Energy-absorbing device, structure forming a mounting for an aircraft seat having such a device, and seat having such a structure

• US 5,344,210 A
• Filed: 01/21/1992
• Issued: 09/06/1994
• Est. Priority Date: 01/22/1991
• Status: Expired due to Fees

• Current Assignee: Sicma Aero Seat Societe Industrielle et Commerciale de Materiel Aeronautique
• Original Assignee: Sicma Aero Seat Societe Industrielle et Commerciale de Materiel Aeronautique
• Inventors: Marwan, Dannawi, Thierry, Prott
• Primary Examiner(s): Brittain, James R.
• Application Number:
  US07/823,327
• Time in Patent Office: 959 Days
• Field of Search: 297/216, 297/216.1, 297/216.2, 244/122 R, 244/122 AG
• US Class Current: 297/216.2
• CPC Class Codes: B64D 25/04 Seat modifications
• CPC Class Codes: F16F 7/123 Deformation involving a bending action, e.g. strap moving through multiple rollers, folding of members F16F7/125, F16F7/128 take precedence

Abstract

An energy absorbing device for an aircraft seat supporting structure providing an elongate one piece element pivotably connected to front and rear seat supporting legs and having a general crescent shape with two curved arm portions of opposite convexities separated by a space arranged in a central portion of the crescent shape.

Claims

1. An energy-absorbing device interposed between the front foot and the rear foot of a structure forming a mounting of an aircraft seat, in such a way that, when the structure is deformed in the event of a shock, the device undergoes at least one longitudinal compressive force, comprising a substantially elongate one-piece element, each end of which is associated respectively with one of the feet,3 in that said element comprises a first portion which shape is predetermined in such a way that this element undergoes a natural general structural plastic deformation according to a mode of deformation prescribed by said predetermined shape of said first portion, and in that said element comprises a second portion arranged so as to oppose the general structural plastic deformation of the element and to undergo a natural plastic bending deformation by buckling from a predetermined value of the longitudinal compressive force applied between said ends of said element.

2. The device as claimed in claim 1, wherein the element is arranged so as to undergo a general plastic bending deformation.

3. The device as claimed in claim 2, wherein the element is arranged so as to undergo a general plastic bending deformation by buckling.

4. The device as claimed in claim 1, wherein said first portion is constituted of a predeformation part of said element, and wherein said second portion is arranged so as to constitute an arched abutment opposing said predeformed part.

5. The device as claimed in claim 1, wherein the element comprises a localized zone which, before deformation, is set out from the alignment of its two ends, wherein the mechanical characteristics and dimensions of this localized zone are such that the general plastic deformation of the element is concentrated in this localized zone, and wherein there are means for energy absorption by plastic deformation which are active during the bending deformation of the element in the localized zone generated by the longitudinal compressive force.

6. The device as claimed in claim 5, wherein the energy-absorbing means comprises plastic bending deformation of the localized zone.

7. The device as claimed in claim 5, wherein the localized zone is at least substantially central.

8. The device as claimed in claim 5, wherein the element is dimensioned so as not to undergo any deformation outside the localized zone.

9. The device as claimed in claim 5, wherein the energy-absorbing means consist at least partly of said first portion which is a less resistant finest portion of the localized zone of the element, this less resistant portion experiencing plastic bending deformation and thereby absorbing the energy, the plastic bending deformation of this less resistant portion corresponding to the general being deformation of the element.

10. The device as claimed in claim 9 , wherein the second portion is arranged so as to oppose the general bending deformation of the element and the bending deformation of the less resistant first portion.

11. The device as claimed in claim 10, wherein the second portion consists of a strut opposing the general bending deformation of the element and the bending deformation of the less resistant first portion, and wherein this second portion is dimensioned so as to undergo a deformation by buckling from a predetermined value of the compressive force undergone by the element.

12. The device as claimed in claim 5, wherein the localized zone consists of two curved-arm portions of opposite convexities separated by a space, the curvatures of these portions corresponding to and determining the bending deformations which they undergo during the shock.

