GB2105014A - Bearing - Google Patents
Bearing Download PDFInfo
- Publication number
- GB2105014A GB2105014A GB08221955A GB8221955A GB2105014A GB 2105014 A GB2105014 A GB 2105014A GB 08221955 A GB08221955 A GB 08221955A GB 8221955 A GB8221955 A GB 8221955A GB 2105014 A GB2105014 A GB 2105014A
- Authority
- GB
- United Kingdom
- Prior art keywords
- seat
- bearing
- linear bearing
- linear
- tube
- 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.)
- Withdrawn
Links
- 239000000463 material Substances 0.000 claims abstract description 24
- 239000002184 metal Substances 0.000 claims description 16
- 230000001050 lubricating effect Effects 0.000 claims description 6
- 229910000906 Bronze Inorganic materials 0.000 claims description 4
- OAICVXFJPJFONN-UHFFFAOYSA-N Phosphorus Chemical compound [P] OAICVXFJPJFONN-UHFFFAOYSA-N 0.000 claims description 4
- 239000010974 bronze Substances 0.000 claims description 4
- KUNSUQLRTQLHQQ-UHFFFAOYSA-N copper tin Chemical compound [Cu].[Sn] KUNSUQLRTQLHQQ-UHFFFAOYSA-N 0.000 claims description 4
- ZHPNWZCWUUJAJC-UHFFFAOYSA-N fluorosilicon Chemical compound [Si]F ZHPNWZCWUUJAJC-UHFFFAOYSA-N 0.000 claims description 4
- 229920002635 polyurethane Polymers 0.000 claims description 4
- 239000004814 polyurethane Substances 0.000 claims description 4
- 230000035939 shock Effects 0.000 claims description 4
- 241000237519 Bivalvia Species 0.000 claims description 2
- 230000002238 attenuated effect Effects 0.000 claims description 2
- 235000020639 clam Nutrition 0.000 claims description 2
- 238000013016 damping Methods 0.000 claims description 2
- 230000001419 dependent effect Effects 0.000 claims description 2
- 230000000694 effects Effects 0.000 claims description 2
- 239000004519 grease Substances 0.000 claims description 2
- 230000008018 melting Effects 0.000 claims description 2
- 238000002844 melting Methods 0.000 claims description 2
- 230000000717 retained effect Effects 0.000 claims description 2
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
- B64D11/0619—Arrangements of seats, or adaptations or details specially adapted for aircraft seats with energy absorbing means specially adapted for mitigating impact loads for passenger seats, e.g. at a crash
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60N—SEATS SPECIALLY ADAPTED FOR VEHICLES; VEHICLE PASSENGER ACCOMMODATION NOT OTHERWISE PROVIDED FOR
- B60N2/00—Seats specially adapted for vehicles; Arrangement or mounting of seats in vehicles
- B60N2/24—Seats specially adapted for vehicles; Arrangement or mounting of seats in vehicles for particular purposes or particular vehicles
- B60N2/42—Seats specially adapted for vehicles; Arrangement or mounting of seats in vehicles for particular purposes or particular vehicles the seat constructed to protect the occupant from the effect of abnormal g-forces, e.g. crash or safety seats
- B60N2/4207—Seats specially adapted for vehicles; Arrangement or mounting of seats in vehicles for particular purposes or particular vehicles the seat constructed to protect the occupant from the effect of abnormal g-forces, e.g. crash or safety seats characterised by the direction of the g-forces
- B60N2/4242—Seats specially adapted for vehicles; Arrangement or mounting of seats in vehicles for particular purposes or particular vehicles the seat constructed to protect the occupant from the effect of abnormal g-forces, e.g. crash or safety seats characterised by the direction of the g-forces vertical
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60N—SEATS SPECIALLY ADAPTED FOR VEHICLES; VEHICLE PASSENGER ACCOMMODATION NOT OTHERWISE PROVIDED FOR
- B60N2/00—Seats specially adapted for vehicles; Arrangement or mounting of seats in vehicles
- B60N2/24—Seats specially adapted for vehicles; Arrangement or mounting of seats in vehicles for particular purposes or particular vehicles
- B60N2/42—Seats specially adapted for vehicles; Arrangement or mounting of seats in vehicles for particular purposes or particular vehicles the seat constructed to protect the occupant from the effect of abnormal g-forces, e.g. crash or safety seats
- B60N2/427—Seats or parts thereof displaced during a crash
- B60N2/42727—Seats or parts thereof displaced during a crash involving substantially rigid displacement
- B60N2/42736—Seats or parts thereof displaced during a crash involving substantially rigid displacement of the whole seat
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B61—RAILWAYS
- B61D—BODY DETAILS OR KINDS OF RAILWAY VEHICLES
- B61D33/00—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
- B64D11/0689—Arrangements of seats, or adaptations or details specially adapted for aircraft seats specially adapted for pilots
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F7/00—Vibration-dampers; Shock-absorbers
- F16F7/12—Vibration-dampers; Shock-absorbers using plastic deformation of members
- F16F7/127—Vibration-dampers; Shock-absorbers using plastic deformation of members by a blade element cutting or tearing into a quantity of material; Pultrusion of a filling material
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Transportation (AREA)
- General Engineering & Computer Science (AREA)
- Sliding-Contact Bearings (AREA)
- Vibration Dampers (AREA)
Abstract
An aircraft seat assembly has one or more support members 2 which are capable of being slidably engaged by the seat through a linear bearing 4. The linear bearing has inner and outer liners 7,8 separated by a shearable material 6 so that under conditions of shear e.g. in a crash, the shearable material ruptures and allows the outer liner to become the part of the bearing engaging with the support tubes. <IMAGE>
Description
SPECIFICATION
Bearing
The present invention relates to bearings and more particularly relates to linear bearings.
