WO1994023996A1

WO1994023996A1 - Convertible aircraft passenger seating

Info

Publication number: WO1994023996A1
Application number: PCT/GB1994/000817
Authority: WO
Inventors: Anthony Thomas Jackson-Wynch; John Frederick Branham
Original assignee: Flight Equipment & Engineering Limited
Priority date: 1993-04-21
Filing date: 1994-04-18
Publication date: 1994-10-27
Also published as: AU6510794A; GB2277438A; GB9308227D0

Abstract

An aircraft passenger seating unit which is convertible to provide different numbers and/or widths of seats comprises a support frame (1) and at least one web (6) for supporting a seat, slidable on said support frame. The frame includes two transverse beams (9) mounted on a leg structure. A beam has first and second locating portions (8, 9) extending lengthwise of the beam. A part of the leg structure is secured to the first locating portion and the slidable web has a locating part slidably engaging the second locating portion, so shaped that the web, when slid along the beams, can pass the said part of the leg structure. The locating portions may be projections such as flanges or grooves or channels. The flanges are preferably of dovetail cross section widening from their roots towards their tips so as to retain the parts engaging them. Preferably both beams have such locating portions.

Description

CONVERTIBLE AIRCRAFT PASSENGER SEATING

TECHNICAL FIELD

Aircraft passenger sealing is commonly constructed in units each comprising seats for two or more passengers mounted on a support frame having leg structures terminated by feet designed to engage releasably with a pair of parallel tracks secured in the aircraft cabin floor and extending longitudinally thereof. Seating units have been known for some time which are constructed so as to be convertible to provide different numbers and/or widths of seats, for example to accommodate passengers travelling on different categories of fare.

BACKGROUND ART

For many years most seating units have been constructed on support frames comprising two transverse beams mourned on the leg structures and spaced by longitudinally disposed support members, sometimes called "webs", which carry the seats. Examples of such frames are described and illustrated in U.S. Patent Specifications Nos. 4,099,780, 4,229,040 and 4,489,978. The beams are usually of hollow circular cross section and pass through circular bores in the support members. In some cases they also pass through circular bores in the leg structures. In other cases the leg structures have part-cylindrical recesses to receive the beams. The leg structures may include webs. Generally the beams are secured to the leg structures, for example by bolts passing through walls of the bores or recesses to enter holes in the beams.

Examples of seating units which are convertible to vary the numbers and/or widths of seats are described in U.S. Patent Specifications Nos. 4,881,702, 5,104,065, 5,131,607 and 5,178,345 and corresponding European Patent Specifications Nos. 0 322 930 A2, 0530 923 A1 and 0530 920 A1. These Specifications disclose seating units in which a laterally outer seat comprises an outer web mounted on a pair of tubes which are slidably received in the transverse beams and an inner web which is slidable on the beams. Thus the outer seat may be moved laterally with respect to the leg structures to which the beams are secured. In a unit comprising three or more seats an inner seat comprises two webs which are laterally slidable on the beams. In order to provide the necessary rigidity and strength the slidable webs have bores which are a close sliding fit on the beams.

Terms such as lateral", "longitudinal", "transverse" and the like are used herein and in the claims which follow in relation to an aircraft in which a seating unit is fitted or intended to be fined. Thus in relation to a passenger properly seated in a sealing unit the term "lateral" and "transverse" indicate the side-to-side direction and "longitudinal" indicates the fore-and-aft direction.

The lateral spacing of the feet of the leg structures is determined by the spacing between the tracks in the aircraft. In order to provide the desired degree of adjustment in the spacing between the seats and/or in their widths it is sometimes necessary for a laterally slidable web to pass through the vertical longitudinal plane containing the feet. Clearly that would not be possible if the leg structure lay in that plane, since the top part of the leg structure, to which the beams are secured, would obstruct the passage of the slidable web. To overcome this difficulty the leg structures shown in U.S. Specification No. 4,881,702 are inclined to the vertical longitudinal planes through the respective feet. In an arrangement illustrated in U.S. Specification No. 5,131,607 the leg structures are cranked so that their top pans, to which the beams are secured, are laterally spaced from me vertical longitudinal planes through their feet. These inclined and cranked structures obviously complicate the manufacture of the units and may affect their strength.

DISCLOSURE OF THE INVENTION

According to this invention an aircraft passenger seating unit which is convertible to provide different numbers and/or widths of seats comprising a support frame and at least one web for supporting a seat, laterally slidable on the support frame, the support frame including two parallel transverse beams mounted on a leg structure is characterized in that at least one beam has first and second locating portions extending lengthwise of the beam; a part of the leg structure is secured to the first locating portion; the laterally slidable web has a locating part slidably engaging the second locating portion and the web and the leg structure are so shaped that the web, when sliding along the beams, can pass the said part of the leg structure. With this arrangement, the part of the leg structure secured to the first locating portion does not need to be inclined, cranked or otherwise shaped in order to avoid the necessity for a web to pass through a vertical longitudinal plane containing a foot attached to that leg part. Thus a constraint on the design of the leg structure which might affect its strength or manufacturing cost is removed.

The locating portions may simply be parallel parts of a beam of rectangular or other simple cross section, which are suitable for locating pans of the leg structures and webs, or they may be projections such as flanges or grooves or channels. They are preferably undercut or tapered so that the respective parts engaging them can be self-retaining once properly engaged. Preferably each beam of the seating unit has two locating portions as described, the leg structures are secured to a first locating portion of each beam and the or each laterally slidable web has complementary locating pans to engage slidably the second locating portion of each beam. Each transverse beam may comprise a major part of hollow circular cross section with one or more flanges extending lengthwise of the beam and outwardly with respect to the circular section. The major part of hollow circular cross section may form one locating portion, for example to be received in part-cylindrical recesses in the leg structures and be secured thereto in the usual manner as previously described. A lengthwise flange may be received slidably in a complementary locating groove in a slidable web. The slidable web may then slide along the flange when required and if desired it may pass a leg structure engaging and supporting the major part. The flange is preferably of undercut cross section and the complementary locating groove is of a similar cross section so that the slidable web is self-retaining on the flange other shapes of beam could be used, for example of dumbell or figure-of-eight or I cross section. BEST MODE OF CARRYING OUT THE INVENTION

In a preferred embodiment, illustrated by way of example by Figures 1 to 3 of the accompanying drawings, a beam has a major part of hollow circular cross section with two oppositely-directed outward locating flanges extending lengthwise of the beam. The flanges are of dovetail cross section - widening from their roots towards their tips. A leg structure has a groove of corresponding cross section defined between the body of the leg structure and a clamping member adjustably secured to the body by clamping screws. The lower flange of a beam is received in the groove and clamped by the clamping member and screws to secure the beam to the leg structure. The upper flange is engaged by a corresponding groove in a slidable web, defined between the body of the web and a jaw part secured to the body by screws or other fastening means to retain the groove on the flange but permit the slidable web to be moved along the beam. Figure 4 shows some other possible shapes of beam.

BRIEF DESCRIPTION OF THE DRAWINGS

In the drawings :

Figure 1 is a diagrammatic sectional view of a seating unit, sectioned on a plane perpendicular to a surface supporting the unit, such as an aircraft cabin floor and parallel to the longitudinal supporting members or webs,

Figure 2 is a diagrammatic scrap elevation on arrow A of Figure 1, with part removed,

Figure 3 is a diagrammatic side elevation of the seating unit fitted in an aircraft and

Figure 4 shows four other cross sections of beam which could be used in sealing units embodying the invention.

The seating unit comprises a leg structure 1 comprising a front leg 2 and rear leg 3 which are joined together and support two parallel transverse beams 4, 5 on which is carried a slidable support member or web 6 for a seat. Each beam 4, 5 comprises a major part / of hollow circular cross section with two oppositely-directed outward flanges 8, 9 of dovetail section extending lengthwise of the beam. The lower flanges 8 of the two beams are received in front and rear grooves 10, 11 in the leg structure. Each of the grooves 10, 11 is formed partly in the body of the leg structure and partly by a separate clamping jaw 12 which is secured to the body by clamping screws (not shown) which pass on the chain-dotted lines 13, 14 through bores (not shown) in the jaws, notches 15 in the flanges and 16 in the body of the leg structure and are screwed into bores 17 in the body to urge the clamping jaws against the flanges. This gives very secure fastening of the beams to the leg structures, providing a rigid supporting structure. The clamping jaw 12 has been removed in Figure 2 to show details of the notches 15 and 16.

The upper flanges 9 of the two beams are received in complementary grooves 18 in the slidable web 6, each defined between the body of the web and a jaw part 19 secured to the body by setscrews 20. The jaw parts 19 can be adjusted by means of the setscrews 20 so that the slidable web 6 can slide freely along the beams 4, 5 as indicated by the arrows B, but the web is securely retained on the beams by the dovetail section of the flanges 8, 9 and the corresponding shape of parts of the grooves 17. In sliding along the beams 4, 5, the web 6 can pass the leg structure 1 freely without obstruction. This is illustrated in Figure 2 in which the web 6 is shown to be lying in the central vertical plane C of the leg structure 1. It is not necessary to crank or incline the legs in order to achieve this.

As shown in Figure 3, the seating unit is fitted in an aircraft 21 in the usual manner by means of feet 22 at the ends of the legs 2 and 3 which engage and are secured in longitudinal tracks 23 in the floor of the aircraft The construction and operation of such feet and tracks are well-known and need not be described further.

Figure 4 shows four cross sections of beams which could be used instead of the beams 4 and 5. (a) is a rectangular section, opposite sides or ends of which could provide the locating portions, though the respective para engaging them would not be self-retaining. That property is provided by the other examples, (b) is a rectangular section with grooves to receive complementary projections on the respective pans; (c) is a beam of dumbell-shaped cross section and (d) is a beam of I section. Other alternative shapes could be used.

INDUSTRIAL APPLICATION

Sealing units embodying the invention are useful in any passenger-carrying aircraft which is designed to carry more than a small number, say five or six, of passengers. The invention provides seating units which are of stronger and simpler construction than known units without the impediment of significantly increased weight.

Claims

1. An aircraft passenger seating unit which is convertible to provide different numbers and/or widths of seats comprising a support frame and at least one web for supporting a seat, laterally slidable on the support frame, the support name including two parallel transverse beams mounted on a leg structure, characterized in that at least one beam has first and second locating portions extending lengthwise of the beam; a pan of the leg structure u secured to the first locating portion; the laterally slidable web has a locating pan slidably engaging the second locating portion and the web and the leg structure are so shaped that the web, when sliding along the beams, can pass the said pan of the leg structure.

2. An aircraft passenger sealing unit as claimed in Claim 1 characterized in that each beam has first and second locating portions extending lengthwise of the beam; pans of the leg structure are secured respectively to the first locating portions of the beams; the laterally slidable web has locating parts slidably engaging respectively the second locating portions of the beams and web and the leg structure are so shaped that the web, when sliding along the beams, can pass the said pan of the leg structure.

3. An aircraft passenger seating unit as claimed in Claim 1 or Claim 2 characterized in that a locating portion is a projection.

4. An aircraft passenger seating unit as claimed in Claim 1 or Claim 2 characterized in that a locating portion is a groove or channel in a beam.

5. An aircraft passenger seating unit as claimed in Claim 1 or Claim 2 characterized in that a beam comprises a major pan of hollow circular cross section with one or more flanges extending lengthwise of the beam and outwardly with respect to the circular section.

6. An aircraft passenger seating unit as claimed in Claim 5 characterized in that the major part of hollow circular cross section is one of the said first and second locating portions.

7. An aircraft passenger seating unit as claimed in Claim 6 characterized in that the other of said first and second locating portions is a lengthwise flange on the said major part.

8. An aircraft passenger seating unit as claimed in Claim 5 characterized in that the or each flange is of undercut cross section and the pan engaging it has a complementary shape so as to be self-retaining on the flange.

9. An aircraft passenger searing unit as claimed in Claim 1 or Claim 2 characterized in that a beam has a major pan of hollow cross section with two oppositely-directed outward flanges extending lengthwise of the beam, the flanges forming the first and second locating portions.

10. An aircraft passenger seating unit as claimed in Claim 9 characterized in that the major part is of hollow circular cross section.

11. An aircraft passenger setting unit as claimed in Claim 9 characterized in that the flanges are of dovetail cross section widening from their roots towards their tips.

12. An aircraft passenger seating unit as claimed in Claim 9 characterized in that the major pan is of hollow circular cross section and the flanges are of dovetail cross section widening from their roots towards their tips.

13. An aircraft passenger seating unit which is convertible to provide different numbers and widths of seats and in which the support frame comprises two transverse beams mounted on the leg structures and spaced by longitudinally disposed support members, wherein each beam has two locating portions extending lengthwise of the beam, the leg structures are secured to one of said locating portions and at least one slidable web for supporting a seat has complementary locating pans to engage slidably the other of said locating portions and the pans are so shaped that the pan of the slidable web engaging the said other locating portion can pass the pan of the leg structure engaging the said one locating portion as it slides along the beams.

14. The fitting in an aircraft of an aircraft passenger seating unit as claimed in any preceding Claim.