CN108715227A - The full aero seat skeleton structure that lies low - Google Patents
The full aero seat skeleton structure that lies low Download PDFInfo
- Publication number
- CN108715227A CN108715227A CN201810517463.3A CN201810517463A CN108715227A CN 108715227 A CN108715227 A CN 108715227A CN 201810517463 A CN201810517463 A CN 201810517463A CN 108715227 A CN108715227 A CN 108715227A
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- flat
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- 238000000034 method Methods 0.000 description 7
- 238000013461 design Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
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
- B64D11/0639—Arrangements of seats, or adaptations or details specially adapted for aircraft seats with features for adjustment or converting of seats
- B64D11/0641—Seats convertible into beds
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chairs For Special Purposes, Such As Reclining Chairs (AREA)
- Seats For Vehicles (AREA)
Abstract
The invention discloses a kind of aero seat skeleton structures that lies low entirely, including fixed skeleton component, traction skeleton component, bottom deck assembly, backrest module and the first telescopic component；Traction skeleton component is slidably mounted in the fixed skeleton component；Bottom deck assembly is slidably mounted in the fixed skeleton component, and is articulated with the top of traction skeleton component；The bottom of backrest module is articulated with above the rear end of the base plate assembly；The lower end of strut component and the rear end bottom of fixed skeleton component are hinged, and the bottom of the upper end and backrest module is hinged, the top of hinge joint hinge joint between backrest module and base plate assembly between strut component and backrest module；One end of first telescopic component is fixedly mounted on the fixed skeleton component, and the other end is fixedly mounted on the traction skeleton component.The present invention may be implemented that seat is electronic to lie low or reset entirely, have the advantages that simple in structure, light-weight, can also improve the reliability of chair framework entirety.
Description
Technical Field
The invention belongs to the technical field of aviation seats, and particularly relates to a full-flat-lying aviation seat framework structure.
Background
Foreign countries have a lot of electronic full flat aviation seats of lying, and it has multiple seat skeleton texture, but the mode that the drive mode adopted the rotating electrical machines to pull the rack mostly realizes that the seat is flat to lie, just so leads to seat skeleton texture complicated to be unfavorable for seat maintenance and reset. In China, an electric reclining aviation seat is also arranged and is driven by a linear motor, but the full reclining can not be realized, and the traction force is larger.
Disclosure of Invention
The invention aims to provide a full-flat-lying aviation seat framework structure, which converts the linear motion of a linear motor into backward tilting of a backrest component and forward extending motion of a seat plate component, finally realizes electric full-flat lying or resetting of a seat, has the advantages of simple structure and light weight, and can also improve the overall reliability of the seat framework.
The technical scheme adopted by the invention for solving the technical problems is as follows:
a full-flat-lying aviation seat framework structure comprises a fixed framework assembly, a traction framework assembly, a bottom plate assembly, a backrest assembly and a first telescopic assembly; wherein,
the bottom of the fixed framework component is fixedly arranged on a plane foundation;
the traction framework assembly is slidably mounted in the fixed framework assembly, and a certain included angle is formed between a sliding straight line of the traction framework assembly and a plane foundation;
the bottom plate assembly is slidably mounted in the fixed framework assembly and hinged above the traction framework assembly, and a sliding straight line between the bottom plate assembly and the fixed framework assembly is approximately parallel to the plane foundation;
the bottom of the backrest component is hinged above the rear end of the seat plate component;
the lower end of the support rod assembly is hinged with the bottom of the rear end of the fixed framework assembly, the upper end of the support rod assembly is hinged with the bottom of the backrest assembly, and a hinge point between the support rod assembly and the backrest assembly is positioned above a hinge point between the backrest assembly and the seat plate assembly;
the one end fixed mounting of first flexible subassembly is in on the fixed skeleton subassembly, its other end fixed mounting be in on the traction skeleton subassembly, first flexible subassembly drives through the concertina movement of self under external drive traction skeleton subassembly and bottom plate subassembly are straight line slip around doing along fixed skeleton subassembly simultaneously, and then drive keeping flat or reseing of back subassembly.
