard, the boss section does the bending extension of wallboard section, the boss section sets up on the boss.
Preferably, the centroid of the test clamping section coincides with the centroid formed by the combination of the wall plate, the boss provided on the wall plate and the stringer.
Preferably, the second side edge is provided with a test frame edge for fixing the aircraft stringer wallboard tensile test piece on a test frame.
Preferably, the stringers are disposed on the wall panels and the bosses by rivets.
Preferably, the slope of the boss is 2 to 5 degrees.
Preferably, the extension distances of the bosses in the extension direction of the bosses are different, so that the bosses are wavy.
Preferably, the wave-like projection comprises a peak and a trough, and the peak is far away from the test clamping section relative to the trough.
Preferably, the wave trough and the test clamping section have a distance therebetween in the extension direction of the boss; and the wave crests and the wave troughs are in smooth transition.
Preferably, the wave trough contacts with the test clamping section in the extending direction of the lug boss; and the wave crests are in smooth transition, and the wave troughs are in angular transition.
The utility model discloses an among the aircraft stringer wallboard tensile test spare, because the design extends to the wallboard for the mode that experimental centre gripping section reduces with thickness gradually to form the boss, and set up partial stringer on the boss at least, adopt this kind of structure, can guarantee that the load of loading end transmits the load through the stringer, thereby solved the problem that the stringer does not transmit the load basically among the prior art.
Drawings
Fig. 1 is a schematic structural view of an aircraft stringer panel tensile test piece according to a first embodiment of the present invention.
FIG. 2 is a side schematic view of the aircraft stringer panel tensile test piece of the embodiment shown in FIG. 1.
FIG. 3 is a schematic illustration of the installation of the aircraft stringer panel tensile test piece of the embodiment shown in FIG. 1.
Fig. 4 is a schematic view of an installation of an aircraft stringer panel tensile test piece according to a second embodiment of the present invention.
Reference numerals:
| 1 | wall panel | 22 | Boss section |
| 2 | Stringer | 5 | Test frame |
| 3 | Test clamping section | 41 | Wave crest |
| 4 | Boss | 42 | Trough of wave |
| 21 | Wall panel segment |
Detailed Description
In order to make the purpose, technical solution and advantages of the present invention clearer, the following will combine the drawings in the embodiments of the present invention to perform more detailed description on the technical solution in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present invention, and should not be construed as limiting the present invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.
In the description of the present invention, it is to be understood that the terms "central", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience of description and for simplicity of description, and do not indicate or imply that the device or element so referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be considered as limiting the scope of the invention.
Fig. 1 is a schematic structural view of an aircraft stringer panel tensile test piece according to a first embodiment of the present invention. FIG. 2 is a side schematic view of the aircraft stringer panel tensile test piece of the embodiment shown in FIG. 1. FIG. 3 is a schematic illustration of the installation of the aircraft stringer panel tensile test piece of the embodiment shown in FIG. 1. Fig. 4 is a schematic view of an installation of an aircraft stringer panel tensile test piece according to a second embodiment of the present invention.
An aircraft stringer panel tensile test piece as shown in fig. 1 to 4 comprises a panel 1 and a stringer 2; the wall plate comprises a wall plate 1, a test clamping section 3, a test clamping fixture and a test clamping section, wherein the test clamping section 3 is arranged on one side edge of the wall plate 1, the test clamping section 3 is used for clamping a test fixture, the side edge provided with the test clamping section 3 is called a first side edge, and the other side edge opposite to the side edge is called a second side edge; the thickness of the test clamping section 3 is larger than that of other positions of the wallboard, and the test clamping section 3 extends towards the direction of the second side edge from the junction position of the test clamping section 3 and the first side edge in a trend of gradually reducing the thickness to form a boss 4; the minimum thickness of the boss 4 is equal to the thickness of the wall plate; stringer 2 sets up on the face that is provided with boss 4 of wallboard 1, and stringer 2 includes wallboard section 21 and boss section 22, and wallboard section 21 sets up on wallboard 1, and boss section 22 extends for buckling of wallboard section 21, and boss section 22 sets up on boss 4.
The utility model discloses an among the aircraft stringer wallboard tensile test spare, because the design extends to the wallboard for the mode that experimental centre gripping section reduces with thickness gradually to form the boss, and set up partial stringer on the boss at least, adopt this kind of mechanism, can guarantee that the load of loading end transmits the load through the stringer, thereby solved the problem that the stringer does not transmit the load basically among the prior art.
Referring to fig. 1 to 4, in the present embodiment, the centroid of the test clip section 3 coincides with the centroid formed by the combination of the panel 1, the boss 4 provided on the panel 1, and the stringer 2.
Referring to fig. 3, in this embodiment, a test rim 5 is provided on the second side edge for securing an aircraft stringer panel tensile test piece to a test stand.
In this embodiment, stringers 2 are placed on the panels and bosses by rivets.
The slope of boss 4 among the aircraft stringer wallboard tensile test spare of this application is 2 degrees to 5 degrees.
Referring to fig. 2, in the present embodiment, the slope is 3.03 °.
Referring to fig. 1, in the present embodiment, the extension distances of the bosses 4 in the extension direction thereof are different, so that the bosses have a wave shape.
