WO2004007283A1

WO2004007283A1 - Wheel rotating apparatus

Info

Publication number: WO2004007283A1
Application number: PCT/GB2003/003119
Authority: WO
Inventors: Andrew J. Boulton
Original assignee: Individual
Current assignee: Individual
Priority date: 2002-07-17
Filing date: 2003-07-17
Publication date: 2004-01-22
Anticipated expiration: 2005-01-17
Also published as: AU2003251338A1; GB0216546D0

Abstract

An apparatus for producing pre-rotation of an aircraft wheel (10) for landing comprises a carrier (110) mounting a number of wind vanes (112). The carrier (110) has a base member (114) with apertures (116) for locating on studs (20) of an aircraft wheel hub (22) on top of the aircraft wheel (14). The carrier (110) includes spacers (120) to position the vanes (112) outwardly of the aircraft wheel and tyre (12).

Description

Wheel Rotating Apparatus

This invention relates to wheel rotating apparatus, used particularly, but not exclusively, as apparatus which is removably attachable to the wheel of an aircraft to cause air induced pre-rotation of an aircraft wheel as the aircraft prepares for landing so as to reduce wear on the tyres, and to reduce stress to the landing-gear and airframe, when the aircraft touches down on the runway.

When the landing gear assembly of an aircraft is lowered from within the aircraft's wings/fuselage, the wheels, and therefore tyres, are stationary.

As the aircraft lands on the runway, the sudden impact of the stationary tyres onto the runway generates a tremendous amount of energy which is initially absorbed by the tyres, and then dissipated through the landing gear assembly and airframe.

The absorbed energy by the tyres results in wear to the tyres in the form of surface "flat spots" .

This wear reduces the service life of the tyres resulting in costly and more frequent replacement of the tyres and may lead to failure of the landing gear and airframe .

It will be appreciated that such wear can be mitigated by pre-rotating the wheels as the landing gear assembly is lowered, such that their tangential speed is similar to the speed of the aircraft relative to the ground. In this way, the pre- rotating tyres do not absorb as much of the tremendous amount of energy as a stationary tyre would.

In view of the in service weight restrictions applied to aircraft, it is desirable that apparatus to pre-rotate the aircraft's wheels is lightweight and has a minimum number of parts to service, from a cost, maintenance and safety point of view.

According to the present invention there is provided wheel rotating apparatus for rotating at least one aircraft wheel of an aircraft preparing to land, the apparatus comprising a base member for connection to the wheel, and a number of wind vanes connected to the base member, wherein the wind vanes protrude outwardly from the base member and are adapted to provide a rotational force to said wheel.

Preferably, the base member is shaped and dimensioned to be retro-fittable to an existing aircraft wheel .

The base member is typically a ring having apertures located to receive wheel studs of a wheel hub of a given aircraft.

Alternatively, the base member may be integral with an aircra t wheel .

Suitably, the base member is lightweight.

In a preferred form of the apparatus a vane fixing member is interposed between the wind vanes and the base member, the vane fixing member securing one- end of each of said wind vanes.

The vane fixing member may be spaced from the base member by at least one spacer element, the length of which may be chosen to cause the vanes to project outwardly of the aircraft wheel and tyre when the base member is secured to the aircraft wheel hub.

Preferably the wind vanes for the port and starboard sides of the aircraft wheels are readily distinguishable from one another, suitably by the wind vanes for the port and starboard sides of the aircraft wheels being differently coloured.

The invention also provides an aircraft having apparatus as defined above, and in which a braking system is used to prevent the wheels from rotating at a tangential speed which is greater than the speed of the aircraft relative to the runway.

Said braking system may be provided by the aircraft's existing braking system or ABS system.

Embodiments of the present invention will now be described, by way of example only, with reference to the accompanying drawings in which: -

Fig. 1 is a part exploded perspective view of wheel rotating apparatus, removably attachable to a conventional wheel and tyre, which is then affixed to a landing leg of an aircraft; and

Fig. 2 is a perspective view of the apparatus of Fig. 1 in use.

With reference to the drawings, and in particular Fig. 1, there is illustrated a conventional aircraft landing gear apparatus 10 having a tyre 12 mounted on a wheel 14, the wheel 14 having apertures 16 to allow removable attachment to a rotating hub 22, located at an end of a landing leg 18.

In assembly, the wheel 14 is positioned such that its apertures 16 receive studs 20 which protrude from the rotating hub 22 located on the landing leg 18. The wheel 14 is then secured thereon by nuts (not shown) . It will be understood that in other cases the wheel may be secured by bolts engaging threaded holes in the hub. When landing, an aircraft lowers its landing leg 18 such that the tyre 12 is prepared to touchdown onto a runway.

It will be appreciated that whilst one landing gear is described and illustrated, several landing gears may be used on the aircraft .

The present invention provides wheel rotating apparatus 100 comprising a carrier member 110 having wind vanes 112.

