Borealis Technical Limited

Other

Boreaiis Technical Limited

Jonathan Sidney Edelson

Isaiah Watas Cox

Rodney Thomas Cox

Robert M Sweet

Neal Gilleran

Avto Tavkhelidze

Hans Juergen Walitzki

Joseph J Cox

Stuart Harbron

Jan Vana

Scott Perkins

Nechama Cox

Yonatan Rotenberg

John Hanson

Maynard Leo Stangeland

Brian Von Herzen

Joseph M Fine

Donald Henry Morris

Joseph Jeremiah Cox

Rochel Geller

Robert Lincoln Carman, Jr

Wayne Boyer Collier

Michael J Hinton

Peter Vanderwicken

John D Birge

Isaiah Wates Cox

Daniel Liviu Barbalata

Nicholas Paul Ward

Arlie Stonestreet

A stator core design and motor winding method maximizing slot fill are provided. A stator core ring section and open U-shaped slot elements are each formed of multiple layers of lamination steel. Laminations forming the slots have a U-shaped profile corresponding to that of the slots. A straight portion of each lamination adjacent to the slot opening is folded to form stator teeth. Laminations forming the ring section and the slots may have a uniform or variable axial thicknesses and materials. A movable jig configures conducting wire and insulating material into a desired configuration for insertion into the open slots, fills each slot with the wire and insulating material, and partially crimps the open end of the filled slot, leaving an opening. When all slots are filled, the stator core is compressed to a final diameter, inserted into a ring-shaped stator element, and sealed to form a complete stator assembly.

Motor design and winding method

Reduced and low work function materials capable of optimizing electron emission performance in a range of vacuum and nanoscale electronic devices and processes and a method for reducing work function and producing reduced and low work function materials are described. The reduced and low work function materials advantageously may be made from single crystal materials, preferably metals, and from amorphous materials with optimal thicknesses for the materials. A surface geometry is created that may significantly reduce work function and produce a reduced or low work function for the material. It is anticipated that low and ultra-low work function materials may be produced by the present invention and that these materials will have particular utility in the optimization of electron emissions in a wide range of vacuum microelectronics and other nanoscale electronics and processes.

Low work function materials

A powered clutch assembly is provided for an aircraft landing gear or other vehicle wheel drive system equipped with wheel drive motors controllable to move the aircraft or vehicle during ground travel. Electric power for the clutch assembly is transferred to clutch actuation elements by a rotary power transfer assembly mounted between stationary and rotating elements within the landing gear wheel drive system to clutch actuation elements. Actuation elements are powered to securely lock clutch rotating elements when required to improve the reliability of failsafe operation of the clutch assembly when torque should not be transferred and to unlock clutch rotating elements when torque should be transferred when the landing gear wheel drive system is used to drive the aircraft during ground travel. Power transferred from the rotary power transfer assembly may also be used to operate components associated with the aircraft drive wheel other than the powered clutch assembly.

Powered clutch for aircraft wheel drive system

A method is provided that enhances wheel drive assembly acceleration, heat reduction, and energy efficiency performance during ground travel in aircraft equipped with landing gear wheel-mounted drive assemblies to move aircraft on the ground without reliance on the aircraft's engines or external tow vehicles. Inflation pressure levels of tyres on the landing gear wheels are monitored with pressure and/or temperature sensors to determine and maintain an optimum defined high inflation pressure level for the specific kind of aircraft tyre or the aircraft. A clutch-activated drive assembly may be prevented from transferring torque and driving the aircraft when the optimum high inflation pressure levels are not present in the tyres during ground travel. Tyre pressures may be manually or automatically adjusted in response to processed sensor information to maintain the optimum high inflation pressure level in all tyres as the aircraft is driven with the drive assemblies or with engine thrust.

Method for using aircraft wheel tyre pressure to improve aircraft energy efficiency and drive system performance

A wobble gear system is provided with an arrangement of gear elements that permits a motive input to drive planet gear elements to increase the gear reduction ratio while maximizing efficiency of the wobble gear system. The wobble gear system may have eccentrically rotating or oscillating wobble elements including a wobble plate and compound planet gear elements that are non-collinear and may be driven by the motive input, increasing the realized gear ratio in a single stage without reducing efficiency. One wobble gear system embodiment may employ a plurality of ring-supported and driven compound planet gear elements with laterally offset non-collinear central axes to optimize eccentricity and enhance gear reduction ratios. The wobble gear system may be integrated with components of a vehicle drive wheel driven by an in-wheel motor to produce speeds and torques required to drive vehicles including automobiles and aircraft.

Wobble gear system

A method is provided for restoring mobility to an aircraft equipped with at least one self-propelled drive wheel powered by a driver when the aircraft has been rendered immobile as a result of one or more wheel tires adhering to and becoming stuck to tarmac or another ground surface. The method uses forces generated by the cooperative action of the wheel driver, the aircraft steering, and the aircraft braking system to release adherent tires of each set of main wheels and/or nose gear wheels by applying differential force to one set of wheels at a time to release any adherent tires so that the aircraft is able to move on the ground surface and travel in a desired direction at a desired speed.

