Husky Injection Molding Systems Limited

Beta Air, LLC

Manon Danielle Belzile

Edward Joseph Jenko

Patrice Fabien Gaillard

John Knapp

Stephen Widdis

Paul Richard Blais

Patrice Fabien Dezon-Gaillard

Martin H Baumann

James Osborne Plumpton

Brian Esser

David L Churchill

Darrin Albert MacLeod

Abdeslam Bouti

Kyle B Clark

Riley Clinton Griffin

Daniel Hontheim

Chenjie Lin

Douglas Oliver Hall

Raffaelo Verna

Nathan Wiegman

Stefan Stuart Brecher

Paul R Blais

Darrin Macleod

A rotor for a motor of an electric aircraft is provided. The rotor includes a retention band surrounding a plurality of magnets. The retention band is designed to retain the magnets in their positions and provide a way for heat to dissipate from the magnets. The retention band may also reduce eddy currents found within the rotor. A method of manufacturing a rotor with a retention band is also provided.

Rotor for an electric aircraft motor and a method for manufacturing

An aircraft with an in-boom lift propulsor includes a fuselage, a boom with a recess in the upper surface, and a lift propulsor comprising of a motor assembly and a propulsive element. Motor on the aircraft is operated through an interaction between the motor's magnetic field and electric current in a wire winding to generate force on a shaft of the motor. The in-boom lift propulsor helps prevent damages to the motor assembly and the aircraft by absorbing torque from the rotor and absorbing moment from the mating flange, where the mating flange joins the motor assembly to the boom. The boom includes an access panel to service the motor assembly and invertor during maintenance.

System for a vertical takeoff and landing aircraft with an in-boom lift propulsor

In an aspect of the present disclosure is an electric aircraft motor with a fully welded rotor. The motor includes a stator and a rotor. The stator includes an inner cylindrical surface and an outer cylindrical surface. The rotor includes a cylindrical portion and spokes welded to the cylindrical portion. In another aspect of the present disclosure is a method for manufacturing a fully welded rotor.

Motor with a fully welded rotor for an electric aircraft and a method for manufacturing

A rotor for a motor of an electric aircraft is provided. The rotor may include a hub, which includes a plurality of magnets fixed to an inner surface of the hub that are configured to interact with a stator of the motor to rotate rotor. The rotor also includes redial spokes that extend from the hub and provide structural support to the rotor. The rotor may also include a hoop, which provides balance for rotor during operation of motor and may include an integrated fan that provides cooling to various components of the motor.

Rotor for an electric aircraft motor comprising a plurality of magnets

In an aspect this disclosure is directed at a propulsor assembly powered by a dual motor system. The aircraft may comprise a propulsor. The electric aircraft may also include a driveshaft that is mechanically coupled to the propulsor, wherein a driveshaft is configured to provide mechanical power to the propulsor. The aircraft includes a plurality of electric motors. The electric motors may be configured to impart rotational energy to the driveshaft. Wherein each electric motor includes a stator and a rotor. Each electric motor is selectively engaged to the driveshaft by a freewheel clutch.

Propulsor assembly powered by a dual motor system

An apparatus for an inertial separation of air in an electric aircraft, wherein the apparatus includes an intake duct configured to intake an airflow, an inertial air separator configured to separate the airflow into a clean airflow and a dirty airflow, a propulsor configured to intake the clean airflow, wherein the propulsor includes a stator and a rotor, and a heat exchanger configured to intake the dirty airflow.

Methods and apparatus for an inertial separation of air in an electric aircraft

Disclosed is a method of refilling a shooting pot cavity in a molding system, the method comprising: determining that a trigger event has occurred in the molding system; and coordinating a refill of the shooting pot cavity with the occurrence of the trigger event.

Shooting pot refill timing

In an aspect this disclosure is directed at a propulsor assembly powered by a dual motor system. The aircraft may comprise a propulsors. The electric aircraft may also include a driveshaft that is mechanically coupled to the propulsor, wherein a driveshaft is configured to provide mechanical power to the propulsor. The aircraft includes a plurality of electric motors. The electric motors may be configured to impart rotational energy to the driveshaft. Wherein each electric motor includes a stator and a rotor. Each electric motor is selectively engaged to the driveshaft by a freewheel clutch.