According to the technical scheme, two protruding rotating pieces are inwards arranged on two side walls of the fixed framework assembly, linear guide rail grooves are formed in the two side walls of the traction framework assembly, and the traction framework assembly is slidably installed on the protruding rotating pieces of the fixed framework assembly through the linear guide rail grooves.
According to the technical scheme, the inner sides of the two side walls of the fixed framework component are longitudinally provided with the strip-shaped grooves, the two outer sides of the rear end of the seat plate component are provided with the rotating shafts, and the seat plate component is slidably installed in the strip-shaped grooves of the fixed framework component through the rotating shafts.
According to the technical scheme, the included angle between the sliding straight line of the traction framework component and the plane foundation is 7-11 degrees.
According to the technical scheme, the first telescopic assembly is a linear motor.
According to the technical scheme, the framework structure further comprises a leg leaning component and a second telescopic component, wherein the leg leaning component is hinged to the front end of the bottom plate component, one end of the second telescopic component is fixedly installed at the bottom of the leg leaning component, the other end of the second telescopic component is fixedly installed at the bottom of the bottom plate component, and the second telescopic component drives the leg leaning component to rotate through self telescopic motion under the driving of external force so as to realize the flat placement or reset of the leg leaning component.
According to the technical scheme, the second telescopic assembly is a linear motor.
The invention has the following beneficial effects: according to the invention, the linear reciprocating motion of the first telescopic component is converted into the reciprocating sliding of the traction framework component and the bottom plate component along respective sliding lines, and the seat plate component, the backrest component, the support component and the fixed framework component form a crank-slider mechanism together by designing the hinge point of the support component and the fixed framework component and the hinge point of the backrest component and the seat plate component, and the seat plate component reciprocates back and forth to drive the backrest component to rotate, so that the full-flat lying or resetting of the framework structure of the aviation seat is finally realized. According to the invention, the traction framework assembly and the bottom plate assembly both perform linear (or approximately linear) motion, so that the friction force is reduced, and the risk of clamping stagnation in the motion process is reduced. The invention has simple structure, light weight and high overall reliability.
Drawings
The invention will be further described with reference to the accompanying drawings and examples, in which:
FIG. 1 is a schematic structural diagram of an embodiment of the present invention;
FIG. 2 is an exploded view of an embodiment of the present invention;
FIG. 3 is a side view of an embodiment of the present invention;
FIG. 4 is a schematic illustration of the installation of the traction frame assembly and the fixed frame assembly in an embodiment of the present invention;
FIG. 5 is a schematic view of the mounting of the seat pan assembly to the fixed frame in an embodiment of the present invention;
FIG. 6 is a schematic view of a full flat bed in an embodiment of the present invention;
FIG. 7 is a schematic illustration of the construction of a traction frame assembly in an embodiment of the present invention;
FIG. 8 is a schematic structural view of a seat pan assembly in an embodiment of the present invention;
fig. 9 is a schematic structural diagram of a fixing skeleton assembly in the embodiment of the invention.
In the figure: 1-fixed framework component, 1.1-protruded rotating piece, 1.2-strip-shaped groove, 2-traction framework component, 2.1-linear guide rail groove, 3-bottom plate component, 3.1-rotating shaft, 4-backrest component, 5-first telescopic component, 6-leg backrest component, 7-second telescopic component and 8-brace component.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is described in further 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.
