Abstract: In general, techniques are described by which to enable dedicated recovery modules for resolving issues with faulty applications. A server computing device comprising a memory and a. processor may perform various aspects of the techniques. The memory may store a faulty application indication identifying a faulty application of a plurality of applications hosted for distribution by the server computing device, where the faulty application has an issue occurring during execution of the faulty application by a user computing device. The processor may generate, based on the faulty application indication, a dedicated recovery module dial extends the faulty application, and output, to the user computing device, the dedicated recovery' module to resolve the issue occurring during execution of the faulty application.

Abstract: A computing device is described that includes one or more processors configured to receive a software development kit (SDK) bundle, wherein the SDK bundle comprises one or more SDK builds, package the SDK bundle into an SDK package configured to be installed on a device for access by one or more applications installed on the device, wherein each application is dependent upon an SDK build of the one or more SDK builds during runtime, and the software development kit package including the one or more software development kit builds, wherein each software development kit build from the one or more software development kit builds is configured to tun in a process on the device distinct from one or more processes in which the one or more applications run on the device.

Abstract: 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.

Abstract: In general, techniques are described by which to perform memory efficient patching for computing devices. A server computing device comprising a memory and a processor may be configured to perform the techniques. The memory may store first assets that form an unpatched application and second assets that form a patched application. The processor may virtualize the first assets to obtain a single first virtual asset and obtain a single second virtual asset that represents the second assets. The processor may obtain, based on differences between the single first virtual asset and the single second virtual asset, a patch identifying how to update the single first virtual asset to obtain the single second virtual asset. The processor may next segment the patch into a plurality of segments and output to a user computing device a single segment from the plurality of segments for individual application by the user computing device.

Abstract: 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.

Abstract: In general, techniques are described by which to perform memory efficient patching for computing devices. A server computing device comprising a memory and a processor may be configured to perform the techniques. The memory may store first assets that form an unpatched application and second assets that form a patched application. The processor may virtualize the first assets to obtain a single first virtual asset and obtain a single second virtual asset that represents the second assets. The processor may obtain, based on differences between the single first virtual asset and the single second virtual asset, a patch identifying how to update the single first virtual asset to obtain the single second virtual asset. The processor may next segment the patch into a plurality of segments and output to a user computing device a single segment from the plurality of segments for individual application by the user computing device.

Abstract: A system for battery management for a vehicle that includes at least a battery coupled to the vehicle, at least a sensor coupled to the battery, the sensor configured to detect an internal state datum of the battery, and transmit the internal state datum to a computing device, a computing device, the computing device configured to receive the internal state datum from the at least a sensor, generate an alert datum as a function of the internal state datum and an alert threshold, transmit the alert datum to a remote device, and a remote device communicatively connected to the vehicle, the remote device is configured to, receive the alert datum from the computing device, and display the alert datum.

Abstract: An electric vertical takeoff and landing aircraft including a teetering propulsor assembly is provided. Teetering propulsor assembly may include a propeller that includes a hub and blades. Hub of propeller may be mechanically connected to a teeter mechanism of propulsor assembly that may be configured to allow the propeller to pivot about a teeter axis relative to the electric aircraft. Thus, teeter mechanism allows for a rotational axis of propeller to move during teetering of propeller. Teeter mechanism may include one or more springs that reduce teetering or prevent teetering of the propulsor at certain rotational speeds of propeller.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: An electric vertical takeoff and landing aircraft including a teetering propulsor assembly is provided. Teetering propulsor assembly may include a propeller that includes a hub and blades. Hub of propeller may be mechanically connected to a teeter mechanism of propulsor assembly that may be configured to allow the propeller to pivot about a teeter axis relative to the electric aircraft. Thus, teeter mechanism allows for a rotational axis of propeller to move during teetering of propeller. Teeter mechanism may include one or more springs that reduce teetering or prevent teetering of the propulsor at certain rotational speeds of propeller.

