WO2009129992A1 - Structure de support pour ensemble siège - Google Patents

Structure de support pour ensemble siège Download PDF

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Publication number
WO2009129992A1
WO2009129992A1 PCT/EP2009/002890 EP2009002890W WO2009129992A1 WO 2009129992 A1 WO2009129992 A1 WO 2009129992A1 EP 2009002890 W EP2009002890 W EP 2009002890W WO 2009129992 A1 WO2009129992 A1 WO 2009129992A1
Authority
WO
WIPO (PCT)
Prior art keywords
seat assembly
support structure
seat
support
fore
Prior art date
Application number
PCT/EP2009/002890
Other languages
English (en)
Inventor
James Thompson
Original Assignee
J Thompson Solutions Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by J Thompson Solutions Ltd filed Critical J Thompson Solutions Ltd
Publication of WO2009129992A1 publication Critical patent/WO2009129992A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D11/00—Passenger or crew accommodation; Flight-deck installations not otherwise provided for
    • B64D11/06—Arrangements of seats, or adaptations or details specially adapted for aircraft seats
    • B64D11/0696—Means for fastening seats to floors, e.g. to floor rails

Definitions

  • the present invention relates to a support structure for supporting a seat assembly on a surface, especially for vehicle seats and most particularly for aircraft seats.
  • each seat unit must withstand predetermined static loading corresponding to forces applied to the seat during normal use and during impacts and must also accommodate deflection of the aircraft floor during impacts.
  • the typical multiple occupant seat unit is supported by four supporting members joined to the seat unit at four separate points, roughly corresponding to the four corners of the seat unit.
  • the load distribution between the four supporting members can vary depending upon the load applied to the seat unit, for example depending upon the number and position of passengers on the seat unit. Such variation in loading can result in one or more of the supporting members bearing a greater load than the others, possibly resulting in an excessive load being borne by said one or more of the supporting members leading to failure of the connection between such supporting member or members and the floor, particularly in relation to the rearmost supporting members which must bear a substantial upward force tending to tear the supporting member from the floor in a forward impact.
  • FIG. 1 depicts the pitch and roll tested in industry practice, typically 10° pitch of one airframe mounting track and 10° roll of the other track. This test requires simulating airplane floor deformation by deforming the test fixture, as respectively prescribed in Figures 1 and 2 for single occupant and multiple occupant seats, prior to applying forces corresponding to those experienced during dynamic impact conditions.
  • the purpose of providing floor deformation for the test is to demonstrate that the seat/restraint system will remain attached to the airframe and perform properly, even though the airplane and/or seat are deformed by the forces associated with a crash.
  • "A" shows the original position of the airframe mounting tracks and seat/seat frame prior art deformation of the floor while B shows the position of the airframe mounting tracks and seat/seat frame after deformation of the floor.
  • a support structure for supporting a seat assembly or other structure upon a surface, said support structure comprising first and second laterally spaced support members extending between the seat assembly and the surface from first and second laterally spaced locations on the seat assembly and a third support member extending between the seat assembly and the surface from the seat assembly at a third location on the seat assembly between and in front of or behind said first and second laterally spaced locations whereby the seat assembly is supported by the support structure at three locations.
  • the third support member engages said surface at two laterally spaced locations thereon.
  • the third support member may comprise a substantially inverted V or Y shaped structure extending between the seat assembly and the surface. Said third location at which the third support member is connected to the seat assembly may be selected to substantially equalise a load distribution between the first and second support members.
  • said third support member includes a flexible or hinged portion, substantially vertically aligned with said third location at which said third support member is connected to said seat assembly, said flexible or hinged portion permitting flexure or pivotal movement of the third member about a substantially horizontal axis extending in a fore-and-aft direction with respect to the seat assembly to allow the third support member to absorb deflections of surface upon which the support structure is mounted.
  • said flexible portion may comprise one or more substantially vertical blade members arranged in a fore- and-aft direction.
  • said hinged portion may comprise a hinge member pivotal about said substantially horizontal axis arranged to transmit a vertical load from said seat assembly to said surface while permitting pivotal movement of said third support member transverse to said fore-and-aft direction.
  • Said first and second support members may extend between said seat assembly and said surface at an oblique angle.
  • said third support member may comprise a substantially central member, a respective laterally extending bridge member extending the central member in opposing directions downwardly at an oblique angle to engage the surface.
  • Preferably central members comprises a tubular member extending in said fore- and-aft direction connected to the seat assembly via at least one longitudinally extending substantially vertical member extending in said fore-and-aft directions, said vertical member providing predetermined flexibility in the third support member about a horizontal axis extending in the fore-and-aft direction parallel to the axis of the tubular member.
  • the bridge members may extend from respective ends of said tubular member in offset relationship in the fore-and-aft direction.
  • Said first and second support members may also be offset from one another in a fore-and-aft direction.
  • a seat assembly including a support structure in accordance with the first aspect of the invention.
  • the seat assembly comprises a multiple occupancy seat assembly comprising a plurality of seats arranged in a row.
  • the seats may be displaced, or staggered, with respect to one another in the longitudinal direction, preferably to form a row that is obliquely disposed with respect to the longitudinal axis of the aircraft.
  • the seats may be offset in a fore-and-aft direction and are arranged in partially overlapping relationship.
  • the seat assembly is preferably a multiple occupant aircraft seat.
