Abstract: A jump starter for charging or boosting a depleted or discharged battery, the jump starting device, including a rechargeable battery; a positive battery connector for connecting the jump starting device to a positive terminal of the battery; a negative battery connector for connecting the jump starting device to a negative terminal of the battery; a power switch for connecting the rechargeable battery to the depleted or discharged battery when connected to the jump starting device during charging operation of the depleted or discharged battery; a first detector for detecting presence of the depleted or discharged battery connected to the positive and negative battery connectors; and a second detector for detecting presence of the depleted or discharged battery connected to the positive and negative battery connectors.

Abstract: A portable jump starter and air compressor device, including a jump starter, air compressor, and/or vacuum cleaner. One or more of the jump starter, air compressor, and/or vacuum cleaner are powered a same or different one or more rechargeable batteries (e.g. one or more Li-ion batteries). The air compressor, for example, includes a piston/valve arrangement configured to allow a piston of the piston/valve arrangement to move in close proximity to a cylinder head of the cylinder of the air compressor.

Abstract: In an aspect, a system for monitoring a battery system in-flight. The system includes at least a battery pack and a pack monitoring unit (PMU) communicatively connected with a battery pack. The battery pack includes a plurality of battery packs. The PMU may include at least a sensor and a controller. At least a sensor is configured to detect battery datum. A controller is communicatively connected with at least a sensor. A controller is configured to receive battery datum, detect a significant event as a function of battery datum, and transmit the significant event to a remote device.

Abstract: Methods, systems, and devices for wireless communications are described. A user equipment (UE) may receive from a base station a measurement configuration signal comprising a measurement resource configuration associated with a cross-link interference signal strength measurement. The UE may perform the cross-link interference signal strength measurement for one or more UEs associated with one or more intra-frequency neighboring cells according to the measurement resource configuration, wherein the cross-link interference signal strength measurement is performed during an intra-frequency measurement gap. The UE may transmit a report of the cross-link interference signal strength measurement to the base station.

Abstract: There is provided an interface system for joining display modules to a framework structure. The interface system comprises a base structure and a holder structure, the holder structure can be attached to the framework, and the base structure can be attached to two or more of the display modules. The holder structure or the base structure are interfaced by a tiltable planar surface and a curved support structure so that the holder structure and base structre are moveable towards each other. A multiple of base structures can be joined via elongated members.

Abstract: In an aspect, a system for monitoring a battery system in-flight. The system includes at least a battery pack and a pack monitoring unit (PMU) communicatively connected with a battery pack. The battery pack includes a plurality of battery packs. The PMU may include at least a sensor and a controller. At least a sensor is configured to detect battery datum. A controller is communicatively connected with at least a sensor. A controller is configured to receive battery datum, detect a significant event as a function of battery datum, and transmit the significant event to a remote device.

Abstract: Systems, computer-implemented methods, and computer program products for planning of a cutting boundary for removal of a diseased region of an anatomy, such as a bone tumor. A cutting surface is placed relative to the diseased region in a virtual model. An optimization algorithm specifies an optimization criterion that minimizes an amount of healthy region to be removed by the cutting surface and initializes candidate solutions to influence characteristics of the cutting surface. The optimization algorithm identifies a candidate solution that satisfies the optimization criterion and modifies characteristics of the cutting surface based on the identified candidate solution. The cutting boundary is defined relative to diseased region in the virtual model based on the modified cutting surface. The cutting boundary can be registered to the anatomy for constraining operation of a surgical tool in response to interaction of the surgical tool with the registered cutting boundary.

Abstract: A method for communicating with a passenger making a journey in a vehicle is provided, the vehicle having a broadcast system for transmitting information to one or more passengers, the passenger having and operating a Portable Electronic Device (PED), the PED operable to receive information from the broadcast system of the vehicle and to display information content to the passenger; the method comprising transmitting information to the PED of one or more passengers within the vehicle; wherein the PED displays information content derived from the information transmitted to the PED. A communication system for performing the method and a vehicle comprising the communication system are also provided.

Abstract: A system for disconnecting a battery from an electric aircraft upon impact. The system includes an electric aircraft and a battery assembly electrically coupled to the electric aircraft. The battery assembly is configured to include at least a sensor. The at least a sensor is configured to detect impacts to the electric aircraft. The battery assembly is configured to include a connector. The connector attaches the battery assembly to the electric aircraft. The connector includes an electrically actuating disconnection mechanism. The battery assembly is configured to include a control circuit. The control circuit is electrically connected to the electrically actuating disconnection mechanism. The control circuit is configured to detect, using the at least a sensor, an impact to the aircraft. The control sensor disconnects the connector from the electric aircraft using the electrically actuating disconnection mechanism as a function of the detection of impacts to the electric aircraft.

