CN214524458U - Adjustable aircraft cabin door test platform - Google Patents
Adjustable aircraft cabin door test platform Download PDFInfo
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- CN214524458U CN214524458U CN202023220920.4U CN202023220920U CN214524458U CN 214524458 U CN214524458 U CN 214524458U CN 202023220920 U CN202023220920 U CN 202023220920U CN 214524458 U CN214524458 U CN 214524458U
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Abstract
The utility model relates to an aircraft test tool design field specifically is an adjustable aircraft hatch door test platform, and this test platform comprises adjustable strutting arrangement and platform. The adjustable supporting device consists of a supporting rod, an adjusting sleeve, a connecting rod, a support, a connecting shaft and a pin shaft. One end of the support rod is fixedly connected with the ground, the other end of the support rod is connected with the lower portion of the adjusting sleeve through threads, and the upper portion of the adjusting sleeve is connected with the connecting rod through threads. The screw thread directions of the stay bar and the connecting rod are opposite. The tail end of the connecting rod is provided with a double-lug structure, and the connecting shaft is hinged with the double-lug structure. The middle part of the connecting shaft is provided with a through hole, the pin shaft penetrates through the middle through hole of the connecting shaft, and the connecting shaft and the pin shaft form a cross-shaped connecting structure. The support is hinged with the pin shaft. The adjustable supporting device is fixedly connected with the platform through the support. This experimental novel design and the manufacturing cost who has reduced test platform have improved test efficiency.
Description
Technical Field
The utility model relates to an aircraft test tool design field specifically is a can verify the test platform of aircraft hatch door function under different aircraft gestures.
Background
The cabin door is an important part for ensuring the smooth entrance and exit of personnel and goods on the airplane. For the civil aircraft emergency exit cabin door, according to the airworthiness regulation requirement, the aircraft can be normally opened in a normal ground attitude and in each attitude when one or more landing gear supports are broken, and the functions need to be proved by tests to have airworthiness compliance. Different types of test platforms need to be designed for different types of machines, at least three groups of test platforms with different postures need to be designed for the cabin door of each type of machine, the utilization rate of the test platforms is low, and the test cost is obviously increased.
SUMMERY OF THE UTILITY MODEL
The to-be-solved technical problem of the utility model is to provide an adjustable aircraft hatch door test platform, through the adjustment function of this platform, can realize the position simulation of arbitrary aircraft gesture to a platform replaces original a plurality of test platform, thereby reduces test platform's design and manufacturing cost, avoids dismouting hatch door repeatedly simultaneously, improves test efficiency.
For solving the above problems, the specific technical scheme of the utility model is as follows: consists of an adjustable supporting device and a platform. The adjustable supporting device consists of a supporting rod, an adjusting sleeve, a connecting rod, a support, a connecting shaft and a pin shaft. One end of the support rod is fixedly connected with the ground, the other end of the support rod is connected with the lower portion of the adjusting sleeve through threads, and the upper portion of the adjusting sleeve is connected with the connecting rod through threads. The screw thread directions of the stay bar and the connecting rod are opposite. The tail end of the connecting rod is provided with a double-lug structure, and the connecting shaft is hinged with the double-lug structure. The middle part of the connecting shaft is provided with a through hole, the pin shaft penetrates through the middle through hole of the connecting shaft, and the connecting shaft and the pin shaft form a cross-shaped connecting structure. The support is hinged with the pin shaft. The adjustable supporting device is fixedly connected with the platform through the support.
The number of the adjustable supporting devices is not less than three.
The utility model discloses have following advantage and beneficial effect:
1. the multi-degree-of-freedom adjustment of the test platform can be realized, any position can be simulated, the number of test beds is reduced, and the manufacturing cost of the test beds is reduced;
2. the screw thread is adopted to adjust the position of multiple degrees of freedom, the adjusting mode is simple, repeated disassembly of a test piece is avoided, and the adjusting efficiency is improved;
3. the method is suitable for various test verifications with different position requirements, has high universality and has great popularization and application values.
Drawings
Fig. 1 is a schematic view of an adjustable aircraft door test platform.
FIG. 2 is a detail view of the universal connection position of an adjustable test platform.
Detailed Description
As shown in fig. 1 to 2, an adjustable aircraft door test platform consists of an adjustable support device (1) and a platform (6). The adjustable supporting device (1) is composed of a supporting rod (2), an adjusting sleeve (3), a connecting rod (4), a support (5), a connecting shaft (8) and a pin shaft (9). One end of the support rod (2) is fixedly connected with the ground, the other end of the support rod is connected with the lower part of the adjusting sleeve (3) through threads, and the upper part of the adjusting sleeve (3) is connected with the connecting rod (4) through threads. The screw thread directions of the stay bar (2) and the connecting rod (4) are opposite. A double-lug structure (7) is designed at the tail end of the connecting rod (4), and the connecting shaft (8) is hinged with the double-lug structure (7). A through hole is formed in the middle of the connecting shaft (8), the pin shaft (9) penetrates through the through hole in the middle of the connecting shaft (8), and the connecting shaft (8) and the pin shaft (9) form a cross-shaped connecting structure. The support (5) is hinged with the pin shaft (9). The adjustable supporting device (1) is fixedly connected with the platform (6) through the support (5).
The number of the adjustable supporting devices (1) is not less than three.
When in specific use: according to the specific position requirement of the platform (6), the height of each adjustable supporting device is calculated, the adjusting sleeve (3) is rotated, and the height of each adjustable supporting device (1) is adjusted respectively until the position of the platform (6) meets the requirement.
Claims (2)
1. An adjustable aircraft door test platform, characterized in that: consists of an adjustable supporting device and a platform; the adjustable supporting device consists of a supporting rod, an adjusting sleeve, a connecting rod, a support, a connecting shaft and a pin shaft; one end of the support rod is fixedly connected with the ground, the other end of the support rod is connected with the lower part of the adjusting sleeve through threads, and the upper part of the adjusting sleeve is connected with the connecting rod through threads; the screw thread directions of the stay bar and the connecting rod are opposite; a double-lug structure is designed at the tail end of the connecting rod, and the connecting shaft is hinged with the double-lug structure; a through hole is formed in the middle of the connecting shaft, the pin shaft penetrates through the through hole in the middle of the connecting shaft, and the connecting shaft and the pin shaft form a cross-shaped connecting structure; the support is hinged with the pin shaft; the adjustable supporting device is fixedly connected with the platform through the support.
2. An adjustable aircraft door test platform according to claim 1, wherein: the number of the adjustable supporting devices is not less than three.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023220920.4U CN214524458U (en) | 2020-12-28 | 2020-12-28 | Adjustable aircraft cabin door test platform |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202023220920.4U CN214524458U (en) | 2020-12-28 | 2020-12-28 | Adjustable aircraft cabin door test platform |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN214524458U true CN214524458U (en) | 2021-10-29 |
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ID=78297856
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202023220920.4U Active CN214524458U (en) | 2020-12-28 | 2020-12-28 | Adjustable aircraft cabin door test platform |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN214524458U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR102615009B1 (en) * | 2023-06-07 | 2023-12-19 | (주)위플로 | Adjustable horizontally inspection apparatus for aircraft |
-
2020
- 2020-12-28 CN CN202023220920.4U patent/CN214524458U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR102615009B1 (en) * | 2023-06-07 | 2023-12-19 | (주)위플로 | Adjustable horizontally inspection apparatus for aircraft |
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