CN213566442U - Aircraft undercarriage - Google Patents
Aircraft undercarriage Download PDFInfo
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- CN213566442U CN213566442U CN202021357994.XU CN202021357994U CN213566442U CN 213566442 U CN213566442 U CN 213566442U CN 202021357994 U CN202021357994 U CN 202021357994U CN 213566442 U CN213566442 U CN 213566442U
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- flexible beam
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Abstract
The utility model belongs to aircraft design and manufacturing field, concretely relates to aircraft undercarriage, this undercarriage includes: the aircraft comprises a first flexible beam, a second flexible beam, a third flexible beam, a first bush, a second bush and a third bush, wherein the first bush is arranged at one end of the first flexible beam, the other end of the first flexible beam is connected with one end of the third flexible beam, the third bush is arranged at the joint, the other end of the third flexible beam is connected with one end of the second flexible beam, the second bush is arranged at the other end of the second flexible beam, one end of the first flexible beam and the other end of the second flexible beam are respectively used for being connected with an aircraft body, the joint of the first flexible beam and the third flexible beam is used for installing an aircraft wheel, the three flexible beams are of arc-shaped structures, and the three flexible beams are made of fiber reinforced composite materials. The double-cantilever structure is adopted to elastically deform to absorb impact energy when the aircraft lands, and the aircraft has the advantages of simple structure, light weight, no air-tightness requirement, simple maintenance and long service life.
Description
Technical Field
The utility model belongs to aircraft design and manufacturing field, concretely relates to aircraft undercarriage.
Background
At present, most of aircraft landing gears are aeroelastic strut type metal landing gears, impact energy generated when the aircraft lands is absorbed by compressing gas in struts or changing internal liquid distribution, and impact on an engine body structure and personnel is reduced. And the outer cylinder of the landing gear can pierce the structure of the machine body when the landing gear is overloaded, so that certain potential safety hazards exist.
SUMMERY OF THE UTILITY MODEL
Utility model purpose: an aircraft landing gear is provided with high safety to avoid safety hazards by piercing the airframe structure during an overload.
The technical scheme is as follows:
in a first aspect, there is provided an aircraft landing gear comprising: the airplane wheel mounting structure comprises a first flexible beam 2, a second flexible beam 4, a third flexible beam 5, a first bushing 1, a second bushing 3 and a third bushing 6, wherein the first bushing 1 is arranged at one end of the first flexible beam 2, the other end of the first flexible beam 2 is connected with one end of the third flexible beam 5, the third bushing 6 is arranged at the joint of the first flexible beam 2 and the third flexible beam 5, the other end of the third flexible beam 5 is connected with one end of the second flexible beam 4, the second bushing 3 is arranged at the other end of the second flexible beam 4, one end of the first flexible beam 2 and the other end of the second flexible beam 4 are respectively used for being connected with an airplane body, one end of the first flexible beam 2 is positioned in front of the airplane body compared with the other end of the second flexible beam 4, the joint of the first flexible beam 2 and the third flexible beam 5 is used for mounting an airplane wheel, and the first flexible beam 2, the second flexible beam 4 and the third flexible beam 5 are all of arc-shaped structures, the first flexible beam 2, the second flexible beam 4 and the third flexible beam 5 are made of fiber reinforced composite materials.
Further, the arc structure is a single-segment arc structure, and the single-segment arc structure comprises an arch.
Further, the arc-shaped structure is a multi-section arc-shaped structure, and the multi-section arc-shaped structure comprises a spring-like shape with an S shape, a Z shape or multiple radians.
Further, the first flexible beam 2, the second flexible beam 4 and the third flexible beam 5 are all in an arched shape, wherein the specific structural form of the first flexible beam 2 and the third flexible beam 5 is that the arched openings are forward, and the specific structural form of the second flexible beam 4 is that the arched openings are upward.
Further, the other end of the third flexible beam 5 is connected with the second flexible beam 4 by gluing, and the connection is wound with adhesive fiber.
Further, the first flexible beam 2, the second flexible beam 4 and the third flexible beam 5 are integrally formed.
Further, the fiber reinforced composite includes, but is not limited to: glass fiber reinforced epoxy resin-based composite materials, glass fiber reinforced polyether-ether-ketone thermoplastic composite materials and carbon fiber reinforced epoxy resin-based composite materials.
In a second aspect, an aircraft landing gear comprises: a first connecting end, a transition section and a second connecting end,
the first connecting end is used for being connected with the machine body, the transition section is of an arc-shaped structure and used for bearing stress, the second connecting end is used for mounting the machine wheel, the first connecting end and the second connecting end are provided with bushings, and the transition section is made of fiber reinforced composite materials.