In the preferred embodiment of the present invention, as shown in fig. 1-3, a full-flat-down airline seat frame structure includes a fixed frame assembly 1, a towing frame assembly 2, a floor assembly 3, a backrest assembly 4, a strut assembly 8, and a first telescoping assembly 5; wherein,
the bottom of the fixed framework component 1 is fixedly arranged on a plane foundation;
the traction framework component 2 is slidably arranged in the fixed framework component 1, a certain included angle is arranged between a sliding straight line of the traction framework component 2 and a plane foundation, the included angle is related to the movement of the backrest component in the process of backward tilting, the backrest component can be switched between a flat lying position and an initial position within the stroke range (204mm) of the first telescopic component, the design of the included angle is also related to the output force value of the first telescopic component (namely a linear motor in the embodiment) so as to finish the required movement process by the minimum force or the shortest movement stroke, the included angle is 7-11 degrees, the optimal included angle is 9 degrees, the output force is small at 9 degrees, and the stroke is not too long;
as shown in fig. 4 and 5, the bottom plate assembly 3 is slidably mounted in the fixed framework assembly 1 and is hinged above the traction framework assembly 2, a sliding straight line between the bottom plate assembly 3 and the fixed framework assembly 1 is approximately parallel to the plane foundation, namely, a slight inclination angle within 5 degrees is arranged between the strip-shaped groove 1.2 and the plane foundation in the embodiment, specifically 2.3 degrees is selected to ensure the comfort of passengers in the process of falling;
the bottom of the backrest component 4 is hinged above the rear end of the seat plate component;
the stay bar component 8 is used as a support of the backrest component, the lower end of the stay bar component 8 is hinged with the bottom of the rear end of the fixed framework component 1, the upper end of the stay bar component 8 is hinged with the bottom of the backrest component 4, and a hinge point between the stay bar component 8 and the backrest component 4 is positioned above a hinge point between the backrest component 4 and the seat plate component;
one end fixed mounting of first flexible subassembly 5 is on fixed skeleton subassembly 1, its other end fixed mounting is on pulling skeleton subassembly 2, first flexible subassembly 5 drives through the concertina movement of self under the external force drive and pulls skeleton subassembly 2 and bottom plate subassembly 3 and do the straight line simultaneously and slide around fixed skeleton subassembly 1, the back subassembly begins the hypsokinesis, the bedplate subassembly reduces at the in-process focus that moves ahead gradually, can hypsokinesis to 176 full flat state of lying of inclining backward, thereby realize keeping flat or reseing of back subassembly 4, the reset state is as shown in fig. 3, the state of keeping flat is as shown in fig. 6.
In a preferred embodiment of the present invention, as shown in fig. 9, two protruding rotating members 1.1 are inwardly disposed on two side walls of the fixed frame assembly 1, as shown in fig. 7, linear guide rail grooves 2.1 are disposed on two side walls of the traction frame assembly 2, and the traction frame assembly 2 is slidably mounted on the protruding rotating members 1.1 of the fixed frame assembly 1 through the linear guide rail grooves 2.1, wherein the protruding rotating members may be bearings, and the protruding rotating members and the linear guide rail grooves are adopted as guide rails, so that the assembly between the protruding rotating members and the linear guide rail grooves is facilitated, and the sliding stability is ensured.
In the preferred embodiment of the present invention, as shown in fig. 9, the inner sides of the two side walls of the fixed frame component 1 are longitudinally provided with strip-shaped grooves 1.2, as shown in fig. 8, the two outer sides of the rear end of the seat plate component are provided with rotating shafts 3.1, and the seat plate component is slidably mounted in the strip-shaped grooves 1.2 of the fixed frame component 1 through the rotating shafts 3.1, wherein the rotating shafts can be bearings, and the bearings and the strip-shaped grooves are used as guide rails, so that the assembly between the bearings and the strip-shaped grooves can be facilitated, and the sliding stability can.
In a preferred embodiment of the present invention, as shown in fig. 1 to 3, the framework structure further includes a leg rest assembly 6 and a second telescopic assembly 7, the leg rest assembly 6 is hinged to the front end of the base plate assembly 3, one end of the second telescopic assembly 7 is fixedly mounted at the bottom of the leg rest assembly 6, the other end of the second telescopic assembly 7 is fixedly mounted at the bottom of the base plate assembly 3, and the second telescopic assembly drives the leg rest assembly 6 to rotate through its own telescopic movement under the driving of an external force, so as to realize the horizontal placement or the reset of the leg rest assembly 6.
