CN111422363B - Buffering and energy absorbing device for aviation seat - Google Patents
Buffering and energy absorbing device for aviation seat Download PDFInfo
- Publication number
- CN111422363B CN111422363B CN201911396535.4A CN201911396535A CN111422363B CN 111422363 B CN111422363 B CN 111422363B CN 201911396535 A CN201911396535 A CN 201911396535A CN 111422363 B CN111422363 B CN 111422363B
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- energy
- cavity
- buffering
- cushioning
- damping
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- 230000003139 buffering effect Effects 0.000 title claims abstract description 47
- 238000013016 damping Methods 0.000 claims abstract description 87
- 239000007788 liquid Substances 0.000 claims abstract description 17
- 239000000872 buffer Substances 0.000 claims description 67
- 238000001125 extrusion Methods 0.000 claims description 23
- 238000010521 absorption reaction Methods 0.000 claims description 17
- 239000012530 fluid Substances 0.000 claims description 12
- 239000006096 absorbing agent Substances 0.000 claims description 9
- 238000000034 method Methods 0.000 abstract description 10
- 230000006378 damage Effects 0.000 abstract description 8
- 208000027418 Wounds and injury Diseases 0.000 abstract description 7
- 208000014674 injury Diseases 0.000 abstract description 7
- 230000008878 coupling Effects 0.000 description 10
- 238000010168 coupling process Methods 0.000 description 10
- 238000005859 coupling reaction Methods 0.000 description 10
- 230000000694 effects Effects 0.000 description 8
- 235000017166 Bambusa arundinacea Nutrition 0.000 description 4
- 235000017491 Bambusa tulda Nutrition 0.000 description 4
- 241001330002 Bambuseae Species 0.000 description 4
- 235000015334 Phyllostachys viridis Nutrition 0.000 description 4
- 239000011425 bamboo Substances 0.000 description 4
- 230000007423 decrease Effects 0.000 description 4
- 238000004146 energy storage Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 210000000845 cartilage Anatomy 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000012536 storage buffer Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/60—Crew or passenger accommodations
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Vibration Dampers (AREA)
Abstract
The invention discloses a buffering and energy-absorbing device for an aviation seat, which comprises a buffering component, a buffering barrel used for being connected with a fixing piece and a connecting component used for being connected with the aviation seat, wherein an energy-absorbing cavity is formed in the buffering barrel, the buffering component is arranged between the buffering barrel and the connecting component, the end part of the connecting component is slidably arranged in the energy-absorbing cavity, damping liquid is arranged in the energy-absorbing cavity, and the damping liquid is arranged on the upper side and the lower side of the end part of the connecting component. The buffering and energy-absorbing are carried out on the aviation seat through the buffering component, and the damping liquid is arranged in the energy-absorbing cavity, so that the buffering and energy-absorbing are carried out on the aviation seat through the damping force generated between the damping liquid and the connecting component, the buffering component can be prevented from being excessively large in the rebound process, and the aviation seat can be further slowly restored to the initial state, so that the injury to a pilot is avoided.
Description
Technical Field
The invention relates to the technical field of aviation, in particular to a buffering and energy-absorbing device for an aviation seat.
Background
With the rapid development of aerospace industry, the requirements on aerospace devices are higher and higher, and meanwhile, the safety of pilots is guaranteed. After the aircraft descends to ground, the aircraft seat inside the aircraft still has great kinetic energy, and buffering energy-absorbing devices in the existing aircraft seat buffer energy-absorbing through structures such as spring groups and elastic guard plates, and after the structures rebound after energy storage, the structures still enable the aircraft seat to generate upward kinetic energy, so that the buffering effect is poor, a certain uncomfortable feeling is easily caused for a pilot sitting on the aircraft seat, and even a certain injury is easily caused for the pilot.
Disclosure of Invention
The invention aims to overcome the defects that the buffering energy-absorbing device in the aero seat in the prior art still can enable the aero seat to generate upward kinetic energy after rebound, so that the buffering effect is poor, the riding comfort of a pilot is influenced, and even the pilot is easily injured, and provides the buffering energy-absorbing device and the aero seat comprising the buffering energy-absorbing device.
