CN110697052B - Different-axis rotary shearing energy-absorbing aviation seat - Google Patents
Different-axis rotary shearing energy-absorbing aviation seat Download PDFInfo
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- CN110697052B CN110697052B CN201910928243.4A CN201910928243A CN110697052B CN 110697052 B CN110697052 B CN 110697052B CN 201910928243 A CN201910928243 A CN 201910928243A CN 110697052 B CN110697052 B CN 110697052B
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- axis
- backrest
- connecting plate
- shear
- plate
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D11/00—Passenger or crew accommodation; Flight-deck installations not otherwise provided for
- B64D11/06—Arrangements of seats, or adaptations or details specially adapted for aircraft seats
- B64D11/0619—Arrangements of seats, or adaptations or details specially adapted for aircraft seats with energy absorbing means specially adapted for mitigating impact loads for passenger seats, e.g. at a crash
Abstract
The invention discloses an off-axis rotating shearing energy-absorbing aviation seat, which comprises: the chair comprises a chair basin, side plates, a backrest, a connecting plate, a shearing pin, a shearing ring and a driving mechanism; the side plate is fixed on the left side or the right side of the chair basin; the lower end of the backrest is hinged with the rear side of the chair basin, and the hinge axis of the backrest and the chair basin is a first axis; the first end of the connecting plate is hinged with the side plate, the second end of the connecting plate is hinged with the backrest, the third end of the connecting plate is provided with the shearing ring, and the hinge axis of the first end of the connecting plate and the hinge axis of the side plate is a second axis; when the backrest leans forward under the action of large inertia, the backrest rotates relative to the side plate by taking the first axis as the rotating shaft, in the process, the shearing ring is torn by the shearing pin, the rotating shaft of the backrest and the axis of the shearing ring are staggered by the structure, and meanwhile, the interference caused by the stress of the shearing ring due to the linkage structure is avoided.
Description
Technical Field
The invention relates to the technical field of aviation passenger seats, in particular to an off-axis rotating shearing energy-absorbing aviation seat.
Background
At present, airline passenger seat includes chair basin, curb plate, back, connecting plate, shear ring and actuating mechanism, the curb plate is fixed in the left side or the right side of chair basin, the back set up in the rear side of chair basin, the one end of connecting plate is articulated with the curb plate, the other end of connecting plate with the pivot of back is articulated, actuating mechanism is used for the drive the connecting plate is relative the curb plate rotates, thereby drives the back leans forward or hypsokinesis, and this kind of mechanism can realize the linkage of chair basin and back, the pivot and the shear ring coaxial arrangement of back, when the back receives forward effort great, the shear ring can be cut off to reach the effect of energy-absorbing protection, but there is the linkage design between chair basin and the back, the linkage structure is right the upset of back can produce certain interference, thereby leads to the shear ring to be difficult to be cut off, can't produce the energy-absorbing effect, will produce serious damage or can't pass through HIC (Head Injury neck damage Criterion) experiment to the passenger.
It should be noted here that the technical contents provided as described in this section are intended to assist those skilled in the art in understanding the present invention, and do not necessarily constitute prior art.
Disclosure of Invention
The invention aims to overcome the technical defects and provide an off-axis rotary shearing energy-absorbing aviation seat, so that the backrest rotates by different rotating shafts before and after the shearing ring is torn, and the rotation of the backrest is prevented from being interfered.
In order to achieve the technical purpose, the technical scheme of the invention provides an off-axis rotating shear energy-absorbing aviation seat, which comprises: the chair comprises a chair basin, side plates, a backrest, a connecting plate, a shearing pin, a shearing ring and a driving mechanism;
the side plate is fixed on the left side or the right side of the chair basin;
the lower end of the backrest is hinged with the rear side of the chair basin, and the hinge axis of the backrest and the chair basin is a first axis;
the first end of the connecting plate is hinged to the side plate, the second end of the connecting plate is hinged to the backrest, the third end of the connecting plate is provided with the shear ring, the hinge axis of the first end of the connecting plate and the hinge axis of the side plate are a second axis, the hinge axis of the second end of the connecting plate and the hinge axis of the backrest are a third axis, the third axis is collinear with the first axis, the axis of the shear ring is a fourth axis, and the third axis, the fourth axis and the second axis are all parallel to each other;
the driving mechanism is used for driving the connecting plate to rotate relative to the second axis;
the shear pin is connected with the backrest, the shear pin is arranged below the first axis, and the shear ring is sleeved on the shear pin.
