Magnetically induced aircraft landing wheel rotation

• US 20070284478A1
• Filed: 06/08/2006
• Published: 12/13/2007
• Est. Priority Date: 06/08/2006
• Status: Active Grant

• Current Assignee: Rod Soderberg
• Original Assignee: Rod Soderberg
• Inventors: Soderberg, Rod
• Granted Patent: US 7,594,626 B2
• Time in Patent Office: Days
• US Class Current: 244/103.R
• CPC Class Codes: B64C 25/36 Arrangements or adaptations of wheels, tyres or axles in general
• CPC Class Codes: B64C 25/405 Powered wheels, e.g. for taxing
• CPC Class Codes: B64C 25/42 Arrangement or adaptation of brakes
• CPC Class Codes: H02K 21/22 with magnets rotating around the armatures, e.g. flywheel magnetos
• CPC Class Codes: H02K 3/02 Windings characterised by the conductor material
• CPC Class Codes: H02K 49/00 Dynamo-electric clutches; Dynamo-electric brakes
• CPC Class Codes: H02K 7/102 with friction brakes
• CPC Class Codes: H02K 7/14 Structural association with mechanical loads, e.g. with hand-held machine tools or fans with fan or impeller for cooling the machine H02K9/06
• CPC Class Codes: Y02T 50/80 Energy efficient operational measures, e.g. ground operations or mission management

Abstract

An aircraft landing wheel assembly comprising a set of rotating components and a set of static components wherein an applied electrical current applied to conductive elements associated with one set of components gives rise to primary magnetic fields which interact with reactive magnetic fields associated with the other set of components whereby the interaction of magnetic field forces gives rise to rotational forces which act on the rotating components of said aircraft landing wheel assembly to induce controlled forward rotation of the landing wheel prior to contact with the runway and controlled retardation assistance as required during deceleration of the aircraft after touch down with the runway.

Claims

1. An aircraft landing wheel assembly such that an imposed electrical current in electrically conductive material gives rise to primary magnetic fields and such electrically conductive material is incorporated into at least one static component of the aircraft landing wheel assembly and brake assembly including their mounting structures such that the primary magnetic field forces interact with reactive magnetic field forces originating from material sustaining a magnetic field incorporated into rotating components of the aircraft landing wheel assembly, so as to induce rotational forces acting on rotating components creating controlled forward rotation of aircraft landing wheels prior to contact with a runway and controlled retardation assistance after touch down during deceleration of an aircraft.

2. The aircraft landing wheel assembly of claim 1 wherein a primary magnetic field is electrically induced in a disk shaped field winding otherwise known in electric motor theory as a stator winding incorporated into a static housing of a brake stack and reacts with an adjacent magnetic field created by a plurality of magnetic material formed into a disk shaped ring incorporated into an inner wheel rim in close proximity to the stator winding whereby an interaction of magnetic field forces creates rotational forces acting on rotating components of the aircraft landing wheel assembly.

3. The aircraft landing wheel assembly of claim 1 wherein a primary magnetic field is electrically induced in a disk shaped field winding otherwise known in electric motor theory as a stator winding incorporated into a static housing of a brake stack and reacts with an adjacent magnetic field created by magnetically soft material incorporated into rotating components in which a secondary magnetic field is induced by the primary magnetic field of the stator winding whereby an interaction of magnetic field forces creates rotational forces acting on rotating components of the aircraft landing wheel assembly.

4. The aircraft landing wheel assembly of claim 1 wherein a primary magnetic field is electrically induced within a cylindrical field winding incorporated into an inner static casing of a brake stack and an opposed reactive magnetic field is due to a plurality of magnetic material forming a cylinder incorporated into a wheel hub in close proximity to the primary magnetic field whereby interaction of magnetic field forces creates rotational forces acting on the rotating components of the aircraft landing wheel assembly.

