CN217533251U

CN217533251U - Aircraft seat energy absorption device

Info

Publication number: CN217533251U
Application number: CN202221793298.2U
Authority: CN
Inventors: 徐策; 邵良; 石晓龙
Original assignee: Zhejiang Zhonghang Tongfei Research Institute Co ltd
Current assignee: Zhejiang Zhonghang Tongfei Research Institute Co ltd
Priority date: 2022-07-08
Filing date: 2022-07-08
Publication date: 2022-10-04
Anticipated expiration: 2032-07-08

Abstract

The application discloses aircraft seat energy absorption device, including chair basin frame and chair basin, still include energy-absorbing aluminium honeycomb piece, the chair basin is rotatable to be installed on chair basin frame, energy-absorbing aluminium honeycomb piece sets up between chair basin frame and chair basin, the up end of energy-absorbing aluminium honeycomb piece with the cooperation is glued to the lower surface of chair basin frame. This application improves the seat, places energy-absorbing aluminium honeycomb piece under the seat basin, thereby utilizes energy-absorbing aluminium honeycomb piece can be compressed under the loaded condition characteristic of energy absorption, and the maximum protection passenger when the seat receives violent vertical impact realizes that it avoids receiving the injury.

Description

Aircraft seat energy absorption device

Technical Field

The utility model relates to an aircraft structure field especially relates to an aircraft seat energy absorption device.

Background

The seat is widely applied to various vehicles such as airplanes, high-speed rails, automobiles, ships and the like, the types of the seat are various, and the general structure of the airplane seat in the prior art can refer to patent document with publication number CN106628190 a: the chair comprises a chair basin frame body (namely a chair basin frame), a chair basin (namely a chair basin) fixed on the chair basin frame body and a chair back. Wherein the chair basin is fixed and only the chair back is adjustable. The seat fixed by the seat basin generally only depends on the soft cushion wrapped on the seat basin to relieve the impact on the passenger, and in the landing process of the airplane, the vertical impact on the seat is far greater than the impact on the seat in the land vehicle at ordinary times, so that the probability of injury of the passenger when the passenger is subjected to vertical violent impact is greatly increased, and the soft cushion wrapped by the seat is not enough.

SUMMERY OF THE UTILITY MODEL

To the above problem, the utility model provides an aircraft seat energy absorption device.

The utility model discloses the technical scheme who takes as follows:

the utility model provides an aircraft seat energy absorption device, includes chair basin frame and chair basin, still includes energy-absorbing aluminium honeycomb piece, the chair basin is installed on chair basin frame, energy-absorbing aluminium honeycomb piece sets up between chair basin frame and chair basin, the up end of energy-absorbing aluminium honeycomb piece with the cooperation of gluing of the lower surface of chair basin frame.

This application improves the seat, places energy-absorbing aluminium honeycomb piece under the seat basin, thereby utilizes energy-absorbing aluminium honeycomb piece can be compressed under the loaded condition characteristic of energy absorption, and the maximum protection passenger when the seat receives violent vertical impact realizes that it avoids receiving the injury.

In one embodiment of the present invention, the chair basin covers the upper end of the chair basin frame, the upper end of the chair basin frame has a recessed opening, and the recessed opening forms a supply for the movable space of the chair basin moving down.

In one embodiment of the present invention, one end of the chair basin is rotatably mounted on the chair basin frame, and the energy-absorbing aluminum honeycomb block is located at the other end of the chair basin.

In one embodiment of the present invention, there are two energy-absorbing aluminum honeycomb blocks symmetrically disposed on two sides of the basin frame.

In one embodiment of the present invention, the chair basin frame has a mounting base therein, and the energy-absorbing aluminum honeycomb block is fixed on the mounting base.

In one embodiment of the present invention, the energy-absorbing aluminum honeycomb block is bonded to the mounting base.

In one embodiment of the present invention, the chair further comprises a movable hinge, and the chair basin is rotatably mounted on the chair basin frame through the movable hinge.