The invention solves the technical problems by the following technical scheme:
the utility model provides a buffering energy-absorbing device for aviation seat, includes buffer unit, is used for the buffer section of thick bamboo of being connected with the mounting and is used for the coupling assembling who is connected with aviation seat, have the energy-absorbing cavity in the buffer section of thick bamboo, buffer unit set up in the buffer section of thick bamboo with coupling assembling between, coupling assembling's tip is smooth to be located in the energy-absorbing cavity, its characterized in that is provided with damping liquid in the energy-absorbing cavity, damping liquid is located the upper and lower both sides of coupling assembling's tip.
In this scheme, after the aircraft drops subaerial, aviation seat still can the down movement under inertial effect, and coupling assembling can extrude buffer unit this moment to cushion aviation seat, simultaneously owing to be provided with damping fluid in the energy-absorbing cavity, this just makes in the decline in-process damping fluid produce damping force to coupling assembling, thereby further cushion aviation seat, so that the buffering effect to aviation seat is better. When the energy-storage buffer part rebounds, the connecting component moves upwards, damping liquid can avoid the excessive upward kinetic energy of the aero seat caused by the damping force generated by the connecting component during rebound, so that the aero seat is slowly restored to an initial state, and the damage to a pilot is avoided.
Preferably, the connecting assembly further comprises a damping piece, the damping piece is connected to the end portion of the connecting assembly, a gap is reserved between the damping piece and the side wall of the energy absorption cavity, and damping liquid is located on the upper side and the lower side of the damping piece.
In this scheme, further make damping fluid of damping piece upper and lower both sides flow in order to produce damping force through the clearance between damping piece and the lateral wall of energy-absorbing cavity from top to bottom, and then cushion aviation seat, also can prevent to kick-back too fast, lead to causing the injury to the pilot.
Preferably, a plurality of damping holes are formed in the damping piece at intervals, and the damping holes are communicated with the energy absorption cavities on the upper side and the lower side of the damping piece.
In this scheme, through setting up the damping hole to increase damping liquid flow time and damping piece's area of contact, and then increase damping force, thereby improve the cushioning properties to aviation seat, also can prevent more that aviation seat from kick-backing too fast simultaneously, lead to causing the injury to the pilot.
Preferably, the mouth of the energy absorbing cavity is provided with a seal.
In the scheme, a sealing piece is arranged at the opening part of the energy absorption cavity and used for preventing damping liquid in the energy absorption cavity from overflowing.
Preferably, the buffer component comprises a first buffer piece, and the first buffer piece is arranged in the energy absorption cavity and is positioned below the connecting component.
In this scheme, through set up first bolster in the energy-absorbing cavity, and then make coupling assembling extrude first bolster at the decline in-process to cushion aviation seat.
Preferably, the connecting assembly comprises a fixing plate and a plurality of stand columns, wherein the fixing plate is connected with the aviation seat, the stand columns are connected with the fixing plate, and the stand columns are slidably arranged in the energy absorption cavity.
Preferably, the buffer component further comprises a second buffer piece, the second buffer piece is sleeved on the upright post, and the second buffer piece is abutted against the fixing plate and the buffer cylinder.
In this scheme, through set up the second bolster on a plurality of stands for at coupling assembling decline in-process, extrude the second bolster, in order to cushion aviation seat.
Preferably, the connecting assembly further comprises a center pillar and an extrusion piece, two ends of the center pillar are respectively connected with the fixing plate and the extrusion piece, and one end of the center pillar and the extrusion piece are slidably arranged in the energy absorption cavity.
In this scheme, set up the extrusion piece in order to increase the area of contact of extrusion piece and first bolster, and then improve the cushioning effect.
Preferably, the connecting assembly further comprises a friction piece, the friction piece is sleeved on the extrusion piece, and the friction piece abuts against the inner wall of the energy absorption cavity.
In this scheme, overlap on the extruded piece and establish friction piece and make the center pillar in the downward movement in-process for rub between friction piece and the inner wall of energy-absorbing cavity, thereby produce the heat, and then with the kinetic energy conversion of buffering seat internal energy, and in the transfer to the outside air through the oral area of energy-absorbing cavity, with better buffering energy-absorbing to the aviation seat.
Preferably, a first cushion pad is provided between the fixed plate and the airline seat.
In the scheme, the structure is adopted to further improve the buffering and energy absorbing performance of the aero seat.