Method of operating aircraft drive to move an aircraft under adverse ground conditions

An identification system and method are provided for aircraft equipped with electric taxi systems for autonomous ground movement that enables airport ground personnel and others outside the aircraft to safely and easily identify the aircraft moving on ground surfaces at an airport as equipped with a pilot-controlled electric taxi system and to distinguish these aircraft from aircraft not moved by electric taxi systems. The identification system may be mounted with nose or main landing gear drive wheels supporting the electric taxi system. The identification system includes an identifying lighting system with lighting elements of a selected number, shape, color, or arrangement positioned on at least a visible face of one or more landing gear wheels. Automatic or manual controls may actuate the identification system to identify electric taxi system-equipped aircraft when the aircraft are moved with the electric taxi system or are stopped.

Aircraft landing gear drive wheel identification system

An electric connector assembly is provided that is designed to provide a simple and reliable electric connection between a source of electric power on an aircraft and a plurality of electrical connections, such as those from stator windings, in an electric drive means powering an aircraft landing gear drive wheel. The plurality of drive means electrical connections are individually connected to power distribution elements designed to significantly reduce the number of connectors required to establish an electrical connection between the drive means and an aircraft power supply. The reduced number of connectors is directed out of the wheel and guided along a path by a path guide element to a connector element designed to connect directly with a wire harness or other connection with an aircraft source of electric power. This electric connector design facilitates disconnection and reconnection when removal and remounting of the drive wheel is required.

Electric power connector for aircraft drive wheel drive system

A compact in-wheel vehicle motor and gearing system designed to meet high power and torque requirements for driving a vehicle on the ground independently of other power sources is provided. The motor and gearing system includes a motor assembly with an outside rotor element mounted for rotation about an inside stator element and a gear assembly with a plurality of gear stages mounted inside the stator and drivingly connected to the motor assembly. The motor assembly and gear assembly are mounted interiorly of the wheel and completely within a space defined by the internal dimensions of the wheel. This motor and gearing system can be effectively installed in an existing aircraft wheel without changes to other components to produce a drive wheel with the torque and power required to move the aircraft independently on the ground.

Motor and gearing system for aircraft wheel

A system is provided for dissipating heat in an onboard non-engine powered aircraft wheel drive assembly with drive means that power one or more aircraft wheels to drive the aircraft autonomously on the ground without directly using the aircraft engines. The heat dissipation system is integral with a wheel drive assembly mounted substantially completely within a nose or main landing gear wheel. A reservoir mounted outboard or inboard of the wheel drive assembly increases thermal distribution mass and fluidically communicates with wheel drive assembly components to automatically circulate heat transfer fluid between the wheel drive assembly and the reservoir when the operating temperature exceeds a predetermined maximum temperature during aircraft ground travel. The heat dissipating system can be retrofitted in an existing aircraft to improve thermal distribution and prolong wheel drive assembly and drive means operation and useful life.

Heat dissipation system for aircraft drive wheel drive assembly

A wheel testing system and method are provided that simulates realistically conditions likely to be encountered during operation of vehicle wheels, especially powered drive wheels and wheel-connected structures. The system may include an integral support frame designed to adjustably mount wheels or wheel-connected structures to be tested, a load motor drivingly connected to an inertial load, and an adjustable mounting sled configured to adjustably mount a test wheel or a wheel-connected structure with an hydraulic system actuatable to adjust the location of the test wheel relative to the inertial load to vary or fix the load on the test wheel desired. Speed of the test wheel can be varied or fixed by controlling the speed of the load motor. System measurement and data collection electronics measure a range of selected wheel parameters and gather data for transmission to a processor or non-transitory storage medium for processing and evaluation.

Active resistance dynamometer for wheel testing

A sprag clutch assembly for an aircraft drive wheel drive system capable of moving an aircraft autonomously on the ground in both forward and reverse directions is provided. The clutch is mounted within an aircraft drive wheel to be operatively engaged to control drive means braking torque when the aircraft is driven in a forward or reverse direction. The clutch assembly includes a plurality of pivoted sprag elements activatable to transmit torque and configured so that ratcheting occurs only when the aircraft drive wheel is driven in a forward direction and a braking torque is applied when the aircraft drive wheel is driven in reverse when the relative speed of the drive system is slower than the drive wheel speed, thereby permitting the drive system drive motor to function as a brake when the clutch assembly is engaged and the aircraft is reversing.

Sprag clutch assembly for aircraft drive wheel drive system

A traction control system and method are provided for an aircraft equipped with a ground travel drive system with drive wheels powered by onboard wheel drive means that are capable of translating torque through the aircraft drive wheels and that are automatically controllable to control traction without reliance on the aircraft's brakes to keep the aircraft moving efficiently and autonomously on the ground under a range of environmental conditions.

Aircraft ground travel traction control system and method

A drive system with harmonic drive designed to meet the high power and torque requirements required to drive an aircraft independently on the ground is provided. The drive system includes an electric motor driven by a harmonic drive assembly that may be configured to be integral with the motor. This drive system with harmonic drive can be effectively installed in an existing aircraft nose wheel or main wheel without changes to other components.

Growing community of inventors

Portland, OR, United States of America

Jonathan Sidney Edelson