CN214200590U - Fatigue test loading device for airplane spoiler - Google Patents
Fatigue test loading device for airplane spoiler Download PDFInfo
- Publication number
- CN214200590U CN214200590U CN202022714094.2U CN202022714094U CN214200590U CN 214200590 U CN214200590 U CN 214200590U CN 202022714094 U CN202022714094 U CN 202022714094U CN 214200590 U CN214200590 U CN 214200590U
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- spoiler
- girder
- rotating
- fatigue test
- wing box
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- 238000009661 fatigue test Methods 0.000 title claims abstract description 17
- 229910000831 Steel Inorganic materials 0.000 claims description 3
- 239000010959 steel Substances 0.000 claims description 3
- 239000000725 suspension Substances 0.000 claims description 3
- 238000005096 rolling process Methods 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
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- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The utility model belongs to the technical field of aircraft structural strength, a aircraft spoiler fatigue test loading device is disclosed, include: the spoiler, the wing box rotating assembly, the loading actuating cylinder and the bearing frame. The spoiler structure of the airplane is usually composed of a plurality of spoilers, the spoilers are similar in function and structure, if all the spoilers are selected for fatigue test, the complete wings are required to be used as supporting pieces, the test scale is large, the cost is high, and the period is long, so that the spoilers with the most serious load are selected as test objects through analysis, local wing boxes are designed according to the wing structure to be used as the supporting pieces, the test is simplified on the premise of meeting the test and assessment requirements, the period is shortened, and the test cost is reduced by at least more than 50%.
Description
Technical Field
The utility model belongs to the technical field of aircraft structural strength, in particular to aircraft spoiler fatigue test loading device.
Background
The fatigue test is an important basis for identifying whether the aircraft structure meets the service life requirement in the aircraft design and development, and provides test data and conclusions for verifying whether the aircraft meets the service life index.
The spoiler structure is an important component for improving the rolling performance of the airplane and shortening the ground sliding distance during landing, and the spoiler structure is connected with the wing girder, so the fatigue performance of the spoiler structure directly influences the service life of the airplane, and fatigue test examination is needed.
The spoiler structure of the airplane is generally composed of a plurality of spoilers, the spoilers are similar in function and structure, if all the spoilers are selected for fatigue test, the complete wings are required to be used as supporting pieces, and the test scale is large, the cost is high, and the period is long.
SUMMERY OF THE UTILITY MODEL
In order to solve the problem, the utility model provides an aircraft spoiler fatigue test loading device.
An aircraft spoiler fatigue test loading device, comprising: the spoiler, the wing box rotating assembly, the loading actuating cylinder and the bearing frame; wherein,
one end of the wing box is provided with a bracket, and the spoiler is suspended on the wing box bracket and can rotate around a bracket suspension point;
the wing box swivel assembly comprises: the supporting girder, the rotating upright post, the side girder and the rotating girder;
a top beam is arranged in the air, a support crossbeam is arranged on the ground below the top beam, two rotating stand columns are respectively and vertically arranged at two ends of the support crossbeam, the two rotating stand columns are respectively connected with one ends of two side crossbeams, and the rotating crossbeam is connected with the other ends of the two side crossbeams; two sides of the wing box are fixedly connected with the two side girders;
a rotary actuating cylinder is hung on the bearing frame, the rotary actuating cylinder is connected with the rotary girder and can drive the rotary girder to move so as to drive the wing box to rotate around the hinge joint of the rotary upright post and the side girder,
the loading actuating cylinder is hung on the force bearing frame and acts on the spoiler to apply normal load to the spoiler.
Further, the bearing frame comprises a bottom beam, four upright posts and a top beam; the four upright posts are vertically fixed on the ground, and a plurality of bottom beams are arranged on the ground and connected with the bottom ends of the four upright posts; the top beam is fixed at the top ends of the four upright posts.
Further, the support girder is arranged on the bottom beam.
Furthermore, the rotating upright post and the side girder are hinged through a bearing.
Furthermore, the rotating upright post, the side girder and the rotating girder are made of high-strength steel.
Furthermore, two sides of the wing box are fixedly connected with the two side girders through bolts.
The utility model discloses a wherein the spoiler that bears the load the most seriously is the test object, according to local wing box of wing structural design as the supporter, simplifies the experiment under the prerequisite that satisfies experimental examination requirement, shortens the cycle, reduces experimental cost more than 50% at least.
