Abstract: An apparatus for manufacturing a stator for an electric aircraft motor, wherein the apparatus includes at least a manufacturing device. The manufacturing device further includes at least a work-holding device configured to hold a first segment of teeth. The manufacturing device further includes at least a winding device configured to create a modular winding set in the first segment of teeth, wherein creating a modular winding set further include acquiring a continuous conductor and winding a continuous conducting coil upon each tooth of the plurality of teeth using the continuous conductor. The manufacturing device further includes at least an installation device configured to install a plurality of segment of teeth into the stator.

Abstract: An electric vertical takeoff and landing (eVTOL) aircraft lift motor is disclosed. The eVTOL aircraft lift motor includes a stator connected to the eVTOL motor and a rotor coaxial within the stator. The stator includes an inner cylindrical surface and an outer cylindrical surface coaxial about an axis. The rotor includes a rotor cylindrical surface defining the axis, an air gap formed by combining the rotor cylindrical surface with the inner cylindrical surface of the stator, a magnet array positioned opposite to and spaced from the inner cylindrical surface by the air gap. The eVTOL aircraft lift motor also includes a first fan connected to and configured to rotate with the rotor. In addition, in some embodiments, the first fan is connected to an axial end of the rotor. The first fan may include a base platform, a roof platform, and a blade configured to direct air toward the air gap.

Abstract: A system for rolling landing gear is illustrated. System includes a skid component attached to an aircraft and comprising at least a skid tube oriented laterally to a longitudinal axis of the aircraft. System also includes at least a wheel journaled on a rotational fulcrum and at least a biasing means attaching the rotational fulcrum to the skid tube, wherein the biasing means comprises at least a leaf spring and exerts a recoil force resisting upward displacement of the rotational fulcrum with respect to the skid tube.

Abstract: A power source assembly for an electric eVTOL aircraft comprising a battery pack. The battery pack further comprising an end panel, a plurality of high energy density battery modules, wherein each module comprises a plurality of battery units, further comprising a plurality of battery cells electronically coupled together, a cell retainer disposed in a predetermined arrangement comprising two columns, a protective wrapping of thermally insulating material woven between columns of battery units, and a terminal electronically disposed on the end panel electronically connected to each of the plurality of high energy density battery modules.

Abstract: In an aspect of the present disclosure is an electric aircraft lift motor with air cooling, the motor including a stator connected to the electric aircraft, the stator including: an inner cylindrical surface and an outer cylindrical surface, wherein each of the inner cylindrical surface and the outer cylindrical surface is coaxial about an axis of rotation; and a rotor coaxial within the stator, the rotor including a rotor cylindrical surface, wherein the rotor cylindrical surface and the inner cylindrical surface combine to form an air gap between the rotor cylindrical surface and the inner cylindrical surface; and a first fan connected to an axial end of the rotor and configured to rotate with the rotor, the first fan comprising at least a blade configured to direct air toward the air gap.

Abstract: In an aspect of the present disclosure is an electric aircraft lift motor with air cooling, the motor including a stator connected to the electric aircraft, the stator including: an inner cylindrical surface and an outer cylindrical surface, wherein each of the inner cylindrical surface and the outer cylindrical surface is coaxial about an axis of rotation; and a rotor coaxial within the stator, the rotor including a rotor cylindrical surface, wherein the rotor cylindrical surface and the inner cylindrical surface combine to form an air gap between the rotor cylindrical surface and the inner cylindrical surface; and a first fan connected to an axial end of the rotor and configured to rotate with the rotor, the first fan comprising at least a blade configured to direct air toward the air gap.

Abstract: A power source assembly for an electric eVTOL aircraft comprising a battery pack. The battery pack further comprising an end panel, a plurality of high energy density battery modules, wherein each module comprises a plurality of battery units, further comprising a plurality of battery cells electronically coupled together, a cell retainer disposed in a predetermined arrangement comprising two columns, a protective wrapping of thermally insulating material woven between columns of battery units, and a terminal electronically disposed on the end panel electronically connected to each of the plurality of high energy density battery modules.

Abstract: A high energy density battery module may comprise a plurality of battery units. The battery units may be electronically coupled to at least one other battery unit and may further comprise a plurality of electrochemical battery cells. The battery units may comprise a cell retainer to fix cells in a predetermined arrangement comprising a first and second column of battery cells. The battery units may comprise protective wrapping of thermally insulating material woven between at least a portion of the first and second column of battery cells. An electrical contact may be may be disposed in or on each of the plurality of battery units.

Abstract: A system for rapid securement and disengagement of a battery assembly-type power source element is provided herein. The system can include a battery assembly that includes a battery element having opposite, opposing surfaces and configured to provide power to at least a portion of a vehicle. On the surface of the battery assembly a pin element can be disposed. The system also includes a receiver assembly configured to mechanically couple the battery assembly. The receiver assembly can include an insertion opening having a size configured to receive the battery assembly and a hook assembly. The hook assembly can include a hook configured to mechanically couple to the pin element of the battery assembly and shaft configured to drive the hook such that a distance between the insertion opening and the battery assembly is changed.

Abstract: A system for rolling landing gear is illustrated. System includes a skid component attached to an aircraft and comprising at least a skid tube oriented laterally to a longitudinal axis of the aircraft. System also includes at least a wheel journaled on a rotational fulcrum and at least a biasing means attaching the rotational fulcrum to the skid tube, wherein the biasing means comprises at least a leaf spring and exerts a recoil force resisting upward displacement of the rotational fulcrum with respect to the skid tube.

