CN210707912U

CN210707912U - Collision energy absorption device for aircraft partition plate

Info

Publication number: CN210707912U
Application number: CN201921357964.6U
Authority: CN
Inventors: 林策; 洪苏雁; 李磊子
Original assignee: Avic Hubei Ali Jiatai Aircraft Equipment Co ltd
Current assignee: Avic Hubei Ali Jiatai Aircraft Equipment Co ltd
Priority date: 2019-08-20
Filing date: 2019-08-20
Publication date: 2020-06-09
Anticipated expiration: 2029-08-20

Abstract

The utility model discloses an aircraft baffle collision energy-absorbing device, it is installed on the preceding baffle of aircraft, aircraft baffle collision energy-absorbing device include: the energy-absorbing metal plate comprises a metal plate body and a first connecting piece, the metal plate body covers the opening end of a groove formed in the front partition plate, and the opening end of the groove is arranged around the edge of the metal plate body; the both sides of panel beating body all are provided with first connecting piece, every the equal one end of first connecting piece with panel beating body fixed connection, every the equal other end of first connecting piece with preceding baffle fixed connection, when aircraft head row seat passenger head and preceding baffle collided when the acceleration was strikeed, head row passenger's head can be strikeed on the energy-absorbing panel beating, thereby lead to first connecting piece is broken, the panel beating body simultaneously to the recess internal curvature to the energy of absorbing part head impact.

Description

Collision energy absorption device for aircraft partition plate

Technical Field

The utility model relates to an energy-absorbing device, concretely relates to aircraft baffle collision energy-absorbing device.

Background

According to airworthiness regulations, when the Head of a passenger collides with a front seat or an interior equipment (generally a partition) during emergency landing of an airplane, HIC (Head interior Criterion) verification is required, but when the distance between a seat reference point where the passenger sits and the front seat or a front side partition is more than 50 inches, HIC verification is not required. Currently, in the industry, the HIC verification between an aircraft seat and a seat is relatively mature, but the HIC verification between a head row seat and a front clapboard is not effectively solved. Therefore, when an airplane manufacturer designs a seat layout, the distance between the first row of seats and the front partition plate is generally designed to be larger so as to avoid HIC verification, which may reduce the installation amount of the airplane seats, or in a limited space between an emergency cabin door and the front partition plate of the airplane, the increase of the distance between the first row of seats and the front partition plate indirectly causes the reduction of the distance between the rows of seats in the space, thereby compressing the leg space of passengers and reducing the riding comfort.

SUMMERY OF THE UTILITY MODEL

An object of the utility model is to overcome above-mentioned technique not enough, provide an aircraft baffle collision energy-absorbing device for the aircraft is when acceleration strikes first row seat passenger head and preceding baffle collision energy-absorbing.

In order to achieve the technical purpose, the technical scheme of the utility model provide an aircraft baffle collision energy-absorbing device, it is installed on the preceding baffle of aircraft, aircraft baffle collision energy-absorbing device include: the energy-absorbing metal plate comprises a metal plate body and a first connecting piece, the metal plate body covers the opening end of a groove formed in the front partition plate, and the opening end of the groove is arranged around the edge of the metal plate body; the both sides of panel beating body all are provided with first connecting piece, every the equal one end of first connecting piece with panel beating body fixed connection, every the equal other end of first connecting piece with preceding baffle fixed connection.

Compared with the prior art, the beneficial effects of the utility model include: this aircraft baffle collision energy-absorbing device installs on the preceding baffle of aircraft, and when the aircraft was when the acceleration was strikeed first row seat passenger's head and preceding baffle collision, the head of first row passenger can strike on the energy-absorbing panel beating, thereby lead to first connecting piece is broken by the snap, the panel beating body simultaneously to the recess internal bending to absorb the energy that partial head was strikeed, play certain guard action to passenger's head.

Drawings

Fig. 1 is an explosion structure diagram of an embodiment of an aircraft partition collision energy absorption device provided by the present invention.

Fig. 2 is a partial enlarged structure diagram of the upper right corner of fig. 1.

Fig. 3 is a schematic front structural view of an embodiment of the energy-absorbing sheet metal provided by the present invention.

Fig. 4 is a schematic side structure diagram of an embodiment of the energy-absorbing sheet metal provided by the present invention.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more clearly understood, the present invention is further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

Referring to fig. 1 to 4, the present embodiment provides an aircraft bulkhead collision energy absorption device, which is installed on a front bulkhead 1 of an aircraft, and the aircraft bulkhead collision energy absorption device includes: the energy-absorbing sheet metal 2 comprises a sheet metal body 21 and a first connecting piece 22.

