CN219468000U - Main landing gear cabin door - Google Patents
Main landing gear cabin door Download PDFInfo
- Publication number
- CN219468000U CN219468000U CN202320584325.3U CN202320584325U CN219468000U CN 219468000 U CN219468000 U CN 219468000U CN 202320584325 U CN202320584325 U CN 202320584325U CN 219468000 U CN219468000 U CN 219468000U
- Authority
- CN
- China
- Prior art keywords
- landing gear
- door body
- cabin door
- stay
- joint
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Body Structure For Vehicles (AREA)
Abstract
The utility model belongs to the technical field of aviation, and relates to a main landing gear cabin door. Comprising the following steps: the landing gear cabin door body (1), at least two stay bars (2) and adjustable joint pair (3), wherein, landing gear cabin door body (1) is shell structure, transversely cuts into the curve, and longitudinal cut is the straight line, and two horizontal outer edges of landing gear cabin door body (1) are connected through two stay bars (2) respectively, and two stay bars (2) are located the both ends of the horizontal direction of landing gear cabin door body (1) respectively, and two stay bars (2) are all connected through adjustable joint pair (3) with landing gear cabin door body (1).
Description
Technical Field
The utility model belongs to the technical field of aviation, and relates to a main landing gear cabin door.
Background
The main landing gear cabin door has the functions of rectifying and protecting, does not participate in the whole force transmission of the machine body structure, has the design index of rigidity, and can not produce harmful deformation affecting the retraction of the landing gear in the opening and closing process of the main landing gear cabin door when the clearance and the step difference between the cabin door and the machine body skin are required to meet the design requirements after the main landing gear cabin door is closed in a shutdown state. The existing main landing gear cabin door has the problem that local skin deformation, gaps and step differences exceed the rigidity required by design under the shutdown condition.
Disclosure of Invention
The utility model aims to: a main landing gear door is provided to overcome the problem of insufficient local stiffness of existing landing gear doors.
The technical scheme is as follows:
a main landing gear door comprising: the landing gear cabin door body 1, at least two stay bars 2, adjustable joint pair 3, wherein, landing gear cabin door body 1 is shell structure, transversely cuts into the curve, and vertically cuts into straight line, and two horizontal outer fringe of landing gear cabin door body 1 is connected through two stay bars 2 respectively, and two stay bars 2 are located the both ends of the horizontal direction of landing gear cabin door body 1 respectively, and two stay bars 2 are all connected through adjustable joint pair 3 with landing gear cabin door body 1.
Further, the adjustable joint pair 3 comprises a base joint 3-1, a stay bar joint 3-2 and a pin 6, wherein the base joint 3-1 is fixed with the landing gear cabin door body 1, and the other end of the base joint 3-1 is provided with two ears; one end of the stay bar connector 3-2 is in threaded connection with the stay bar 2, the other end of the stay bar connector 3-2 is a single lug, and the other end of the base connector 3-1 is connected with the other end of the stay bar connector 3-2 through a pin 6.
Further, an adjustable spacer 4 is provided between the base joint 3-1 and the landing gear door body 1.
Further, the base joint 3-1 is fixed to the landing gear door body 1 by a connector 5.
Further, a middle section in the transverse direction of the landing gear door body 1 is provided with a stay bar 2.
Further, the stay bar 2 is a hollow tubular structure.
The beneficial effects are that:
according to the main landing gear cabin door, the force transmission path is optimized, so that the rigidity of the door is greatly improved under the condition that the requirements of strength and rigidity are met; manufacturing errors are compensated for by the adjustable spacer and the adjustable brace. The method effectively improves the harmful influence caused by insufficient local rigidity of the existing aircraft landing gear cabin door, and reduces the manufacturing difficulty.
Drawings
FIG. 1 is a schematic view of a landing gear door body configuration;
FIG. 2 is a schematic diagram of the connection between a base joint and a brace;
FIG. 3 is a schematic illustration of a strut joint and strut connection;
FIG. 4 is a schematic view of the connection of the base joint to the landing gear door body;
wherein: 1. the landing gear cabin door comprises a landing gear cabin door body, a supporting rod, an adjustable joint pair, a base joint, a supporting rod joint, an adjustable gasket, a connecting piece and a pin, wherein the landing gear cabin door body, the supporting rod, the adjustable joint pair, the base joint, the supporting rod joint, the adjustable gasket and the connecting piece are respectively arranged in sequence, and the landing gear cabin door body, the supporting rod, the adjustable joint pair, the base joint, the supporting rod joint, the adjustable gasket and the connecting piece are respectively arranged in sequence.
