Abstract: An embodiment of the invention may include a memory structure. The memory structure may include a first terminal connected to a first contact. The memory structure may include a second terminal connected to a second contact and a third contact. The memory structure may include a multi-level nonvolatile electrochemical cell having a variable resistance channel and a programming gate. The memory structure may include the first contact and second contact connected to the variable resistance channel. The memory structure may include the third contact is connected to the programming gate. This may enable decoupled read-write operations of the device.

Abstract: The present disclosure provides technologies for treatment and/or prevention of cancer and metastatic tumors. For example, in some embodiments, a biomaterial (e.g., polymeric biomaterial) or scaffold that can stimulate innate immunity is administered in the absence of an immunomodulatory payload to a target site in a subject following tumor removal (e.g., by surgical resection). Such technologies can reduce or inhibit incidence of tumor regrowth and/or metastasis.

Abstract: Method, systems, crosspoint arrays, and systems for tuning a neural network. A crosspoint array includes: a set of conductive rows, a set of conductive columns intersecting the set of conductive rows to form a plurality of crosspoints, a circuit element coupled to each of the plurality of crosspoints configured to store a weight of the neural network, a voltage source associated with each conductive row, a first integrator attached at the end of at least one of the conductive column, and a first variable resistor attached to the integrator and the end of the at least one conductive column.

Abstract: A motor driven propulsor of an aircraft includes magnets disposed in fan shrouds of fan blades connected with a fan hub, a stator having individual conductive coils in a nacelle located radially outside of the fan hub, and a distributed inverter assembly having several inverter power stages and gate drivers, each of the inverter power stages coupled with a separate gate driver of the gate drivers and a separate coil of the coils in the stator. Each of the gate drivers is configured to individually control supply of direct current to the corresponding inverter power stage. Each of the inverter power stages is configured to convert the direct current supplied to the inverter power stage to an alternating current that is supplied to the corresponding coil in the stator to rotate the magnets and the fan blades around a center line of the fan hub for propelling the aircraft.

Abstract: An atomizing spray nozzle device includes an atomizing zone housing that receives different phases of materials used to form a coating. The atomizing zone housing mixes the different phases of the materials into a two-phase mixture of ceramic-liquid droplets in a carrier gas. The device also includes a plenum housing fluidly coupled with the atomizing housing and extending from the atomizing housing to a delivery end. The plenum housing includes an interior plenum that receives the two-phase mixture of ceramic-liquid droplets in the carrier gas from the atomizing zone housing. The device also includes one or more delivery nozzles fluidly coupled with the plenum chamber. The delivery nozzles provide outlets from which the two-phase mixture of ceramic-liquid droplets in the carrier gas is delivered onto one or more surfaces of a target object as the coating on the target object.

Abstract: An atomizing spray nozzle device includes an atomizing zone housing that receives different phases of materials used to form a coating. The atomizing zone housing mixes the different phases of the materials into a two-phase mixture of ceramic-liquid droplets in a carrier gas. The device also includes a plenum housing fluidly coupled with the atomizing housing and extending from the atomizing housing to a delivery end. The plenum housing includes an interior plenum that receives the two-phase mixture of ceramic-liquid droplets in the carrier gas from the atomizing zone housing. The device also includes one or more delivery nozzles fluidly coupled with the plenum chamber. The delivery nozzles provide outlets from which the two-phase mixture of ceramic-liquid droplets in the carrier gas is delivered onto one or more surfaces of a target object as the coating on the target object.

Abstract: A propulsion system for an aircraft includes a turbomachine, a primary fan, and an electric machine. The turbomachine includes a first turbine and a second turbine, with at least one of the first turbine or second turbine operably connected to the electric machine and the second turbine driving the primary fan. The propulsion system additionally includes an auxiliary propulsor assembly configured to be mounted at a location away from the turbomachine and the primary fan. The electric machine is in electrical communication with the auxiliary propulsor assembly for transferring power with the auxiliary propulsor assembly during operation of the propulsion system.

Abstract: Provided are drug delivery compositions and devices useful for the treatment and/or prevention of cancer and metastatic tumors. For example, a drug delivery device is provided that comprises a biodegradable scaffold carrying one or more anti-cancer therapeutic agents that activate the innate immune system (e.g., STING agonists) and/or the adaptive immune system (e.g., anti-PD-1 antibodies). The compositions and devices may include a cytokine (e.g., IL-15 superagonist). The drug delivery device can be implanted in the void volume of a resected tumor to prevent tumor regrowth and tumor metastasis. Also provided are methods of making the drug delivery compositions and devices as well as kits containing materials to provide the compositions and devices.

Abstract: According to some embodiments, a lossless protection procedure may be applied to control distribution of a print geometry of an industrial asset item. For example, an item definition data store may contain electronic records defining a geometry of the industrial asset item. A signature identifier encoder platform may determine a unique signature identifier associated with the industrial asset item and modify the geometry of the industrial asset item to encode therein information about the unique signature identifier. In some cases, for example, this may be done by adjusting a scanning pattern of a fill region (e.g., stripe, checkerboard, etc.) or a support structure of the industrial asset item. An authentication platform may then receive, from a sensor (e.g., an X-ray), a measured characteristic parameter of an item to be authenticated and determine a signature identifier of the item (which can be used to authenticate the item).