5. The aircraft landing wheel assembly of claim 1 wherein a primary magnetic field is electrically induced within a cylindrical field winding incorporated into an inner static casing of a brake stack and an opposed reactive magnetic field is due to a plurality of magnetically soft material forming a cylinder incorporated into a wheel hub in close proximity to the primary magnetic field wherein induction of secondary magnetic fields results from the primary magnetic field whereby an interaction of magnetic field forces causes rotational forces acting on the rotating components of the aircraft landing wheel assembly.

6. The aircraft landing wheel assembly of claim 1 wherein a primary magnetic field is electrically induced in a series of field windings located around an outer perimeter of a brake actuating mechanism and said primary magnetic field reacts with a magnetic field created by a plurality of magnetic material which forms a cylindrical ring incorporated into an inner wheel rim in close proximity to the primary magnetic field whereby interaction of magnetic field forces gives rise to rotational forces acting on the rotating components of the aircraft landing wheel assembly.

7. The aircraft landing wheel assembly of claim 1 wherein a primary magnetic field is electrically induced in a series of field windings located around an outer perimeter of a brake actuating mechanism and said primary magnetic field reacts with a magnetic field created by a plurality of magnetically soft material which form a cylindrical ring incorporated into an inner wheel rim in close proximity to the primary magnetic field such that the primary magnetic field induces secondary reactive magnetic fields in the magnetically soft material whereby an interaction of magnetic field forces gives rise to rotational forces acting on the rotating components of the aircraft landing wheel assembly.

8. The aircraft landing wheel assembly of claim 1 wherein a primary magnetic field is electrically induced in a disk shaped field winding incorporated into at least one static component of a brake stack and housing comprising, stators of a brake stack providing friction braking, a brake stack housing axial end restraints, a brake stack housing and pushers of a brake stack housing whereby rotors providing friction braking in close proximity to said static component will have a plurality of magnetic material in the form of a disk ring incorporated into the rotors around a circumference in close proximity to the disk shaped field winding of the static component resulting in an interaction of magnetic field forces giving rise to rotational torque forces applied to rotating components of the aircraft landing wheel assembly.

9. The aircraft landing wheel assembly of claim 1 wherein a primary magnetic field is electrically induced in a disk shaped field winding incorporated into at least one static component of a brake stack and housing comprising, stators of a brake stack providing friction braking, a brake stack housing axial end restraints, a brake stack housing and pushers of a brake stack housing whereby rotors providing friction braking in close proximity to said static component will incorporate magnetically soft material in close proximity to the disk shaped field winding so as to act as secondary reactive magnetic field material in which magnetic field forces are induced by the primary magnetic field of a static component in close proximity whereby interacting magnetic field forces give rise to rotational forces acting on rotating components of the aircraft landing wheel assembly.

10. The aircraft landing wheel assembly of claim 1 wherein electrical control of components causing rotation and retardation forces within the aircraft landing wheel assembly is linked to micro processing equipment which is adapted for monitoring wheel rotation rate in relation to ground speed thereby having the ability to automatically adjust forward wheel rotation rate prior to landing and retardation assistance after landing.

11. The aircraft landing wheel assembly of claim 1 wherein an imposed electrical current which gives rise to primary magnetic fields is energized within a Synthetic Multifunctional Material which due to an imposed electrical current produces magnetic fields whereby primary magnetic field forces produced interact with reactive magnetic field forces created by magnetic fields within another Synthetic Multifunctional Material capable of maintaining a magnetic field thereby giving rise to rotational forces acting on rotating components of the aircraft landing wheel assembly due to an interaction of primary and reactive magnetic field forces.

12. An aircraft landing wheel assembly comprising a set of rotating components and a set of static components wherein static and rotating components are said to be alternate sets of components such that an applied electrical current applied to conductive material incorporated into at least one component of a set of components gives rise to primary magnetic fields which interact with reactive magnetic fields produced by material sustaining a magnetic field incorporated into at least one component of an alternate set of components whereby an interaction of magnetic field forces gives rise to rotational forces which act on rotating components of said aircraft landing wheel assembly to induce controlled forward rotation of landing wheels prior to contact with a runway and controlled retardation assistance during deceleration of an aircraft after touch down with a runway.