Preferably, a second buffer pad is arranged between the buffer cylinder and the fixing piece.
In the scheme, the structure is adopted to further improve the buffering and energy absorbing performance of the aero seat.
On the basis of conforming to the common knowledge in the field, the above preferred conditions can be arbitrarily combined to obtain the preferred examples of the invention.
The invention has the positive progress effects that: according to the buffering and energy-absorbing device for the aviation seat, the buffering and energy-absorbing device is used for buffering and energy-absorbing the aviation seat through the buffering component, and damping liquid is arranged in the energy-absorbing cavity, so that damping force generated between the damping liquid and the connecting component is used for buffering and energy-absorbing the aviation seat, and excessive kinetic energy of the buffering component in a rebound process can be prevented, and the aviation seat is slowly restored to an initial state, so that injury to pilots is avoided.
Drawings
FIG. 1 is a schematic structural view of a cushioning and energy absorbing device for an aircraft seat according to a preferred embodiment of the present invention.
FIG. 2 is a schematic perspective view of a cushioning and energy absorbing device for an aircraft seat according to a preferred embodiment of the present invention.
FIG. 3 is a schematic view of a damping member for use in a cushioning energy absorber for an aircraft seat in accordance with a preferred embodiment of the present invention.
Reference numerals illustrate:
Extrusion 202
Rubber ring 203
Fixing plate 204
Upright 205
Cushioning member 30
Detailed Description
The invention will now be more fully described by way of example only and with reference to the accompanying drawings, but the invention is not thereby limited to the scope of the examples described.
As shown in fig. 1 to 3, the present embodiment provides a buffering and energy absorbing device for an aero seat, which includes a buffering component 30, a buffering barrel 10 for connecting with a fixing piece, and a connecting component 20 for connecting with the aero seat, wherein an energy absorbing cavity is formed in the buffering barrel 10, the buffering component 30 is disposed between the buffering barrel 10 and the connecting component 20, an end portion of the connecting component 20 is slidably disposed in the energy absorbing cavity, damping liquid is disposed in the energy absorbing cavity, and the damping liquid is disposed on upper and lower sides of the end portion of the connecting component 20.
Wherein, after the aircraft drops subaerial, aviation seat still can the down movement under inertial effect, and coupling assembling 20 can extrude buffer unit 30 this moment to cushion aviation seat, simultaneously owing to be provided with damping fluid in the energy-absorbing cavity, this just makes in the decline in-process damping fluid produce damping force to coupling assembling 20, thereby further cushion aviation seat, so that the cushioning effect to aviation seat is better. When the energy-stored buffer component 30 rebounds, the connecting component 20 moves upwards, and the damping force generated by the damping fluid on the connecting component 20 can avoid excessive upward kinetic energy of the aero-seat during rebound, so that the aero-seat slowly returns to the initial state, and the injury to a pilot is avoided.
It should be noted that the number and the structural form of the buffer member 30, the buffer tube 10, the energy absorbing cavity and the connection assembly 20 are not limited, and in this embodiment, the buffer tube 10 is a double-layer hollow cylindrical structure, which is to enable the energy absorbing cavity to include a first cavity 101 and a second cavity 102, and the second cavity 102 surrounds the outside of the first cavity 101. The damping fluid is disposed in the second chamber 102, but the damping fluid may be disposed in the first chamber 101 as needed. In this embodiment, the damping fluid is damping oil (not shown).
As shown in fig. 1 and 3, the connection assembly 20 further includes a damping member 201, the damping member 201 is connected to an end portion of the connection assembly 20, a gap is formed between the damping member 201 and a sidewall of the energy absorption cavity, and damping fluid is located on upper and lower sides of the damping member 201. The damping piece 201 is provided with a plurality of damping holes 2011 which are arranged at intervals, and the damping holes 2011 are communicated with the energy absorption cavities on the upper side and the lower side of the damping piece 201. The mouth of the energy absorbing cavity is provided with a sealing member 40.