With this structure, one is to prevent the extension in the direction from being dispersed if the same, and one is to be able to relatively reduce unnecessary material weight.
Referring to fig. 1, in the present embodiment, the wave-breaking projection 4 includes a peak 41 and a valley 42, and the peak 41 is far from the test clamping section 3 relative to the valley 42.
Referring to fig. 1, in the present embodiment, there is a distance between the valleys and the test grip segment in the direction of extension of the lands. And the wave trough and the wave crest are in smooth transition.
It will be appreciated that with a smooth transition, the force transfer will be relatively even and there will be no stress concentration points.
Referring to fig. 4, in this embodiment, the contact between the valleys and the test grip segments is in the direction of extension of the lands. The wave crests are in smooth transition, and the wave troughs are in angular transition.
It will be appreciated that in this embodiment the troughs are angled transitions such that the force of the trial clamping segments is concentrated at the troughs so that the force transmitted to the troughs is not distributed.
Finally, it should be pointed out that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit it. Although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention in its corresponding aspects.
Claims (9)
1. An aircraft stringer tensile test piece, characterized in that it comprises a panel (1) and a stringer (2); wherein,
a test clamping section (3) is arranged on one side edge of the wall plate (1), the test clamping section (3) is used for clamping a test fixture, the side edge provided with the test clamping section (3) is called a first side edge, and the other side edge opposite to the side edge is called a second side edge;
the thickness of the test clamping section (3) is larger than that of other positions of the wallboard, and the test clamping section (3) extends towards the direction of the second side edge from the junction position of the test clamping section (3) and the first side edge in a trend of gradually reducing the thickness to form a boss (4); the minimum thickness of the boss (4) is equal to the thickness of the wall plate;
stringer (2) set up on the face that is provided with boss (4) of wallboard (1), stringer (2) include wallboard section (21) and boss section (22), wallboard section (21) set up on wallboard (1), boss section (22) do the bending and extending of wallboard section (21), boss section (22) set up on boss (4).
2. An aircraft stringer web tensile test member according to claim 1, wherein the centroid of said test clip section (3) coincides with the centroid formed by the combination of said web (1), a boss (4) provided on the web (1) and the stringer (2).
3. An aircraft stringer panel tensile test member according to claim 2, wherein said second side edge is provided with a test rim (5) for securing said aircraft stringer panel tensile test member to a test frame.
4. The aircraft stringer panel tensile test member of claim 3, wherein said stringer (2) is disposed on said panel and said boss by rivets.
5. The aircraft stringer panel tensile test member of claim 4, wherein said bosses (4) have a slope of 2 to 5 degrees.
6. An aircraft stringer panel tensile test member according to claim 5, wherein said projections (4) extend at different distances in their own extension, so that the projections are undulated.
7. The aircraft stringer panel tensile test member of claim 6, wherein said wave-broken projections (4) comprise peaks (41) and troughs (42), said peaks (41) being remote from said test clip section (3) relative to said troughs (42).
8. The aircraft stringer panel tension test piece of claim 7, wherein said valleys have a distance from said test clip segment in a direction of extension of said bosses; and the wave crests and the wave troughs are in smooth transition.
9. The aircraft stringer panel tension test piece of claim 7, wherein said valleys contact said test clip segments in a direction of extension of said bosses; and the wave crests are in smooth transition, and the wave troughs are in angular transition.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620514970.8U CN205679383U (en) | 2016-05-31 | 2016-05-31 | A kind of aircraft stringer wallboard tension test part |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620514970.8U CN205679383U (en) | 2016-05-31 | 2016-05-31 | A kind of aircraft stringer wallboard tension test part |
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| CN205679383U true CN205679383U (en) | 2016-11-09 |
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| CN201620514970.8U Active CN205679383U (en) | 2016-05-31 | 2016-05-31 | A kind of aircraft stringer wallboard tension test part |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107515088A (en) * | 2017-08-04 | 2017-12-26 | 中国航空工业集团公司西安飞机设计研究所 | A kind of model test part design method of the main box section bending stiffness test of metal wings |
| CN109110103A (en) * | 2018-09-12 | 2019-01-01 | 淮北创之社信息科技有限公司 | A kind of aircraft cabin siding docking structure |
| 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 |
| CN110672402A (en) * | 2019-10-25 | 2020-01-10 | 中航西飞民用飞机有限责任公司 | Shearing test piece for composite material reinforced wall plate |
-
2016
- 2016-05-31 CN CN201620514970.8U patent/CN205679383U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107515088A (en) * | 2017-08-04 | 2017-12-26 | 中国航空工业集团公司西安飞机设计研究所 | A kind of model test part design method of the main box section bending stiffness test of metal wings |
| 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 |
| CN109110103A (en) * | 2018-09-12 | 2019-01-01 | 淮北创之社信息科技有限公司 | A kind of aircraft cabin siding docking structure |
| CN110672402A (en) * | 2019-10-25 | 2020-01-10 | 中航西飞民用飞机有限责任公司 | Shearing test piece for composite material reinforced wall plate |
| CN110672402B (en) * | 2019-10-25 | 2022-03-15 | 中航西飞民用飞机有限责任公司 | Shearing test piece for composite material reinforced wall plate |
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| GR01 | Patent grant |