Further, the transition section is of a multi-section arc structure.
Further, the fiber reinforced composite includes, but is not limited to: glass fiber reinforced epoxy resin-based composite materials, glass fiber reinforced polyether-ether-ketone thermoplastic composite materials and carbon fiber reinforced epoxy resin-based composite materials.
Has the advantages that:
the utility model discloses an undercarriage adopts cantilever structure, utilizes elastic deformation to absorb impact energy when the airborne vehicle descends, and this structure has advantages such as the structure is succinct, light in weight, airtight requirement, maintenance are simple, long service life.
Drawings
Fig. 1 is a schematic structural view of a landing gear according to a first embodiment of the present invention.
Wherein, first bush 1, first flexible roof beam 2, second bush 3, second flexible roof beam 4, third flexible roof beam 5, third bush 6.
Detailed Description
The present invention will be described in detail with reference to the accompanying drawings.
The first embodiment:
fig. 1 is a schematic structural view of a landing gear according to a first embodiment of the present invention. The landing gear in this embodiment includes a first flexible beam 2, a second flexible beam 4, a third flexible beam 5, and a first bushing 1, a second bushing 3, and a third bushing 6, where the first bushing 1 is disposed at one end of the first flexible beam 2, the other end of the first flexible beam 2 is connected to one end of the third flexible beam 5, the third bushing 6 is disposed at a joint of the first flexible beam 2 and the third flexible beam 5, the other end of the third flexible beam 5 is connected to one end of the second flexible beam 4, and the second bushing 3 is disposed at the other end of the second flexible beam 4. One end of the first flexible beam 2 and the other end of the second flexible beam 4 are respectively used for being connected with the machine body, and one end of the first flexible beam 2 is located in front of the machine body compared with the other end of the second flexible beam 4. The connection of the first flexible beam 2 and the third flexible beam 5 is used for mounting the wheel. The first flexible beam 2, the second flexible beam 4 and the third flexible beam 5 are all arc-shaped structures.
The arc structure comprises a single-section arc structure and a multi-section arc structure. The single segment arcuate structure includes an arcuate shape. The multi-segment arc structure comprises an S-shaped, Z-shaped or spring-like shape with a plurality of radians. Preferably, the first flexible beam 2, the second flexible beam 4 and the third flexible beam 5 are arched, wherein the specific structural form of the first flexible beam 2 and the third flexible beam 5 is that the arched openings are forward, the structure is simple, the processing is convenient, and the weight is light, and the maintenance is convenient. In case of a large load, it is preferable to replace the first and third flexible beams 2 and 5 with a multi-segment arc structure.
Preferably, the other end of the third flexible beam 5 is connected with the second flexible beam 4 by gluing, and the connection is wound with adhesive fiber to ensure the safety of the connection and reduce the weight.
The first flexible beam 2, the second flexible beam 4 and the third flexible beam 5 may be formed separately and then assembled, or may be formed integrally.
The materials of the first flexible beam 2, the second flexible beam 4 and the third flexible beam 5 are fiber reinforced composite materials, specifically, the materials may be reinforced composite materials of glass fibers or carbon fibers, including but not limited to: glass fiber reinforced epoxy resin-based composite materials, glass fiber reinforced polyether-ether-ketone thermoplastic composite materials (PEEK) and carbon fiber reinforced epoxy resin-based composite materials. The use of the above materials can increase elasticity and increase the life.
The specific implementation process comprises the following steps: 1. calculating and analyzing the load of the aircraft landing gear; 2. calculating the rigidity and the strength of the flexible beam according to the load; 3. selecting materials; 4. designing the appearance of a flexible beam of the composite landing gear and a composite material layer; 5. respectively co-curing and molding the flexible beam combination (the first bush 1, the first flexible beam 2, the third flexible beam 5 and the third bush 6) and the flexible beam (the second bush 3 and the second flexible beam 4); 6. gluing the flexible beam combination (the first bush 1, the first flexible beam 2, the third flexible beam 5 and the third bush 6) and the flexible beams (the second bush 3 and the second flexible beam 4), and winding and reinforcing; 7. mounted to an aircraft.
The principle is as follows: when the aircraft lands, impact force is transmitted to the flexible beams through the aircraft wheels, and the first flexible beam 2 and the third flexible beam 5 are subjected to bending deformation to absorb impact energy. When overloading, the third flexible beam 5 will also deform until it breaks, and no body-piercing will occur.