The panel beating body 21 cover in the open end of the recess that sets up on the preceding baffle 1, the open end of recess centers on the edge arrangement of panel beating body 21 makes the outer fringe of panel beating body 21 with the edge formation clearance of the open end of recess.

The both sides of panel beating body 21 all are provided with first connecting piece 22, every the equal one end of first connecting piece 22 with panel beating body 21 fixed connection, every the equal other end of first connecting piece 22 with 1 fixed connection of preceding baffle, in this embodiment, first connecting piece 22 with the integrative stamping forming of panel beating body 21, be provided with first locating hole 22a on the first connecting piece 22, aircraft baffle collision energy-absorbing device still include first installation nail b, the one end of first installation nail b is passed behind first locating hole 22a with 1 fixed connection of preceding baffle.

This aircraft baffle collision energy-absorbing device installs on the preceding baffle 1 of aircraft, and when the aircraft was collided with preceding baffle 1 in the head row seat passenger's head when the acceleration was strikeed, the head of the head row passenger can strike on the energy-absorbing panel beating 2, thereby lead to first connecting piece 22 is broken by the stretch, panel beating body 21 simultaneously to the recess internal curvature to absorb the energy that partial head was strikeed, play certain guard action to passenger's head, panel beating body 2 after the bending adopts the dotted line to draw in figure 4, and mark as 02, thereby the reader of being convenient for understands.

In this embodiment, the cross-sectional area of the first connecting piece 22 connected to one end of the front partition board 1 is larger than the cross-sectional area of the first connecting piece 22 connected to one end of the sheet metal body 21, so that the connecting portion between the first connecting piece 22 and the sheet metal body 21 is more easily broken, and the first connecting piece 22 absorbs the impact energy more easily.

The embodiment further provides a preferable implementation manner, the energy-absorbing sheet metal 2 further includes a second connecting piece 23, the second connecting piece 23 is fixed to the upper side of the sheet metal body 21, a second chute 23a which is vertically arranged is arranged on the second connecting piece 23, the second chute 23a penetrates through the front and rear end faces of the second connecting piece 23, a second mounting ring 23b is arranged in the lower portion of the second chute 23a, and the second mounting ring 23b is fixedly connected with the second connecting piece 23; the aircraft baffle collision energy-absorbing device still include second installation nail 3, the one end of second installation nail 3 pass behind second collar 23b with preceding baffle 1 fixed connection, when panel beating body 21 receives the impact, can with second connection piece 23 pulls downwards, makes second connection piece 23 relative second installation nail 3 downstream, in this process, second collar 23b by second installation nail 3 is cut off to absorb some impact energy, later the second spout 23a is relative second installation nail 3 slides downwards.

In this embodiment, the plurality of second sliding grooves 23a are provided, the plurality of second sliding grooves 23a are sequentially arranged along the transverse axis of the sheet metal body 21, the plurality of second mounting rings 23b are provided, the plurality of second mounting rings 23b are correspondingly arranged in the lower portions of the plurality of second sliding grooves 23a one to one, and the plurality of second sliding grooves 23a play a better guiding role in downward sliding of the second connecting piece 23.

The aircraft baffle collision energy-absorbing device still include first pretension preforming 4, second connection piece 23 presss from both sides and locates preceding baffle 1 with first pretension preforming 4, be provided with a plurality of fourth locating holes that run through its front and back terminal surface on the first pretension preforming 4, it is a plurality of the fourth locating hole one-to-one with a plurality of the coaxial mutual disposition of second collar 23b, the one end of second collar 3 passes in proper order behind fourth locating hole, the second collar 23b with preceding baffle 1 fixed connection, first pretension preforming 4 can avoid second connection piece 23 with the separation of second collar 3.

The energy-absorbing sheet metal 2 further comprises a third connecting piece 24, the third connecting piece 24 is fixed on the lower side of the sheet metal body 21, a third chute 24a which is vertically arranged is formed in the third connecting piece 24, the third chute 24a penetrates through the front end face and the rear end face of the third connecting piece 24, a third mounting ring 24b is arranged in the upper portion of the third chute 24a, the third mounting ring 24b is fixedly connected with the third connecting piece 24, the aircraft partition collision energy-absorbing device further comprises a third mounting nail 5, one end of the third mounting nail 5 penetrates through the third mounting ring 24b and then is fixedly connected with the front partition 1, when the sheet metal body 21 is impacted, the third connecting piece 24 can be pulled upwards, so that the third connecting piece 24 moves upwards relative to the third mounting nail 5, and in the process, the third mounting ring 24b is sheared by the third mounting nail 5, thereby absorbing a part of the impact energy and then the third runner 24a slides upward relative to the third mounting nail 5.

