WO1992015483A1 - Aircraft wheel prerotation apparatus - Google Patents

Aircraft wheel prerotation apparatus Download PDF

Info

Publication number
WO1992015483A1
WO1992015483A1 PCT/AU1992/000094 AU9200094W WO9215483A1 WO 1992015483 A1 WO1992015483 A1 WO 1992015483A1 AU 9200094 W AU9200094 W AU 9200094W WO 9215483 A1 WO9215483 A1 WO 9215483A1
Authority
WO
WIPO (PCT)
Prior art keywords
wheel
rotor device
aircraft
vane
blade
Prior art date
Application number
PCT/AU1992/000094
Other languages
French (fr)
Inventor
Julian Pasqua
Original Assignee
Julian Pasqua
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 Julian Pasqua filed Critical Julian Pasqua
Publication of WO1992015483A1 publication Critical patent/WO1992015483A1/en

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

  • the present invention relates to pre-rotation of aircraft wheels prior to landing.
  • the present invention is at least one rotor device adapted to be attached to an aircraft wheel, wherein when said aircraft is flying and said wheel is lowerd or being lowered in position for landing said rotor device and said wheel are caused to rotate due to air flow past said rotor device.
  • the present invention is a wheel for an aircraft, said wheel comprising at least one rotor device wherein when said aircraft is flying and said wheel is lowered or being lowered in position for landing said wheel are caused to rotate due to air flow past said rotor device.
  • the present invention is a wheel assembly for an aircraft, said wheel assembly comprising a rotor device attached to a wheel thereto, wherein rotor device is adapted to rotate when exposed to airflow passing said aircraft during flight thereby rotating said wheel.
  • the present invention is a rotor device attached to at least one aircraft wheel, said
  • the rotor device comprises a plurality of
  • each rotor device comprises a plurality of vanes.
  • vanes are arranged in an annulus concentric with the axis of rotation of the wheel.
  • the rotor comprises a plurality of helical vanes.
  • the vanes may extend axially or radially from the wheel.
  • the rotor device is located on one side of the wheel.
  • Fig. 1 is a side view of an aircraft wheel and a rotation device of the present invention.
  • Fig. 2 is a cross sectional view of an aircraft wheel and the rotation device of Fig. 1.
  • Fig. 3 shows a plan view of another embodiment of the invention.
  • Fig. 4 shows a side view of the embodiment of Fig. 3.
  • Fig. 5 shows a plan view of a further embodiment of the invention.
  • Fig. 6 shows a side view of the embodiment of Fig. 5.
  • Figs. 6a and 6b show alternative blade shapes for use with the embodiments of Figs. 5 and 6.
  • Fig. 7 shows a further embodiment of the invention.
  • Fig. 8 shows a side view of the embodiment of Fig. 7.
  • Fig. 9 shows a cross section view along line AA of Fig. 8.
  • Fig. 10 shows an alternate vane for use in the embodiment of Figs. 7 and 8.
  • Fig. 11 shows a cross-section view along line BB of Fig. 10.
  • Figs. 1 and 2 depict a typical aircraft wheel 1 and tyre 2 arrangement with a rotor device 3 protruding from an axial end face of the wheel 1.
  • the rotor device 3 comprises a plurality of helical vanes 4 which extend axially.
  • the rotor device 3 has four vanes 4, but more or less may be used, as desired.
  • the vanes 4 are - 3 - arranged around the axis of rotation 5 of the wheel 1 and are equally spaced.
  • the wheel 1 is mounted on the aircraft such that the normal direction of travel when the aircraft is flying is indicated by arrow 6.
  • the wheel and rotor when exposed to the airflow, are subjected to a relative airflow in the direction opposite to arrow 6. This occurs when the undercarriage is lowered fully or partially to the "landing position"
  • the wheel When the aircraft has a fixed undercarriage the wheel is always exposed to the airflow.
  • This relative airflow acts on the helical vanes 4 of the rotor device 3 and urges the rotor device 3 and the wheel 1 to rotate about axis 5 in the direction of arrow 7.
  • the wheels 1 are free to rotate about axis 5 and so such rotation occurs.
  • the speed of rotation of the wheel 1 caused by the rotor device 3 prior to landing of the aircraft may result in the peripheral velocity of the tyre 2 being substantially equal to the landing speed. This will substantially eliminate skidding.
