Abstract: A hub assembly for a ducted-rotor aircraft includes a plurality of stator supports, a first integral fitting that attaches to first ends of the stator supports, and a second integral fitting that attaches to second ends of the stator supports. The first fitting includes a plurality of motor attachment portions configured to locate and support a motor of the ducted-rotor aircraft, a plurality of fairing mounts configured to support attachment of an aerodynamic fairing to the hub assembly, and a plurality of stator locators configured to locate respective ones of the plurality of stator supports for attachment to the hub assembly. The first fitting has a body portion with an annular wall that supports the motor attachment portions, the fairing mounts, and the stator locators. The first fitting may be fabricated as a monolith that includes the body portion, motor attachment portions, fairing mounts, and stator locators.

Abstract: A duct for a ducted-rotor aircraft may include internal structural components such as a spindle that is supported by a fuselage of the aircraft, first and second annular spars that are attached to an end of the spindle, a central hub that supports a motor of the aircraft, a plurality of stators that extend from the central hub to the second spar, and a plurality of ribs that are attached to the first spar and the second spar at respective opposed ends. The spindle may include an attachment interface to which the first and second spars are attached. The attachment interface may be disposed at the second end of the spindle. The attachment interface may define first and second arc-shaped planar surfaces to which the first and second spars, respectively, are attached.

Abstract: A duct for a ducted-rotor aircraft may include an internal structure and an aerodynamic exterior skin that is adhesively bonded to the internal structure. The skin may include a leading-edge portion disposed at an inlet of the duct and an inner portion disposed along an interior of the duct. The inner portion of the skin may be bonded to the internal structure with a first bondline of adhesive and the leading-edge portion of the skin may be bonded to the inner portion of the skin with a second bondline of adhesive. One or both of the first and second bondlines of adhesive may be of non-uniform thickness to take up tolerance stackups between the inner portion of the skin, the leading-edge portion of the skin, and the internal structure.

Abstract: A computer implemented preventative maintenance schedule can includes a plurality of predetermined maintenance intervals. A replaceable maintenance item may be initially assigned to an initially assigned maintenance interval. A performance data associated with the replaceable maintenance item may be measured and an estimated end of useful life may be determined based on the performance data. The estimated end of useful life is compared to the assigned maintenance interval and, if warranted, the assigned maintenance schedule is modified.

Abstract: The present invention relates to microbial compositions useful in treating and remediating wastewater, removing organic matter from the surfaces of post harvested fruits and vegetables, and decreasing post-harvest disease in fruit and vegetables.

Abstract: An annular spar for a ducted-rotor of an aircraft may be fabricated from composite material, such as carbon-fiber-reinforced plastic (CFRP). The spar may include an annular plate, a first circumferential flange that extends from an outer edge of the plate, and a second circumferential flange that extends from an inner edge of the plate. The first and second circumferential flanges may taper inwardly toward a center axis of the spar. The spar may be constructed of a plurality of layers of CFRP. One or more of the layers may be fabricated from a single ply of CFRP, and one or more other layers may be fabricated from a plurality of plies of CFRP. The spar may exhibit a coefficient of thermal expansion (CTE) that allows an associated tip gap to remain essentially constant throughout a range of operating temperatures.

Abstract: A device for detecting energy theft from a utility network configured to access energy data for utilities, generate energy results, identify an outlying utility in the energy results, access behavioral data, determine whether there is a likelihood of energy theft associated with the outlying utility, generate descriptive results from the behavioral data indicating the likelihood of energy theft, receive a response of whether the energy theft occurred, and refine operation of the detecting of energy theft of the device.

Abstract: Systems and approaches for interacting with industrial equipment are provided that include an interface having an input and an output, and a processor coupled to the interface. The processor is configured to link a uniform identification construct to a device and receive a request to access the uniform identification construct. The processor is further configured to translate the uniform identification construct into an internet protocol (IP) address and route the request to the device having the uniform identification construct according to the IP address via the output.

Abstract: Various implementations described herein are directed to a battery case assembly. In one implementation, the battery case assembly includes a plurality of structural beams and a chassis coupled to the plurality of structural beams. The plurality of structural beams of the battery case assembly is configured to be coupled to a portion of an aircraft frame.

Abstract: Devices, systems, and methods including a lubricating solution bath for a pump integrated into an ophthalmic surgical hand piece are provided. In some embodiments, an ophthalmic pump system includes a housing defining a cavity. The system includes a rotating element positioned within the cavity of the housing. The system includes a flexible tubular structure positioned within the housing adjacent to the rotating element such that rotation of the rotation element urges a fluid through the flexible tubular structure. The system includes a lubricating solution positioned within the cavity around the rotating element and at least a portion of the flexible tubular structure.

Abstract: Systems and approaches for interacting with industrial equipment are provided that include an interface having an input and an output, and a processor coupled to the interface. The processor is configured to link a uniform identification construct to a device and receive a request to access the uniform identification construct. The processor is further configured to translate the uniform identification construct into an internet protocol (IP) address and route the request to the device having the uniform identification construct according to the IP address via the output.

Abstract: A fluid degradation monitoring system may detect a replacement of a fluid of a machine. The fluid degradation monitoring system may determine, after detecting the replacement of the fluid, a first degradation estimate of the fluid using a first technique based on characteristics relating to an operation of the machine. The fluid degradation monitoring system may detect a transition in a value of a dielectric constant of the fluid from a first phase to a second phase. The fluid degradation monitoring system may determine, after detecting the transition in the value of the dielectric constant, a second degradation estimate of the fluid using a second technique based on characteristics relating to the fluid.

Abstract: In some examples, an aircraft comprises an airframe, a rotor system coupled to the airframe, and a vibration attenuation system. The rotor system is operable to exert a vibratory force on the airframe. The vibration attenuation system comprises two or more batteries and elastic devices. The two or more batteries are operable to supply power to the rotor system. The elastic devices coupled to the two or more batteries and the airframe. The elastic devices are configured to attenuate the vibratory force based on facilitating oscillation of the two or more batteries. In other examples, a method comprises coupling elastic devices to two or more batteries and an airframe of an aircraft. The elastic devices receiving a vibratory force via the airframe and attenuate the vibratory force based on facilitating oscillation of the two or more batteries.

Abstract: An aircraft has a ducted thruster. The ducted thruster includes a duct having an inner wall, a stator hub disposed within the duct, a first stator extending along a first longitudinal axis between the inner wall and the stator hub, and a second stator. The second stator extends along a second longitudinal axis between the inner wall and the stator hub. The second longitudinal axis is either (1) substantially perpendicular to the first longitudinal axis or (2) substantially parallel to the first longitudinal axis and offset from the first longitudinal axis.

Abstract: Ocular surgery may be performed by a variety of systems, processes, and techniques. In certain implementations, systems and processes for ocular surgery may include the ability to emulsify a lens in an eye using a modular hand-held system including a phacoemulsification unit detachably coupled to a pump unit and remove lens portions from the eye using suction provided by the pump unit. The system and the process may also include the ability to decouple the phacoemulsification unit from the pump unit, couple an irrigation-aspiration unit to the pump unit to form a second hand-held system, and remove material from the eye using suction provided by the pump unit.

Abstract: A ducted fan assembly has a central axis, a duct having an outer wall and an inner wall, a fan hub at least partially disposed on the central axis, a plurality of fan blades coupled to the fan hub, and a first stator. The first stator has a first end coupled to the inner wall, a second end coupled to the inner wall, and a hub interface disposed between the first end and the second end, wherein the hub interface is coupled to the fan hub.