Second embodiment:
the landing gear of this embodiment takes the form of a single cantilever, specifically comprising a first connection end, a transition section and a second connection end. Wherein the first link end is used for being connected with the organism, and the changeover portion is used for bearing the weight of stress for the arc structure, and the second link end is used for installing the wheel. The first connecting end and the second connecting end are provided with bushings.
The arc structure described in the above embodiments includes a single-segment arc structure and a multi-segment arc structure. The single segment arcuate structure includes an arcuate shape. The multi-segment arc structure comprises an S-shaped, Z-shaped or spring-like shape with a plurality of radians.
Preferably, the transition section is in an arc shape, so that the structure is simple, the processing is convenient, and meanwhile, the weight is light, and the maintenance is convenient. In the case of large loads, a multi-segment arc structure is preferred.
The material of the transition section is a fiber reinforced composite material, and specifically can be a glass fiber or carbon fiber reinforced composite material, including but not limited to: glass fiber reinforced epoxy resin-based composite materials, glass fiber reinforced polyether-ether-ketone thermoplastic composite materials (PEEK) and carbon fiber reinforced epoxy resin-based composite materials. The use of the above materials can increase elasticity and increase the life.
The principle is as follows: when the aircraft lands, impact force is transmitted to the transition section through the aircraft wheels, and the transition section is bent and deformed to absorb impact energy. No piercing of the body occurs.
In summary, the embodiment adopts the cantilever structure, and utilizes the elastic deformation to absorb the impact energy when the aircraft lands, and the structure has the advantages of simple structure, light weight, no air-tightness requirement, simple maintenance, long service life and the like.
Claims (7)
1. An aircraft landing gear, comprising: a first flexible beam (2), a second flexible beam (4), a third flexible beam (5), and a first bushing (1), a second bushing (3), and a third bushing (6),
wherein, the first bush (1) is arranged at one end of the first flexible beam (2), the other end of the first flexible beam (2) is connected with one end of the third flexible beam (5), the third bush (6) is arranged at the joint of the first flexible beam (2) and the third flexible beam (5), the other end of the third flexible beam (5) is connected with one end of the second flexible beam (4), the second bush (3) is arranged at the other end of the second flexible beam (4), one end of the first flexible beam (2) and the other end of the second flexible beam (4) are respectively used for being connected with the machine body, and one end of the first flexible beam (2) is positioned in front of the machine body compared with the other end of the second flexible beam (4), the joint of the first flexible beam (2) and the third flexible beam (5) is used for installing the airplane wheel, the first flexible beam (2), the second flexible beam (4) and the third flexible beam (5) are all in arc structures, the first flexible beam (2), the second flexible beam (4) and the third flexible beam (5) are made of fiber reinforced composite materials.
2. A landing gear according to claim 1, wherein the arcuate structure is a single segment arcuate structure comprising an arcuate shape.
3. A landing gear according to claim 1, wherein the arcuate structure is a multi-segment arcuate structure comprising an S-shape, a Z-shape or a multiple arc spring-like shape.
4. Landing gear according to claim 1, wherein the first flexible beam (2), the second flexible beam (4) and the third flexible beam (5) are each arched, wherein the first flexible beam (2) and the third flexible beam (5) are embodied with an arched opening forward and the second flexible beam (4) is embodied with an arched opening upward.
5. Landing gear according to claim 1, wherein the other end of the third flexible beam (5) is adhesively connected to the second flexible beam (4) and where the connection is wrapped with adhesive fibres.
6. Landing gear according to claim 1, wherein the first flexible beam (2), the second flexible beam (4) and the third flexible beam (5) are integrally formed.
7. A landing gear according to claim 1, wherein the fibre-reinforced composite material includes, but is not limited to: glass fiber reinforced epoxy resin-based composite materials, glass fiber reinforced polyether-ether-ketone thermoplastic composite materials and carbon fiber reinforced epoxy resin-based composite materials.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021357994.XU CN213566442U (en) | 2020-07-10 | 2020-07-10 | Aircraft undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021357994.XU CN213566442U (en) | 2020-07-10 | 2020-07-10 | Aircraft undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN213566442U true CN213566442U (en) | 2021-06-29 |
Family
ID=76551669
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021357994.XU Active CN213566442U (en) | 2020-07-10 | 2020-07-10 | Aircraft undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN213566442U (en) |
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2020
- 2020-07-10 CN CN202021357994.XU patent/CN213566442U/en active Active
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