  • the invention is not restricted to causing specific rotational speeds and includes generation of any rotation of the wheel of the aircraft.
  • an aircraft wheel 11 has a tyre 12 mounted thereon and is adapted to rotate about axis 15.
  • the wheel has on an axial end face 18 a rotor device 13.
  • the rotor device 13 extends axially outwardly of the tyre 12 so as to extend into an airflow 9 passing the wheel.
  • the rotor device has three vanes 14 which extend axially outward from the wheel, these vanes 14 being equally spaced about the axis of rotation 15.
  • Each vane 14 has a curved shape which, as seen in Fig. 4, converges on the axis of rotation 15 in an anticlockwise direction.
  • a wheel 21 adapted for rotation about an axis 25 has a tyre 22 mounted thereon.
  • the wheel 21 has a rotation device 23 extending from an axial end face 28 to extend beyond the tyre 22 into an airflow 29.
  • the rotor device 23 comprises a series of curved blades 24 which extend away from the wheel 21 in the axial direction.
  • the blades 24 are configured with their concave surfaces facing in a clockwise direction, as seen in Fig. 6.
  • the blades 24 are arranged concentrically about axis 25 at a constant radius, but if desired two or more annuli of blades 24 may be used.
  • a relative airflow in the direction of arrow 29 will urge the rotor device 23 and hence wheel 21 to rotate anticlockwise in the direction of arrow 27.
  • Figures 6a and 6b show alternate vane shapes for use with the embodiment of figures 5 and 6.
  • Fig. 6a shows an end view of a v-shaped blade 30
  • Fig. 6b shows an end view of a wide u-shaped blade 32. Both blades 30 and 32 are mounted so that their open mouths 31, 33, respectively, face clockwise, similarly to blades 24 of Fig. 6.
  • FIG. 7 and 8 there is shown a fourth embodiment of the invention.
  • a wheel 41 adapted for rotation 45 is provided with a rotation device 43 on one axial end face 48. Again the rotation device 43 extends beyond the edge of the tyre 42 mounted on wheel 41 to be exposed to any airflow 49.
  • the rotation device comprises a plurality of cup shaped members 44, which in this embodiment the number of blades is 14.
  • the members 44 are each the shape of a quarter sphere and have their open mouths facing in a clockwise direction such that airflow in direction of arrow 49 urges rotation in direction of arrow 47 about axis 45.
  • the cup shaped members 44 are arranged in a single annulus about axis 45 but it is to be understood that the members 44 may be arranged in more - 5 - than one circle about axis 45.
  • FIGS. 10 and 11 show an alternate blade shape for use with the embodiment of Figs. 7 and 8.
  • each blade exends out of the radial plane of the wheel at a constant angle and has side walls to define a cone-shaped opening.
  • the mouth of the opening is arranged in the same direction to face clockwise as per the cup-shaped members 44.
  • the blades or vanes of the rotor device all extend axially from the wheel. It is to be understood that the vanes or blades may be configured to extend radially, next to the tyre, rather than axially.
  • the use of the rotor device requires low maintenance as compared with pre-rotation being powered from within the aircraft.
  • the aircraft wheel may have a rotor device protruding from each side.
  • a rotor device attached to a first aircraft wheel may also rotate one or more further wheels which are rotatably connected to the first aircraft wheel by means of an axle.
  • the aircraft wheel may be axled in pairs or sets with the outside of the wheels having the rotor device protruding from them.
  • rotor device of the invention is not limited to the abovementioned embodiments can and be configured to suit the particular aircraft, its use and the environment it operates within.
  • the invention includes a separate rotor adapted for attachment to an aircraft wheel together with an aircraft wheel including an integral rotor device.
  • the embodiments described above are therefore to be understood to relate to both integral and non-integral wheel/rotor configurations.
  • the advantage offered by the invention is that pre-rotation of wheels for the purposes of reducing tyre wear without having to power the pre-rotation of the wheel from within the aircraft.