Compared with the prior art, the invention has the beneficial effects that: in the different-axis rotation shearing energy-absorbing aviation seat, the second end of the connecting plate is hinged with the backrest, the third end of the connecting plate is provided with the shearing ring, the driving mechanism drives the connecting plate to rotate around the second axis, the second end and the third end of the connecting plate both rotate around the second axis, the second end of the connecting plate is hinged with the backrest, and the third end of the connecting plate is connected with the backrest through the shearing pin, namely two non-collinear shafts are arranged on the connecting plate and connected with the backrest, so that when the driving mechanism drives the connecting plate to rotate, the backrest can be driven to tilt forwards or backwards, and the first axis revolves around the second axis, so that the seat pan moves synchronously with the backrest, and when the backrest is operated by a person and does not bear large inertia and is in a normal working state, the backrest rotates relative to the side plate by taking the second axis as a rotating shaft and performs forward/backward tilting angle adjustment; when the driving mechanism is in an unmanned operation and is in a locking state, the connecting plate is static relative to the side plate, when the backrest leans forward under large inertia, the backrest rotates relative to the side plate by taking the second axis as a rotating shaft, and in the process, the shearing ring is torn by the shearing pin, so that the influence of a linkage structure on the stress of the shearing ring in the prior art is avoided, the backrest is also locked after the connecting plate is locked relative to the first axis, and the interference in the backrest overturning process is avoided, so that the shearing ring cannot be sheared; the structure misplaces the rotating shaft of the backrest and the axis of the shearing ring, so that the shearing ring is conveniently arranged at the optimal shearing position of the connecting plate, and meanwhile, the interference caused by the stress of the shearing ring due to the linkage structure is avoided.
Drawings
FIG. 1 is a schematic diagram of an explosive structure of an embodiment of the off-axis rotating shear energy-absorbing aircraft seat provided by the invention.
Fig. 2 is a schematic view of a part a of fig. 1.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, 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 and fig. 2, the embodiment provides an aircraft seat with different axes of rotation, shear and energy absorption, including: a seat pan 1, side panels 2, a backrest 3, a connecting plate 4, a shear pin 5, a shear ring 6 and a drive mechanism 7 (the chain line drawn in fig. 2 is the assembly line).
The side plate 2 is fixed on the left side or the right side of the seat pan 1, in this embodiment, the side plate 2 is a fixing member, the position and the angle of the side plate 2 do not change, and the seat pan 1, the backrest 3 and the connecting plate 4 all change the angle and the position by using the side plate 2 as a reference.
The lower end of the backrest 3 is hinged with the rear side of the seat pan 1, and the hinge axis of the backrest 3 and the seat pan 1 is a first axis.
The first end of connecting plate 4 with curb plate 2 is articulated, the second end of connecting plate 4 with back 3 is articulated, the third end of connecting plate 4 is provided with shear ring 6, the first end of connecting plate 4 with the articulated axis of curb plate 2 is the second axis, the second end of connecting plate 4 with the articulated axis of back 3 is the third axis, the third axis with the first axis collineation, the axis of shear ring 6 is the fourth axis, third axis, fourth axis, second axis all are parallel to each other.
The driving mechanism 7 is used for driving the connecting plate 4 to rotate relative to the second axis.
The shear pin 5 is connected with the backrest 3, the shear pin 5 is arranged below the first axis, and the shear ring 6 is sleeved on the shear pin 5.