The damping liquid on the upper side and the lower side of the damping piece 201 further flows up and down through a gap between the damping piece 201 and the side wall of the energy absorption cavity to generate damping force, so that the aero seat is buffered, and the aero seat can be prevented from rebounding too fast, so that the pilot is injured. Through setting up the damping hole 2011 to increase the area of contact with damping piece 201 when the damping liquid flows, and then increase damping force, thereby improve the cushioning properties to the aviation seat, also can prevent more that the aviation seat from kick-backing too fast simultaneously, lead to causing the injury to the pilot. A seal 40 is provided at the mouth of the energy absorbing cavity for preventing the escape of damping fluid within the energy absorbing cavity.
The shape of the damper 201 is not limited as long as it matches the shape of the energy absorbing cavity. In this embodiment, the damping member 201 is slidably disposed in the second cavity 102, the damping member 201 is a circular thin plate, a side surface of the circular thin plate in a radial direction is close to a side wall of the second cavity 102, and a plurality of through holes are uniformly disposed in the circular thin plate, and the through holes are damping holes 2011. When the damping member 201 moves downward, damping oil flows from the gap between the annular thin plate and the energy absorption cavity and the through hole of the annular thin plate to generate damping force with the annular thin plate, so that the aero seat is buffered, and the pilot is prevented from being injured by too fast rebound.
As shown in fig. 1, cushioning member 30 comprises a first cushioning member 301, with first cushioning member 301 disposed within the energy absorbing cavity and positioned below connection assembly 20. The first buffer member 301 is disposed in the energy absorbing cavity, so that the connection assembly 20 presses the first buffer member 301 in the descending process to buffer the aero seat.
As shown in fig. 1 and 2, the connection assembly 20 includes a fixing plate 204 and a plurality of columns 205, the fixing plate 204 is connected to the air seat, the columns 205 are connected to the fixing plate 204, and the columns 205 are slidably disposed in the energy absorbing cavities. The buffer component 30 further comprises a second buffer member 302, the second buffer member 302 is sleeved on the upright post 205, and the second buffer member 302 abuts against the fixing plate 204 and the buffer tube 10. The second cushioning members 302 are disposed on the plurality of upright posts 205, so that the second cushioning members 302 are pressed to cushion the airline seat during the descent of the connection assembly 20.
The connection assembly 20 further includes a center post 206 and an extrusion 202, with both ends of the center post 206 being connected to the mounting plate 204 and the extrusion 202, respectively, and one end of the center post 206 and the extrusion 202 being slidably disposed within the energy absorbing cavity. The connecting assembly 20 further comprises a friction piece, the friction piece is sleeved on the extrusion piece 202, and the friction piece abuts against the inner wall of the energy absorption cavity. Wherein the pressing member 202 is provided to increase the contact area of the pressing member 202 with the first cushioning member 301, thereby improving the cushioning effect. The friction piece is sleeved on the extrusion piece 202, so that the center column 206 rubs with the inner wall of the energy-absorbing cavity in the downward movement process, heat is generated, kinetic energy of the buffer seat is converted into internal energy, and the internal energy is transmitted to the outside air through the opening of the energy-absorbing cavity, so that the buffer energy absorption is performed on the aviation seat better.
It should be noted that the forms of the first buffer 301 and the second buffer 302 are not limited. In this embodiment, the first buffer member 301 is a buffer block made of ACF artificial cartilage material, and the buffer block is disposed at the bottom of the first cavity 101. The extrusion 202 on the center post 206 would squeeze the bumper block through which the airline seat can be further cushioned, which may make the cushioning properties of the airline seat better. The second buffer member 302 is a spring, and the lower end of the spring is connected to the upper surface of the buffer cartridge 10. When the aircraft falls on the ground, the aero seat still moves downwards under the action of inertia, and at the moment, the center column 206 and the plurality of upright columns 205 are driven to move downwards, so that the plurality of springs can be extruded, the plurality of springs start to store energy, and the aero seat can be buffered. The center post 206 is welded to the middle of the fixing plate 204, and the pressing member 202 is fixedly coupled to the lower end of the center post 206. The plurality of upright posts 205 are uniformly distributed around the center post 206, the upright posts 205 are welded with the fixing plate 204, and the upright posts 205 extend into the second cavity 102. The friction piece is a rubber ring 203, and the rubber ring 203 is sleeved on the extrusion piece 202 and is attached to the side wall of the first cavity 101. When the extrusion 202 moves downwards, the rubber ring 203 rubs with the inner wall of the buffer barrel 10, so that heat energy is generated, kinetic energy of the buffer seat can be converted into internal energy and is conducted into the outside air through the buffer barrel 10, and therefore the buffer energy absorption of the aviation seat can be better carried out. It should be noted that the elastic force of the spring is greater than the friction force between the rubber ring 203 and the sidewall of the first cavity 101. The situation that the buffer energy absorbing device cannot be restored to the original position and the aviation seat cannot be restored to the original state due to the fact that the friction force between the rubber ring 203 and the side wall of the second cavity 102 is too large is avoided.