An aircraft with an in-boom lift propulsor includes a fuselage, a boom with a recess in the upper surface, and a lift propulsor comprising of a motor assembly and a propulsive element. Motor on the aircraft is operated through an interaction between the motor's magnetic field and electric current in a wire winding to generate force on a shaft of the motor. The in-boom lift propulsor helps prevent damages to the motor assembly and the aircraft by absorbing torque from the rotor and absorbing moment from the mating flange, where the mating flangejoins the motor assembly to the boom. The boom includes an access panel to service the motor assembly and invertor during maintenance.

An electrical propulsor motor includes a stator having a hollow cylinder with an inner cylindrical surface and an outer cylindrical surface, rotor incorporated in a hub of a propulsor and mounted to the stator, including a first cylindrical surface facing the inner cylindrical surface, where the inner cylindrical surface and first cylindrical surface form a first air gap, a second cylindrical surface facing the outer cylindrical surface, wherein the outer cylindrical surface and the second cylindrical surface form a second air gap, and a plurality of axial impeller vanes mounted to at least one of the first cylindrical surface and the second cylindrical surface and within at least one of the first air gap and the second air gap and positioned to force air through the at least one of the first air gap and the second air gap when the rotor rotates about the axis of rotation.

Integrated electric propulsion assembly

An electric propulsion assembly for an electric aircraft propulsor including an integrated stator assembly including a mandrel having an outer cylindrical surface, an inner cylindrical surface, an upper edge, and a lower edge, the mandrel includes a plurality of electrically insulating guide walls disposed on at least a portion of the outer cylindrical surface and at least a portion of the inner cylindrical surface, wherein the electrically insulating guide wall forms a path across the outer and inner cylindrical surfaces. Assembly includes a plurality of copper windings wound upon the mandrel, electrically insulating epoxy, wherein the epoxy envelops at least a portion of the plurality of copper windings, a first cylindrical surface facing the inner cylindrical surface including a permanent magnet array, a second cylindrical surface facing the outer cylindrical surface including a back iron and a void disposed between the first cylindrical surface and the second cylindrical surface.

Methods and systems for a stator with helical windings configured for use in electric aircraft motor

An integrated stator assembly incorporated in an electric motor including a rotor that includes a plurality of rotor magnets, each rotor magnet of the plurality of magnets having a polar axis running from a rotor magnet south pole to a rotor magnet north pole. The assembly comprising a mandrel of dielectric material, wherein the mandrel includes a first cylindrical surface coaxial to an axis of rotation of the rotor, an upper edge, and a lower edge. A plurality of electrically conductive stator windings wound upon the mandrel, each winding of the plurality of windings including a plurality of turns traversing the first cylindrical surface, wherein each turn of the plurality turns further comprises a first upper section disposed on the first cylindrical surface, wherein the first upper section intersects the upper edge of the mandrel, and the first upper section forms a first angle to the axis of rotation.

Disclosed is a method of adjusting a motion profile of a shooting pot plunger for use in a molding system, the shooting pot plunger slidably movable within a shooting pot cavity, the method comprising: sensing a characteristic at a predetermined location in an injection circuit of the molding system; determining that the sensed characteristic is outside of a threshold range; adjusting the motion profile of the shooting pot plunger to account for determining that the sensed characteristic is outside of the threshold range; and storing the adjusted motion profile in a memory.

Shooting pot plunger control

An apparatus and method of coupling and decoupling a valve stem to an actuator are disclosed. In one embodiment, the actuator includes a moveable member that is coupled to the valve stem. One of the valve stem and the moveable member is a male coupling portion and the other of the valve stem and moveable member is the female coupling portion. The male coupling portion is nested within the female coupling portion. A retaining pin retains the male coupling portion with respect to the female coupling portion.

Growing community of inventors

Fairfield, VT, United States of America

Manon Danielle Belzile