Abstract: Provided in this disclosure are components and methods for diagnostic and communication for an electric aircraft. Components may include a diagnostic element connected to a flight component which may include a sensor and a diagnostic circuit. Component may detect a module datum, maintenance phenomenon, maintenance datum, and flight status. Flight status may be transmitted to a remote device accessible by a user.

Abstract: Systems, computer-implemented methods, and computer program products are provided for automated planning of a cutting boundary for removal of a diseased region of an anatomy, such as a bone tumor. A model is provided for the diseased region of the anatomy, and optionally, a healthy region of the anatomy. One or more cutting geometries are defined relative the diseased region. Algorithms are provided which enable automated optimization of characteristics (e.g., shape, size, position, orientation) of the cutting geometries relative to the diseased region in order to plan for complete removal of the diseased region, en bloc, while minimizing an amount of healthy region to be removed.

Abstract: In an aspect, a system for monitoring a battery system in-flight. The system includes at least a battery pack and a pack monitoring unit (PMU) communicatively connected with a battery pack. The battery pack includes a plurality of battery packs. The PMU may include at least a sensor and a controller. At least a sensor is configured to detect battery datum. A controller is communicatively connected with at least a sensor. A controller is configured to receive battery datum, detect a significant event as a function of battery datum, and transmit the significant event to a remote device.

Abstract: In an aspect of the present disclosure is a system for locking a battery for an electric aircraft, the system including a battery pack including a high voltage (HV) connection configured to electrically connect to the electric aircraft; and a lock attached to the battery pack and configured to electrically disconnect the battery pack from the electric aircraft when locked, wherein the lock is configured to only be unlocked manually.

Abstract: In an aspect of the present disclosure is a system for locking a battery for an electric aircraft, the system including a battery pack including a high voltage (HV) connection configured to electrically connect to the electric aircraft; and a lock attached to the battery pack and configured to electrically disconnect the battery pack from the electric aircraft when locked, wherein the lock is configured to only be unlocked manually.

Abstract: Certain aspects relate to a battery pack for an electric vehicle. Exemplary battery pack includes a first pouch cell and a vent configured to vent the ejecta from the first pouch cell. The first pouch cell includes at least an outer coating, at least a first pair of electrodes, at least a first pair of foil tabs electrically connected to the at least a first pair of electrodes, at least a first insulator layer located substantially between the at least a first pair of foil tabs, a first pouch substantially encompassing the at least a first pair of foil tabs and the at least a first insulator layer, and a first electrolyte within the first pouch. The battery pack is also configured to power at least a propulsor component.

Abstract: In an aspect, a system for monitoring a battery system in-flight. The system includes at least a battery pack and a pack monitoring unit (PMU) communicatively connected with a battery pack. The battery pack includes a plurality of battery packs. The PMU may include at least a sensor and a controller. At least a sensor is configured to detect battery datum. A controller is communicatively connected with at least a sensor. A controller is configured to receive battery datum, detect a significant event as a function of battery datum, and transmit the significant event to a remote device.

Abstract: Certain aspects relate to a battery pack for electric vertical take-off and landing aircraft. Exemplary battery pack includes a first pouch cell, a second pouch cell, at least a sensor, where the at least a sensor is configured to sense battery pack data and transmit the battery pack data to a data storage system, and a vent configured to vent the ejecta from the first pouch cell. In some embodiments, battery pack may be configured to power at least a propulsor component.

Abstract: A system for disconnecting a battery from an electric aircraft upon impact. The system includes an electric aircraft and a battery assembly electrically coupled to the electric aircraft. The battery assembly is configured to include at least a sensor. The at least a sensor is configured to detect impacts to the electric aircraft. The battery assembly is configured to include a connector. The connector attaches the battery assembly to the electric aircraft. The connector includes an electrically actuating disconnection mechanism. The battery assembly is configured to include a control circuit. The control circuit is electrically connected to the electrically actuating disconnection mechanism. The control circuit is configured to detect, using the at least a sensor, an impact to the aircraft. The control sensor disconnects the connector from the electric aircraft using the electrically actuating disconnection mechanism as a function of the detection of impacts to the electric aircraft.

Abstract: A system for a pouch cell casing configured for use in an electric aircraft includes at least a pouch cell. The at least a pouch cell includes at least a pair of cell tabs, a battery cell, a pouch substantially encompassing the battery cell and the at least a pair of cell tabs. The at least a pouch cell includes at least a first side, a cell casing configured to substantially encompass the at least a pouch cell and including a first face disposed parallel and adjacent to the at least a first side, a second face disposed perpendicular and affixed to the first face, and at least an opening disposed on the first face opposite and adjacent to the at least a first side.

Abstract: Certain aspects relate to a battery pack for electric vertical take-off and landing aircraft. Exemplary battery pack includes a first pouch cell, a second pouch cell, at least a sensor, where the at least a sensor is configured to sense battery pack data and transmit the battery pack data to a data storage system, and a vent configured to vent the ejecta from the first pouch cell. In some embodiments, battery pack may be configured to power at least a propulsor component.