Abstract: Apparatuses, systems, and techniques to indicate how to generate image-to-column transformations. In at least one embodiment, one or more circuits are to perform an application programming interface (API) to indicate how to generate one or more image-to-column transformations.

Abstract: Apparatuses, systems, and techniques to cause a first tensor to be translated into a second tensor according to a tensor map. In at least one embodiment, one or more circuits are to perform an application programming interface (API) to cause a first tensor to be translated into a second tensor according to a tensor map.

Abstract: Apparatuses, systems, and techniques to cause a first tensor to be translated into a second tensor according to a tensor map without storing information about a memory transaction corresponding to the translation. In at least one embodiment, one or more circuits are to perform an application programming interface (API) to cause a first tensor to be translated into a second tensor according to a tensor map without storing information about one or more memory transactions corresponding to the translation.

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: A system for flight control in electric aircraft includes a flight controller configured to provide an initial vehicle torque signal including a plurality of attitude commands. The system includes a mixer configured to receive the initial vehicle torque signal and a vehicle torque limit, receive prioritization data including a prioritization datum corresponding to each of the plurality of attitude command, determine a plurality of modified attitude commands as a function of the vehicle torque limit, the attitude commands, and the prioritization data, generate, as a function of modified attitude commands, an output torque command including the initial vehicle torque signal adjusted as a function of the vehicle torque limit, generate, as a function of the output torque command, a remaining vehicle torque. The system includes a display, wherein the display is configured to present, to a user, the remaining vehicle torque and the output torque command.

Abstract: An electric aircraft battery pack that includes an integrated battery management component, which determines if a power supply connection between the battery pack and the electric aircraft should be terminated due to a failure, defect, or malfunction of the battery pack, such as a failure of a battery module of the battery pack.

Abstract: A system for distributed pilot control of an aircraft includes a plurality of flight components, an aircraft control located within the aircraft, and an aircraft component attached to a flight component of the plurality of flight components, wherein the aircraft component is configured to receive, from a command sensor attached to the aircraft control, an aircraft command, obtain, from an attitude sensor, an aircraft orientation, receive, as a function of a notification unit, a pilot signal, and command the flight component to produce a response command as a function of the pilot signal.

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: An electric aircraft battery pack that includes an integrated battery management component, which determines if a power supply connection between the battery pack and the electric aircraft should be terminated due to a failure, defect, or malfunction of the battery pack, such as a failure of a battery module of the battery pack.

Abstract: A system for a distributed pilot control of an aircraft is disclosed. The system includes a plurality of flight components. The system also includes an aircraft control located within the aircraft. The system includes an aircraft component attached to a flight component of the plurality of flight components. The aircraft component is configured to receive, from a command sensor attached to the aircraft control, an aircraft command. The aircraft component is configured to obtain, from an attitude sensor, an aircraft orientation. The aircraft component is configured to receive, as a function of a notification unit, a pilot signal. The aircraft component is additionally configured to command the flight component to produce a response command as a function of the pilot signal.

Abstract: Aspects relate to methods and systems for reversionary flight control for an electrical vertical take-off and landing (eVTOL) aircraft. An exemplary system includes a pilot control, a sensor configured to sense and transmit analog control data associated with a pilot interaction with the pilot control, a pilot interface module configured to receive the analog control data, convert the analog control data to digital control data, and transmit digital control, an actuator, and a flight controller. The flight controller may be configured to receive the digital control data, determine a primary command datum as a function of the digital control data, transmit the primary command datum to the actuator, determine that the digital control signal is non-functional, receive the analog control data, determine a reversionary command datum as a function of the analog control data, and transmit the reversionary command datum to the actuator.

Abstract: In an aspect a system for fly-by-wire flight control configured for use in electric aircraft including at least a sensor, wherein the sensor is communicatively connected a pilot control and configured to detect a pilot input from the pilot control and generate, as a function of the pilot input, command datum. A system includes a flight controller, the flight controller including a computing device and configured to perform a voting algorithm, wherein performing the voting algorithm includes determining that the sensor is an allowed sensor, wherein determining that the sensor is an allowed sensor includes determining that the command datum is an active datum, determining the command datum is an admissible datum, generating, as a function of the command datum and the allowed sensor, a control surface datum wherein the control surface datum is correlated to the pilot input.

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, 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: A system for battery management for electric aircraft batteries includes an energy storage system configured to provide energy to the electric aircraft via a power supply connection, the energy storage system including: a battery pack, a sensor configured to detect a condition parameter of the battery pack and generate a battery datum based on the condition parameter, a pack monitoring unit (PMU) configured to receive the battery datum, and a high voltage disconnect configured to terminate the power supply connection between the battery pack and the electric aircraft; a high voltage bus electrically connected to the high voltage disconnect; a primary functional display configured to display information based on battery datum; and a first controller area network (CAN) bus and a second CAN bus communicatively connected to the PMU, the high voltage bus, and the primary functional display.

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: A system of fall back flight control configured for use in electric aircraft includes an input control configured to receive a pilot input and generate a control datum. System includes a flight controller communicatively coupled to the input control and configured to receive the control datum and generate an output datum. The system includes the actuator having a primary mode in which the actuator is configured to move the at least a portion of the electric aircraft as a function of the output datum and a fall back mode in which the actuator is configured to move the at least a portion of the aircraft as a function of the control datum. The actuator configured to receive the control datum, receive the output datum, detect a loss of communication with the flight controller, and select the fall back mode as a function of the detection.

Abstract: An electric aircraft battery pack that includes an integrated battery management component, which determines if a power supply connection between the battery pack and the electric aircraft should be terminated due to a failure, defect, or malfunction of the battery pack, such as a failure of a battery module of the battery pack.

Abstract: In an aspect a system for fly-by-wire flight control configured for use in electric aircraft including at least a sensor, wherein the sensor is communicatively connected a pilot control and configured to detect a pilot input from the pilot control and generate, as a function of the pilot input, command datum. A system includes a flight controller, the flight controller including a computing device and configured to perform a voting algorithm, wherein performing the voting algorithm includes determining that the sensor is an allowed sensor, wherein determining that the sensor is an allowed sensor includes determining that the command datum is an active datum, determining the command datum is an admissible datum, generating, as a function of the command datum and the allowed sensor, a control surface datum wherein the control surface datum is correlated to the pilot input.

Abstract: The present disclosure is generally directed to a flight control system and method of flight control for an electric aircraft. The system includes a pilot input communicatively connected to an electric aircraft, wherein the pilot input is configured to receive an input datum, and plurality of flight components communicatively connected to the electric aircraft, wherein the plurality of flight components includes a plurality of control surfaces. The system also includes a flight controller, wherein the flight controller is configured to determine a phase of flight, determine a command datum to control a position of the plurality of control surfaces as a function of the input datum, and command, when the phase of flight is determined to be hover, the plurality of control surfaces using the command datum.