Chairs and seats – Plural related seats
Patent
1985-07-02
1986-12-23
Dorner, Kenneth J.
Chairs and seats
Plural related seats
297445, 297452, A47C 300, B64D 1106
Patent
active
046308644
DESCRIPTION:
BRIEF SUMMARY
FIELD OF THE INVENTION
The present invention relates to an improved aircraft seat.
BACKGROUND TO THE INVENTION
A single spar aircraft seat frame is described in specification No. GB-A 2022403 and employs a single laterally extending spar secured to the apex of leg subframes and in turn carrying arm-rest frames. Seat pad supports of webbing are resiliently suspended between the arm-rest frames by coil springs and wire hangers. But insofar as the lateral spar is positioned below the arm-rest frames it obstructs the free space of the passenger immediately to the rear. And in the event of a heavy down load, the occupant's legs may come into contact with and be fractured by the laterally extending spar. Moreoever the seat frame is made from metal and is inherently heavier than when carbon fibre reinforced plastics materials and aramid materials are used, e.g. as described in our Patent Specification No. WO-82/03366.
SUMMARY OF THE INVENTION
It is an object of the invention to provide a lightweight aircraft seat frame construction using carbon fibre and aramid materials that is inherently safe in heavy down load situations, is free from risk of passenger forward load shin impact and can be used for high density (26-27 inch or 66-69 cms pitch) seat accommodation.
The invention comprises a combined seat frame and cushion support for an aircraft seat comprising a single laterally extending spar of non-circular cross-section presenting a bluff upper surface and formed from a core of expanded material and a skin of carbon fibre reinforced plastics, a plurality of seat supports of fibre reinforced plastics material secured to the spar at laterally spaced locations, a seat cushion support diaphragm on and spanning between the seat supports and the spar and of profile defined by the seat supports, and one or more legs of inverted U-shaped side profile each leg being formed at its apex with a recess in which the spar is located and rigidly secured.
The invention also provides a combined seat frame and cushion support for an aircraft seat comprising an integrally moulded structure in carbon fibre including a spar presenting a flat upper surface, rearwardly facing J-shaped seat supports secured to the spar at laterally spaced locations, a diaphragm spanning between the seat supports to define an uninterrupted top surface with the spar and cantilevered from the spar to deform elastically in response to the normal weight of an occupant and to undergo progressive inelastic deformation with energy absorption in response to a heavy down load, and a front portion of curvilinear profile cantilevered forwardly and upwardly from the spar with which it also defines an uninterrupted top surface and terminated in a downwardly curved nose. Said front portion also undergoing progressive inelastic deformation with energy absorption in response to a heavy down load.
The term "carbon fibre reinforced plastics" includes plastics materials reinforced additionally with glass or Kevlar (polyimide) fibres, the carbon fibres predominating.
BRIEF DESCRIPTION OF DRAWINGS
An embodiment of the invention will now be described, by way of example only, with reference to the accompanying drawings, in which:
FIG. 1 is a perspective view of a two place seat for an aircraft;
FIG. 2 is a view of the seat with the front portion and diaphragm removed to show the main load-bearing structure;
FIG. 3 is a side view of an assembled seat according to the invention; and
FIG. 4 is a section through the seat showing the diaphragm and nose portion .
DETAILED DESCRIPTION OF PREFERRED EMBODIMENT
As illustrated in FIGS. 1 and 2 the seat frame comprises a laterally extending spar 20 in the form of a generally rectangular member presenting a flat upper surface and having a core of acrylic or polyimide structural foam (or aluminium or Nomex honeycomb) filling a hollow skin of carbon fibre reinforced plastics. The spar 20 is of constant section throughout its length and is supported by a leg assembly 22 which is adapted to be secured to an aircraft floor which i
REFERENCES:
patent: 3091497 (1963-05-01), Houser
patent: 3111344 (1963-11-01), Hoven et al.
patent: 3468582 (1969-09-01), Judd
patent: 4296967 (1981-10-01), Vogel
patent: 4375300 (1983-03-01), Long et al.
patent: 4526421 (1985-07-01), Brennan et al.
patent: 4529247 (1985-07-01), Stumpf et al.
Brown Peter R.
Dorner Kenneth J.
Futaire Limited
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