Abstract: A power source assembly for an electric eVTOL aircraft comprising a battery pack. The battery pack further comprising an end panel, a plurality of high energy density battery modules, wherein each module comprises a plurality of battery units, further comprising a plurality of battery cells electronically coupled together, a cell retainer disposed in a predetermined arrangement comprising two columns, a protective wrapping of thermally insulating material woven between columns of battery units, and a terminal electronically disposed on the end panel electronically connected to each of the plurality of high energy density battery modules.

Abstract: A high energy density battery module may comprise a plurality of battery units. The battery units may be electronically coupled to at least one other battery unit and may further comprise a plurality of electrochemical battery cells. The battery units may comprise a cell retainer to fix cells in a predetermined arrangement comprising a first and second column of battery cells. The battery units may comprise protective wrapping of thermally insulating material woven between at least a portion of the first and second column of battery cells. An electrical contact may be may be disposed in or on each of the plurality of battery units.

Abstract: A system for rapid securement and disengagement of a battery assembly-type power source element is provided herein. The system can include a battery assembly that includes a battery element having opposite, opposing surfaces and configured to provide power to at least a portion of a vehicle. On the surface of the battery assembly a pin element can be disposed. The system also includes a receiver assembly configured to mechanically couple the battery assembly. The receiver assembly can include an insertion opening having a size configured to receive the battery assembly and a hook assembly. The hook assembly can include a hook configured to mechanically couple to the pin element of the battery assembly and shaft configured to drive the hook such that a distance between the insertion opening and the battery assembly is changed.

Abstract: A system for rolling landing gear includes a skid component attached to an aircraft, wherein the skid component further comprises a first skid tube oriented laterally to a longitudinal axis of the axis, a second skid tube oriented laterally to the longitudinal axis of the aircraft, wherein the second skid tube is parallel to the first skid tube, a first wheel journaled on a first rotational fulcrum, a second wheel journaled on a second rotational fulcrum, a first biasing means attaching the first rotational fulcrum to the first skid tube, and a second biasing means attaching the second rotational fulcrum to the second skid tube, wherein the first biasing means and second biasing means exert a recoil force resisting upward displacement of the first rotational fulcrum and second rotational fulcrum with respect to the first skid tube and second skid tube.

Abstract: A gyratory compactor apparatus adapted to interact with a mold that defines a mold axis is provided. The gyratory compactor apparatus includes a frame defining a frame axis, a pivoted support carried by the frame, and a mold-engaging device carried by the pivoted support and having a carriage plate spaced-apart from the pivoted support for receiving the mold. The carriage plate is movable relative to the frame axis by rotation of the pivoted support. At least one actuator is in engagement with the carriage plate for imparting translation to the carriage plate relative to the frame axis.

Abstract: Nuclear gauges, their components and method for assembly and adjustment of the same are provided. The nuclear gauges are used in measuring the density and/or moisture of construction-related materials. The nuclear gauge can include a gauge housing having a vertical cavity therethrough and at least one radiation detector located within the housing. The nuclear gauge can include a vertically moveable source rod and a radiation source operatively positioned within a distal end of the source rod.

Abstract: Nuclear gauges, their components and method for assembly and adjustment of the same are provided. The nuclear gauges are used in measuring the density and/or moisture of construction-related materials. The nuclear gauge can include a gauge housing having a vertical cavity therethrough and at least one radiation detector located within the housing. The nuclear gauge can include a vertically moveable source rod and a radiation source operatively positioned within a distal end of the source rod. The nuclear gauge can also include a radiation shield assembly.

Abstract: A method for calibrating a gyratory compactor apparatus is provided. The gyratory compactor apparatus is of the type being configured to compact and impart an orbital motion to a sample in a mold that defines a mold axis and includes at least one actuator for imparting lateral displacement of the mold relative to a longitudinal axis of the gyratory compactor apparatus. The method includes the steps of imparting lateral orbital displacement of the mold relative to the gyratory compactor apparatus by actuation of the at least one actuator to thereby define a gyratory angle between the gyratory compactor apparatus and the mold axis, measuring the gyratory angle, and determining adjustments to actuation of the at least one actuator based on the measured gyratory angle and a target angle. An associated apparatus and method for calibrating the apparatus are also included.

Abstract: A gyratory compactor apparatus adapted to interact with a mold that defines a mold axis is provided. The gyratory compactor apparatus includes a frame defining a frame axis and having a first mounting plate and a pivoted support carried by the frame and capable of rotation in at least a first and a second rotational degree of freedom. A mold-engaging device is carried by the pivoted support and includes a first carriage plate proximal the pivoted support and a spaced-apart second carriage plate that defines a space therebetween for receiving the mold. The second carriage plate has at least one clamping rod in communication with an actuator for translating the second carriage plate about the mold axis to thereby secure the mold in the space between the first and second carriage plates. An associated method is also provided.

Abstract: A gyratory compactor apparatus is provided that is adapted to interact with a mold that defines a mold axis. The gyratory compactor apparatus includes a frame that defines a frame axis and has a first mounting plate and a spaced-apart second mounting plate. A pivoted support is carried by the frame and capable of rotation in at least a first and a second rotational degree of freedom. A mold-engaging device is carried by the pivoted support and has a first carriage plate proximal the pivoted support and a second carriage plate axially spaced-apart from the pivoted support for receiving the mold therebetween. At least one actuator having a first end is carried by the frame and a second end is carried by the second carriage plate for imparting lateral translation to the second carriage plate relative to the frame axis. An associated method is also provided.