Beta Air, LLC

Cullen Forrest Jemison

Braedon Andrew Lohe

Andrew Joseph Giroux

Tom Michael Hughes

Stuart Denson Schreiber

Nathan William Joseph Wiegman

Grayson King

Myles Tallada

Miles Tallada

A apparatus for fault detection for use in an electric aircraft is disclosed herein. The apparatus includes a battery module with a plurality of battery cells, a plate extending along the row of cells, insulation between the plate and the plurality of cells, a sensor configured to detect a potential signal, and a controller communicatively connected to the sensor. The controller is configured to receive the potential signal and determine a fault.

Apparatus and method for fault detection in a battery module

A battery management system integrated in a battery pack configured for use in electric aircraft, the system comprising a first battery management component comprising a first sensor suite configured to measure a first plurality of battery pack data. The battery management system comprising a second battery management component comprising a second sensor suite configured to measure a second plurality of battery pack data. The battery management system comprising a data storage system configured to store the first plurality of battery pack data and the second plurality of battery pack data.

Systems and methods for a battery management system integrated in a battery pack configured for use in electric aircraft

The disclosure provides a battery management system and related method. A battery management system for an electric aircraft includes a control circuit communicatively connected to a plurality of sensors configured to detect a plurality of measurement data related to a battery pack. The control circuit is configured to: identify a state transition criterion as a function of an operating condition of the battery pack; and transition from a first state and a second state as a function of the state transition criterion.

Battery management system with operational states

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.

Systems and methods for battery management for electric aircraft batteries

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.

Pack monitoring unit for an electric aircraft battery pack and methods of use for battery management

A battery management and monitoring system integrated in a battery pack configured for use in electric aircraft. The system includes a sensor suite configured to measure a plurality of battery pack data. The system includes a battery monitoring component configured to detect a first fault in the battery pack and produce a first fault detection response notifying a user of the first fault in the battery pack. The system includes a battery management component configured to detect a second fault in the battery pack and produce a second fault detection response configured to mitigate the second fault in the battery pack. The system includes an interlock component having a first mode and a second mode, configured to enable the battery monitoring component and disable the battery management component when in the first mode and enable the battery management component and disable the battery monitoring component when in the second mode.

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.

System for monitoring a battery system in-flight and a method for its use

Electric aircraft battery pack and methods of use

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.

Systems and methods for locking a battery for an electric aircraft

A battery management system includes a low-power chip that allows battery management system, or components thereof, to alternate between operational states. Operational states may include a first state, a second state, a third state, and the like. A method of operation by a battery management system for an electric aircraft is also provided.

Growing community of inventors

Winooski, VT, United States of America

Cullen Forrest Jemison