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WO2004007283A1 - Dispositif de rotation de roue - Google Patents

Dispositif de rotation de roue Download PDF

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Publication number
WO2004007283A1
WO2004007283A1 PCT/GB2003/003119 GB0303119W WO2004007283A1 WO 2004007283 A1 WO2004007283 A1 WO 2004007283A1 GB 0303119 W GB0303119 W GB 0303119W WO 2004007283 A1 WO2004007283 A1 WO 2004007283A1
Authority
WO
WIPO (PCT)
Prior art keywords
aircraft
wheel
base member
wind vanes
wheels
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.)
Ceased
Application number
PCT/GB2003/003119
Other languages
English (en)
Inventor
Andrew J. Boulton
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to AU2003251338A priority Critical patent/AU2003251338A1/en
Publication of WO2004007283A1 publication Critical patent/WO2004007283A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/40—Alighting gear characterised by elements which contact the ground or similar surface  the elements being rotated before touch-down

Definitions

  • 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.
  • the absorbed energy by the tyres results in wear to the tyres in the form of surface "flat spots" .
  • 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.
  • 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.
  • 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.
  • the base member may be integral with an aircra t wheel .
  • the base member is lightweight.
  • 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.
  • 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.
  • 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;
  • Fig. 2 is a perspective view of the apparatus of Fig. 1 in use.
  • FIG. 1 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.
  • the wheel 14 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.
  • an aircraft When landing, an aircraft lowers its landing leg 18 such that the tyre 12 is prepared to touchdown onto a runway.
  • 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.
  • 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) .
  • a braking system or ABS system (not shown)
  • the aircraft's existing braking system or ABS system may be used.
  • 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.
  • 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 .
  • 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.
  • 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 .
  • 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.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Wind Motors (AREA)

Abstract

L'invention concerne un dispositif permettant de produire une rotation préalable d'une roue d'aéronef (10) pour l'atterrissage. Ce dispositif comprend un support (110) sur lequel sont montées plusieurs girouettes (112). Le support (110) présente un élément de base (114) doté d'ouvertures (116) conçues pour être placées sur des pivots (20) d'un moyeu de roue (22) d'un aéronef sur le haut de la roue (14) de l'aéronef. Le support (110) comprend des séparateurs (120) permettant de positionner les girouettes (112) en saillie par rapport à la roue et au pneu (12) de l'aéronef.
PCT/GB2003/003119 2002-07-17 2003-07-17 Dispositif de rotation de roue Ceased WO2004007283A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AU2003251338A AU2003251338A1 (en) 2002-07-17 2003-07-17 Wheel rotating apparatus

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB0216546A GB0216546D0 (en) 2002-07-17 2002-07-17 Wheel rotating apparatus
GB0216546.2 2002-07-17

Publications (1)

Publication Number Publication Date
WO2004007283A1 true WO2004007283A1 (fr) 2004-01-22

Family

ID=9940593

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB2003/003119 Ceased WO2004007283A1 (fr) 2002-07-17 2003-07-17 Dispositif de rotation de roue

Country Status (3)

Country Link
AU (1) AU2003251338A1 (fr)
GB (1) GB0216546D0 (fr)
WO (1) WO2004007283A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016004472B3 (de) 2016-04-15 2017-03-30 Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. Profilscheibe zur Drehbeschleunigung eines Flugzeugrades sowie mit einer solchen Profilscheibe ausgestattetes Flugzeugrad

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2410625A (en) * 1944-07-19 1946-11-05 Bernard D Branner Landing gear for aircraft
DE3416416A1 (de) * 1984-01-13 1985-07-18 Hans-Dieter 6100 Darmstadt Kelm Flugzeugfahrgestell
US4732350A (en) * 1985-11-07 1988-03-22 Lamont John S Aircraft wheel rotation apparatus
US5104063A (en) * 1990-04-27 1992-04-14 Hartley James M Aircraft landing gear prerotation system
GB2256402A (en) * 1991-06-05 1992-12-09 Kevin Mchale Aircraft undercarriages with means to rotate the wheels.
DE29706839U1 (de) * 1997-04-16 1998-08-13 Beling, Manfred, 65199 Wiesbaden Radantriebsvorrichtung für Flugzeugräder
BE1013978A3 (nl) * 2001-02-22 2003-01-14 Ridder Walter Renu De Vliegtuigwiel.

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2410625A (en) * 1944-07-19 1946-11-05 Bernard D Branner Landing gear for aircraft
DE3416416A1 (de) * 1984-01-13 1985-07-18 Hans-Dieter 6100 Darmstadt Kelm Flugzeugfahrgestell
US4732350A (en) * 1985-11-07 1988-03-22 Lamont John S Aircraft wheel rotation apparatus
US5104063A (en) * 1990-04-27 1992-04-14 Hartley James M Aircraft landing gear prerotation system
GB2256402A (en) * 1991-06-05 1992-12-09 Kevin Mchale Aircraft undercarriages with means to rotate the wheels.
DE29706839U1 (de) * 1997-04-16 1998-08-13 Beling, Manfred, 65199 Wiesbaden Radantriebsvorrichtung für Flugzeugräder
BE1013978A3 (nl) * 2001-02-22 2003-01-14 Ridder Walter Renu De Vliegtuigwiel.

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102016004472B3 (de) 2016-04-15 2017-03-30 Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. Profilscheibe zur Drehbeschleunigung eines Flugzeugrades sowie mit einer solchen Profilscheibe ausgestattetes Flugzeugrad

Also Published As

Publication number Publication date
AU2003251338A1 (en) 2004-02-02
GB0216546D0 (en) 2002-08-28

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