CN216509189U - Middle and outer wing fatigue test butt joint simulation piece - Google Patents
Middle and outer wing fatigue test butt joint simulation piece Download PDFInfo
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- CN216509189U CN216509189U CN202121771594.8U CN202121771594U CN216509189U CN 216509189 U CN216509189 U CN 216509189U CN 202121771594 U CN202121771594 U CN 202121771594U CN 216509189 U CN216509189 U CN 216509189U
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Abstract
The utility model belongs to the technical field of aviation strength tests, and particularly relates to a middle and outer wing fatigue test butt joint simulation piece. Comprises a wing box (100) and a stand column assembly (200); one end of the wing box section (100) is connected with the middle and outer wings, and the other end is connected with the bearing wall; the upright post assembly (200) is connected with the lower parts of the front and rear beams of the wing box section (100) through bolts. The clamp is used for the butt joint transition section clamp between the middle and outer wings and the bearing wall (frame) during the static force/fatigue test of the wing, and the clamp avoids the problem that the local damage of the middle and outer wings is caused by overlarge bending moment of the root when the middle and outer wings are directly connected with the bearing wall (frame). The wing structure part test is an important means for examining the static strength and fatigue performance of the wing, and is mainly used for directly connecting the middle and outer wings with the bearing wall (frame), reducing the loading of the root of the middle and outer wings and laying a foundation for the smooth test.
Description
Technical Field
The utility model belongs to the technical field of aviation strength tests, and particularly relates to a middle and outer wing fatigue test butt joint simulation piece.
Background
The static force/fatigue test is an important basis for identifying whether the structure of the airplane meets the use safety in the design and development of the airplane, and provides test data and conclusions for verifying whether the airplane meets the service life indexes.
The clamp is used for the butt joint transition section clamp between the middle and outer wings and the bearing wall (frame) during the static force/fatigue test of the wing, and the clamp avoids the problem that the local damage of the middle and outer wings is caused by overlarge bending moment of the root when the middle and outer wings are directly connected with the bearing wall (frame). The wing structure part test is an important means for examining the static strength and fatigue performance of the wing, and is mainly used for directly connecting the middle and outer wings with the bearing wall (frame), reducing the loading of the root of the middle and outer wings and laying a foundation for the smooth test.
SUMMERY OF THE UTILITY MODEL
The purpose of the utility model is as follows: the utility model provides a china and foreign wing fatigue test butt joint simulation piece, has solved the problem that the local destruction of china and foreign wing caused by the root bending moment is too big when china and foreign wing directly is connected with bearing wall (frame).
The technical scheme of the utility model is as follows: in order to achieve the purpose, the docking simulation piece for the fatigue test of the middle and outer wings comprises a wing box section 100 and a stand column assembly 200;
one end of the wing box section 100 is connected with the middle and outer wings, and the other end is connected with the bearing wall;
the pillar assembly 200 is connected to the lower portions of the front and rear beams of the wing box 100 by bolts.
In one possible embodiment, the wing box section 100 comprises a front spar 1, an upper wall panel 2, a lower wall panel 3, a rib 4, a rear spar 5, an end rib 6; the upper wall plate 2 and the lower wall plate 3 form the upper end surface and the lower end surface of the wing box section 100, the front beam 1 and the rear beam 5 are positioned on the front end surface and the rear end surface of the wing box section 100, and the end ribs 6 are arranged on the left end surface and the right end surface of the wing box section 100 and are connected with the upper wall plate 2 and the lower wall plate 3 through bolts; the front beam 1, the rear beam 5, the upper wall plate 2, the lower wall plate 3 and the end rib 6 are respectively connected through bolts; the wing rib 4 is disposed in the wing box section 100, is arranged in parallel with the end rib 6, and is connected to the upper wall plate 2 and the lower wall plate 3 by bolts respectively.
In one possible embodiment, the front beam 1 and the rear beam 5 are identical in structure; the beam reinforcing joint comprises a beam upper edge strip 11, a beam lower edge strip 12, a beam web 13 and a beam reinforcing joint 14; the sections of the beam upper edge strip 11 and the beam lower edge strip 12 are both in a T shape, wherein one end with a plane is respectively connected with the upper wall plate 2 and the lower wall plate 3, and the extension section of the other end is respectively riveted with the upper end and the lower end of the beam web plate 13; the beam reinforcing joints 14 are arranged on two sides of the beam web 13 and are respectively connected with the beam upper edge strip 11, the beam lower edge strip 12 and the beam web 13 through bolts. For reinforcing the structure of the front beam 1 and the rear beam 5.