Abstract

A rotor device (3) adapted to be attached to an aircraft wheel (1) or an aircraft wheel including an integral rotor device, the rotor device (3) causing the aircraft wheel (1) to rotate when subject to an air flow, such as when the aircraft is approaching a runway to land. Prerotation of the aircraft wheel (1) prior to landing reduces skidding on landing and reduces wear of the tyre (2).

Description

AIRCRAFT WHEEL PREROTATION APPARATUS
The present invention relates to pre-rotation of aircraft wheels prior to landing.
Conventional air craft do not provide any pre-rotation of their wheels prior to landing. Thus when an aircraft lands its wheels initially skid on the runway and then commence rotation. If the wheels do not commence rotation the tyres can suffer premature wear, flat spots and blowouts, the latter of which has been known to cause accidents. Furthermore it takes some time for the tyres to rotate at the correct speed without skidding and this tends to generate shuddering and vibration in the aircraft.
In the past mechanical pre-rotation of aircraft wheels has been considered in order to reduce the wear on tyres which occurs as a result of the tyres coming in contact with the ground during landing. The mechanical pre-rotation of wheels requires electro-mechanical/hydraulic means which involves additional weight and power requirements by the aircraft for this to be achieved.
In one broad form the present invention is at least one rotor device adapted to be attached to an aircraft wheel, wherein when said aircraft is flying and said wheel is lowerd or being lowered in position for landing said rotor device and said wheel are caused to rotate due to air flow past said rotor device.
In another form the present invention is a wheel for an aircraft, said wheel comprising at least one rotor device wherein when said aircraft is flying and said wheel is lowered or being lowered in position for landing said wheel are caused to rotate due to air flow past said rotor device.
In a further form the present invention is a wheel assembly for an aircraft, said wheel assembly comprising a rotor device attached to a wheel thereto, wherein rotor device is adapted to rotate when exposed to airflow passing said aircraft during flight thereby rotating said wheel.
In an even further form the present invention is a rotor device attached to at least one aircraft wheel, said
SUBSTITUTE SHEET - la - rotor device adapted to rotate as airflow passes it during flight, thereby rotating said aircraft wheel.
In one form the rotor device comprises a plurality of
SUBSTITUTESHEET rotors .
Preferably each rotor device comprises a plurality of vanes.
Most preferably the vanes are arranged in an annulus concentric with the axis of rotation of the wheel.
In another form the rotor comprises a plurality of helical vanes.
The vanes may extend axially or radially from the wheel.
Preferably the rotor device is located on one side of the wheel.
The invention will now be described by way of non-limiting example with reference to the accompanying drawings in which:
Fig. 1 is a side view of an aircraft wheel and a rotation device of the present invention.
Fig. 2 is a cross sectional view of an aircraft wheel and the rotation device of Fig. 1.
Fig. 3 shows a plan view of another embodiment of the invention.
Fig. 4 shows a side view of the embodiment of Fig. 3.
Fig. 5 shows a plan view of a further embodiment of the invention.
Fig. 6 shows a side view of the embodiment of Fig. 5.
Figs. 6a and 6b show alternative blade shapes for use with the embodiments of Figs. 5 and 6.
Fig. 7 shows a further embodiment of the invention.
Fig. 8 shows a side view of the embodiment of Fig. 7.
Fig. 9 shows a cross section view along line AA of Fig. 8.
Fig. 10 shows an alternate vane for use in the embodiment of Figs. 7 and 8.
Fig. 11 shows a cross-section view along line BB of Fig. 10.
Figs. 1 and 2 depict a typical aircraft wheel 1 and tyre 2 arrangement with a rotor device 3 protruding from an axial end face of the wheel 1. The rotor device 3 comprises a plurality of helical vanes 4 which extend axially. In the present embodiment the rotor device 3 has four vanes 4, but more or less may be used, as desired. The vanes 4 are - 3 - arranged around the axis of rotation 5 of the wheel 1 and are equally spaced.
In use the wheel 1 is mounted on the aircraft such that the normal direction of travel when the aircraft is flying is indicated by arrow 6. Thus when the aircraft and wheel 1 travel in direction of travel 6, the wheel and rotor, when exposed to the airflow, are subjected to a relative airflow in the direction opposite to arrow 6. This occurs when the undercarriage is lowered fully or partially to the "landing position" When the aircraft has a fixed undercarriage the wheel is always exposed to the airflow. This relative airflow acts on the helical vanes 4 of the rotor device 3 and urges the rotor device 3 and the wheel 1 to rotate about axis 5 in the direction of arrow 7. When the aircraft is flying, such as when approaching a runway to land, the wheels 1 are free to rotate about axis 5 and so such rotation occurs. Hence on landing tyre peripheral velocity relative to the ground is reduced with a subsequent reduction in skidding and associated disadvantages.