In a preferred embodiment of the present invention, the first telescopic assembly 5 and the second telescopic assembly 7 are both electrically driven to realize automatic full-flat lying of the framework structure of the aviation seat, and the first telescopic assembly 5 and the second telescopic assembly 7 can be linear motors.
The key points of the invention are the design of the hinge point of the backrest component and the fixed framework component and the length size of the stay bar component, and meanwhile, the inclination angle of the linear guide rail groove on the traction framework component is a key factor influencing the posture of the seat plate component in the whole movement process. According to the invention, the positions of the hinged points of the support rod assembly and the backrest assembly and the inclination angle of the traction framework assembly are determined through ADAMS software dynamic simulation, so that the backrest assembly can be inclined backwards to 176-degree full-flat lying state when the push rod of the first telescopic assembly extends out for 204mm, and meanwhile, the seat plate assembly is still in a horizontal state under the condition of reduced gravity center, the output force of the linear motor serving as the first telescopic assembly in the whole movement process is not more than 2500N, the driving torque of the motor is reduced, and the movement overload is reduced.
The skeleton structure of the aviation seat is the core structure of the aviation seat, and the technical advantages of the skeleton structure are directly related to the cost, price, reliability, airworthiness and market competitiveness of the product. The invention is used as a structural platform of a new generation of electric seats, can be widely applied to the models of seats of wide-body passenger planes, and can become the basis of the research and development of the electric seats in the next years.
It will be understood that modifications and variations can be made by persons skilled in the art in light of the above teachings and all such modifications and variations are intended to be included within the scope of the invention as defined in the appended claims.
Claims (7)
1. A full-flat-lying aviation seat framework structure is characterized by comprising a fixed framework component (1), a traction framework component (2), a bottom plate component (3), a backrest component (4) and a first telescopic component (5); wherein,
the bottom of the fixed framework component (1) is fixedly arranged on a plane foundation;
the traction framework assembly (2) is slidably mounted in the fixed framework assembly (1), and a certain included angle is formed between a sliding straight line of the traction framework assembly (2) and a plane foundation;
the bottom plate assembly (3) is slidably mounted in the fixed framework assembly (1) and hinged above the traction framework assembly (2), and a sliding straight line between the bottom plate assembly (3) and the fixed framework assembly (1) is approximately parallel to a plane foundation;
the bottom of the backrest component (4) is hinged above the rear end of the seat plate component;
the lower end of the support rod component (8) is hinged with the bottom of the rear end of the fixed framework component (1), the upper end of the support rod component (8) is hinged with the bottom of the backrest component (4), and a hinge point between the support rod component (8) and the backrest component (4) is positioned above a hinge point between the backrest component (4) and the seat plate component;
the one end fixed mounting of first flexible subassembly (5) is in on fixed skeleton subassembly (1), its other end fixed mounting pull on skeleton subassembly (2), first flexible subassembly (5) drive through the concertina movement of self under the exogenic drive pull skeleton subassembly (2) and bottom plate subassembly (3) and do the straight line simultaneously and slide around along fixed skeleton subassembly (1), and then drive keeping flat or reseing of back subassembly (4).
2. The full-flat-lying aircraft seat framework structure according to claim 1, characterized in that two protruding rotating pieces (1.1) are inwardly arranged on two side walls of the fixed framework component (1), linear guide grooves (2.1) are formed on two side walls of the traction framework component (2), and the traction framework component (2) is slidably mounted on the protruding rotating pieces (1.1) of the fixed framework component (1) through the linear guide grooves (2.1).
