Aircraft seat with a single-beam structure and aircraft comprising such a seat
An aircraft seat includes a seat bucket that is integral by its seatback with a single beam oriented along an axis that is approximately perpendicular to the aircraft floor, which beam is integral with fastening points located on at least two separate lines on the aircraft floor.
1. Aircraft seat comprising:
a seat bucket ( 1 ), which establishes a longitudinal direction X forward of the seat and a vertical direction Z above the seat, said seat bucket comprising a seatback ( 3 ) and a seat pan ( 2 ) integral with said seatback, and
a single structural guide beam ( 5 ), located in a rear part of the seat, oriented in an approximately vertical or inclined direction Z 1 in relation to the vertical direction Z in a plane XZ determined by the longitudinal direction X and vertical direction Z, on which said guide beam the seat bucket ( 1 ) is fastened,
said guide beam ( 5 ) being integral with a connecting structure for connecting said guide beam to a floor ( 100 ) of an aircraft,
said connecting structure comprising,
at least four fastening points, for fastening to said floor, distributed along two lines that are approximately parallel to the longitudinal direction X and that are apart from a vertical plane of symmetry XZ of said seat, and
a mounting sleeve ( 6 ) of the guide beam ( 5 ) and with which sleeve four feet ( 8 a , 8 b , 9 a , 9 b ) are integral and at the free ends of the four feet the fastening points are placed.
2. Aircraft seat according to claim 1 , wherein the seat bucket ( 1 ) is held in front of the guide beam ( 5 ) by two attachment parts ( 10 , 11 ) that are integral with the seatback ( 3 ) on a rear face of said seatback and apart from one another in the direction Z 1 .
3. Aircraft seat according to claim 2 , wherein the two attachment parts ( 10 , 11 ) that are integral with the seatback ( 3 ) slide along the guide beam ( 5 ) in the direction Z 1 and comprise a device for locking the position in the direction Z 1 of at least one of said two attachment parts.
4. Aircraft seat according to claim 3 , wherein two of the four feet ( 8 b , 9 b ) of a same line of fasteners that is approximately parallel to the direction X of the connecting structure are rigidly connected to the guide beam ( 5 ) and wherein another two of the four feet ( 8 a , 9 a ), rigidly integral with one another, of another line of fasteners are fixed in an articulated manner, along an axis Y oriented perpendicularly to the plane XZ, in relation to a sub-unit formed by the guide beam ( 5 ) and the two feet ( 8 b , 9 b ) that are rigidly connected to said guide beam.
5. Aircraft seat according to claim 4 , wherein the two feet ( 8 b , 9 b ) of the same line of fasteners that are approximately parallel to the direction X of the connecting structure rigidly linked to the guide beam ( 5 ) are linked by means of an articulation around the axis Y, said articulation comprising a device for locking in rotation.
6. Seat according to claim 5 , wherein two of the four feet ( 8 a , 9 a ) ( 8 b , 9 b ) of a same line of fasteners that is approximately parallel to the direction X comprise a stationary part ( 8 a , 8 b ), provided with an interface for a fastening point on the floor ( 100 ) that is integral with the guide beam ( 5 ), and an adjustable part ( 9 a , 9 b ), also provided with an interface for a fastening point, the adjustable part ( 9 a , 9 b ) being integral with the stationary part ( 8 a , 8 b ) and being able to slide in relation to the stationary part ( 8 a , 8 b ) in a direction X that is parallel to the lines of fastening points, with at least one space between two floor ( 100 ) fastening points or that can be changed in length in the direction X.
7. Aircraft seat according to claim 4 , wherein the two feet ( 8 a , 9 a ) ( 8 b , 9 b ) of the same line of fasteners that is approximately parallel to the direction X comprise a stationary part ( 8 a , 8 b ), provided with an interface for a fastening point on the floor ( 100 ) that is integral with the guide beam ( 5 ), and an adjustable part ( 9 a , 9 b ), also provided with an interface for a fastening point, the adjustable part ( 9 a , 9 b ) being integral with the stationary part ( 8 a , 8 b ) and being able to slide in relation to the stationary part ( 8 a , 8 b ) in a direction X that is parallel to the lines of fastening points, with at least one space between two floor ( 100 ) fastening points or that can be changed in length in the direction X.
8. Aircraft seat according to claim 4 , further comprising a safety belt that is integral with the seat bucket 1 , said safety belt having a free length on an interior side of the bucket that is a function of morphological characteristics of a passenger and in which said belt from each fastening point of the belt to the bucket passes through a first guide ( 14 a , 14 b ) that is integral with the guide beam ( 5 ), located at a height greater than the attachment to the bucket, then passes through a second guide ( 15 a , 15 b ) that is integral with a foot of the corresponding side ( 8 a , 8 b ), located at a height lower than the first guide and at a height lower than the seat pan ( 2 ), and then rises above the seat pan.
9. Aircraft seat according to claim 2 , wherein the structure for connecting the guide beam ( 5 ) to the floor ( 100 ) comprises a mounting sleeve ( 6 ) of the guide beam ( 5 ) and with which sleeve four feet ( 8 a , 8 b , 9 a , 9 b ) are integral and at the free ends of which feet the fastening points are placed.
10. Aircraft seat according to claim 1 , wherein the guide beam ( 5 ) slides in a direction parallel to Z 1 in the sleeve ( 6 ) and is held in the direction of sliding by a damping device with an approximately vertical axis.
11. Aircraft seat according to claim 10 , wherein the feet ( 8 a , 8 b , 9 a , 9 b ) are placed to absorb, by deformation, energy linked to a force, a vertical component downward of which exceeds a predefined threshold.
12. Aircraft seat according to claim 1 , wherein the four feet ( 8 a , 8 b , 9 a , 9 b ) are placed to absorb, by deformation, energy linked to a force, a vertical component downward of which exceeds a predefined threshold.
13. Aircraft seat according to claim 1 , wherein one of the two attachment parts ( 10 ) ( 11 ) that are integral with the seatback ( 3 ) comprises a pivot pin ( 111 ) for articulation of the seatback around an axis parallel to a direction Y that is perpendicular to the plane XZ, and the other attachment part ( 11 ) ( 10 ) comprises an extendable part ( 101 ) for locally changing a distance from said seatback to the guide beam ( 5 ).
14. Aircraft seat according to claim 13 , wherein the guide beam ( 5 ) comprises at least two slides ( 51 a ) that are approximately symmetrical in relation to a vertical symmetry plane XZ of said guide beam in which slides the attachment parts ( 10 , 11 ) that are integral with the seatback ( 3 ) are mounted to slide freely.
15. Aircraft seat according to claim 14 , wherein the attachment part comprising an extendable element comprises at least two arms ( 112 a , 112 b ) sliding in an anterior slide ( 51 a ) at independent ends and pivoting around a common axis parallel to the direction Y linked to the seatback ( 3 ) at other ends of said at least two arms to form an angle that can be changed.
16. Aircraft seat according to claim 1 , wherein the guide beam ( 5 ) comprises a fastener in an upper part of said guide beam for connection to a ceiling structure or to a structure of a bulkhead of an aircraft.
17. Aircraft comprising at least one aircraft seat according to claim 1 .