In the different-axis rotation shearing energy-absorbing aviation seat, the second end of the connecting plate 4 is hinged to the backrest 3, the third end of the connecting plate 4 is provided with the shearing ring 6, the driving mechanism drives the connecting plate 4 to rotate around the second axis, the second end and the third end of the connecting plate 4 both rotate around the second axis, and the driving mechanism 7 drives the connecting plate 4 to rotate, so that the backrest 3 can be driven to tilt forwards or backwards, and the first axis revolves around the second axis, so that the seat pan 1 can synchronously move along with the backrest 3, because the second end of the connecting plate 4 is hinged to the backrest 3, and the third end of the connecting plate 4 is connected with the backrest 3 through the shearing pin 5.
When the backrest 3 is not subjected to large inertia and in a normal working state, the backrest 3 rotates relative to the side plate 2 by taking the second axis as a rotating shaft and performs forward/backward tilting angle adjustment, obviously, after the adjustment is completed, the driving mechanism 7 stops acting and enables the connecting plate 4 to be locked relative to the first axis, so that the backrest 3 is prevented from being turned over continuously.
When the driving mechanism 7 is in an unmanned operation state and is in a locking state, the connecting plate 4 is static relative to the side plate 2, when the backrest 3 is inclined forwards by large inertia, the backrest 3 rotates relative to the side plate 2 by taking the first axis as a rotating shaft, and in the process, the shearing ring 6 is torn by the shearing pin 5, so that the situation that the connecting plate 4 is locked relative to the first axis is avoided, the backrest 3 is also locked, and interference in the overturning process of the backrest 3 is avoided.
The above structure offsets the rotation axis of the backrest 3 from the axis of the shear ring 6 so as to facilitate the arrangement of the shear ring 6 at the optimum shearing position of the link plate 4. In the present embodiment, the shear ring 6 is fixed to the back surface of the lowermost end of the link plate 4, and when the upper portion of the backrest 3 is subjected to a large inertia and is tilted forward about the third axis as the rotation axis, the shear pin 5 moves backward relative to the shear ring 6 so as to tear the shear ring 6.
In the present embodiment, the backrest 3 includes a backrest body 31 and a backrest joint 32, the backrest joint 32 is fixed to a lower end of the backrest body 31, and the backrest joint 32 is provided with a first connection hole 32a.
The shear pin 5 is disposed below the first connection hole 32a, and an axis of the shear pin 5 is parallel to an axis of the first connection hole 32a.
A second rotating shaft 4a is arranged at a second end of the connecting plate 4, and the second rotating shaft 4a is coaxially connected with the first connecting hole 32a.
The connecting plate 4 is provided with a limiting shaft 4b, the axis of the limiting shaft 4b is parallel to the axis of the first connecting hole 32a, the shearing ring 6 is arranged at the front lower part of the second rotating shaft 4a, and the limiting shaft 4b is arranged at the middle position of the connecting line of the shearing ring 6 and the second rotating shaft 4 a.
In this embodiment, chair basin 1 includes chair basin body 11 and chair basin connecting rod 12, chair basin connecting rod 12 is fixed in the rear end of chair basin body 11, be provided with second connecting hole 12a on the chair basin connecting rod 12, screw hole 4a1 rather than coaxial arrangement is seted up at the center of second pivot 4a, the rotatory energy-absorbing aviation seat of shearing of different axes still include screw 8, screw 8 passes in proper order behind second connecting hole 12a, the first connecting hole 32a with screw hole 4a1 is connected.
The front side that the back connects 32 is provided with the groove 32b of stepping down that forms backward sunken, place in spacing axle 4b in the groove 32b of stepping down works as be provided with the regional quilt of shear ring 6 on the connecting plate 4 after shear pin 5 damages, spacing axle 4b is used for the restriction the angle of 3 retroverteds of back, be provided with first pivot 2a and spacer pin 2b on the curb plate 2, the axis of first pivot 2a does first axis.