The plurality of third sliding chutes 24a are arranged, and the plurality of third sliding chutes 24a are sequentially arranged along the transverse axis of the sheet metal body 21; the third mounting rings 24b are provided with a plurality of third mounting rings 24b which are arranged in the upper parts of the third sliding grooves 24a in a one-to-one correspondence manner, and the third sliding grooves 24a play a good guiding role in the upward sliding of the third connecting piece 24.

The aircraft baffle collision energy-absorbing device still include second pretension preforming 6, third connection piece 24 presss from both sides and locates preceding baffle 1 with second pretension preforming 6, be provided with a plurality of fifth locating holes that run through its front and back terminal surface on the second pretension preforming 6, it is a plurality of the fifth locating hole one-to-one with a plurality of the coaxial mutual disposition of third collar 24b, the one end of third collar 5 passes in proper order behind fifth locating hole, the third collar 24b with preceding baffle 1 fixed connection, second pretension preforming 6 can avoid third connection piece 24 with third collar 5 takes off.

This embodiment still provides a preferred embodiment, be provided with the score line 21a that can be torn on the panel beating body 21, score line 21a is provided with two, two the symmetry of score line 21a set up in the left and right sides of panel beating body 21, every the uniform end of score line 21a extends to the edge of panel beating body 21, every the equal other end of score line 21a all to the longitudinal axis of panel beating body 21 extends, and two interval between the score line 21a reduces gradually from top to bottom, when panel beating body 21 receives the impact, second mounting nail 3 will panel beating body 21 is upwards pulled, third mounting nail 3 will panel beating body 21 is pulled downwards, and in this process, panel beating body 21 can along score line 21a is torn to absorb partial impact energy.

In order to avoid cutting passengers at the edge of the sheet metal body 21, the aircraft partition plate collision energy absorption device further comprises a decoration frame 7, wherein the decoration frame 7 is coated on the outer edge of the sheet metal body 21, the first connecting sheet 22, the second connecting sheet 23, the third connecting sheet 24, the first pre-tightening pressing sheet 4 and the second pre-tightening pressing sheet 6, and in the embodiment, the energy absorption sheet metal 2 is formed by integral blanking.

In this embodiment, the edge of the groove is fixed with a positioning block, specifically, the positioning block 8 is fixedly connected with the front partition board 1 through a fourth mounting nail 9, and the decoration frame 7 is fixedly connected with the positioning block 8 through a fifth mounting nail c.

The working principle is as follows: in the HIC verification process, when the head initially collides, the first connecting piece 22 and the second mounting ring 23b are instantly pulled and sheared (the upper part of the energy-absorbing sheet metal 2 is tightly installed and pressed with the first pre-tightening pressing plate 4 by the second mounting nail 3, the mounting torque is set to be small, the second mounting ring 23b can be ensured to be sheared by the first mounting nail 3), certain head energy is absorbed, and the HIC verification process is called as an energy-absorbing process.

After the initial collision, the head still has larger energy, and because of the restraint of the safety belt, the head approximately rotates around the safety belt connection point as the rotation center, in the process, because the first chute 23a is arranged above the second mounting ring 23b, the energy-absorbing sheet metal 1 drives the upper half part of the energy-absorbing sheet metal 2 to pull downwards after the third mounting ring 24b is sheared, and absorbs certain head energy by means of the deformation of the energy-absorbing sheet metal 2, which is called a secondary energy-absorbing process.

When the second mounting nail 3 is drawn to the upper end of the first sliding chute 22a, the drawing stops, but the head still has larger energy, so that the energy-absorbing metal plate 2 starts to tear from the score line 21a with the weakest strength (the stress concentration area).

In the tearing process, the energy-absorbing metal plate 2 still deforms continuously and drives the third mounting ring 24b to be sheared by the third mounting nail 5, after the third mounting ring is sheared, the metal plate body 21 drives the third connecting piece 24 to be pulled upwards and pulled, and the third connecting piece 24b and the third mounting ring are sheared together. And after the third energy absorption, the head collision energy is completely absorbed, the collision motion is terminated, and after the three energy absorption processes, the HIC index meets the requirement through verification.

The above description of the present invention does not limit the scope of the present invention. Any other corresponding changes and modifications made according to the technical idea of the present invention should be included in the scope of the claims of the present invention.

