CN211543859U - Airplane floor supporting device - Google Patents
Airplane floor supporting device Download PDFInfo
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- CN211543859U CN211543859U CN201922428109.6U CN201922428109U CN211543859U CN 211543859 U CN211543859 U CN 211543859U CN 201922428109 U CN201922428109 U CN 201922428109U CN 211543859 U CN211543859 U CN 211543859U
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- support
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- pipe
- aircraft floor
- support pipe
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Abstract
The utility model provides an aircraft floor strutting arrangement, connects between aircraft floor and fuselage frame, its characterized in that: the aircraft floor support comprises a first support pipe, a second support pipe and a connecting joint, wherein the lower end of the first support pipe is inserted into the upper end of the second support pipe, the connecting joint is of a single lug structure, and the connecting joint is connected to the lower end of the second support pipe. Under the action of axial impact load, the device is triggered, the first supporting tube moves towards the second supporting tube quickly, the tube wall of the second supporting tube is extruded to expand, impact energy is absorbed, deformation in the process is uniform, impact duration is long, impact load is small, damage to other parts of the airplane is reduced, and the purpose of protecting passengers is achieved.
Description
Technical Field
The utility model belongs to aviation structural design field, concretely relates to aircraft floor strutting arrangement.
Background
Safety is a fundamental requirement for civil aircraft operation, which must meet crashworthiness requirements in order to ensure that passengers can survive a survivable accident. The general layout of a civil aircraft fuselage is as follows: the passenger cabin is arranged above the floor, and the luggage cabin is arranged below the floor. The under-floor structure of the passenger cabin of a civil fuselage is an important area for the design of improving the crashworthiness of the airplane, and the support of the airplane floor is one of important design units.
The airplane floor support is positioned at the lower part of the floor, is connected with the floor cross beam and the airplane body frame, plays a role in supporting the floor, and transmits load on the floor to the lower wall plate in the form of axial force. The existing civil aircraft floor support is generally an open-section beam structure or a closed-section thin-wall pipe fitting, the aircraft floor support is greatly deformed and absorbs impact energy in the process of falling and colliding of an aircraft, but finite element calculation results and a typical frame section falling and colliding test of a fuselage indicate that the aircraft floor support is generally integrally bent and hardly generates progressive buckling, the absorption energy is limited, and the deformation mode of the aircraft floor support is uncontrollable in the process of falling and colliding of the aircraft.
Disclosure of Invention
In order to solve the problem, the utility model provides an aircraft floor strutting arrangement to improve the aircraft and weigh down the energy-absorbing effect and the control deformation of hitting the in-process.
The utility model provides an aircraft floor strutting arrangement, connects between aircraft floor and fuselage frame, its characterized in that: the aircraft floor support comprises a first support pipe, a second support pipe and a connecting joint, wherein the lower end of the first support pipe is inserted into the upper end of the second support pipe, the connecting joint is of a single lug structure, and the connecting joint is connected to the lower end of the second support pipe.
The lower end of the first supporting pipe is provided with a wedge-shaped contraction section, and the upper end of the second supporting pipe is provided with a bell mouth expansion section corresponding to the lower end of the first supporting pipe.
And a cavity of the second supporting tube is filled with foamed aluminum material.
Friction grains are arranged on the outer wall of the wedge-shaped contraction section at the lower end of the first supporting pipe, and friction grains are arranged on the inner wall of the horn mouth expansion section at the upper end of the second supporting pipe.
The rigidity of the first support tube is greater than that of the second support tube.
In the aircraft crash process, the aircraft floor of this application supports and bears axial impact load, first stay tube inserts the second stay tube gradually, make the second stay tube expand gradually, along with the continuation of impact time, the second stay tube is constantly expanded, first stay tube and the continuous increase of second stay tube overlap portion, the impact energy is absorbed through expansion deformation to the second stay tube, on the other hand, the foamed aluminium material who fills in the second stay tube receives the extrusion, also can absorb partly impact energy, and first stay tube does not take place to buckle with the second stay tube in impact process, buckling deformation, deformation process is controllable.
The utility model has the advantages that: under the action of axial impact load (vertical overload caused when the airplane is forced to land), the device is triggered, the first supporting pipe moves towards the second supporting pipe quickly to extrude the pipe wall of the second supporting pipe to expand and absorb impact energy, the deformation in the process is uniform, the impact duration is long, the impact load is small, the damage to other parts of the airplane is reduced, and the purpose of protecting passengers is achieved. Compared with the existing open-section or closed-section airplane floor support frame, the defects that the whole support frame is bent, gradual buckling is difficult to generate, the absorbed energy is limited, and the deformation mode of the support frame is uncontrollable in the airplane crash process are overcome.
The present application is described in further detail below with reference to the accompanying drawings of embodiments.
Drawings
Fig. 1 is a schematic structural view of an aircraft floor support.
Fig. 2 is a schematic cross-sectional view of an aircraft floor support.
FIG. 3 is a schematic view of the connection of an aircraft floor support structure to a fuselage.
Wherein, 1 first stay tube, 2 second stay tubes, 3 expansion sections, 4 attach fittings, 5 contraction sections, 6 foamed aluminum material, 7 aircraft floor supports, 8 floor crossbeams, 9 fuselage frames, 10 fuselages.
Detailed Description
Referring to the attached drawings, the airplane floor support device is connected between a floor beam 8 and a fuselage frame 9 of an airplane floor, and comprises a first support pipe 1, a second support pipe 2 and a connecting joint 4, wherein the lower end of the first support pipe 1 is inserted into the upper end of the second support pipe 2, the connecting joint 4 is of a single lug structure, and the connecting joint 4 is connected to the lower end of the second support pipe 2 through threads.
