Method of manufacturing a composite leg structure for a lightweight aircraft seat assembly

• US 8,590,126 B2
• Filed: 11/26/2011
• Issued: 11/26/2013
• Est. Priority Date: 12/22/2006
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Kismarton, Max U., Fullerton, James A.
• Primary Examiner(s): Afzali, Sarang
• Application Number:
  US13/304,639
• Publication Number:
  US 20120067513A1
• Time in Patent Office: 731 Days
• Field of Search: 298/97, 298/972, 298/973, 298/973.1, 298/973.12, 298/973.3, 298/973.4, 298/973.5, 294/45, 294/48, 29/911, 244/118.5, 244/118.6, 244/122.B, 244/122.R, 244/141, 297/216.1, 297/216.2, 297/232, 297/445.1, 297/452.18, 297/452.65, 297/451.11, 105/345
• US Class Current: 29/91.1
• CPC Class Codes: A47C 5/00 Chairs of special materials
• CPC Class Codes: B64D 11/06 Arrangements of seats, or adaptations or details specially adapted for aircraft seats crew seat constructions for emergency purposes B64D25/04
• CPC Class Codes: B64D 11/0649 Seats characterised by special features for reducing weight
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y10T 29/481 Method
• CPC Class Codes: Y10T 29/49616 Structural member making
• CPC Class Codes: Y10T 29/49622 Vehicular structural member making

Abstract

An aircraft passenger seat configured in accordance with an embodiment of the invention utilizes composite materials to achieve significant weight savings relative to conventional seat designs. The seat includes one or more lightweight composite support legs, a lightweight composite seat pan, and a lightweight composite seat back structure. The support legs are coupled to the seat pan, which is in turn coupled to the seat back structure. The support legs utilize composite frame elements that are formed as continuous compression molded composite extrusions. The seat pan includes composite fore and aft cross beams that are also formed as continuous compression molded composite extrusions. The aft cross beam includes a rear flange that serves as a flexible “hinge” for the seat back structure. The seat can leverage producible and relatively inexpensive composite manufacturing techniques such that the seat can be economically produced for use as an economy class seat.

Claims

1. A method of manufacturing a composite support leg for a lightweight aircraft passenger seat, the method comprising:

forming a composite extrusion using a continuous compression molding process;

obtaining extruded composite frame elements from the composite extrusion;

coupling the extruded composite frame elements together with a core material;

producing a structural box having a seat end and a foot end opposite the seat end by sandwiching the extruded composite frame elements and the core material between a first skin and a second skin, the first skin corresponding to a first side of the structural box, and the second skin corresponding to a second side of the structural box; and

coupling a first end of a composite brace to a front edge of the structural box, the composite brace having a second end opposite the first end and configured for attachment to an aircraft mounting feature behind the structural box, the second end extending away from the seat end of the structural box and extending away from the foot end of the structural box, and the first end including a first flange coupled to the first side of the structural box and a second flange coupled to the second side of the structural box.

2. The method according to claim 1, wherein:

the forming step forms the composite extrusion from a plurality of plies; and

each of the plies comprises a thermoplastic resin and at least one layer of carbon graphite fiber material.

3. The method according to claim 2, wherein the thermoplastic resin comprises polyetherketoneketone (PEKK).

4. The method according to claim 1, further comprising:

forming the first skin from a thermoplastic resin and at least one layer of carbon graphite fiber material; and

forming the second skin from the thermoplastic resin and at least one layer of carbon graphite fiber material.

5. The method according to claim 1, further comprising forming reinforcing pad-up areas in the first skin and in the second skin, the reinforcing pad-up areas corresponding to mounting locations for components of the composite support leg.

6. The method according to claim 1, further comprising:

forming a second composite extrusion using the continuous compression molding process; and

producing the composite brace from the second composite extrusion.

7. The method according to claim 1, wherein producing the structural box comprises bonding the first skin and the second skin to the extruded composite frame elements and to the core material.

8. The method according to claim 1, further comprising coupling a shock-absorbing fitting to the foot end of the structural box, the fitting being configured for attachment to an aircraft mounting feature and facilitating limited travel of the structural box toward the aircraft mounting feature under high loading conditions.

9. A method of manufacturing a composite support leg for a lightweight aircraft passenger seat, the method comprising:

forming a composite extrusion using a continuous compression molding process;

obtaining extruded composite frame elements from the composite extrusion;

coupling the extruded composite frame elements together with a core material; and

producing a structural box having a seat end and a foot end opposite the seat end by sandwiching the extruded composite frame elements and the core material between a first skin and a second skin, the first skin corresponding to a first side of the structural box, the second skin corresponding to a second side of the structural box, and producing the structural box comprises bonding the first skin and the second skin to the extruded composite frame elements and to the core material; and

coupling a first end of a composite brace to a front edge of the structural box, the composite brace having a second end opposite the first end and configured for attachment to an aircraft mounting feature behind the structural box, the second end extending away from the seat end of the structural box and extending away from the foot end of the structural box, and the first end including a first flange coupled to the first side of the structural box and a second flange coupled to the second side of the structural box.

10. The method according to claim 9, further comprising coupling a shock-absorbing fitting to the foot end of the structural box, the fitting being configured for attachment to an aircraft mounting feature and facilitating limited travel of the structural box toward the aircraft mounting feature under high loading conditions.