Depending on the aircraft type, wheel arrangement, tyre diameter and rotor device size, the speed of rotation of the wheel 1 caused by the rotor device 3 prior to landing of the aircraft may result in the peripheral velocity of the tyre 2 being substantially equal to the landing speed. This will substantially eliminate skidding. However it is to be understood that the invention is not restricted to causing specific rotational speeds and includes generation of any rotation of the wheel of the aircraft.
Referring to figures 3 to 10 there are shown further embodiments of the invention, which all act similarly to the embodiment of figures 1 and 2.
Referring to figures 3 and 4, an aircraft wheel 11 has a tyre 12 mounted thereon and is adapted to rotate about axis 15. The wheel has on an axial end face 18 a rotor device 13. The rotor device 13 extends axially outwardly of the tyre 12 so as to extend into an airflow 9 passing the wheel. The rotor device has three vanes 14 which extend axially outward from the wheel, these vanes 14 being equally spaced about the axis of rotation 15. Each vane 14 has a curved shape which, as seen in Fig. 4, converges on the axis of rotation 15 in an anticlockwise direction. Thus airflow relative to the wheel in direction of arrow 9 will cause rotation about the axis 15 in direction of arrow 17.
Referring to figures 5 and 6 there is shown another embodiment. Again a wheel 21 adapted for rotation about an axis 25 has a tyre 22 mounted thereon. The wheel 21 has a rotation device 23 extending from an axial end face 28 to extend beyond the tyre 22 into an airflow 29.
The rotor device 23 comprises a series of curved blades 24 which extend away from the wheel 21 in the axial direction. The blades 24 are configured with their concave surfaces facing in a clockwise direction, as seen in Fig. 6. The blades 24 are arranged concentrically about axis 25 at a constant radius, but if desired two or more annuli of blades 24 may be used. As in the previous embodiments, a relative airflow in the direction of arrow 29 will urge the rotor device 23 and hence wheel 21 to rotate anticlockwise in the direction of arrow 27.
Figures 6a and 6b show alternate vane shapes for use with the embodiment of figures 5 and 6. Fig. 6a shows an end view of a v-shaped blade 30 while Fig. 6b shows an end view of a wide u-shaped blade 32. Both blades 30 and 32 are mounted so that their open mouths 31, 33, respectively, face clockwise, similarly to blades 24 of Fig. 6.
Referring to Figs. 7 and 8 there is shown a fourth embodiment of the invention. A wheel 41 adapted for rotation 45 is provided with a rotation device 43 on one axial end face 48. Again the rotation device 43 extends beyond the edge of the tyre 42 mounted on wheel 41 to be exposed to any airflow 49.
The rotation device comprises a plurality of cup shaped members 44, which in this embodiment the number of blades is 14. The members 44 are each the shape of a quarter sphere and have their open mouths facing in a clockwise direction such that airflow in direction of arrow 49 urges rotation in direction of arrow 47 about axis 45. The cup shaped members 44 are arranged in a single annulus about axis 45 but it is to be understood that the members 44 may be arranged in more - 5 - than one circle about axis 45.
Figures 10 and 11 show an alternate blade shape for use with the embodiment of Figs. 7 and 8. Instead of being cup-shaped, each blade exends out of the radial plane of the wheel at a constant angle and has side walls to define a cone-shaped opening. The mouth of the opening is arranged in the same direction to face clockwise as per the cup-shaped members 44.
In the above described embodiments the blades or vanes of the rotor device all extend axially from the wheel. It is to be understood that the vanes or blades may be configured to extend radially, next to the tyre, rather than axially. The use of the rotor device requires low maintenance as compared with pre-rotation being powered from within the aircraft.
In another not shown embodiment the aircraft wheel may have a rotor device protruding from each side.
In another not shown embodiment a rotor device attached to a first aircraft wheel may also rotate one or more further wheels which are rotatably connected to the first aircraft wheel by means of an axle.
In a further not shown embodiment the aircraft wheel may be axled in pairs or sets with the outside of the wheels having the rotor device protruding from them.
It is to be understood that the rotor device of the invention is not limited to the abovementioned embodiments can and be configured to suit the particular aircraft, its use and the environment it operates within.
In particular it is to be understood that the invention includes a separate rotor adapted for attachment to an aircraft wheel together with an aircraft wheel including an integral rotor device. The embodiments described above are therefore to be understood to relate to both integral and non-integral wheel/rotor configurations.
The advantage offered by the invention is that pre-rotation of wheels for the purposes of reducing tyre wear without having to power the pre-rotation of the wheel from within the aircraft.
It should be obvious to those skilled in the art that numerous variations and modifications could be made to the apparatus and method of the present invention as described and with reference to the illustrations without departing from the overall scope and spirit of the invention.