3. The full-flat-lying aviation seat framework structure according to claim 1, wherein strip-shaped grooves (1.2) are formed in the inner sides of the two side walls of the fixed framework component (1) along the longitudinal direction, rotating shafts (3.1) are arranged on the two outer sides of the rear end of the seat plate component, and the seat plate component is slidably mounted in the strip-shaped grooves (1.2) of the fixed framework component (1) through the rotating shafts (3.1).
4. The full flat aircraft seat frame structure of claim 1, characterized in that the angle between the straight sliding line of the towing frame assembly (2) and the plane base is 7-11 °.
5. The full flat aircraft seat frame structure of claim 1 wherein the first telescoping assembly (5) is a linear motor.
6. The full-flat-lying aircraft seat framework structure according to claim 1, characterized in that the framework structure further comprises a leg rest assembly (6) and a second telescopic assembly (7), wherein the leg rest assembly (6) is hinged to the front end of the bottom plate assembly (3), one end of the second telescopic assembly (7) is fixedly installed at the bottom of the leg rest assembly (6), the other end of the second telescopic assembly is fixedly installed at the bottom of the bottom plate assembly (3), and the second telescopic assembly drives the leg rest assembly (6) to rotate through self telescopic movement under the driving of external force so as to realize the flat placement or resetting of the leg rest assembly (6).
7. The full flat aircraft seat frame structure of claim 6 wherein the second telescoping assembly (7) is a linear motor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810517463.3A CN108715227B (en) | 2018-05-25 | 2018-05-25 | Framework structure of full-flat-lying aviation seat |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810517463.3A CN108715227B (en) | 2018-05-25 | 2018-05-25 | Framework structure of full-flat-lying aviation seat |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108715227A true CN108715227A (en) | 2018-10-30 |
| CN108715227B CN108715227B (en) | 2021-07-06 |
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ID=63900397
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810517463.3A Active CN108715227B (en) | 2018-05-25 | 2018-05-25 | Framework structure of full-flat-lying aviation seat |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021083754A1 (en) * | 2019-10-31 | 2021-05-06 | Safran Seats | Seat, in particular for an aircraft, with a single actuator |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1116654A2 (en) * | 2000-01-13 | 2001-07-18 | Be Aerospace, Inc. | Passenger sleeper seat |
| CN101863236A (en) * | 2009-04-14 | 2010-10-20 | 上海坦达轨道车辆座椅系统有限公司 | Train seat |
| CN105163628A (en) * | 2013-04-08 | 2015-12-16 | B/E航空公司 | Vehicle seat with simultaneous articulation of seat pan and seat back |
| CN105197036A (en) * | 2015-09-28 | 2015-12-30 | 敏华家具制造(惠州)有限公司 | Shank adjusting seat |
-
2018
- 2018-05-25 CN CN201810517463.3A patent/CN108715227B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1116654A2 (en) * | 2000-01-13 | 2001-07-18 | Be Aerospace, Inc. | Passenger sleeper seat |
| CN101863236A (en) * | 2009-04-14 | 2010-10-20 | 上海坦达轨道车辆座椅系统有限公司 | Train seat |
| CN105163628A (en) * | 2013-04-08 | 2015-12-16 | B/E航空公司 | Vehicle seat with simultaneous articulation of seat pan and seat back |
| CN105197036A (en) * | 2015-09-28 | 2015-12-30 | 敏华家具制造(惠州)有限公司 | Shank adjusting seat |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021083754A1 (en) * | 2019-10-31 | 2021-05-06 | Safran Seats | Seat, in particular for an aircraft, with a single actuator |
| FR3102721A1 (en) * | 2019-10-31 | 2021-05-07 | Safran Seats | SEAT ESPECIALLY FOR A SINGLE ACTUATOR AIRPLANE |
| US11958614B2 (en) | 2019-10-31 | 2024-04-16 | Safran Seats | Seat, in particular for an aircraft, with a single actuator |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108715227B (en) | 2021-07-06 |
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