As shown in fig. 1 to 3, a first cushion 303 is provided between the fixing plate 204 and the airline seat. A second cushioning pad 304 is provided between the cushioning cartridge 10 and the mount. The buffer energy absorption performance of the aviation seat is further improved by adopting the structural form. In this embodiment, the interiors of the first cushion 303 and the second cushion 304 are each honeycomb-shaped. The buffer effect of the aviation seat can be achieved through the first buffer pad 303 and the second buffer pad 304, and the buffer effect of the aviation seat can be better through matching with a plurality of springs and buffer blocks.
In the buffering and energy absorbing device for the aviation seat in the embodiment, after the aircraft falls on the ground, the aviation seat still moves downwards under the action of kinetic energy, and at the moment, the middle column 206 and the plurality of upright columns 205 are driven to move downwards, so that a plurality of springs can be extruded, and the plurality of buffering springs start to store energy. And then can cushion the aviation seat, the extrusion 202 on the center pillar 206 can extrude the buffer block simultaneously, can further cushion the aviation seat through the buffer block, and the device can make the buffer performance of aviation seat better. And the buffer performance of the aero seat can be further improved by matching the first buffer pad 303 and the second buffer pad 304. And when center column 206 moves down, can drive extrusion 202 down motion, the rubber circle 203 on the extrusion 202 can rub with the section of thick bamboo wall of buffer tube 10 this moment to produce heat energy, can convert the kinetic energy of buffering seat into the internal energy, and in the conduction is conducted outside air through buffer tube 10, thereby can be better to the energy-absorbing of buffering of aviation seat. In this process, the damping oil in the second cavity 102 can generate damping force to the damping piece 201, and further buffer and absorb energy to the aero seat. When a plurality of springs and buffer blocks rebound, the damping piece 201 is driven to move upwards, damping oil in the second cavity 102 can generate damping force through a plurality of through holes in the damping piece 201 at the moment, so that the situation that upward kinetic energy of the aviation seat is overlarge when the springs and buffer blocks rebound can be avoided, the aviation seat can be slowly restored to an initial state, and a pilot takes the chair more comfortably.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that this is by way of example only, and the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the principles and spirit of the invention, but such changes and modifications fall within the scope of the invention.
Claims (11)
1. The buffering and energy-absorbing device for the aviation seat comprises a buffering component, a buffering barrel used for being connected with a fixing piece and a connecting component used for being connected with the aviation seat, wherein an energy-absorbing cavity is formed in the buffering barrel, the buffering component is arranged between the buffering barrel and the connecting component, and the end part of the connecting component is slidably arranged in the energy-absorbing cavity;
the energy absorption cavity comprises a first cavity and a second cavity, the second cavity surrounds the outside of the first cavity, and the damping liquid is arranged in the second cavity;
the connecting assembly comprises a center column, an extrusion part, a friction piece and a plurality of upright posts, wherein the upright posts are arranged in the second cavity in a sliding manner, one end of the center column and the extrusion part are arranged in the first cavity in a sliding manner, the friction piece is sleeved on the extrusion part, and the friction piece is propped against the inner wall of the first cavity;
the buffer component comprises a first buffer piece and a second buffer piece, the first buffer piece is arranged in the first cavity and located below the middle column, and the second buffer piece is sleeved on the upright column.
2. The cushioning energy absorber for an aircraft seat of claim 1, wherein the connecting assembly further comprises a damping member connected to an end of the connecting assembly, wherein a gap is provided between the damping member and a side wall of the energy absorbing cavity, and wherein the damping fluid is located on both sides of the damping member.
3. The cushioning and energy absorbing device for an aircraft seat of claim 2, wherein a plurality of spaced damping holes are provided in the damping member, the damping holes being in communication with the energy absorbing cavities on the upper and lower sides of the damping member.