13. The device as claimed in claim 12, wherein the device comprises a convex face and an essentially concave face and wherein one of the curved-arm portions of the localized zone forms an apex of greatest curvature of the convex face of the device, and its convexity is therefore oriented in the same direction as that of the device, and wherein the other curved-arm portion partly forms the essentially concave face of the device, but its convexity is oriented in the other direction so as to form a strut opposing the general bending deformation of the device.

14. The device as claimed in claim 1, wherein the element is generally crescent-shaped.

15. The device as claimed in claim 1 , wherein the element is essentially curved or angular, the localized zone being that of greatest overall curvature.

16. A structure forming a mounting for an aircraft seat, comprising;

an energy-absorbing device;

a front foot; and

a rear foot, said energy absorbing device interposed between the front foot and the rear foot; and

wherein the device undergoes at least one longitudinal compressive force, when the structure is deformed in the event of a shock, wherein the device comprises a substantially elongate one-piece element, each end of which is associated respectively with one of the feet, in that said element comprises a first portion which shape is predetermined in such a way that this element undergoes a natural general structure plastic deformation according to a mode of deformation prescribed by said predetermined shape of said first portion, and in that said element comprises a second portion arranged so as to oppose the general structural plastic deformation of the element and to undergo a natural plastic bending deformation by buckling from a predetermined value of the longitudinal compressive force applied between said ends of said element.

17. A structure forming a mounting for an aircraft seat, associated in an anchored manner with the fixed structure of the craft, by means of at least one front anchorage of a front foot and by means of at least one rear anchorage of a rear foot, the front and rear feet being associated with a framework of the seat, in a normal position the front foot extending at least substantially vertically from the lower front anchorage thereof, especially perpendicularly to the floor of the craft, the front and rear feet being articulated at the respective upper ends thereof on the framework of the seat, so as to be capable of pivoting about horizontal and transverse pivot axes, the structure comprising an energy-absorbing device associated with an upper part of the rear foot, but at a distance from an upper rear articulation, and associated with the lower front anchorage and in the vicinity or at the lower front anchorage, wherein the energy-absorbing device undergoes at least one longitudinal compressive force, when the structure is deformed in the event of a shock, wherein the device comprises a substantially elongate one-piece element, in that said element comprises a first portion which shape is predetermined in such a way that this element undergoes a natural general structure plastic deformation according to a mode of deformation prescribed by said predetermined shape of said first portion, and in that said element comprises a second portion arranged so as to oppose the general structural plastic deformation of the element and to undergo a natural plastic bending deformation by buckling from a predetermined value of the longitudinal compressive force applied between said ends of said element.

18. The structure as claimed in claim 17, which, in combination, comprises means limiting or preventing the forward pivoting of the rear foot about its rear anchorage on the fixed structure of the craft.

19. The structure as claimed in claim 17, wherein, in combination, the rear foot is in the form of a bracket, the convexity of which is oriented forwards, so that, when the structure is deformed, the rear foot undergoes a forward bending deformation, the theoretical or prescribed bending axis of rotation of which is remote from the rear anchorage and substantially vertically in line with the normal initial position of the axis of articulation of the rear foot on the framework of the seat.

20. The structure as claimed in claim 19, wherein the rear foot is formed in such a way that the theoretical or prescribed bending axis of rotation is shifted towards the top of the fixed structure of the craft.

21. The structure as claimed in claim 19, wherein the energy-absorbing device is connected to the upper part of the rear foot above a zone of maximum curvature of the rear foot.

22. The structure as claimed in claim 17, wherein the front anchorage comprises an articulation allowing the front foot to pivot forwards from its normal position about a transverse horizontal pivot axis of this front anchorage.

23. The structure as claimed in claim 17, wherein the energy-absorbing device is connected in an articulated manner with the rear foot, so as to be capable of pivoting about a transverse horizontal pivot axis.

24. The structure as claimed in claim 17, wherein the energy-absorbing device is connected rigidly with the front anchorage in its vicinity or thereat, without the possibility of pivoting about a transverse horizontal axis.