Claims

- 7 - CLAIMS :The claims defining the invention are as follows:
1. A rotor device adapted to be attached to an aircraft wheel, wherein when said aircraft is flying and said wheel is lowered or being lowered in position for .landing said rotor device and said wheel are caused to rotate about an axis of rotation due to air flow past said rotor device.
2. A rotor device attached to at least one aircraft wheel, said rotor device adapted to rotate as airflow passes it during flight, thereby rotating said aircraft wheel about an axis of rotatio .
3. The rotor device of claim 1 or claim 2 wherein in use the rotor is attached to an axial end face of the wheel.
4. The rotor device of any one of claims 1 to 3 comprising at least one vane or blade.
5. The rotor device of claim 4 wherein the at least one vane or blade extends axially from the wheel.
6. The rotor device of claim 4 wherein the at least one vane or blade extends radially from the wheel.
7. The rotor device of any one of claims 4 to 6 wherein the at least one vane or blade is arranged in an annulus concentric with the axis of rotation.
8. The rotor device of any one of claims 4 to 7 wherein the vanes or blades comprise cup shaped members.
9. The rotor device of any one of claims 1 to 7 wherein the at least one vane or blade comprises helicaly shaped members.
10. The rotor device of any one of claims 1 to 7 wherein the at least one vane or blade is curved.
11. A wheel for an aircraft, said wheel comprising at least one rotor device wherein when said aircraft is flying and said wheel is lowered or being lowered in position for landing said wheel are caused to rotate about an axis of rotation due to air flow past said rotor device.
12. A wheel assembly for an aircraft, said wheel assembly comprising a rotor device attached to a wheel thereto, wherein said rotor device is adapted to rotate when exposed to airflow passing said aircraft during flight thereby rotating said wheel about an axis of rotation.
13. The wheel or wheel assembly of claim 11 or claim 12 wherein the rotor is attached to an axial end face of the wheel. - -
14. The wheel or wheel assembly of any one of claims 11 to 13 comprising at least one vane or blade.
15. The wheel or wheel assembly of claim 14 wherein the at least one vane or blade extends axially from the wheel.
16. The wheel or wheel assembly of claim 14 wherein the at least one vane or blade extends radially from the wheel.
17. The wheel or wheel assembly of any one of claims 14 to 16 wherein the at least one vane or blade is arranged in an annulus concentric with the axis of rotation.
18. The wheel or wheel assembly of any one of claims 14 to 17 wherein the vanes or blades comprise cup shaped members.
19. The wheel or wheel assembly of any one of claims 11 to 17 wherein the at least one vane or blade comprises helicaly shaped members.
20. The wheel or wheel assembly of any one of claims 11 to 17 wherein the at least one vane or blade is curved.
21. A rotor device substantially as herein described with reference to the drawings.
22. A wheel or wheel assembly substantially as herein described with reference to the drawings.
PCT/AU1992/000094 1991-03-05 1992-03-05 Aircraft wheel prerotation apparatus WO1992015483A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
AUPK494791 1991-03-05
AUPK4947 1991-03-05