Abstract: A use tracking razor assembly for tracking the number of times a razor has been used for shaving includes a razor handle that has an engagement thereon for releasably engaging a razor head for shaving. A dial is rotatably coupled to the engagement and the dial can be rotated by a user. The dial is sequentially rotated between a start position and an end position each time the razor head is employed for shaving. In this way the dial assists the user with keeping track of the number of times the razor head has been used.

Abstract: A motor driven propulsor of an aircraft includes magnets disposed in fan shrouds of fan blades connected with a fan hub, a stator having individual conductive coils in a nacelle located radially outside of the fan hub, and a distributed inverter assembly having several inverter power stages and gate drivers, each of the inverter power stages coupled with a separate gate driver of the gate drivers and a separate coil of the coils in the stator. Each of the gate drivers is configured to individually control supply of direct current to the corresponding inverter power stage. Each of the inverter power stages is configured to convert the direct current supplied to the inverter power stage to an alternating current that is supplied to the corresponding coil in the stator to rotate the magnets and the fan blades around a center line of the fan hub for propelling the aircraft.

Abstract: Provided are drug delivery compositions and devices useful for the treatment and/or prevention of cancer and metastatic tumors. For example, a drug delivery device is provided that comprises a biodegradable scaffold carrying one or more anti-cancer therapeutic agents that activate the innate immune system (e.g., STING agonists) and/or the adaptive immune system (e.g., anti-PD-1 antibodies). The compositions and devices may include a cytokine (e.g., IL-15 superagonist). The drug delivery device can be implanted in the void volume of a resected tumor to prevent tumor regrowth and tumor metastasis. Also provided are methods of making the drug delivery compositions and devices as well as kits containing materials to provide the compositions and devices.

Abstract: A processing unit, including a first circuit, and a first circuit element connected to the first circuit. The first circuit element is at least charged by the first circuit.

Abstract: A processing unit, including a first circuit part, and a capacitor connected to the first circuit part. The capacitor is charged or discharged by the first circuit part.

Abstract: The present invention provides circularized RNA and methods of making, purifying, and using same.

Abstract: A vertical injection punchthrough based metal oxide semiconductor (VIPMOS) device and method of manufacturing the same, include a control gate, an erase gate, a floating gate, and an active area where the control gate, the erase gate, and the floating gate are coplanar and perpendicular to the active area.

Abstract: Provided are drug delivery compositions and devices useful for the treatment and/or prevention of cancer and metastatic tumors. For example, a drug delivery composition and/or device is provided that comprises a biodegradable scaffold or biomaterial comprising one or more agents that inhibit one or more proinflammatory pathways, such as one or more immune responses mediated by a p38 mitogen-activated protein kinase (MAPK) pathway. In some embodiments, a drug delivery composition and/or device may further comprise one or more agents that activate the innate immune system (e.g., STING agonists) and/or the adaptive immune system (e.g., anti-PD-1 antibodies). In some embodiments, a drug delivery composition and/or device may include a cytokine (e.g., IL-15 superagonist). In some embodiments, a drug delivery composition and/or device can be administered to a tumor resection site (e.g., a void volume resulting from a tumor resection).

Abstract: Provided are drug delivery compositions and devices useful for the treatment and/or prevention of cancer and metastatic tumors. For example, a drug delivery device is provided that comprises a biodegradable scaffold carrying one or more anti-cancer therapeutic agents that activate the innate immune system (e.g., STING agonists) and/or the adaptive immune system (e.g., anti-PD-1 antibodies). The compositions and devices may include a cytokine (e.g., IL-15 superagonist). The drug delivery device can be implanted in the void volume of a resected tumor to prevent tumor regrowth and tumor metastasis. Also provided are methods of making the drug delivery compositions and devices as well as kits containing materials to provide the compositions and devices.

Abstract: An aircraft propulsor assembly includes a fan having a nacelle and plural fan blades radially disposed within the nacelle. The fan blades are configured to be rotated by torque generated by a turbine engine of an aircraft to generate thrust for propelling the aircraft. The assembly also includes an electric motor including a stator in the nacelle of the fan and a rotor in tips of two or more of the fan blades. The electric motor is configured to generate torque that also rotates the fan blades to generate thrust for propelling the aircraft. The assembly also includes a controller configured to reduce or prevent an increase in an operating temperature of the turbine engine of the aircraft by automatically supplanting at least some of the torque generated by the turbine engine with the torque generated by the electric motor.

Abstract: A motor driven propulsor of an aircraft includes magnets disposed in fan shrouds of fan blades connected with a fan hub, a stator having individual conductive coils in a nacelle located radially outside of the fan hub, and a distributed inverter assembly having several inverter power stages and gate drivers, each of the inverter power stages coupled with a separate gate driver of the gate drivers and a separate coil of the coils in the stator. Each of the gate drivers is configured to individually control supply of direct current to the corresponding inverter power stage. Each of the inverter power stages is configured to convert the direct current supplied to the inverter power stage to an alternating current that is supplied to the corresponding coil in the stator to rotate the magnets and the fan blades around a center line of the fan hub for propelling the aircraft.