4. A cushioning energy absorber for an aircraft seat according to claim 1, wherein the mouth of the energy absorbing cavity is provided with a seal.
5. The cushioning energy absorber for an aircraft seat of claim 1, wherein the first cushioning member is disposed within the energy absorbing cavity and below the connecting assembly.
6. The cushioning energy absorber for an aircraft seat of claim 1, wherein the connecting assembly comprises a fixed plate, wherein the fixed plate is connected to the aircraft seat, wherein the post is connected to the fixed plate, and wherein the post is slidably disposed within the energy absorbing cavity.
7. The cushioning energy absorber for an aircraft seat of claim 6, wherein the second cushioning member abuts both the fixed plate and the cushioning cylinder.
8. The cushion energy absorber for an aircraft seat of claim 6, wherein the center post has ends connected to the fixed plate and the extrusion, respectively, and wherein the center post has one end and the extrusion are slidably disposed within the energy absorbing cavity.
9. The cushioning energy absorber for an aircraft seat of claim 8, wherein the friction member abuts an inner wall of the energy absorbing cavity.
10. The cushioning energy absorber for an aircraft seat of claim 6, wherein a first cushion is provided between the anchor plate and the aircraft seat.
11. A cushioning and energy absorbing device for an aircraft seat according to any one of claims 1 to 10, wherein a second cushion pad is provided between the cushion cylinder and the anchor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911396535.4A CN111422363B (en) | 2019-12-30 | 2019-12-30 | Buffering and energy absorbing device for aviation seat |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201911396535.4A CN111422363B (en) | 2019-12-30 | 2019-12-30 | Buffering and energy absorbing device for aviation seat |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111422363A CN111422363A (en) | 2020-07-17 |
| CN111422363B true CN111422363B (en) | 2023-06-13 |
Family
ID=71546958
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911396535.4A Active CN111422363B (en) | 2019-12-30 | 2019-12-30 | Buffering and energy absorbing device for aviation seat |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111422363B (en) |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN205479105U (en) * | 2016-04-07 | 2016-08-17 | 安徽普源分离机械制造有限公司 | Inhale formula shock absorber that shakes |
| WO2016164299A1 (en) * | 2015-04-08 | 2016-10-13 | Zodiac Seat Shells U.S. Llc | Universal rest seats |
| DE102015224849A1 (en) * | 2015-12-10 | 2017-06-29 | Volkswagen Aktiengesellschaft | Damper device and method for influencing a vibration behavior of a damper device |
| FR3058949A1 (en) * | 2016-11-21 | 2018-05-25 | Peugeot Citroen Automobiles Sa | VEHICLE SEAT SUSPENSION DEVICE |
| CN108657376A (en) * | 2018-04-25 | 2018-10-16 | 武汉理工大学 | A kind of river-sea through ship cabin seat damping device |
| CN108790978A (en) * | 2018-07-26 | 2018-11-13 | 湖北海联技术咨询有限公司 | A kind of seat damper convenient for adjusting |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11066172B2 (en) * | 2015-10-15 | 2021-07-20 | The Boeing Company | Controlled energy absorption of seats for impact |
-
2019
- 2019-12-30 CN CN201911396535.4A patent/CN111422363B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2016164299A1 (en) * | 2015-04-08 | 2016-10-13 | Zodiac Seat Shells U.S. Llc | Universal rest seats |
| DE102015224849A1 (en) * | 2015-12-10 | 2017-06-29 | Volkswagen Aktiengesellschaft | Damper device and method for influencing a vibration behavior of a damper device |
| CN205479105U (en) * | 2016-04-07 | 2016-08-17 | 安徽普源分离机械制造有限公司 | Inhale formula shock absorber that shakes |
| FR3058949A1 (en) * | 2016-11-21 | 2018-05-25 | Peugeot Citroen Automobiles Sa | VEHICLE SEAT SUSPENSION DEVICE |
| CN108657376A (en) * | 2018-04-25 | 2018-10-16 | 武汉理工大学 | A kind of river-sea through ship cabin seat damping device |
| CN108790978A (en) * | 2018-07-26 | 2018-11-13 | 湖北海联技术咨询有限公司 | A kind of seat damper convenient for adjusting |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111422363A (en) | 2020-07-17 |
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