Linear bearings are well known for bearing the load and friction generated by an object sliding along a tube or shaft. These bearings are dependent for their operation on the symmetry of the tube as any distortion will cause seizure onto the tube.
Linear bearings are used in adjustable seats in aircraft, e.g. helicopters. The seat is retained and guided by linear bearings capable of slidable adjustment on parallel tubes. Under disruptive conditions, for example, during a crash, the tubes carrying the seat can distort and cause the bearing to seize onto the tube thereby preventing the shock to the pilot being dissipated by the seat stroking through a shock attenuating distance.
An alternative to the linear bearing is bearings mounted in a spherical housing but this is likely to add to the weight of the system and require further cockpit space. The present invention relates to a linear bearing which overcomes or alleviates some of these problems.
Thus according to the present invention there is provided a linear bearing capable of attachment to a stationary or moving member comprising annular inner and outer liners spaced apart by a shearable mounting material.
In normal use, for example, in a helicopter seat, the linear bearing acts as a conventional bearing with the inner liner engaging the seat support tubes. Under conditions of shear such as in a crash, the mounting material between the inner and outer linings is capable of rupturing such that the outer liner becomes the part of the bearing engaging with the support tubes.
The shearable mounting material preferably comprises a polymeric material which is fabricated to give suitable pull out or shear properties, for example, a polyurethane or a fluorosilicon. The force required to pull out or shear the mounting material is designed to suit the specific application.
The inner liners are preferably fabricated from metal such as self-lubricated metal, e.g.
phosphor bronze. The outer liners are preferably made from a self-lubricating material such as Deirin or Acetile, which has a fairly high melting point. The sliding faces of the bearing may alternatively be lubricated by oil, grease, etc.
The invention also includes a seat assembly suitable for use in aircraft comprising a seat and one or more support members, for example tubes, the seat being capable of slidably engaging the support members through a linear bearing as hereinbeiore described.
The invention will now be described by way of example only.
Figure 1 shows a schematic side view of a helicopter pilot seat and
Figures 2 and 3 show vertical sections through the shearable bearing of the seat before and after shear.
A pilot seat 1 is fastened onto a pair of inclined cylindrical support tubes 2 by means of an upper and lower bearing 3 on each tube 2. The seat 1 is normally adjustable by the pilot over a limited range. The seat is capable of further downward travel outside the normal adjustable limits A and this travel is indicated by the dotted lines. This travel would only be used, for example, during crash conditions, and it is known as the crash attenuated travel
D, (Fig. 1). The crash attentuated travel is controlled at a constant load to give a damping effect.
The bearing 3 comprises a housing 4 attached through a metal bar 5 to the pilot seat 1, the housing 4 enclosing a flexible mounting 6 sandwiched between inner and outer liners 7,8. The support tube 2 is in sliding contact with the inner liner 7 and the bearing 3. The flexible mounting 6 allows the bearing 3 to have a small angular movement and about the central tube 2, (Fig. 2). The liners are fabricated from a self-lubricated metal.
Under conditions of extreme shear, for example, during a crash where the support tube buckles, the flexible mounting 6 is designed to shear and break away from the inner liner 7 of the bearings thereby enabling the outer liner 8 to act as the bearing for the seat 1 on the support tube 2 and to pass over the buckle point 9 so as to take advantage of the crash attentuated travel. This condition is shown in Fig. 3.
CLAMS 1. A linear bearing capable of attachment to a stationary or moving member comprising annular inner and outer liners spaced apart by a shearable mounting material.
