Borealis Technical Limited

Other

Methane Drainage Ventures

Robert M Sweet

Jonathan Sidney Edelson

Isaiah Watas Cox

Neal Gilleran

Rodney Thomas Cox

Scott Perkins

Carel J Brest Van Kempen

Anil Mahyera

Amber C Davidson

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 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 wheel design is provided for an aircraft landing gear wheel that is configured to maximize the space available within a landing gear wheel well to support a motor driver assembly that drives the aircraft wheel when the aircraft is on the ground. The wheel includes inboard and outboard support walls that are spaced apart a selected distance along the wheel axle so that the motor driver assembly components are substantially completely contained within the wheel space defined by the support walls. The preferred motor driver assembly includes an electric motor and a gear and clutch assembly operatively connected to the wheel to drive the wheel and move the aircraft on the ground. The wheel and motor driver assembly described herein may be retrofitted in an existing aircraft wheel without changing existing landing gear components, including tires, piston, and axle.

Wheel structure for integrating an electric drive motor

An integral motor and wheel assembly for aircraft landing gear is provided that includes an electric motor packaged within at least one gear wheel and configured to fit completely within the space provided in an existing aircraft for the landing gear components. The motor is positioned within the wheel to minimize the spin-up weight and to maximize the space within a given volume allocated for the motor. Installation of this motor and gear wheel assembly in an existing aircraft landing gear is designed to permit the continued use of existing landing gear components, including tires, axles, and pistons, so that the assembly can be easily retrofitted into existing aircraft.

Electric motor integrated with a wheel

An aircraft ground control system that moves an aircraft on the ground between landing and take off without external mechanical assistance from airport tugs or tow vehicles or reliance on thrust produced by the aircraft's engines is provided. The aircraft ground control system interfaces only with an aircraft auxiliary power unit or other aircraft power supply, but otherwise operates independently of aircraft systems. A system integrator and controller links cockpit controls designed to actuate the transmission of power to system components and to activate system components only under predetermined conditions with selectively activatable drivers in driving connection with one or more aircraft wheels to move the aircraft on the ground at selected torques and speeds.

Integrated aircraft ground navigation control system

A failsafe system and method for ensuring the safe operation of an aircraft with a ground movement system to drive the aircraft independently on the ground is provided. The system includes at least one aircraft nose or main drive wheel powered by an onboard wheel driver responsive to sensed aircraft and ground movement system operating parameters to continue operation in response to parameters within normal limits or to prevent continued operation if sensed parameters are outside normal limits and indicate continued operation to be unsafe. The onboard wheel driver includes a locking assembly responsive automatically or manually to signals indicating sensed parameters to lock the onboard wheel driver in an activated or an inactivated condition, depending on whether operation of the ground movement system can be continued safely.

System and method for failsafe operation of aircraft ground movement system

A split circumference wheel assembly is provided for an aircraft landing gear wheel configured to maximize the space available within a landing gear wheel well to support a motor driver assembly with drive means that drives the aircraft wheel on the ground. The split circumference wheel assembly includes separable inboard and outboard support walls that are spaced axially apart a maximized distance so that the motor driver assembly is completely contained within the maximized space defined. A preferred wheel assembly employs a demountable flange and a locking ring to integrally and removably support the motor driver assembly within the maximized wheel volume to drive one or more aircraft wheels and move the aircraft independently on the ground. The wheel and motor driver assembly described herein are designed to be retrofitted in an existing aircraft wheel.

Split circumference aircraft wheel assembly with integrated drive motor assembly

A wheel design is provided for an aircraft landing gear wheel that is configured to maximize the space available within a landing gear wheel well to support a geared motor assembly that drives the aircraft wheel when the aircraft is on the ground. The wheel includes inboard and outboard support walls that are spaced apart a selected distance along the wheel axle so that the geared motor assembly components are substantially completely contained within the wheel space defined by the support walls. The preferred motor driver assembly includes an electric motor and a gear and clutch assembly operatively connected to the wheel to drive the wheel and move the aircraft on the ground. The wheel and motor driver assembly described herein may be retrofitted in an existing aircraft wheel without changing existing landing gear components, including tires, piston, and axle.

Integrated electric motor and gear in an aircraft wheel

A gas-liquid-solids separation system for use with a drilling device includes a surge tank for holding drilling efflux comprising gas, liquid and solids, and adapted for mounting on a drilling device in a position for having a drill shaft extending therethrough. A stuffing box attached to a back side of the surge tank means and configured for enabling passage of the drill shaft therethrough prevents the drilling efflux from escaping the surge tank. A flange attached to the front side of the surge tank and aligned with the stuffing box for allowing passage of the drill shaft therethrough provides a seal between the surge tank and a borehole casing to enable the drilling efflux to flow into the surge tank means. An agitator disposed within the surge tank maintains suspension of the solids within the liquid, and a gas cyclone in fluid communication with the surge tank withdraws gas from the surge tank and separates any entrained liquid therefrom. The liquid and solids suspended therein are transferred to a slurry cyclone for separation and thereafter the liquid is stored in a tank for subsequent reuse as a cutting fluid.

Gas-liquid-solids separation system

A self-aligning stuffing box for use with a drilling device having a rotatable drill shaft includes a packing gland having an opening therethrough sized for passage of the rotatable drill shaft and includes packing rings for forming a seal between the packing gland and the drill shaft. A generally spherical exterior surface on the packing gland is supported by an interior spherical surface of a socket in a ball-and-socket like manner to enable the packing gland, packing rings and the rotatable drill shaft to pivot about the longitudinal axis of the rotatable drill shaft together. A frame slidably supports the socket and enables the socket, packing gland and packing ring means and rotatable drill shaft to be laterally displaced, with respect to the longitudinal axis of the drill shaft, as a single unit, in order to prevent damage to the packing rings by vibrational movement of the drill shaft during drilling.

Growing community of inventors

Beaver, UT, United States of America

Robert M Sweet