Aircraft Wheel Rotating Device

An aircraft wheel rotating device comprising:

• a mounting plate;
• a plurality of holes positioned in the mounting plate, such that respective holes of the plurality of holes are alignable with bolts of a hub of a wheel rotationally attached to an axle of an aircraft, wherein the mounting plate is configured for mounting to the hub;
• a tubular housing attached by a first terminus to and extending axially from the mounting plate, the mounting plate being configured as a plurality of flanges, each flange of the plurality of flanges being attached to and extending radially from the first terminus of the tubular housing, a respective hole of the plurality of holes being positioned in each flange of the plurality of flanges;
• an endcap selectively attachable to the tubular housing for closing a second terminus of the tubular housing;
• a plurality of blades, each blade of the plurality of blades being rotationally attached to the tubular housing, wherein the plurality of blades is configured for engaging an airstream for rotating the wheel about the axle, the plurality of blades comprising from four to sixteen blades;
• a pitch adjustment module attached to and positioned within the tubular housing, the pitch adjustment module being operationally engaged to the plurality of blades, such that the pitch adjustment module is positioned for selectively adjusting a pitch of each blade of the plurality of blades for substantially matching a tangential speed of the wheel to a speed of the aircraft relative to the ground at landing, the pitch adjustment module comprising:
• a linear actuator attached to and axially positioned within the tubular housing,
• a plurality of support members, each support member of the plurality of support members being attached to and extending between the linear actuator and the tubular housing, such that the linear actuator is fixedly positioned in the tubular housing;
• a swashplate attached to the linear actuator, such that the linear actuator extends from the swashplate toward the first terminus of the tubular housing and such that the linear actuator is positioned for selectively motivating the swashplate within the tubular housing, and
• a plurality of pivot linkages, each pivot linkage of the plurality of pivot linkages being attached to and extending between the swashplate and a shaft of a respective blade of the plurality of blade, the pivot linkage being offset from an axis of rotation of the shaft, such that the linear actuator is positioned for selectively extending and retracting the pivot linkage concurrently with the swashplate for reversibly positioning the respective blade in a stowed configuration, wherein the respective blade is oriented substantially parallel planarly to the mounting plate, and a deployed configuration, wherein the respective blade is oriented for acting as an airfoil;
• a controller housing defining an interior space, the controller housing being attached to and positioned within the tubular housing, the controller housing being insulated, wherein the controller housing is configured for insulating the interior space from heat generated by a brake operationally engaged to the wheel;
• a microprocessor attached to controller housing, positioned in the interior space, and operationally engaged to the pitch adjustment module;
• a pair of electrical contacts attached to the controller housing and operationally engaged to the microprocessor, wherein the pair of electrical contacts is configured for operationally engaging the microprocessor to an electrical circuit of the aircraft;
• a tachometer attached to the controller housing, positioned in the interior space, and operationally engaged to the microprocessor, such that the tachometer is enabled for measuring rotations per minute of the wheel for communicating the rotations per minute to the microprocessor, enabling the microprocessor for calculating the tangential speed of the wheel;
• a receiver attached to the controller housing, positioned in the interior space, and operationally engaged to the microprocessor, the receiver being Global Positioning System enabled, wherein the receiver is configured for receiving positional coordinates of the aircraft and enabled for communicating the positional coordinates to the microprocessor, enabling the microprocessor for calculating the speed of the aircraft relative to the ground, for comparing the speed of the aircraft relative to the ground to the tangential speed of the wheel, and for selectively actuating the pitch adjustment module for adjusting the pitches of the blades of the plurality of blades for increasing or decreasing the tangential speed of the wheel to substantially match the speed of the aircraft relative to the ground;
• and
• an electromagnet attached to the controller housing, positioned in the interior space, and operationally engaged to the microprocessor, such that the microprocessor is enabled for selectively actuating the electromagnet for fixedly positioning the blades of the plurality of blades in the stowed configuration.

An aircraft wheel rotating system comprising:

• an aircraft comprising a wheel, a hub of the wheel being rotationally attached to an axle;
• a mounting plate bolted to the hub;
• a tubular housing attached by a first terminus to and extending axially from the mounting plate;
• a plurality of blades, each blade of the plurality of blades being rotationally attached to the tubular housing, wherein the plurality of blades is configured for engaging an airstream for rotating the wheel about the axle;
• and
• a pitch adjustment module attached to and positioned within the tubular housing, the pitch adjustment module being operationally engaged to the plurality of blades, such that the pitch adjustment module is positioned for selectively adjusting a pitch of each blade of the plurality of blades for substantially matching a tangential speed of the wheel to a speed of the aircraft relative to the ground at landing.