Drawings
Fig. 1 is a schematic view of a wing box rotating assembly of the present invention;
FIG. 2 is a schematic view of the loading device of the present invention;
in the figure, 1-spoiler; 12-a wing box; 21-supporting the girder; 22-rotating the upright; 23-side girder; 24-rotating the girder; 25-rotating the actuator cylinder; 3-loading the actuator cylinder; 41-upright post; 42-top beam; 43-bottom beam.
Detailed Description
An aircraft spoiler fatigue test loading device, comprising: the spoiler comprises a spoiler 1, a wing box 12, a wing box rotating assembly, a loading actuator cylinder 3 and a bearing frame; wherein,
one end of the wing box is provided with a bracket, and the spoiler is suspended on the wing box bracket and can rotate around a bracket suspension point;
the wing box swivel assembly comprises: a support girder 21, a rotating upright column 22, a side girder 23, and a rotating girder 24;
a top beam is arranged in the air, a support crossbeam is arranged on a bottom beam, two rotating stand columns are respectively and vertically arranged at two ends of the support crossbeam, the two rotating stand columns are respectively hinged with one ends of two side crossbeams through bearings, and the rotating crossbeam is connected with the other ends of the two side crossbeams; the two sides of the wing box are fixedly connected with the two side girders through bolts;
a rotary actuating cylinder 25 is hung on the bearing frame, the rotary actuating cylinder is connected with the rotary girder and can drive the rotary girder to move so as to drive the wing boxes to rotate around the hinge joint of the rotary upright post and the side girder,
the loading actuating cylinder is hung on the force bearing frame and acts on the spoiler to apply normal load to the spoiler.
The bearing frame comprises a bottom beam 43, four upright posts 41 and a top beam 42; the four upright posts are vertically fixed on the ground, and a plurality of bottom beams are arranged on the ground and connected with the bottom ends of the four upright posts; the top beam is fixed at the top ends of the four upright posts.
The rotating upright post, the side girder and the rotating girder are all made of high-strength steel.
The utility model discloses a wherein the spoiler that bears the load the most seriously is the test object, according to local wing box of wing structural design as the supporter, simplifies the experiment under the prerequisite that satisfies experimental examination requirement, shortens the cycle, reduces experimental cost more than 50% at least.
Claims (6)
1. An aircraft spoiler fatigue test loading device, characterized in that the device comprises: the spoiler, the wing box rotating assembly, the loading actuating cylinder and the bearing frame; wherein,
one end of the wing box is provided with a bracket, and the spoiler is suspended on the wing box bracket and can rotate around a bracket suspension point;
the wing box swivel assembly comprises: the supporting girder, the rotating upright post, the side girder and the rotating girder;
two ends of the supporting girder are respectively and vertically provided with two rotating stand columns, the two rotating stand columns are respectively connected with one ends of the two side girders, and the rotating girder is connected with the other ends of the two side girders; the two sides of the wing box are fixedly connected with the two side girders;
the rotary actuator cylinder is connected with the rotary girder and can drive the rotary girder to move up and down so as to drive the wing box to rotate around the hinge joint of the rotary upright post and the side girder,
the loading actuating cylinder is hung on the force bearing frame and acts on the spoiler to apply normal load to the spoiler.
2. The aircraft spoiler fatigue test loading device according to claim 1, wherein the force bearing frame comprises a bottom beam, four upright posts and a top beam; the four upright posts are vertically fixed on the ground, and a plurality of bottom beams are arranged on the ground and connected with the bottom ends of the four upright posts; the top beam is fixed at the top ends of the four upright posts;
the rotary actuating cylinder is hung on the top beam;
the support girder is arranged on the ground below the top beam.
3. An aircraft spoiler fatigue test loading unit according to claim 2, wherein said support girder is provided on a bottom beam.
4. The aircraft spoiler fatigue test loading device according to claim 1, wherein the rotating upright post and the side frame are hinged through a bearing.
5. The aircraft spoiler fatigue test loading device according to claim 1, wherein the rotating upright post, the side frame and the rotating frame are made of high strength steel.
6. The aircraft spoiler fatigue test loading device according to claim 1, wherein two sides of the wing box are fixedly connected with two side girders through bolts.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022714094.2U CN214200590U (en) | 2020-11-20 | 2020-11-20 | Fatigue test loading device for airplane spoiler |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022714094.2U CN214200590U (en) | 2020-11-20 | 2020-11-20 | Fatigue test loading device for airplane spoiler |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214200590U true CN214200590U (en) | 2021-09-14 |
Family
ID=77646760
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202022714094.2U Active CN214200590U (en) | 2020-11-20 | 2020-11-20 | Fatigue test loading device for airplane spoiler |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214200590U (en) |
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2020
- 2020-11-20 CN CN202022714094.2U patent/CN214200590U/en active Active
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