In one possible embodiment, the mast assembly 200 includes a mast 20, a mast upper joint 21, a mast lower joint 22; the upright post upper joint 21 and the upright post lower joint 22 are respectively connected with the upper end and the lower end of the upright post 20 through bolts; the upright post 20 is connected with the end surface of the beam lower edge strip 12 through the upright post upper joint 21 through a bolt; the upright post 20 is fixedly connected with the ground through the upright post lower joint 22.
In one possible embodiment, the pillar 20 includes a pillar cap 23, a pillar web 24, a pillar reinforcement 25; the section of the upright column edge strip 23 is T-shaped and is respectively riveted with two ends of the upright column web plate 24; the pillar reinforcement 25 is disposed between the pillar beads 23, and both ends thereof are riveted to the pillar beads 23, respectively.
In a possible embodiment, the upper wall plate 2 and the lower wall plate 3 are provided with reinforcing ribs.
The utility model has the beneficial effects that: the utility model fills the blank of the unilateral wing and bearing wall frame butt joint simulation piece in the static force/fatigue test of the wing during the static force/fatigue test, and provides a butt joint simulation piece for checking the wing structure. The simulation piece can reduce the whole load of the root of the middle and outer wing, avoid the problem that the root of the bearing wall frame directly connected with the middle and outer wings is overloaded to cause local damage, can be repeatedly applied to other tests with the same interface, realize that the test risk is reduced, ensure the reliability of the test result, shorten the model development period and reduce the manufacturing cost of the simulation piece about the follow-up test.
Drawings
FIG. 1 is a schematic view of a wing box section 100 according to a preferred embodiment of the present invention
FIG. 2 is a schematic view of a stud assembly 200 according to a preferred embodiment of the present invention
Fig. 3 is a schematic view illustrating the connection of the front beam 1 and the rear beam 5 with the pillar assembly 200 according to the preferred embodiment of the present invention.
Fig. 4 is a schematic structural view of the pillar 20 according to the preferred embodiment of the present invention.
Detailed Description
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below. It should be apparent that the drawings in the following description are merely exemplary, and that other embodiments can be derived from the drawings provided by those of ordinary skill in the art without inventive effort.
The structures, ratios, sizes, and the like shown in the present specification are only used for matching with the contents disclosed in the specification, so that those skilled in the art can understand and read the present invention, and do not limit the conditions for implementing the present invention, so that the present invention has no technical significance, and any structural modifications, changes in the ratio relationship, or adjustments of the sizes, without affecting the functions and purposes of the present invention, should still fall within the scope of the present invention.
As shown in fig. 1-2, a middle and outer wing fatigue test docking simulator comprises a wing box section 100 and a stand column assembly 200;
one end of the wing box section 100 is connected with the middle and outer wings, and the other end is connected with the bearing wall;
the pillar assembly 200 is connected to the lower portions of the front and rear beams of the wing box 100 by bolts.
In one possible embodiment, the wing box section 100 comprises a front spar 1, an upper wall panel 2, a lower wall panel 3, a rib 4, a rear spar 5, an end rib 6; the upper wall plate 2 and the lower wall plate 3 form the upper end surface and the lower end surface of the wing box section 100, the front beam 1 and the rear beam 5 are positioned on the front end surface and the rear end surface of the wing box section 100, and the end ribs 6 are arranged on the left end surface and the right end surface of the wing box section 100 and are connected with the upper wall plate 2 and the lower wall plate 3 through bolts; the front beam 1, the rear beam 5, the upper wall plate 2, the lower wall plate 3 and the end rib 6 are respectively connected through bolts; the wing rib 4 is disposed in the wing box section 100, is arranged in parallel with the end rib 6, and is connected to the upper wall plate 2 and the lower wall plate 3 by bolts respectively.
In one possible embodiment, as shown in fig. 3, the front beam 1 and the rear beam 5 are identical in structure; the beam reinforcing joint comprises a beam upper edge strip 11, a beam lower edge strip 12, a beam web 13 and a beam reinforcing joint 14; the sections of the beam upper edge strip 11 and the beam lower edge strip 12 are both in a T shape, wherein one end with a plane is respectively connected with the upper wall plate 2 and the lower wall plate 3, and the extension section of the other end is respectively riveted with the upper end and the lower end of the beam web plate 13; the beam reinforcing joints 14 are arranged on two sides of the beam web 13 and are respectively connected with the beam upper edge strip 11, the beam lower edge strip 12 and the beam web 13 through bolts. For reinforcing the structure of the front beam 1 and the rear beam 5.
In one possible embodiment, the mast assembly 200 includes a mast 20, a mast upper joint 21, a mast lower joint 22; the upright post upper joint 21 and the upright post lower joint 22 are respectively connected with the upper end and the lower end of the upright post 20 through bolts; the upright post 20 is connected with the end surface of the beam lower edge strip 12 through the upright post upper joint 21 through a bolt; the upright post 20 is fixedly connected with the ground through the upright post lower joint 22.