Claims

1. The utility model provides an aircraft baffle collision energy-absorbing device, its installs on the preceding baffle of aircraft, its characterized in that, aircraft baffle collision energy-absorbing device include: the energy-absorbing metal plate comprises a metal plate body and a first connecting piece, the metal plate body covers the opening end of a groove formed in the front partition plate, and the opening end of the groove is arranged around the edge of the metal plate body; the both sides of panel beating body all are provided with first connecting piece, every the equal one end of first connecting piece with panel beating body fixed connection, every the equal other end of first connecting piece with preceding baffle fixed connection.

2. An aircraft bulkhead crash energy absorber according to claim 1, wherein the cross-sectional area of the end of the first connecting tab connected to the bulkhead is greater than the cross-sectional area of the end of the first connecting tab connected to the sheet metal body.

3. The aircraft partition plate collision energy absorption device according to claim 1, wherein the energy absorption sheet metal further comprises a second connecting piece, the second connecting piece is fixed on the upper side of the sheet metal body, a second sliding chute which is vertically arranged is arranged on the second connecting piece, the second sliding chute penetrates through the front end face and the rear end face of the second connecting piece, a second mounting ring is arranged in the lower portion of the second sliding chute, and the second mounting ring is fixedly connected with the second connecting piece; the collision energy-absorbing device for the aircraft partition plate further comprises second mounting nails, and one ends of the second mounting nails penetrate through the second mounting rings and are fixedly connected with the front partition plate.

4. An aircraft bulkhead collision energy absorption device according to claim 3, wherein a plurality of second chutes are provided, and the plurality of second chutes are sequentially arranged along a transverse axis of the sheet metal body; the second mounting rings are arranged in a plurality and are arranged at the lower parts of the second sliding grooves in a one-to-one correspondence manner; the collision energy absorption device for the aircraft partition plate further comprises a first pre-tightening pressing plate, the second connecting plate is clamped between the front partition plate and the first pre-tightening pressing plate, a plurality of fourth positioning holes penetrating through the front end face and the rear end face of the first pre-tightening pressing plate are formed in the first pre-tightening pressing plate, and the plurality of fourth positioning holes are in one-to-one correspondence with the plurality of second mounting rings and are coaxially and oppositely arranged; one end of the second mounting nail penetrates through the fourth positioning hole and the second mounting ring in sequence and then is fixedly connected with the front partition plate.

5. The aircraft partition plate collision energy absorption device according to claim 3, wherein the energy absorption sheet metal further comprises a third connecting piece, the third connecting piece is fixed to the lower side of the sheet metal body, a third sliding chute which is vertically arranged is formed in the third connecting piece, the third sliding chute penetrates through the front end face and the rear end face of the third connecting piece, a third mounting ring is arranged in the upper portion of the third sliding chute, and the third mounting ring is fixedly connected with the third connecting piece; the collision energy-absorbing device for the aircraft partition plate further comprises third mounting nails, and one ends of the third mounting nails penetrate through the third mounting rings and are fixedly connected with the front partition plate.

6. An aircraft bulkhead collision energy absorption device according to claim 5, wherein a plurality of the third chutes are provided, and the plurality of the third chutes are sequentially arranged along a transverse axis of the sheet metal body; the plurality of third mounting rings are arranged and are arranged on the upper parts of the plurality of third sliding grooves in a one-to-one correspondence manner; the collision energy absorption device for the aircraft partition plate further comprises a second pre-tightening pressing sheet, wherein a third connecting sheet is clamped between the front partition plate and the second pre-tightening pressing sheet, a plurality of fifth positioning holes penetrating through the front end face and the rear end face of the second pre-tightening pressing sheet are formed in the second pre-tightening pressing sheet, and the fifth positioning holes are in one-to-one correspondence with the third mounting rings and are coaxially and oppositely arranged; one end of the third mounting nail penetrates through the fifth positioning hole and the third mounting ring in sequence and then is fixedly connected with the front partition plate.

7. An aircraft bulkhead crash energy absorber according to claim 1, wherein the sheet metal body is provided with a score line that can be torn.

8. The aircraft partition collision energy absorption device according to claim 7, wherein the number of the score lines is two, and the two score lines are symmetrically arranged on the left side and the right side of the sheet metal body.

9. The aircraft partition collision energy absorption device of claim 8, wherein a uniform end of each score line extends to the edge of the sheet metal body, the other end of each score line extends towards the longitudinal axis of the sheet metal body, and the distance between the two score lines is gradually reduced from top to bottom.

10. The aircraft baffle collision energy absorption device of claim 1, further comprising a decoration frame, wherein the decoration frame is coated on the outer edge of the sheet metal body, the first connecting sheet, the second connecting sheet, the third connecting sheet, the first pre-tightening pressing sheet and the second pre-tightening pressing sheet.