The lower end of the first supporting pipe 1 is provided with a wedge-shaped contraction section 5, and the upper end of the second supporting pipe 2 is provided with a bell mouth expansion section 3 corresponding to the lower end of the first supporting pipe 1.
The cavity of the second support tube 2 is filled with foamed aluminum material 6.
Friction grains are arranged on the outer wall of the wedge-shaped contraction section at the lower end of the first supporting pipe 1, and friction grains are arranged on the inner wall of the bell mouth expansion section at the upper end of the second supporting pipe 2.
The rigidity of the first support tube 1 is greater than that of the second support tube 2. The first support tube and the second support tube are preferably of the same length.
When in use, the upper end of the aircraft floor support 7 is connected to a floor beam 8 of an aircraft cabin, and the lower end of the aircraft floor support 7 is connected with a fuselage frame 9 of a fuselage 10 through a lug.
The technical characteristics ensure the connection rigidity of the first supporting tube and the second supporting tube so as to meet the static strength design requirement of the aircraft floor supporting device.
The utility model discloses a new thinking designs the aircraft floor and supports to improve the energy-absorbing effect and the control of aircraft at the weight and hit the in-process and warp. The airplane floor support 7 bears axial impact load in the process of crash, the first support pipe 1 is gradually inserted into the second support pipe 2, so that the second support pipe 2 gradually expands, the second support pipe 2 continuously expands along with the continuation of impact time, the overlapping part of the first support pipe 1 and the second support pipe 2 is continuously increased, the second support pipe 2 absorbs impact energy through expansion deformation, the first support pipe 1 and the second support pipe 2 do not bend or bend and deform in the impact process, and the deformation process is controllable.
It will be appreciated that the contraction section 5 and the expansion section 3 together form a connection region, the inner surface of the second support tube 2 and the outer surface of the contraction section of the first support tube, should be roughened, and the first support tube 1 and the second support tube 2 are connected together by friction generated by extrusion, for example, the inner surface of the expansion section 3 and the outer surface of the contraction section 5 are provided with friction lines.
In this embodiment, the first support tube 1 and the second support tube 2 have the same length. This enables the second support tube 2 to have sufficient capacity to house the first support tube 1 while at the same time maximizing the variable length of the aircraft floor support. The first supporting tube and the second supporting tube are aluminum alloy thin-wall cylindrical tubes with equal length, and the first supporting tube is larger in diameter, larger in wall thickness and higher in material rigidity than the second supporting tube, so that the first supporting tube is inserted into the second supporting tube to force the second supporting tube to expand and deform in the impact process.
In this embodiment, the length of the expanding section 3 is not less than 30% to 50% of the length of the second support tube 2. Similarly, the length of the contraction section 5 is not less than 30-50% of the length of the first support pipe 1. So that there is enough buffering squeezing space.
The first support tube 1 and the second support tube 2 are made of aluminum alloy. When the aluminum alloy material is selected, firstly, static stiffness checking is carried out on a first supporting pipe 1, a second supporting pipe 2 and a connecting joint 4 of the designed airplane floor support, so that the requirement of supporting a cabin floor is met; under the action of axial impact load (vertical overload caused when an airplane is forced to land), the device is triggered, the first supporting tube 1 moves towards the second supporting tube 2 quickly to extrude the tube wall of the second supporting tube 2 to expand to absorb impact energy, on the other hand, the foamed aluminum material 6 filled in the second supporting tube 2 is extruded to absorb a part of the impact energy, and the first supporting tube 1 and the second supporting tube 2 do not bend or bend to deform in the impact process, and the deformation process is controllable. The deformation in the process is uniform, the impact duration is long, the impact load is small, the damage to other parts of the airplane is reduced, and the purpose of protecting passengers is achieved.
Claims (5)
1. The utility model provides an aircraft floor strutting arrangement, connects between aircraft floor and fuselage frame, its characterized in that: the aircraft floor support comprises a first support pipe, a second support pipe and a connecting joint, wherein the lower end of the first support pipe is inserted into the upper end of the second support pipe, the connecting joint is of a single lug structure, and the connecting joint is connected to the lower end of the second support pipe.
2. An aircraft floor support assembly as claimed in claim 1 wherein the first support tube has a tapered lower end and the second support tube has a flared upper end corresponding to the lower end of the first support tube.
3. An aircraft floor support arrangement according to claim 1 wherein the lumen of the second support tube is filled with an aluminium foam material.
4. An aircraft floor support assembly as claimed in claim 1 wherein friction ridges are provided on the outer wall of the wedge-shaped convergent section at the lower end of said first support tube and friction ridges are provided on the inner wall of the flared section at the upper end of said second support tube.
5. An aircraft floor support arrangement according to claim 1, wherein the stiffness of the first support tube is greater than the stiffness of the second support tube.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922428109.6U CN211543859U (en) | 2019-12-27 | 2019-12-27 | Airplane floor supporting device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922428109.6U CN211543859U (en) | 2019-12-27 | 2019-12-27 | Airplane floor supporting device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211543859U true CN211543859U (en) | 2020-09-22 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922428109.6U Active CN211543859U (en) | 2019-12-27 | 2019-12-27 | Airplane floor supporting device |
Country Status (1)
| Country | Link |
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| CN (1) | CN211543859U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113044198A (en) * | 2021-03-09 | 2021-06-29 | 上海交通大学 | Collision energy-absorbing diagonal strut capable of being fixedly connected and hinged under airplane floor |
-
2019
- 2019-12-27 CN CN201922428109.6U patent/CN211543859U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113044198A (en) * | 2021-03-09 | 2021-06-29 | 上海交通大学 | Collision energy-absorbing diagonal strut capable of being fixedly connected and hinged under airplane floor |
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