The first end of connecting plate 4 is provided with rotates cover 4c, it locates to rotate cover 4c coaxial cover first pivot 2a, and rotate cover 4c with first pivot 2a rotates and is connected, the outer peripheral face that rotates cover 4c is provided with stopper 4c1, stopper 4c1 along with rotate cover 4c when rotating can with gag pin 2b offsets, and the restriction rotates the turned angle of cover 2 b.
The outer peripheral face of the rotating sleeve 4c is provided with an adapter plate 4c2 extending outwards to form, the adapter plate 4c2 and the limiting block 4c1 are fixed at two ends of the rotating sleeve 4c respectively, the driving mechanism 7 is a telescopic mechanism, in the embodiment, the driving mechanism 7 is a telescopic oil cylinder, a fixed end of the driving mechanism 7 is hinged to the side plate 2, a telescopic end of the driving mechanism 7 is hinged to the adapter plate 4c2, and the driving mechanism 7 is used for driving the connecting plate 4 to rotate by taking the second axis as a rotating shaft.
The working principle is as follows: in the different-axis rotation shearing energy-absorbing aviation seat, the second end of the connecting plate 4 is hinged to the backrest 3, the third end of the connecting plate 4 is provided with the shearing ring 6, when the driving mechanism 7 drives the connecting plate 4 to rotate around the second axis, the second end and the third end of the connecting plate 4 both rotate around the second axis, because the second end of the connecting plate 4 is hinged to the backrest 3, and the third end of the connecting plate 4 is connected with the backrest 3 through the shearing pin 5, namely, two non-collinear axes are arranged on the connecting plate 4 and connected with the backrest 3, when the driving mechanism 7 drives the connecting plate 4 to rotate, the backrest 3 can be driven to tilt forwards or backwards, and simultaneously the first axis revolves around the second axis, so that the seat pan 1 synchronously moves with the backrest 3, and when the backrest 3 is not subjected to large inertia and normal working state by a human being operated driving mechanism 7, the backrest 3 rotates relative to the side plate 2 by taking the second axis as a rotating shaft and adjusts the forward/backward tilting angle; when the driving mechanism 7 is in an unmanned operation state and is in a locking state, the connecting plate 4 is static relative to the side plate 2, when the backrest 3 is inclined forwards by large inertia, the backrest 3 rotates relative to the side plate 2 by taking the first axis as a rotating shaft, and in the process, the shearing ring 6 is torn by the shearing pin 5, so that the backrest 3 is prevented from being locked after the connecting plate 4 is locked relative to the first axis, interference in the overturning process of the backrest 3 is avoided, and the shearing ring 6 cannot be sheared.
The above-described embodiments of the present invention should not be construed as limiting 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 protection scope of the claims of the present invention.
Claims (5)
1. The utility model provides an energy-absorbing aviation seat is cuted in rotation of different axles, its characterized in that includes: the chair comprises a chair basin, side plates, a backrest, a connecting plate, a shearing pin, a shearing ring and a driving mechanism;
the side plate is fixed on the left side or the right side of the chair basin;
the lower end of the backrest is hinged with the rear side of the chair basin, and the hinge axis of the backrest and the chair basin is a first axis;
the first end of the connecting plate is hinged to the side plate, the second end of the connecting plate is hinged to the backrest, the third end of the connecting plate is provided with the shear ring, the hinge axis of the first end of the connecting plate and the hinge axis of the side plate are a second axis, the hinge axis of the second end of the connecting plate and the hinge axis of the backrest are a third axis, the third axis is collinear with the first axis, the axis of the shear ring is a fourth axis, and the third axis, the fourth axis and the second axis are all parallel to each other;
the driving mechanism is used for driving the connecting plate to rotate relative to the second axis;
the shear pin is connected with the backrest, the shear pin is arranged below the first axis, and the shear ring is sleeved on the shear pin.
