# US 9,604,725 B2 · Aircraft seat with a single-beam structure and aircraft comprising such a seat

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- Number: US 9,604,725 B2
- Document ID: US9604725B2
- Status: Granted
- Kind: B2
- Application number: 13/911,271
- Filed: 2013-06-06
- Published: 2013-12-12
- Granted: 2017-03-28
- Earliest claimed: 2012-06-06
- Assignees: Stelia Aerospace
- Applicants: Eads Sogerma
- Inventors: Laurent Cecinas; Julien Normandin; Remy Barre; Lionel Bacquey
- Web page: https://patentgrep.com/patent/US9604725B2

## CPC

- B64D 11/0696: {Means for fastening seats to floors, e.g. to floor rails}
- B60N 2/20: the back-rest being tiltable, e.g. to permit easy access (B60N2/04, B60N2/22 {, B60N2/3002} take precedence)
- B60N 2/3031: {in a longitudinal-vertical plane}
- B60N 2/3065: {in a longitudinal-vertical plane}
- B60N 2/309: {rods}
- B60N 2/4242: {vertical}
- B60N 2/427: Seats or parts thereof displaced during a crash
- B60N 2/42709: {involving residual deformation or fracture of the structure}
- B64D 11/06: {Arrangements of seats, or adaptations or details specially adapted for aircraft seats (crew seat constructions for emergency purposes B64D25/04)}
- B64D 11/0619: {with energy absorbing means specially adapted for mitigating impact loads for passenger seats, e.g. at a crash}
- B64D 11/064: {Adjustable inclination or position of seats}
- B64D 11/0649: {Seats characterised by special features for reducing weight}
- B64D 11/0689: {specially adapted for pilots}
- B64D 25/04: Seat modifications
- B60N 2/16: height-adjustable
- Y02T 50/40: Weight reduction
- B64D: EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B60N: SEATS SPECIALLY ADAPTED FOR VEHICLES; VEHICLE PASSENGER ACCOMMODATION NOT OTHERWISE PROVIDED FOR
- Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION

## Abstract

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.

## Claims

### Claim 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 Z1 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 (8a, 8b, 9a, 9b) are integral and at the free ends of the four feet the fastening points are placed.

### Claim 2 (depends on 1)

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 Z1.

### Claim 3 (depends on 2)

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 Z1 and comprise a device for locking the position in the direction Z1 of at least one of said two attachment parts.

### Claim 4 (depends on 3)

Aircraft seat according to claim 3, wherein two of the four feet (8b, 9b) 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 (8a, 9a), 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 (8b, 9b) that are rigidly connected to said guide beam.

### Claim 5 (depends on 4)

Aircraft seat according to claim 4, wherein the two feet (8b, 9b) 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.

### Claim 6 (depends on 5)

Seat according to claim 5, wherein two of the four feet (8a, 9a) (8b, 9b) of a same line of fasteners that is approximately parallel to the direction X comprise a stationary part (8a, 8b), provided with an interface for a fastening point on the floor (100) that is integral with the guide beam (5), and an adjustable part (9a, 9b), also provided with an interface for a fastening point, the adjustable part (9a, 9b) being integral with the stationary part (8a, 8b) and being able to slide in relation to the stationary part (8a, 8b) 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.

### Claim 7 (depends on 4)

Aircraft seat according to claim 4, wherein the two feet (8a, 9a) (8b, 9b) of the same line of fasteners that is approximately parallel to the direction X comprise a stationary part (8a, 8b), provided with an interface for a fastening point on the floor (100) that is integral with the guide beam (5), and an adjustable part (9a, 9b), also provided with an interface for a fastening point, the adjustable part (9a, 9b) being integral with the stationary part (8a, 8b) and being able to slide in relation to the stationary part (8a, 8b) 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.

### Claim 8 (depends on 4)

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 (14a, 14b) 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 (15a, 15b) that is integral with a foot of the corresponding side (8a, 8b), 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.

### Claim 9 (depends on 2)

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 (8a, 8b, 9a, 9b) are integral and at the free ends of which feet the fastening points are placed.

### Claim 10 (depends on 1)

Aircraft seat according to claim 1, wherein the guide beam (5) slides in a direction parallel to Z1 in the sleeve (6) and is held in the direction of sliding by a damping device with an approximately vertical axis.

### Claim 11 (depends on 10)

Aircraft seat according to claim 10, wherein the feet (8a, 8b, 9a, 9b) are placed to absorb, by deformation, energy linked to a force, a vertical component downward of which exceeds a predefined threshold.

### Claim 12 (depends on 1)

Aircraft seat according to claim 1, wherein the four feet (8a, 8b, 9a, 9b) are placed to absorb, by deformation, energy linked to a force, a vertical component downward of which exceeds a predefined threshold.

### Claim 13 (depends on 1)

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).

### Claim 14 (depends on 13)

Aircraft seat according to claim 13, wherein the guide beam (5) comprises at least two slides (51a) 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.

### Claim 15 (depends on 14)

Aircraft seat according to claim 14, wherein the attachment part comprising an extendable element comprises at least two arms (112a, 112b) sliding in an anterior slide (51a) 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.

### Claim 16 (depends on 1)

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.

### Claim 17 (depends on 1)

Aircraft comprising at least one aircraft seat according to claim 1.