The carrier member 110 has a base member or ring base plate 114 with apertures 116 which allow removable attachment to the studs 20.

The ring base plate 114 has an outer diameter substantially equivalent to the inner diameter of the wheel 14. This serves to allow the carrier member 110 to be removably attached or retro-fitted to the wheel 14.

The carrier member 110 also has a vane fixing member in the from of a ring plate 118 extending from the ring base plate 114 supported by a plurality of spacer elements or horizontal supports 120 circumferentially spaced around, and between, both ring plates 114, 118.

Alternatively the carrier 110 may be cast (metal) and/or injection moulded (plastic) as one single integral item, the ring plates 114, 118 being joined by a continuous cylinder . The wind vanes 112 are mounted at their root ends on the outwardly facing surface of the extended ring plate 118. In this way, the wind vanes 112 will protrude outwardly from the wheel 14 when the carrier member 110 is removably attached or retrofitted to the wheel 14.

The wind vanes 112 are orientated and shaped to induce/initiate rotation of the apparatus 100 and wheel 14 as a result of air pressure on the wind vanes 112, when the aircraft is preparing to land. Hence, allowing maximum rotation of the carrier member 110, and the wheel 14.

The wheel 14 would be prevented from rotating too fast by use of a braking system or ABS system (not shown) . Preferably, the aircraft's existing braking system or ABS system may be used.

In assembly, the wheel 14 is removably attached to the studs 20 as described above. The carrier member 110 is also removably attached or retrofitted to the same studs 20 by virtue of apertures 116. Both the wheel 14 and carrier member 110 are then secured to the rotating hub 22 located at the end of the landing leg 18.

In use, as the aircraft comes into land, the landing leg 18 is lowered. The flowing air interacts with the wind vanes 112 causing rotation of the carrier member 110 and thus wheel 14.

The aircraft's existing brake system or ABS system is used to prevent the wheel 14 from rotating too fast .

It will be recognised, that the orientation of the wind vanes 112 cause the wheels 14 to forwardly rotate in relation to the direction of the aircraft.

It will be further recognised that the port wheel 14, will have wind vanes 112 which have a mirrored orientation compared to the starboard wheel 14. Port wheels 14 are distinguishable from starboard wheels 14, for example, by manufacturing port apparatus with red wind vanes 112 and starboard apparatus with green wind vanes 112.

It is to be recognised that the wheel rotating apparatus 100 is passive and comprises no moving parts to fail, break, or cause damage to other adjacent parts of the aircraft.

The wheel rotating apparatus 100 is made from strong, lightweight materials such as aluminium alloy, or (preferably) rigid plastics, which can be self coloured, and which are easy to mould and inexpensive. Where plastics are used, metal inserts may be provided in the area of the apertures 116 to provide local strengthening and to minimise wear. The invention makes it possible for a wheel rotation system to be readily retrofitted to existing aircraft wheels. The arrangement of rings and spacers permits ease of manufacture to match the diameter and depth of a given wheel .

Modifications and improvements may be made to the above without departing from the scope of the present invention, for example, a speedometer, or other means, may be attached to the carrier member to determine the rotational and tangential speed of the rotating wheel which can be compared to the speed of the aircraft in relation to the runway.

Claims

1. Wheel rotating apparatus for rotating at least one aircraft wheel of an aircraft preparing to land, the apparatus comprising a base member for connection to the wheel, and a number of wind vanes connected to the base member, wherein the wind vanes protrude outwardly from the base member and are adapted to provide a rotational force to said wheel .

2. Apparatus according to claim 1, in which the base member is shaped and dimensioned to be retro- fittable to an existing aircraft wheel .

3. Apparatus according to claim 2, in which the base member is a ring having apertures located to receive wheel studs of a wheel hub of a given aircraft .

4. Apparatus according to claim 1, in which the base member is integral with an aircraft wheel.

5. Apparatus according to any preceding claim, in which the base member is lightweight.

6. Apparatus according to any preceding claim, in which a vane fixing member is interposed between the wind vanes and the base member, the vane fixing member securing one end of each of said wind vanes.

7. Apparatus according to claim 6 in which the vane fixing member is spaced from the base member by at least one spacer element .

8. Apparatus according to claim 7, in which the length of the spacer element (s) is chosen to cause the vanes to project outwardly of the aircraft wheel and tyre when the base member is secured to the aircraft wheel hub.

9. Apparatus according to any preceding claim, in which the wind vanes for the port and starboard sides of the aircraft wheels are readily distinguishable from one another.

10. Apparatus according to claim 9, in which the wind vanes for the port and starboard sides of the aircraft wheels are differently coloured.

11. An aircraft having apparatus according to any preceding claim provided on its landing wheels, and in which a braking system is used to prevent the wheels from rotating at a tangential speed which is greater than the speed of the aircraft relative to the runway.

12. An aircraft according to claim 11, in which said braking system is provided by the aircraft's existing braking system or ABS system.