Beta Air, LLC

Braedon Andrew Lohe

Cullen Forrest Jemison

Andrew Joseph Giroux

Sean Richard Donovan

Tom Michael Hughes

Nathan William Joseph Wiegman

Herman Wiegman

Sarah Kathleen Overfield

Sam Wagner

Stuart Denson Schreiber

Raffaello Verna

Peter Adam Gottlieb

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 device for emergency disconnection of a high voltage electrical connection between a power source and a high voltage component of an electric aircraft in response to a crash. The device includes a controller, where the controller is configured to receive a sensor datum from a sensor of device, to determine a crash element between and initiate a disconnection protocol as a function of the crash element.

Emergency high voltage disconnection device for an electric aircraft

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

An apparatus for a ground-based battery management for an electric aircraft is presented. The apparatus includes a battery pack mechanically coupled to the electric aircraft, the battery pack includes at least a battery module that includes at least a battery unit that includes battery cells and a thermal conduit configured to transfer heat between the battery cells and the thermal conduit and a thermal circuit mechanically coupled to the thermal conduit configured to facilitate the heat transfer using thermal media. The apparatus includes a media channel communicatively connected to a computing device and comprising at least a sensor, wherein the media channel is configured to evacuate the thermal media out of the battery pack using the thermal circuit and the computing device that includes a battery management system is configured to receive a condition parameter as a function of the at least a sensor of the media channel.

Apparatus for a ground-based battery management for an electric aircraft

A system for a laminated buswork with flexible conductors for an electric aircraft is presented. The system includes a plurality of electrical devices and an electrical bridging device electrically connected to each electrical device of the plurality of devices. The electrical bridging device includes a laminated busbar and a plurality of flexible contactors, wherein each flexible contactor is configured to attach the laminated busbar to each electrical device of the plurality of electrical devices, apply pressure to each electrical device as a function of at least a spring, and provide electrical connection to the electric aircraft as a function of the tension of the at least a spring.

Systems and methods for laminated buswork with flexible conductors for an electric aircraft

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

The present invention is directed to an apparatus for managing thermal energy of an electric aircraft energy source. Apparatus may include fins, which extend from a skin of electric aircraft. The energy source may bias or be adjacent to the fins so that heat energy may dissipate from the energy source and through the fins and, thus, the skin. A coolant may also be run through the apparatus, where the coolant may flow through channels that are disposed between the fins.

Integrated thermal management apparatus

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

In an aspect an electric aircraft is presented. An electric aircraft includes a consumable coolant reservoir housed within the electric aircraft. A consumable coolant reservoir is configured to contain a coolant. An electric aircraft includes a battery pack temperature control system including at least a thermal pathway. A thermal pathway is in thermal communication with a consumable coolant reservoir and at least a battery pack of an electric aircraft. A thermal pathway is configured to transport a thermal energy away from at least a battery pack.

Electric aircraft and method of cooling a battery pack

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.

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Essex Junction, VT, United States of America

Braedon Andrew Lohe