Abstract: A system for battery management for a vehicle that includes at least a battery coupled to the vehicle, at least a sensor coupled to the battery, the sensor configured to detect an internal state datum of the battery, and transmit the internal state datum to a computing device, a computing device, the computing device configured to receive the internal state datum from the at least a sensor, generate an alert datum as a function of the internal state datum and an alert threshold, transmit the alert datum to a remote device, and a remote device communicatively connected to the vehicle, the remote device is configured to, receive the alert datum from the computing device, and display the alert datum.

Abstract: A system for battery management for a vehicle that includes at least a battery coupled to the vehicle, at least a sensor coupled to the battery, the sensor configured to detect an internal state datum of the battery, and transmit the internal state datum to a computing device, a computing device, the computing device configured to receive the internal state datum from the at least a sensor, generate an alert datum as a function of the internal state datum and an alert threshold, transmit the alert datum to a remote device, and a remote device communicatively connected to the vehicle, the remote device is configured to, receive the alert datum from the computing device, and display the alert datum.

Abstract: In an aspect, a system for vibration monitoring of an electric aircraft. A system include a propulsor. A system includes a sensor coupled to a propulsor. A sensor is configured to measure a vibration datum of a propulsor and transmit the vibration datum to a flight controller. A flight controller is configured to receive a vibration datum from a sensor. A flight controller is configured to generate a throttle datum as a function of a vibration datum. A flight controller is configured to transmit a throttle datum to a propulsor.

Abstract: In general, techniques are described by which to perform memory efficient patching for computing devices. A server computing device comprising a memory and a processor may be configured to perform the techniques. The memory may store first assets that form an unpatched application and second assets that form a patched application. The processor may virtualize the first assets to obtain a single first virtual asset and obtain a single second virtual asset that represents the second assets. The processor may obtain, based on differences between the single first virtual asset and the single second virtual asset, a patch identifying how to update the single first virtual asset to obtain the single second virtual asset. The processor may next segment the patch into a plurality of segments and output to a user computing device a single segment from the plurality of segments for individual application by the user computing device.

Abstract: Rotary motion sensing systems are well-suited for integration in a bearing system of a rotary aircraft to provide information about the operational state of the rotor blades of the aircraft. In some embodiments, sensors are positioned on lateral sides of an elastomeric bearing system and output signals which may be processed to calculate one or more rotor blade operational states. The operational states include, for example, flap angle, lead-lag angle, and pitch angle. In other embodiments, sensors may be distributed along at least a portion of the length of a rotor blade to detect deflection of the rotor blade or its impact with another object. The operational state of the rotor blades may be transmitted to the pilot and/or the flight control computer of the aircraft in order for corrective action to be taken and/or may be stored within a control box for later review.

Abstract: In a decentralised multi-user online virtual environment, object responsibility is efficiently allocated to a controlling peer. The virtual environment is divided into a plurality of cells, and control of each cell is allocated to a responsible peer. Each responsible peer participates in a distributed hash table (DHT) to effect integration of the cells to effect the virtual environment. When a communications and processing load on the responsible peer controlling a cell exceeds a threshold, a second peer creates and takes control responsibility for an object comprising a bounded interest management region covering a region of load. Within the bounded interest management region, objects are removed or de-associated from the associated cell and instead associated with the bounded interest management region.

Abstract: One embodiment of an electronic system includes a network having a first sensing device with a first address and a second sensing device with a second address. The first sensing device includes first sensors, a first processor, a first memory, and a first communications device. The first sensors include a first dry bulb temperature sensor, a first relative humidity sensor, and a first radiant energy sensor. The second sensing device includes a second sensor, a second processor, a second memory, and a second communications device. The second processor includes a program to use the second communications device to communicate the second address and data derived from the second sensor to the first communications device.

Abstract: One embodiment of the present patent application is a method of monitoring a rotating part. The method includes providing a shaft, a sensor, a processor, an energy storage device, and a transmitter. The method further includes mounting the sensor directly on the shaft and mounting said processor, said energy storage device, and said transmitter to rotate with said shaft. The method further includes rotating the shaft and waking the processor for a period of time and drawing energy to the processor from the energy storage device to provide the processor in an active mode during the period of time. The method also includes sampling the sensor during the period of time. It also includes returning the processor to sleep mode. The method also includes transmitting data derived from the sensor.