2. A linear bearing according to claim 1 in which the shearable mounting material comprises a polymeric material.
3. A linear bearing according to claim 2 in which the polymeric material is a polyurethane or a fluorosilicon.
4. A linear bearing according to any one of the preceding claims in which the inner liners are fabricated from metal.
5. A linear bearing according to claim 4 in which the metal is a self lubricating metal.
6. A linear bearing according to claim 5 in which the self lubricating metal is phosphor bronze.
7. A linear bearing according to any one of the preceding claims in which the outer liners are fabricated from a self lubricating material.
8. A linear bearing as hereinbefore de
**WARNING** end of DESC field may overlap start of CLMS **.
Claims (9)
1. A linear bearing capable of attachment to a stationary or moving member comprising annular inner and outer liners spaced apart by a shearable mounting material.
2. A linear bearing according to claim 1 in which the shearable mounting material comprises a polymeric material.
3. A linear bearing according to claim 2 in which the polymeric material is a polyurethane or a fluorosilicon.
4. A linear bearing according to any one of the preceding claims in which the inner liners are fabricated from metal.
5. A linear bearing according to claim 4 in which the metal is a self lubricating metal.
6. A linear bearing according to claim 5 in which the self lubricating metal is phosphor bronze.
7. A linear bearing according to any one of the preceding claims in which the outer liners are fabricated from a self lubricating material.
8. A linear bearing as hereinbefore de scribed and with reference to Figs. 1 to 3 of the accompanying drawings.
9. A seat assembly suitable for use in aircraft comprising a seat and one or more support members for the seat, the seat being capable of slidably engaging the support members through a linear bearing according to any of claims 1 to 8.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB8123531 | 1981-07-31 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB2105014A true GB2105014A (en) | 1983-03-16 |
Family
ID=10523615
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB08221955A Withdrawn GB2105014A (en) | 1981-07-31 | 1982-07-29 | Bearing |
Country Status (3)
| Country | Link |
|---|---|
| FR (1) | FR2510512A1 (en) |
| GB (1) | GB2105014A (en) |
| IT (1) | IT1148394B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4632406A (en) * | 1981-01-15 | 1986-12-30 | Avaa International Corp. | Apparatus in which an annular ring is carried within a groove about one member for slidably engaging the cylindrical surface of another member |
| RU2611326C1 (en) * | 2016-03-10 | 2017-02-21 | Открытое акционерное общество "Научно-производственное предприятие "Звезда" имени академика Г.И. Северина" | Energy-absorbing seat for aircraft |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| IL109446A (en) * | 1994-04-26 | 1999-09-22 | Israel Aircraft Ind Ltd | Vehicle seat |
| DE102012007279B3 (en) * | 2012-04-13 | 2013-07-18 | Rheinmetall Man Military Vehicles Gmbh | Mine-proof seating device |
| ITBG20130024A1 (en) * | 2013-08-29 | 2015-03-01 | Marco Boncompagni | ANTI-SHOCK PLATFORM FOR SEATS OF PASSENGERS OF MEANS OF TRANSPORT |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3459063A (en) * | 1966-09-03 | 1969-08-05 | Toyota Motor Co Ltd | Collapsible steering column assembly |
| FR2374554A1 (en) * | 1976-12-20 | 1978-07-13 | Nadella | COLLAPSABLE TRANSMISSION |
| US4211151A (en) * | 1977-05-26 | 1980-07-08 | United Technologies Corporation | Jam proof piston |
| US4185542A (en) * | 1978-02-27 | 1980-01-29 | Bertea Corporation | Actuator with frangible gland construction |
-
1982
- 1982-07-27 IT IT48890/82A patent/IT1148394B/en active
- 1982-07-29 GB GB08221955A patent/GB2105014A/en not_active Withdrawn
- 1982-07-30 FR FR8213330A patent/FR2510512A1/en not_active Withdrawn
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4632406A (en) * | 1981-01-15 | 1986-12-30 | Avaa International Corp. | Apparatus in which an annular ring is carried within a groove about one member for slidably engaging the cylindrical surface of another member |
| RU2611326C1 (en) * | 2016-03-10 | 2017-02-21 | Открытое акционерное общество "Научно-производственное предприятие "Звезда" имени академика Г.И. Северина" | Energy-absorbing seat for aircraft |
Also Published As
| Publication number | Publication date |
|---|---|
| IT1148394B (en) | 1986-12-03 |
| FR2510512A1 (en) | 1983-02-04 |
| IT8248890A0 (en) | 1982-07-27 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| WAP | Application withdrawn, taken to be withdrawn or refused ** after publication under section 16(1) |