In one embodiment of the present invention, the living hinge is L-shaped, the living hinge includes a first portion, a second portion and a transition portion connecting the first portion and the second portion, the first portion is connected to the seat pan via a fastener, and the second portion is connected to the seat pan frame via a fastener. The movable hinge is convenient and reliable to install.

In one embodiment of the present invention, the transition portion has at least one opening.

The beneficial effects of the utility model are that: this application improves the seat, places energy-absorbing aluminium honeycomb piece under the seat basin, thereby utilizes energy-absorbing aluminium honeycomb piece can be compressed under the loaded condition characteristic of energy absorption, and the maximum protection passenger when the seat receives violent vertical impact realizes that it avoids receiving the injury.

Drawings

FIG. 1 is a schematic structural view of an aircraft seat energy absorption apparatus of the present invention;

fig. 2 is an exploded view of the aircraft seat energy absorption apparatus of the present invention.

The figures are numbered:

1. a chair basin frame; 2. a chair basin; 3. an energy-absorbing aluminum honeycomb block; 4. a recessed port; 5. installing a base; 6. a living hinge; 7. a first portion; 8. a second portion; 9. a transition portion; 10. a fastener; 11. and (4) opening.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application. It is to be understood that the embodiments described are only a few embodiments of the present application and not all embodiments. The components of the embodiments of the present application, generally described and illustrated in the figures herein, can be arranged and designed in a wide variety of different configurations.

In the description of the present application, it should be noted that the terms "inside", "outside", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings or orientations or positional relationships that the products of the application usually place when using, and are only used for convenience in describing the present application and simplifying the description, but do not indicate or imply that the devices or elements that are referred to must have a specific orientation, be constructed in a specific orientation, and operate, and thus, should not be construed as limiting the present application. Furthermore, the terms "first," "second," and the like are used merely to distinguish one description from another, and are not to be construed as indicating or implying relative importance.

In the description of the present application, it should also be noted that, unless expressly stated or limited otherwise, the terms "disposed" and "connected" are to be construed broadly, and may for example be fixedly connected, detachably connected, or integrally connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present application can be understood in a specific case by those of ordinary skill in the art.

The present invention will be described in detail with reference to the accompanying drawings.

As shown in figures 1 and 2, the aircraft seat energy absorption device comprises a seat basin frame 1, a seat basin 2 and an energy-absorbing aluminum honeycomb block 3, wherein the seat basin 2 is rotatably installed on the seat basin frame 1, the energy-absorbing aluminum honeycomb block 3 is arranged between the seat basin frame 1 and the seat basin 2, and the upper end face of the energy-absorbing aluminum honeycomb block 3 is matched with the seat basin frame 1 in a gluing mode.

In this embodiment, the seat pan 2 covers the upper end of the seat pan frame 1, the upper end of the seat pan frame 1 has a recessed opening 4, and the recessed opening 4 forms an activity space for the seat pan 2 to move down.

In this embodiment, one end of the seat pan 2 is mounted on the seat pan frame 1, and the energy-absorbing aluminum honeycomb block 3 is located at the other end of the seat pan 2. Specifically, one end of the seat pan 2 is installed at the front end (the left position in fig. 1) of the seat pan frame 1, the energy-absorbing aluminum honeycomb block 3 is arranged below the other end of the seat pan 2, after a person sits on the seat, the force borne by the rear end (the right position in fig. 1) of the seat pan 2 is the largest, and the energy-absorbing aluminum honeycomb block 3 is arranged below the rear end of the seat pan 2 to better absorb energy.

In this embodiment, there are two energy-absorbing aluminum honeycomb blocks 3 symmetrically disposed on two sides of the seat frame 1.

In the embodiment, the chair basin frame 1 is internally provided with a mounting base 5, and the energy-absorbing aluminum honeycomb block 3 is fixed on the mounting base 5.