2. The aircraft seat with the eccentric rotation shear energy absorption function according to claim 1, wherein the backrest comprises a backrest body and a backrest joint, the backrest joint is fixed at the lower end of the backrest body, and a first connecting hole is formed in the backrest joint; the shear pin is arranged below the first connecting hole, and the axis of the shear pin is parallel to that of the first connecting hole; and a second rotating shaft is arranged at the second end of the connecting plate and is coaxially connected with the first connecting hole.
3. The heteroaxial rotation shear energy absorption aircraft seat according to claim 2, wherein a limiting shaft is arranged on the connecting plate, and the axis of the limiting shaft is parallel to the axis of the first connecting hole; the front side that the back connects is provided with the groove of stepping down that forms of caving in backward, place in the spacing axle the groove of stepping down.
4. The heteroaxial rotation shear energy absorption aviation seat according to claim 2, wherein a first rotating shaft and a limiting pin are arranged on the side plate, and the axis of the first rotating shaft is the first axis; the first end of the connecting plate is provided with a rotating sleeve, the rotating sleeve is coaxially sleeved on the first rotating shaft and is rotatably connected with the first rotating shaft, the peripheral surface of the rotating sleeve is provided with a limiting block, and the limiting block can abut against the limiting pin when rotating along with the rotating sleeve and limit the rotating angle of the rotating sleeve.
5. The aircraft seat with the different-axis rotation, shear and energy absorption function as claimed in claim 4, wherein an adapter plate formed by extending outwards is arranged on the outer peripheral surface of the rotating sleeve, the adapter plate is arranged at one end of the rotating sleeve, and the limiting block is arranged at the other end of the rotating sleeve; the driving mechanism is a telescopic mechanism, one end of the driving mechanism is hinged to the side plate, and the other end of the driving mechanism is hinged to the adapter plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910928243.4A CN110697052B (en) | 2019-09-28 | 2019-09-28 | Different-axis rotary shearing energy-absorbing aviation seat |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910928243.4A CN110697052B (en) | 2019-09-28 | 2019-09-28 | Different-axis rotary shearing energy-absorbing aviation seat |
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| Publication Number | Publication Date |
|---|---|
| CN110697052A CN110697052A (en) | 2020-01-17 |
| CN110697052B true CN110697052B (en) | 2022-12-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910928243.4A Active CN110697052B (en) | 2019-09-28 | 2019-09-28 | Different-axis rotary shearing energy-absorbing aviation seat |
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| CN (1) | CN110697052B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112678185B (en) * | 2021-01-29 | 2021-07-20 | 北京天创凯睿科技有限公司 | Machine gun automatic positioning sliding seat for military helicopter |
| GB2619826A (en) * | 2022-06-13 | 2023-12-20 | Mirus Aircraft Seating Ltd | Method of assembling a seat |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5328234A (en) * | 1992-11-20 | 1994-07-12 | Ford Motor Company | Rotatable seat for vehicles |
| CN202728015U (en) * | 2012-07-31 | 2013-02-13 | 全兴工业（海南）有限公司 | Neck swing-prevention device |
| CN206552277U (en) * | 2017-01-22 | 2017-10-13 | 湖北航宇嘉泰飞机设备有限公司 | Energy absorption device for aero seat |
| DE102017115347B4 (en) * | 2017-07-10 | 2020-07-02 | Grammer Ag | Vehicle seat with adjustable damper and commercial vehicle |
| GB2569303B (en) * | 2017-12-12 | 2020-09-09 | Ipeco Holdings Ltd | Mounting apparatus for a seat |
| CN208882118U (en) * | 2018-03-26 | 2019-05-21 | 湖北航宇嘉泰飞机设备有限公司 | A kind of passenger seat of chair basin linkage |
| CN110051154A (en) * | 2018-04-04 | 2019-07-26 | 永艺家具股份有限公司 | Back seat synchronizing linkage and chair tool for chair tool |
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| CN110697052A (en) | 2020-01-17 |
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