Publications (1)

Publication Number Publication Date
WO1992015483A1 true WO1992015483A1 (en) 1992-09-17

Family

ID=3775263

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/AU1992/000094 WO1992015483A1 (en) 1991-03-05 1992-03-05 Aircraft wheel prerotation apparatus

Country Status (1)

Country Link
WO (1) WO1992015483A1 (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2291844A (en) * 1994-08-03 1996-02-07 Jonathan Taylor Wheel rotating turbine means and a braking system for an aircraft undercarriage
GB2311264A (en) * 1996-03-22 1997-09-24 Paul William Toon Rotating undercarriage wheels prior to landing
GB2330561A (en) * 1997-10-24 1999-04-28 Muhammed Abdul Bashar Rotating undercarriage wheels prior to landing
GB2358162A (en) * 2000-01-15 2001-07-18 Steele Perkins Joanna Rotating aircraft wheels prior to landing
BE1013978A3 (en) * 2001-02-22 2003-01-14 Ridder Walter Renu De Airplane wheel, especially for folding landing gear, provided with scoops
ES2183672A1 (en) * 2000-02-02 2003-03-16 3 14 Era S L System for adjusting the speed of aircraft landing wheels
WO2004014727A1 (en) * 2002-08-05 2004-02-19 Martin Huete Jane Rim for aircraft landing gear wheels
RU212211U1 (en) * 2021-09-03 2022-07-12 Николай Владимирович Конев Aircraft Wheel Disk

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2363126A (en) * 1942-11-21 1944-11-21 Gibson Archic Charles Drive for landing gear wheels of airplanes
US2404018A (en) * 1944-03-23 1946-07-16 Bernard E Yaggy Airplane landing gear
US2408706A (en) * 1945-05-16 1946-10-01 Travis Henry Rotating means for airplane landing wheels
US2412406A (en) * 1944-07-10 1946-12-10 Kerezi Joseph Aircraft landing wheel
US2424941A (en) * 1944-08-02 1947-07-29 Rawley H Musser Wheel gear
US2464872A (en) * 1945-04-23 1949-03-22 George L Koval Wheel rotating device
US2666604A (en) * 1952-01-14 1954-01-19 Albert P Davis Retractable wind scoop
US3178135A (en) * 1963-12-30 1965-04-13 Berwyn C Moore Landing aircraft wheel rotator
US3233849A (en) * 1964-07-13 1966-02-08 Rubin Res Inc B Aircraft wheel accelerating means
US4615498A (en) * 1983-12-15 1986-10-07 Tsurunosuke Ochiai Wheel and tire for aircraft