13. The aircraft landing wheel assembly of claim 12 wherein a primary magnetic field is electrically induced in electrically conductive material, incorporated into rotating components of the aircraft landing wheel assembly, and reacts with field forces resulting from material sustaining a magnetic field incorporated into static components of the aircraft landing wheel assembly which gives rise to interacting magnetic fields whereby an interaction of magnetic fields gives rise to rotational forces acting on rotating components of the aircraft landing wheel assembly.

14. The aircraft landing wheel assembly of claim 12 wherein electrically conductive material in which a primary magnetic field is induced comprises field windings of electrical conducting elements incorporated into at least one component of a set of components and said primary magnetic field interacts with magnetically soft material incorporated into at least one component of an alternate set of components of the aircraft landing wheel assembly causing induction of secondary magnetic fields resulting from the primary magnetic field whereby the interaction of these magnetic field forces gives rise to rotational forces acting on rotating components of the landing wheel assembly.

15. The aircraft landing wheel assembly of claim 12 wherein a primary magnetic field is electrically induced in a disk shaped field winding incorporated into at least one static component of a brake stack and housing comprising, stators of a brake stack providing friction braking, a brake stack housing axial end restraints, a brake stack housing and pushers of a brake stack while rotors providing friction braking in close proximity to the static component have a plurality of permanently magnetic material in the form of a disk ring incorporated into a rotor to form a ring of permanently magnetic material in close proximity to the disk shaped field winding whereby an interaction of rotational component magnetic fields with those of the primary magnetic field of the static components gives rise to rotational torque forces applied to rotating components of the landing wheel assembly.

16. The aircraft landing wheel assembly of claim 12 wherein a primary magnetic field is electrically induced in a disk shaped field winding incorporated into at least one static component of a brake stack and housing comprising, stators of a brake stack providing friction braking, a brake stack housing axial end restraints, a brake stack housing and pushers of a brake stack while rotors providing friction braking in close proximity to the static component incorporate magnetically soft material so as to act as secondary reactive magnetic field medium in which magnetic field forces are induced by the primary magnetic field of the static component in close proximity to said rotors whereby an interaction of magnetic field forces gives rise to rotational forces acting on rotating components of the aircraft landing wheel assembly.

17. The aircraft landing wheel assembly of claim 12 wherein electrical control of components causing rotational forces and retardation assistance of an aircraft landing wheel, are linked to micro processing equipment adapted for monitoring wheel rotation rate in relation to ground speed and thereby having the ability to automatically adjust forward wheel rotation rate prior to landing and retardation assistance during deceleration after landing.

18. An aircraft landing wheel assembly which includes static and rotating components of a strut support structure a mounting structure torque tube and axle, a brake stack, a brake stack housing a brake actuating mechanism, a wheel structure, and a wheel hub wherein a set of components are stationary components and another set of components are free to rotate whereby an imposed electrical current in electrically conductive material incorporated into one set of components gives rise to primary magnetic field forces which interact with reactive magnetic field forces electrically induced in components incorporated into an alternate set of components such that rotational forces are created within at least one of the rotating components of the aircraft landing wheel assembly, to create controlled forward rotation of aircraft landing wheels prior to contact with a runway and controlled retardation assistance during deceleration of an aircraft after landing.

19. The aircraft landing wheel assembly of claim 18 which contains a set of rotating components and a set of stationary components wherein a primary magnetic field is electrically induced in electrically conductive material which when electrically excited gives rise to magnetic field forces and is incorporated into at least one component of a stationary component set of the aircraft landing wheel assembly and interacts with magnetic field forces resulting from an imposed electrical current within conductive material incorporated into at least one component of an alternate set of rotational components of the aircraft landing wheel assembly whereby interacting magnetic field forces give rise to rotational torque forces acting on rotational components of the aircraft landing wheel assembly.

20. The aircraft landing wheel assembly of claim 18 wherein electrical control of components causing rotational forces and retardation assistance of the aircraft landing wheel assembly are linked to micro processing equipment adapted for monitoring wheel rotation rate in relation to ground speed thereby having the ability to automatically adjust forward wheel rotation rate prior to landing and retardation assistance during deceleration after landing.