  • a seat base support structure comprising a plurality of linkage members defining a first substantially rigid connection between the seat base and the surface upon which the seat base is mounted and a second relatively flexible connection between the seat base and said surface, said second connection being laterally spaced from said first connection, whereby said relatively flexible second connection enables pivotal movement of said seat base structure relative to said first connection to readily absorb deflections of said surface.
  • said second connection comprises a linkage member extending from said seat base to said surface at an oblique angle.
  • said linkage members define a substantially central first connection and two second connections respectively provided at or adjacent the lateral sides of the seat base on either side of the first connection.
  • the invention incorporates a plurality of linked members which together act as the seat support structure.
  • the rigid connections of seat support structure to airframe track experience reactionary forces which are significantly converged, with the difference between said loads substantially balanced by the plurality of links.
  • the system of linked members is arranged such that the support structure will readily accept torsional deflections applied along the width of the seat.
  • the links may be arranged such that, around the third support member between seat structure and mounting tracks, the support structure is flexible, pivoting about a defined point. This pivoting functionality may allow the load experienced by the mounting frame connections to converge towards similar or indeed same values.
  • the inherent flexibility within the design readily absorbs airframe deflections, eliminating the pre-stresses in furniture directly connected to the seat base structure, and reduces the possibility of associated assemblies becoming inoperable. Description of the drawings
  • Figure 2 and 2a are front views depicting pitch and roll on a support structure for a seat assembly incorporating the invention.
  • Figure 3 is an isometric view of a seat support structure of Figure 2;
  • Figure 4 is a side view of the seat support structure of Figure 2.
  • Figure 5 is a front view of the seat support structure of Figure 2.
  • a seat support structure for supporting a multiple occupancy aircraft seat assembly embodying the invention is shown in the drawings.
  • the support structure is intended for supporting a multiple occupancy seat assembly of the type disclosed in EP 1461224 wherein adjacent seats in a row are offset in a fore-and-aft direction and overlap such that at least one of the left or right armrests of a first seat overlaps with the other of the left or right armrests of an adjacent seat, the extent of the overlap being such that each overlapping armrest extends beyond the armrest with which it overlaps.
  • the seat assembly comprises a row of seats wherein, within each row, adjacent seats are displaced, or staggered, with respect to one another in the longitudinal direction to form a row which is obliquely disposed with respect to the longitudinal axis of the aircraft.
  • the support structure is also suitable for supporting other types of seat assembly or other structures intended to be supported on a surface, such as vehicle seats, tables or other structures.
  • the support structure includes a mounting structure forming the base of a seat assembly, the mounting structure comprising three laterally spaced substantially horizontally extending members 2,3,4 extending in the fore- and-aft direction, the members 2,3,4 being interconnected by substantially horizontally extending traverse linking members 5,6, 17, 18.
  • the mounting structure is supported on a support structure comprising first and second laterally spaced rear support members 7,8 and a single front support member 9 such that the mounting structure is supported on the support structure at three spaced locations in the manner of a tripod.
  • Each of the first and second rear support members 7,8 extend rearwardly from the mounting structure at an oblique angle to terminate in a respective rear mounting 13,14 for connected to a respective airframe track.
  • the front support member 9 comprises a central tube 21 extending in said fore-and-aft direction connected to the mounting structure via two longitudinally aligned elongate vertical blade members 19,20 extending in said fore-and-aft directions to provide predetermined flexibility in the front support member about a horizontal axis extending in the fore-and-aft direction parallel to the axis of the central tube 21.
  • a respective laterally extending bridge member 22,23 extends from each end of the tube 21 in opposing directions downwardly at an oblique angle to terminate in a respective front mounting 11 , 12 for connection to the respective airframe track.
  • Respective front mountings 11,12 are linked to respective rear mountings 13,14 by bars to link the front and rear support members.
  • the mounts 13,14 at the rear of the seat structure may be pivotal in nature.
  • the transverse linking members 17, 18 of the mounting structure add torsional rigidity above the connections of blade members 19, 20.
  • the blade members 19, 20 could similarly be replaced with a single member or mechanical pivot dependent upon design requirements to provide the required degree of flexibility in the front support members 9.
  • Rigidity in this area is necessary in order to support passengers' weight and in order to provide suitable strength during the various in use and test demands. Flexibility to 'accept' pitch and roll is achieved through the joining of the blade members to the central torsion tube 21 to the seat structure and may also be enhanced by the connection of the central tube 21 to the bridge members 22, 23.
  • balancing of the reactant loads or, at a minimum, the convergence of said loads between left 11, 13 and right hand 12, 14 mounts can be achieved by offsetting the tube 21 pivot point from the centre of the seat assembly.
  • the position of the central tube 21 and the connection of the blades 19,20 to the seat structure can be selected to optimise the load distribution between the left and right hand side mounts for all expected loading conditions.
  • Figure 4 shows a side view of the seat support structure.
  • the relationship between the seat support structure to airframe mounts 11, 12, 13, 14 changes.
  • mounting point 12 may now be sited at a lower point.
  • the resulting torsion within the frame is evenly distributed through the blade members 19, 20, central torsion tube 21 and bridge members 22, 23 due to the flexibility of third support member 9, preferably provided by the blade members 19,20, with minimal distortion of attached seat furniture.
  • the bridge members 22, 23 of the front support member 9 form a balanced beam system, flexing around the central torsion tube 21 via the blade members 19,20.
  • Reactant side loads experienced at seat structure to airframe connection 11, 12 can be reduced by incorporating a slot in each of the bridge members 22, 23 at the point where connection is formed to mountings 11, 12. During loading, this allows the downwardly deflection of the bridge members 22,23 to be absorbed via the mountings 1 1, 12 without transferring side loads.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Seats For Vehicles (AREA)