In one possible embodiment, as shown in fig. 4, the pillar 20 includes a pillar cap 23, a pillar web 24, and a pillar stiffener 25; the section of the upright post edge strip 23 is T-shaped and is respectively riveted with two ends of the upright post web 24; the pillar reinforcement 25 is disposed between the pillar beads 23, and both ends thereof are riveted to the pillar beads 23, respectively.
In a possible embodiment, the upper and lower wall plates 2, 3 are provided with stiffening ribs.
The above embodiments are only used for illustrating the technical solutions of the present application, and not for limiting the same; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equally replaced; such modifications and substitutions do not substantially depart from the spirit and scope of the embodiments of the present application, and are intended to be included within the scope of the present application.
Claims (5)
1. A middle and outer wing fatigue test butt joint simulation piece is characterized by comprising a wing box section (100) and a stand column assembly (200);
one end of the wing box section (100) is connected with the middle and outer wings, and the other end of the wing box section is connected with the bearing wall;
the upright post assembly (200) is connected with the lower parts of the front and rear beams of the wing box section (100) through bolts; the wing box section (100) comprises a front beam (1), an upper wall plate (2), a lower wall plate (3), a wing rib (4), a rear beam (5) and an end rib (6); the upper wall plate (2) and the lower wall plate (3) form the upper end surface and the lower end surface of the wing box section (100), the front beam (1) and the rear beam (5) are positioned on the front end surface and the rear end surface of the wing box section (100), and the end ribs (6) are arranged on the left end surface and the right end surface of the wing box section (100) and are connected with the upper wall plate (2) and the lower wall plate (3) through bolts; the front beam (1), the rear beam (5), the upper wall plate (2), the lower wall plate (3) and the end rib (6) are respectively connected through bolts; the wing ribs (4) are arranged in the wing box section (100) and arranged in parallel with the end ribs (6), and are respectively connected with the upper wall plate (2) and the lower wall plate (3) through bolts.
2. The middle and outer wing fatigue test butt-joint simulation piece as claimed in claim 1, wherein the front beam (1) and the rear beam (5) are identical in structure; the beam reinforcing structure comprises a beam upper edge strip (11), a beam lower edge strip (12), a beam web (13) and a beam reinforcing joint (14); the sections of the upper beam edge strip (11) and the lower beam edge strip (12) are T-shaped, one end with a plane is respectively connected with the upper wall plate (2) and the lower wall plate (3), and the extension section at the other end is respectively riveted with the upper end and the lower end of the beam web plate (13); the beam reinforcing joints (14) are arranged on two sides of the beam web (13) and are respectively connected with the beam upper edge strip (11), the beam lower edge strip (12) and the beam web (13) through bolts.
3. The middle and outer wing fatigue test butt joint simulation piece as claimed in claim 2, wherein the upright post assembly (200) comprises an upright post (20), an upright post upper joint (21) and an upright post lower joint (22); the upright post upper joint (21) and the upright post lower joint (22) are respectively connected with the upper end and the lower end of the upright post (20) through bolts; the upright post (20) is connected with the end surface of the beam lower edge strip (12) through a bolt through the upright post upper joint (21); the upright post (20) is fixedly connected with the ground through the upright post lower joint (22).
4. The middle and outer wing fatigue test butt joint simulation piece as claimed in claim 1, wherein the upright column (20) comprises an upright column edge strip (23), an upright column web plate (24) and an upright column reinforcing piece (25) which are oppositely arranged at two sides; the section of the upright post edge strip (23) is T-shaped and is respectively riveted with two ends of the upright post web plate (24); the upright post reinforcing piece (25) is arranged between the upright post flanges (23), and the two ends of the upright post reinforcing piece are riveted with the upright post flanges (23) on the two sides respectively.
5. The middle and outer wing fatigue test butt joint simulation piece according to claim 1, wherein reinforcing ribs are arranged on the upper wall plate (2) and the lower wall plate (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121771594.8U CN216509189U (en) | 2021-07-30 | 2021-07-30 | Middle and outer wing fatigue test butt joint simulation piece |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121771594.8U CN216509189U (en) | 2021-07-30 | 2021-07-30 | Middle and outer wing fatigue test butt joint simulation piece |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216509189U true CN216509189U (en) | 2022-05-13 |
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ID=81516729
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121771594.8U Active CN216509189U (en) | 2021-07-30 | 2021-07-30 | Middle and outer wing fatigue test butt joint simulation piece |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216509189U (en) |
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2021
- 2021-07-30 CN CN202121771594.8U patent/CN216509189U/en active Active
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