In this embodiment, the energy absorbing aluminum honeycomb block 3 is bonded to the mounting base 5.

In practical application, the energy-absorbing aluminum honeycomb block 3 can be fixed by adopting a double-faced adhesive tape adhesion mode in consideration of low cost and convenience in replacement.

In the embodiment, the chair comprises a movable hinge 6, and the chair basin 2 is rotatably arranged on the chair basin frame 1 through the movable hinge 6.

In this embodiment, the living hinge 6 is L-shaped, the living hinge 6 includes a first portion 7, a second portion 8, and a transition portion 9 connecting the first portion 7 and the second portion 8, the first portion 7 is connected to the seat pan 2 by a fastener 10, and the second portion 8 is connected to the seat pan frame 1 by a fastener 10. The movable hinge 6 is arranged in such a way that the installation is convenient and reliable.

In the present embodiment, the transition portion 9 has at least one opening 11.

The working principle of the application is as follows: when the seat is not impacted vertically, the energy-absorbing aluminum honeycomb blocks 3 enable the seat pan 2 to be kept horizontal at the front end and the rear end, and the seat is the same as a common fixed seat, so that passengers can conveniently sit on the seat. Under the circumstances such as aircraft landing, when the seat received vertical impact, transmit vertical impact load to energy-absorbing aluminium honeycomb piece 3 through chair basin 2 on, energy-absorbing aluminium honeycomb piece 3 can be compressed after the load, because chair basin 2 front end and the articulated cooperation of chair basin frame 1, can make chair basin 2 along 3 compression direction movements of energy-absorbing aluminium honeycomb piece, until laminating with the border of chair basin frame 1, energy-absorbing aluminium honeycomb piece 3 reaches the maximum compression volume this moment, so far furthest absorbed impact energy, thereby play protection passenger's effect.

The above only is the preferred embodiment of the present invention, not therefore the limit the patent protection scope of the present invention, all applications the equivalent structure transformation made by the contents of the specification and the drawings of the present invention is directly or indirectly applied to other related technical fields, and all the same principles are included in the protection scope of the present invention.

Claims

1. The utility model provides an aircraft seat energy absorption device, includes chair basin frame and chair basin, its characterized in that still includes energy-absorbing aluminium honeycomb piece, the chair basin is rotatable to be installed on chair basin frame, energy-absorbing aluminium honeycomb piece sets up between chair basin frame and chair basin, the up end of energy-absorbing aluminium honeycomb piece with the cooperation is glued to the lower surface of chair basin frame.

2. An aircraft seat energy absorbing device as in claim 1, wherein said seat pan covers an upper end of said seat pan frame, said seat pan frame upper end having a recessed opening that forms a living space for said seat pan to move downward.

3. An aircraft seat energy absorbing device as in claim 2, wherein one end of said seat pan is rotatably mounted to a seat pan frame, and said energy absorbing aluminum honeycomb block is located at the other end of said seat pan.

4. An aircraft seat energy absorbing device as in claim 3, wherein two of said energy absorbing aluminum honeycomb blocks are symmetrically disposed on either side of the seat pan frame.

5. An aircraft seat energy absorbing device as in claim 1, wherein said seat pan frame has a mounting base therein, said energy absorbing aluminum honeycomb block being secured to said mounting base.

6. An aircraft seat energy absorbing device according to claim 5, wherein said energy absorbing aluminum honeycomb block is bonded to said mounting base.

7. An aircraft seat energy absorbing device according to claim 1, further comprising a living hinge by which the seat pan is mounted on the seat pan frame.

8. An aircraft seat energy absorbing device according to claim 7, wherein the living hinge is L-shaped and comprises a first portion connected to the seat pan by a fastener, a second portion connected to the seat pan frame by a fastener, and a transition portion connecting the first portion and the second portion.

9. An aircraft seat energy absorbing device according to claim 8, wherein said transition portion has at least one opening.