25. The structure as claimed in claim 17, wherein the two ends associating the energy-absorbing device with the structure define a direction oriented in such a way that the forces projected in this direction and occurring as a result of a longitudinal deceleration of 16 g, with the seat horizontal, and of a vertical deceleration of 14 g, with the seat inclined downwards and forwards at 30°

, are substantially the same, especially a direction forming an angle with the horizontal of the order of 37°

.

26. The structure as claimed in claim 17, wherein the rear foot is rigid and has such dimensions, especially with regard to thickness, that it remains virtually stationary and non-deformable under normal conditions of use, but experiences plastic deformation, especially bending deformation with the effect of a reduction of its curvature, when the deceleration experienced by the seat and its passenger or passengers exceeds a specific value corresponding to that of an accident situation and subjects the structure to deformation stress, with the result that this deformation of the structure occurs only with a dissipation of elastic and then plastic deformation energy of the rear foot.

27. The structure as claimed in claim 26, wherein the rear foot is dimensioned in such a way that it begins to experience plastic deformation, especially bending deformation with the effect of a reduction of curvature, from a deceleration experienced by the seat and its passenger which brings about a dissipation of energy in the energy-absorbing device, and wherein the front foot and the framework, especially a longitudinal member and/or a transverse girder with which the structure is associated, are dimensioned so as to remain rigid or only elastically deformable within the range of the decelerations which do not bring about a mechanical fracture in the structure.

28. The structure as claimed in claim 27, wherein the rear foot and the energy-absorbing device are dimensioned so as to be deformed from a deceleration corresponding to a longitudinal deceleration of the order of 14 g to 16 g.

29. The structure as claimed in claim 17, wherein the energy-absorbing device is oriented with a downwards and rearwards convexity.

30. An aircraft seat which comprises a mounting formed from a structure, the structure associated in an anchored manner with the fixed structure of the craft by means of at least one front anchorage of a front foot and by means of at least one rear anchorage of a rear foot, the front and rear feet being associated with a framework of the seat, in a normal position the front foot extending at least substantially vertically from the lower front anchorage thereof, especially perpendicularly to the floor of the craft, the front and rear feet being articulated at the respective upper ends thereof on the framework of the seat, so as to be capable of pivoting about horizontal and transverse pivot axes, the structure comprising an energy-absorbing device connected to an upper part of the rear foot, but at a distance from an upper rear articulation, and connected to the lower front anchorage in the vicinity or at the lower front anchorage, wherein the energy-absorbing device undergoes at least one longitudinal compressive force, when the structure is deformed in the event of a shock, wherein the device comprises a substantially elongate one-piece element, in that said element comprises a first portion which shape is predetermined in such a way that this element undergoes a natural general structure plastic deformation according to a mode of deformation prescribed by said predetermined shape of said first portion, and in that said element comprises a second portion arranged so as to oppose the general structural plastic deformation of the element and to undergo a natural plastic bending deformation by buckling from a predetermined value of the longitudinal compressive force applied between said ends of said element.

31. An energy absorbing device for installation between front and rear legs of an aircraft seat, comprising:

an elongate strut having a general curvature between opposite ends forming a concave side and a convex side, and having an aperture formed through a central region thereof.

32. The energy-absorbing device according to claim 31, wherein said rear leg of said aircraft seat is curved, with a convex side directed toward a front of said seat, and said strut is arranged with said concave side toward a front side of said seat, said strut pivotally mounted to said rear leg.

33. The energy-absorbing device according to claim 31, wherein said central region is locally bowed outward convexly on said concave side.

34. The energy-absorbing device according to claim 33, wherein said central region is locally bowed outward convexly on said convex side.

35. The energy-absorbing device according to claim 34, wherein said strut comprises a recess formed along the length of said strut between said opposite ends and formed into a front side of said strut, said front side arranged generally planarly perpendicular to said concave side.

36. The energy-absorbing device according to claim 35, wherein said strut comprises a recessed area arranged along a length of said strut between said opposite ends, said recess formed into a back side of said strut, said back side generally planarly perpendicular to said concave side.