Detailed Description
According to the utility model, by optimizing the force transmission path, the rigidity of the opening cover is improved and the harmful influence of the deformation of the cabin door is reduced under the condition of meeting the requirements of strength and rigidity; the partition plate for the conventional cabin door structure overcomes the limitation that the rigidity of the opening cover is weak, and the external supporting structure is adopted in a breakthrough manner, so that the structural weight is effectively reduced on the premise of not affecting the space, and the harmful effect caused by the insufficient local rigidity of the cabin door of the conventional aircraft landing gear is effectively improved.
In order to solve the technical problems, the utility model is realized by the following technical scheme:
1) Optimizing a force transmission route, designing a front (middle) and rear stay bar on a landing gear cabin door body, wherein the stay bar is a two-force bar which is used as a main anti-deformation member and is connected with the skin and a baffle plate of the landing gear cabin door body, and when the cabin door is deformed, load is transmitted to the stay bar and is converted into axial stretching and compression of the stay bar, so that the force transmission is direct;
2) The stay bar is a hollow tubular part instead of a solid rod, and the optimal weight result of the stay bar profile under the working conditions of tension load and ballast load is achieved by reasonably optimizing the tubular profile;
3) And the two ends of the stay bar are provided with single-lug connectors which are connected with the stay bar through threads, and the length of the stay bar can be finely adjusted by adjusting the threaded fit length on the single-lug connectors so as to compensate manufacturing errors.
4) A double-lug fork joint base is designed on the main landing gear cabin door body, an adjustable gasket is added on the base and the landing gear cabin door body support, and manufacturing errors are compensated.
A landing gear door configuration according to the utility model is described in detail below with reference to the accompanying drawings.
As shown in fig. 1-4, a base joint 3-1 is mounted on the landing gear door body 1, and an adjustable gasket 4 is mounted between the base joint 3-1 and the landing gear door body 1 and is connected together through a connecting piece 5.
The base joint 3-1, the stay bar joint 3-2 and the adjustable gasket 4 form an adjustable joint pair 3 together, so as to adjust the length of the stay bar and compensate manufacturing errors.
The two ends of the stay bar 2 are connected with the stay bar joints 3-2 through threads.
When the stay bar is installed, the stay bar connector 3-2 is connected with the base connector 3-1 through the pin 6, so that force transmission is ensured.
Claims (6)
1. A main landing gear door, comprising: the landing gear cabin door body (1), at least two stay bars (2) and adjustable joint pair (3), wherein, landing gear cabin door body (1) is shell structure, transversely cuts into the curve, and longitudinal cut is the straight line, and two horizontal outer edges of landing gear cabin door body (1) are connected through two stay bars (2) respectively, and two stay bars (2) are located the both ends of the horizontal direction of landing gear cabin door body (1) respectively, and two stay bars (2) are all connected through adjustable joint pair (3) with landing gear cabin door body (1).
2. The main landing gear door according to claim 1, wherein the adjustable joint pair (3) comprises a base joint (3-1), a stay joint (3-2) and a pin (6), the base joint (3-1) is fixed with the landing gear door body (1), and the other end of the base joint (3-1) is provided with two ears; one end of the stay bar connector (3-2) is in threaded connection with the stay bar (2), the other end of the stay bar connector (3-2) is a single lug, and the other end of the base connector (3-1) is connected with the other end of the stay bar connector (3-2) through a pin (6).
3. Main landing gear door according to claim 1, characterized in that an adjustable spacer (4) is provided between the base joint (3-1) and the landing gear door body (1).
4. Main landing gear door according to claim 1, characterized in that the base joint (3-1) is fixed to the landing gear door body (1) by means of a connection (5).
5. Main landing gear door according to claim 1, characterized in that the middle section of the landing gear door body (1) in the transverse direction is provided with a stay (2).
6. Main landing gear door according to claim 1, characterized in that the stay (2) is of hollow tubular construction.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320584325.3U CN219468000U (en) | 2023-03-22 | 2023-03-22 | Main landing gear cabin door |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202320584325.3U CN219468000U (en) | 2023-03-22 | 2023-03-22 | Main landing gear cabin door |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN219468000U true CN219468000U (en) | 2023-08-04 |
Family
ID=87438111
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202320584325.3U Active CN219468000U (en) | 2023-03-22 | 2023-03-22 | Main landing gear cabin door |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN219468000U (en) |
-
2023
- 2023-03-22 CN CN202320584325.3U patent/CN219468000U/en active Active
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |