GB1590061A - Aircraft seats - Google Patents
Aircraft seats Download PDFInfo
- Publication number
- GB1590061A GB1590061A GB15764/78A GB1576478A GB1590061A GB 1590061 A GB1590061 A GB 1590061A GB 15764/78 A GB15764/78 A GB 15764/78A GB 1576478 A GB1576478 A GB 1576478A GB 1590061 A GB1590061 A GB 1590061A
- Authority
- GB
- United Kingdom
- Prior art keywords
- support member
- seat
- aircraft
- support
- beams
- Prior art date
- Legal status (The legal status 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 status listed.)
- Expired
Links
- XEEYBQQBJWHFJM-UHFFFAOYSA-N Iron Chemical compound [Fe] XEEYBQQBJWHFJM-UHFFFAOYSA-N 0.000 claims description 7
- 239000004411 aluminium Substances 0.000 claims description 7
- 229910052782 aluminium Inorganic materials 0.000 claims description 7
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 7
- 229910045601 alloy Inorganic materials 0.000 claims description 6
- 239000000956 alloy Substances 0.000 claims description 6
- 229910052804 chromium Inorganic materials 0.000 claims description 4
- 239000011651 chromium Substances 0.000 claims description 4
- 229910052802 copper Inorganic materials 0.000 claims description 4
- 239000010949 copper Substances 0.000 claims description 4
- 230000005484 gravity Effects 0.000 claims description 4
- 229910052742 iron Inorganic materials 0.000 claims description 4
- 229910052749 magnesium Inorganic materials 0.000 claims description 4
- 239000011777 magnesium Substances 0.000 claims description 4
- 229910052710 silicon Inorganic materials 0.000 claims description 4
- 239000010936 titanium Substances 0.000 claims description 4
- 229910052719 titanium Inorganic materials 0.000 claims description 4
- 239000011701 zinc Substances 0.000 claims description 4
- 229910052725 zinc Inorganic materials 0.000 claims description 4
- VYZAMTAEIAYCRO-UHFFFAOYSA-N Chromium Chemical compound [Cr] VYZAMTAEIAYCRO-UHFFFAOYSA-N 0.000 claims description 3
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 3
- 229910000881 Cu alloy Inorganic materials 0.000 claims description 3
- FYYHWMGAXLPEAU-UHFFFAOYSA-N Magnesium Chemical compound [Mg] FYYHWMGAXLPEAU-UHFFFAOYSA-N 0.000 claims description 3
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 3
- HCHKCACWOHOZIP-UHFFFAOYSA-N Zinc Chemical compound [Zn] HCHKCACWOHOZIP-UHFFFAOYSA-N 0.000 claims description 3
- JRBRVDCKNXZZGH-UHFFFAOYSA-N alumane;copper Chemical compound [AlH3].[Cu] JRBRVDCKNXZZGH-UHFFFAOYSA-N 0.000 claims description 3
- WPBNNNQJVZRUHP-UHFFFAOYSA-L manganese(2+);methyl n-[[2-(methoxycarbonylcarbamothioylamino)phenyl]carbamothioyl]carbamate;n-[2-(sulfidocarbothioylamino)ethyl]carbamodithioate Chemical compound [Mn+2].[S-]C(=S)NCCNC([S-])=S.COC(=O)NC(=S)NC1=CC=CC=C1NC(=S)NC(=O)OC WPBNNNQJVZRUHP-UHFFFAOYSA-L 0.000 claims description 3
- 239000010703 silicon Substances 0.000 claims description 3
- 230000002093 peripheral effect Effects 0.000 description 4
- 229910052751 metal Inorganic materials 0.000 description 3
- 239000002184 metal Substances 0.000 description 3
- 238000005728 strengthening Methods 0.000 description 3
- 229910000838 Al alloy Inorganic materials 0.000 description 2
- 229910000831 Steel Inorganic materials 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000004744 fabric Substances 0.000 description 1
- 235000013305 food Nutrition 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 229910001234 light alloy Inorganic materials 0.000 description 1
- 229910052748 manganese Inorganic materials 0.000 description 1
- 239000011572 manganese Substances 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 235000012054 meals Nutrition 0.000 description 1
- 238000000034 method Methods 0.000 description 1
Classifications
-
- A—HUMAN NECESSITIES
- A47—FURNITURE; DOMESTIC ARTICLES OR APPLIANCES; COFFEE MILLS; SPICE MILLS; SUCTION CLEANERS IN GENERAL
- A47C—CHAIRS; SOFAS; BEDS
- A47C5/00—Chairs of special materials
- A47C5/04—Metal chairs, e.g. tubular
-
- 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
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Seats For Vehicles (AREA)
Description
(54) AIRCRAFT SEATS
(71) We, FLIGHT EQUIPMENT & BR<
ENGINEERING LIMITED, a British Company, of Asheridge Road, Chesham, Buckinghamshire, do hereby declare the invention, for which we pray that a patent may be granted to us, and the method by which it is to be performed, to be particularly described in and by the following statement: - This invention relates to aircraft seats and more particularly to the support structure which forms part of the seat.
Aircraft seats must be able to withstand an acceleration of at least 9g without being damaged. This condition can fairly readily be met by constructing the seat support structure from rigid heavy materials. However, it is undesirable from an airline's point of view to use heavy materials in the construction of the seats since this tends to increase an aircraft's payload and thus limit its range or increase its fuel consumption.
It is also desirable that aircraft seats should take up the minimum amount of space consistent with providing adequate comfort for the passenger. The space occupied by an aircraft seat can be reduced if it is possible for a passenger to utilise some space beneath the seat in front in order to give him adequate leg room. To achieve this result, it is desirable for the support beams which hold the seat structure to be positioned as far to the front of the seat as possible. This requirement tends to conflict with the strength requirements of the seat structure, since it increases the stress concentration in the rear part of the seat support structure when the structure is subjected to load.
Hitherto, it has been general to employ tubular steel elements welded together to
constitute a seat support, which support is carried on two generally horizontal
beams. Such a seat support is heavy, and takes a relatively long time to manufacture.
We have now found that, contrary to
current belief, it is possible to produce a
seat support structure of adequate strength
from a forged aluminium alloy part. More particularly, according to one aspect of the present invention there is provided a support member for an aircraft seat which is adapted to be held by two beams locatable within apertures formed in the support member, wherein (1) both of the apertures are positioned on the forward side (with reference to the aircraft seat, in use) of the centre of gravity of the support member, and (2) the support member is forged from aluminium or an aluminium-containing alloy. The support member is preferably constructed to have a peripheral frame with webs extending inwardly therefrom and preferably filling the space between the frame portions at least in the rearmost section of the support member.Conveniently, the support member can consist of a forward portion which contains the two apertures for the seat beams; a rear portion in which the web extends between the peripheral frame portions and which includes strengthening ribs; and a central portion linking the forward and rear portions. At least two strengthening ribs which converge towards the upper surface of the member are preferably provided in the rear portion of the member.
The peripheral outline of the seat support member advantageously consists predominantly of linear sections. It is however convenient for the lower surface of the rear portion of the member to be curved generally upwardly.
Preferably, substantially the whole of the body of the member lies in a single plane.
A number of functional apertures and connections may be provided on the support member as forged. Thus it will be convenient to provide anchorages for seat belt(s), an aperture to receive part of the mechanism which allows the seat back to recline, and an aperture to received a supporting arm for a meal tray. The upper edge of the forward and central sections of the member is preferably linear and/or is adapted to receive a bar to which there can be attached a support for a seat cushion. Such a cushion support will extend between two of the support members of this invention. The bar can be formed so as to take either a hard seat cushion support (for example a metal sheet), or a soft seat cushion support (for example a fabric diaphragm and wire frame which are attached to the support members of the invention by springs and clips).
The support member of this invention is forged from a light alloy such as a high-strength aluminium-copper alloy. The preferred alloy is one consisting of from 3.9 to 5.0% copper, from 0.2 to 0.8% manganese, 0.5 to 1.0% silicon, 0.6 to 0.8% iron, 0.4 to 1.2% magnesium, 0.2% zinc, 0.2% titanium, 0.1% chromium and the balance aluminium (all percentages by weight).
The support member of this invention will be held, in use, on two generally horizontal beams which in turn are held by an underseat assembly which is secured to the aircraft cabin floor.
According to another aspect of the invention, there is provided an aircraft seat structure which comprises two support members according to said one aspect of the invention mounted on two generally horizontal beams; a seat cushion extending between the said two members; an underseat assembly adapted to hold said two beams and, in use, to be secured to an aircraft cabin floor; and a seat back structure attached to said support members.
For a better understanding of the invention, and to show how the same may be carried into effect, reference will now be made, by way of example, to the accompanying drawings, in which:
Figure la is a side elevation, and Figure ib is a plan of a support member of this invention;
Figure 2 is an illustration of a bank of aircraft seats incorporating support members in accordance with the invention; and
Figures 3a and 3b are, respectively, a side elevation and an end elevation of the underseat assembly present in the aircraft seats shown in Figure 2.
Referring to Figures la and lb of the drawings, the suport member 1 comprises a front portion 2, a central portion 3 and a rear portion 4. Apertures 5 and 6 are provided in the lower part of the front portion 2 of the member. These apertures serve to locate the support member on two generally horizontal beams which pass under the aircraft seat. An aperture 7 in the central portion of the support member serves to locate a spindle which forms part of a mechanism for allowing the back of the aircraft seat to recline. A further aperture 8 is located in the rear portion of the support member; this aperture is adapted to receive an anchorage for one or two seat belts. Aperture 9, also in the rear portion 4, serves to locate the rigid
assembly which holds the back of the seat in position.
The peripheral frame portion 10 extending around the whole of the support member is in the form of a T-section flange. The outline of the member consists of a number of adjoining linear sections except in the lower part of the rear portion 4, which is generally upwardly curved. Substantially the whole of the body of the member lies in a single plane, as can be seen from Figures la and lb. Webs of relatively thin metal 1 la to llf extend between the relatively thicker metal parts of the support member. A number of ribs 12a to 12e are formed in the support member to provide the necessary strength and stress relief. A strengthening portion 13 is also formed in the region where the rear portion 4 adjoins the central portion 3.Ribs 12c and 12d are positioned so as to be slightly displaced from a continuation of upper surface regions lOc and loud, respectively.
In the embodiment shown in Figure 1, the apertures 5 and 6 are spaced apart by 51 inches.
The support member 1 is forged from an aluminium alloy consisting of by weight 3.9-5.0% Cu, 0.2-0.8% Mn, 0.5-1.0% Si, 0.7% Fe, 0.4-1.2% Mg, 0.2% Zn, 0.2%Ti, 0.1% Cr and the balance Al. The apertures 5 and 6 are forward of both the centre of gravity and the mid-point of the longitudinal axis of the member.
To form a seat assembly as shown in
Figure 2 of the drawings, four support members as shown in Figures la and 1b are employed. The support members are concealed within the seat structure, one being concealed by a panel 21. The beams which pass through apertures 5 and 6 of the support members are not visible in
Figure 2. An underseat assembly 20 serves to hold the beams which pass through apertures 5 and 6, and to secure the entire seat structure to the floor of the aircraft cabin. The seats comprise an upholstered seat cushion 22, an upholstered back portion 23 and arm rests 24. Food trays can be fitted at the back of the seats (not shown).
The underseat assembly 20 is shown diagrammaticaly in Figures 3a and 3b. The assembly consists of a plurality of tubular members 31, advantageously formed of steel and welded together. At the upper ends of the tubular members 31 there are Ushaped brackets 32 which serve to hold the beams which pass through apertures 5 and 6 in the support member of Figure 1.
A support member of this invention is very vcrsatile in that it can be used in many different types of aeroplane. For example, in the larger bodied jet aeroplanes, a single design of support member in accordance with this invention, such as that shown in Figures la and 1b can be used in all of the different seat locations within the aeroplane-e.g. as an outboard seat support member (adjacent to the fuselage), as a central seat support membel (between two seats) and as an inboard seat support member (adjacent to a gangway).
In smaller aeroplanes, it may be necessary to employ a slightly modified design for the outboard seat locations to take account of the curvature of the aircraft fuselage.
Also, the seats of this invention can be ganged together in any suitable numbers, and the seating arrangement provided in a given aircraft can be modified relatively easily.
WHAT WE CLAIM IS: - 1. A support member for an aircraft seat which is adapted to be held by two beams locatable within apertures formed in the support member, wherein (1) both of the apertures are positioned on the forward side (with reference to the aircraft seat, in use) of the centre of gravity of the support member, and (2) the support member is forged from aluminium or an aluminiumcontaining alloy.
2. A support member as claimed in claim 1, which is forged from a high-strength aluminium-copper alloy.
3. A support member as claimed in claim 2, wherein said alloy consists of from 3.9 to 5.0% copper, from 0.2 to 0.8% manganese, 0.5 to 1.0% silicon, 0.6 to 0.8% iron, 0.4 to 1.2% magnesium, 0.2% zinc, 0.2% titanium, 0. 1% chromium and the balance aluminium (all percentages by weight).
4. A support member as claimed in claim 1, 2 or 3, wherein the periphery of the support member is formed as a Tsection flange.
5. A support member as claimed in claim 1, 2, 3 or 4, wherein substantially the whole of the body of the support member lies in a single plane.
6. A support member for an aircraft seat as claimed in claim 1 and substantially as hereinbefore described.
7. A support member for an aircraft seat substantially as hereinbefore described with reference to, and as illustrated in,
Figures la and 1b of the accompanying drawings.
8. An aircraft seat structure which comprises two support members as claimed in any preceding claims, mounted on two generally horizontal beams; a seat cushion extending between the said two members; an underseat assembly adapted to hold said two beams and, in use, to be secured to an aircraft cabin floor; and a seat back structure attached to said support members.
9. An aircraft seat structure substantially as hereinbefore described with reference to, and as illustrated in, the accompanying drawings.
**WARNING** end of DESC field may overlap start of CLMS **.
Claims (9)
1. A support member for an aircraft seat which is adapted to be held by two beams locatable within apertures formed in the support member, wherein (1) both of the apertures are positioned on the forward side (with reference to the aircraft seat, in use) of the centre of gravity of the support member, and (2) the support member is forged from aluminium or an aluminiumcontaining alloy.
2. A support member as claimed in claim 1, which is forged from a high-strength aluminium-copper alloy.
3. A support member as claimed in claim 2, wherein said alloy consists of from 3.9 to 5.0% copper, from 0.2 to 0.8% manganese, 0.5 to 1.0% silicon, 0.6 to 0.8% iron, 0.4 to 1.2% magnesium, 0.2% zinc, 0.2% titanium, 0. 1% chromium and the balance aluminium (all percentages by weight).
4. A support member as claimed in claim 1, 2 or 3, wherein the periphery of the support member is formed as a Tsection flange.
5. A support member as claimed in claim 1, 2, 3 or 4, wherein substantially the whole of the body of the support member lies in a single plane.
6. A support member for an aircraft seat as claimed in claim 1 and substantially as hereinbefore described.
7. A support member for an aircraft seat substantially as hereinbefore described with reference to, and as illustrated in,
Figures la and 1b of the accompanying drawings.
8. An aircraft seat structure which comprises two support members as claimed in any preceding claims, mounted on two generally horizontal beams; a seat cushion extending between the said two members; an underseat assembly adapted to hold said two beams and, in use, to be secured to an aircraft cabin floor; and a seat back structure attached to said support members.
9. An aircraft seat structure substantially as hereinbefore described with reference to, and as illustrated in, the accompanying drawings.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB15764/78A GB1590061A (en) | 1978-04-20 | 1978-04-20 | Aircraft seats |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB15764/78A GB1590061A (en) | 1978-04-20 | 1978-04-20 | Aircraft seats |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1590061A true GB1590061A (en) | 1981-05-28 |
Family
ID=10065055
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB15764/78A Expired GB1590061A (en) | 1978-04-20 | 1978-04-20 | Aircraft seats |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB1590061A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4375300A (en) * | 1980-11-20 | 1983-03-01 | Uop Inc. | Framing system for aircraft passenger seat |
| FR2648107A1 (en) * | 1989-06-07 | 1990-12-14 | Keiper Recaro Gmbh Co | VEHICLE SEAT, IN PARTICULAR AIRCRAFT PASSENGER SEAT |
-
1978
- 1978-04-20 GB GB15764/78A patent/GB1590061A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4375300A (en) * | 1980-11-20 | 1983-03-01 | Uop Inc. | Framing system for aircraft passenger seat |
| FR2648107A1 (en) * | 1989-06-07 | 1990-12-14 | Keiper Recaro Gmbh Co | VEHICLE SEAT, IN PARTICULAR AIRCRAFT PASSENGER SEAT |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PS | Patent sealed | ||
| PCNP | Patent ceased through non-payment of renewal fee |