Abstract

Structure de support conçue pour porter un ensemble siège ou une autre structure sur une surface. Ladite structure de support comprend un premier et un deuxième élément de support espacés (7, 8) latéralement qui s’étendent entre l’ensemble siège et la surface d’un premier et d’un deuxième emplacement latéralement espacés sur l’ensemble siège. Ladite structure comprend en outre un troisième élément de support (9) s’étendant entre l’ensemble siège et la surface de l’ensemble siège, en un troisième emplacement sur l’ensemble siège, entre et devant ou derrière lesdits premier et deuxième emplacements latéralement espacés. Ainsi, l’ensemble siège est porté en trois emplacements par la structure de support.
PCT/EP2009/002890 2008-04-21 2009-04-21 Structure de support pour ensemble siège WO2009129992A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US0807141.7 2008-04-21
GB0807141A GB0807141D0 (en) 2008-04-21 2008-04-21 Seat frame

Publications (1)

Publication Number Publication Date
WO2009129992A1 true WO2009129992A1 (fr) 2009-10-29

Family

ID=39472378

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/EP2009/002890 WO2009129992A1 (fr) 2008-04-21 2009-04-21 Structure de support pour ensemble siège

Country Status (2)

Country Link
GB (1) GB0807141D0 (fr)
WO (1) WO2009129992A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20220396359A1 (en) * 2019-10-31 2022-12-15 Safran Seats Support pallet for an airplane seat unit

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1228657A (fr) * 1967-07-31 1971-04-15
US3653713A (en) * 1970-07-23 1972-04-04 Hunting Eng Ltd Seating structure
FR2495101A1 (fr) * 1980-12-01 1982-06-04 Socea Siege de securite anticrash notamment pour aeronef
WO2003053735A1 (fr) * 2001-12-20 2003-07-03 James Thompson Places assise pour vehicule

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1228657A (fr) * 1967-07-31 1971-04-15
US3653713A (en) * 1970-07-23 1972-04-04 Hunting Eng Ltd Seating structure
FR2495101A1 (fr) * 1980-12-01 1982-06-04 Socea Siege de securite anticrash notamment pour aeronef
WO2003053735A1 (fr) * 2001-12-20 2003-07-03 James Thompson Places assise pour vehicule

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20220396359A1 (en) * 2019-10-31 2022-12-15 Safran Seats Support pallet for an airplane seat unit

Also Published As

Publication number Publication date
GB0807141D0 (en) 2008-05-21

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