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2363126A (en) * 1942-11-21 1944-11-21 Gibson Archic Charles Drive for landing gear wheels of airplanes
US2404018A (en) * 1944-03-23 1946-07-16 Bernard E Yaggy Airplane landing gear
US2412406A (en) * 1944-07-10 1946-12-10 Kerezi Joseph Aircraft landing wheel
US2424941A (en) * 1944-08-02 1947-07-29 Rawley H Musser Wheel gear
US2464872A (en) * 1945-04-23 1949-03-22 George L Koval Wheel rotating device
US2408706A (en) * 1945-05-16 1946-10-01 Travis Henry Rotating means for airplane landing wheels
US2666604A (en) * 1952-01-14 1954-01-19 Albert P Davis Retractable wind scoop
US3178135A (en) * 1963-12-30 1965-04-13 Berwyn C Moore Landing aircraft wheel rotator
US3233849A (en) * 1964-07-13 1966-02-08 Rubin Res Inc B Aircraft wheel accelerating means
US4615498A (en) * 1983-12-15 1986-10-07 Tsurunosuke Ochiai Wheel and tire for aircraft

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2291844A (en) * 1994-08-03 1996-02-07 Jonathan Taylor Wheel rotating turbine means and a braking system for an aircraft undercarriage
GB2311264A (en) * 1996-03-22 1997-09-24 Paul William Toon Rotating undercarriage wheels prior to landing
GB2330561A (en) * 1997-10-24 1999-04-28 Muhammed Abdul Bashar Rotating undercarriage wheels prior to landing
GB2358162A (en) * 2000-01-15 2001-07-18 Steele Perkins Joanna Rotating aircraft wheels prior to landing
ES2183672A1 (en) * 2000-02-02 2003-03-16 3 14 Era S L System for adjusting the speed of aircraft landing wheels
BE1013978A3 (en) * 2001-02-22 2003-01-14 Ridder Walter Renu De Airplane wheel, especially for folding landing gear, provided with scoops
WO2004014727A1 (en) * 2002-08-05 2004-02-19 Martin Huete Jane Rim for aircraft landing gear wheels
ES2246607A1 (en) * 2002-08-05 2006-02-16 Martin Huete Jane Rim for aircraft landing gear wheels
RU212211U1 (en) * 2021-09-03 2022-07-12 Николай Владимирович Конев Aircraft Wheel Disk

Similar Documents

Publication Publication Date Title
US4111601A (en) Adjustable windmill
JPH0362598B2 (en)
CA2132839A1 (en) Autogyro aircraft
GB1531511A (en) Rotary device driven by a moving fluid
GB2080217A (en) Improvements in or relating to aircraft undercarriage wheels
WO1992015483A1 (en) Aircraft wheel prerotation apparatus
US4335537A (en) Toy aircraft
US4061294A (en) Aircraft wheel rotator
US2370316A (en) Airplane wheel
US4161370A (en) Windmill
US5165624A (en) Apparatus for prerotating aircraft wheels employing forced air and a vacuum
WO1988000556A1 (en) A vtol aircraft and components
US5417387A (en) Aircraft landing wheel rotator
US20040065771A1 (en) Aircraft wheels having vanes
US2424941A (en) Wheel gear
US2369049A (en) Rotary wing aircraft
US20150021435A1 (en) Apparatus for causing an aircraft wheel to rotate
US2372207A (en) Airplane landing gear
US1829500A (en) Landing wheel
US3603700A (en) Rotating circular wing
US4150914A (en) Propeller blades
US2442441A (en) Air deflector
JP2002104293A (en) Lift producing device by continuously rotating impeller
US2377280A (en) Aircraft landing wheel
US2377638A (en) Aircraft landing wheel turbine

Legal Events

Date Code Title Description
AK Designated states

Kind code of ref document: A1

Designated state(s): AT AU BB BG BR CA CH CS DE DK ES FI GB HU JP KP KR LK LU MG MN MW NL NO PL RO RU SD SE US

AL Designated countries for regional patents

Kind code of ref document: A1

Designated state(s): AT BE BF BJ CF CG CH CI CM DE DK ES FR GA GB GN GR IT LU MC ML MR NL SE SN TD TG

NENP Non-entry into the national phase

Ref country code: CA

REG Reference to national code

Ref country code: DE

Ref legal event code: 8642