Beta Air, LLC

Stuart Denson Schreiber

Tyler John Skroski

Peter Adam Gottlieb

Sean Richard Donovan

Sarah Kathleen Overfield

Nathan William Joseph Wiegman

Herman Wiegman

Nicholas Moy

Collin Freiheit

Braedon Andrew Lohe

Cullen Forrest Jemison

Nathan Goldsberry

Tyler Skroski

Grayson King

Sam Wagner

Tom Michael Hughes

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 system and a method for a battery power management system for an electric aircraft can include at least a flight component of an electric aircraft, at least a battery, wherein the at least a battery is configured power the at least a flight component of the electric aircraft, at least a sensor communicatively connected to the at least a battery and a controller communicatively connected to the at least a sensor. The controller is configured to receive sensor data from the at least a sensor, identify a battery status as a function of the sensor data and a battery threshold, and control the power from the at least a battery to the at least a flight component of the electric aircraft as a function of the battery status, further comprising reducing a torque to the at least a flight component.

System and a method for a battery power management system for an electric aircraft

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 state determination of a battery module configured for use in an electric vehicle. The system including a battery module including at least a battery cell, a sensor including a proximity sensor configured to detect a status datum corresponding to the battery module, a processor configured to receive the status datum from the sensor, generate a charge datum as a function of the status datum corresponding to the battery module, generate a health datum as a function of the status datum corresponding to the battery module, transmit the charge datum and the health datum, and a display configured to receive the charge datum and the health datum corresponding to the battery cell, and display the charge datum and the health datum corresponding to the battery cell.

System and method for state determination of a battery module configured for use in an electric aircraft

Aspects of the present disclosure are generally related to a battery pack having a carbon fiber battery case, the battery pack comprising a plurality of pouch cells. Further, the battery pack having a carbon fiber battery case may include a casing formed with carbon fiber, the casing having one or more carbon fiber separation sheets and, the casing configured to dissipate heat from the plurality of pouch cells in a direction along carbon fibers of the casing.

Battery pack for a carbon fiber pouch cell casing configured to cool battery cells

A system and method for using unrecoverable energy in a battery cell is disclosed in this application. A system includes a battery cell, the battery cell includes an excess amount of cathode or anode that can function as half cells in an emergency. A user, such as a pilot, can command a controller to utilize unrecoverable energy based on battery data presented to the user.

System and method for using unrecoverable energy in a battery cell

A stack battery pack for an electric vertical take-off and landing aircraft includes a first pouch cell comprising a first top surface and a first bottom surface, a second pouch cell comprising a second top surface and a second bottom, wherein the first pouch cell and the second pouch cell are aligned such that the first bottom surface is in contact with the second top surface, an ejecta barrier located between the first pouch cell and the second pouch cell, wherein the ejecta barrier is configured to be substantially impermeable to a cell ejecta from the first pouch cell, and a vent configured to vent the cell ejecta, wherein the stack battery pack is configured to power a propulsor component.

Stack battery pack for electric vertical take-off and landing aircraft

A system and a method for a battery power management system for an electric aircraft is disclosed. The system includes at least a flight component of an electric aircraft, at least a battery, wherein the at least a battery is configured power the at least a flight component of the electric aircraft, at least a sensor communicatively connected to the at least a battery and a controller communicatively connected to the at least a sensor. The controller is configured to receive sensor data from the at least a sensor, identify a battery status as a function of the sensor data and a battery threshold, and control the power from the at least a battery to the at least a flight component of the electric aircraft as a function of the battery status, further comprising reducing a torque to the at least a flight component.

A battery pack for an electric aircraft is disclosed. The battery pack may include a pouch cell within a sealed environment, wherein the pouch cell may include a pair of electrodes, wherein the pair of electrodes is configured to carry electrical current. The pouch cell may include an insulator layer, the insulator layer located between the pair of electrodes. The pouch cell may include an electrolyte within the pouch cell. The pouch cell may include a pouch, the pouch substantially surrounding the pair of electrodes, the electrolyte and the insulator layer. The pouch cell may include a pair of foil tabs in electrical communication with the pair of electrodes and emanating from the sealed environment. The pouch cell may include a seal, wherein the seal is configured to seal about the pair of foil tabs and prevent a flow of cell ejecta from a thermal runaway.

Battery pack for an electric aircraft

A battery pack assembly including at least a battery cell, wherein the battery cell may include a pair of electrodes, a pair of conductive foil tabs and an electrolyte. The battery pack assembly may include a battery cell case, wherein the battery cell case is configured to surround a portion of the a battery cell. The battery cell case may include a layer, wherein the layer may be configured to provide a pressure against a battery cell.

System and method for a battery assembly

A system for a venting seal for battery modules in an electric aircraft is presented. The system includes a plurality of battery modules, wherein each battery module comprises a vent conduit, a contactor configured to disengage at least a catalyst battery module as a function of a thermal event, and an electrical bridging device configured to seal off the at least a catalyst battery module as a function of an independent seal, disengage the at least a catalyst battery module from the remaining plurality of battery modules, and transfer electrical energy across the plurality of battery modules.

Systems and methods for a venting seal for battery modules in an electric aircraft

An apparatus for venting battery ejecta for use in an electric aircraft is presented. The apparatus includes a battery module with a plurality of electrochemical cells. The electrochemical cells of the plurality of electrochemical cells are separated by a carbon fiber barrier. Venting port of a plurality of venting ports is configured to vent an electrochemical cell of the plurality of electrochemical cells using a venting path of a plurality of venting paths, wherein the plurality of vent ports is fluidly connected to the plurality of venting paths and the plurality of venting paths are fluidly connected to at least an outlet. Venting paths direct the battery ejecta from the electrochemical cell to the outside of the electric aircraft through at least an outlet.

Venting apparatus for battery ejecta for use in an electric aircraft

A system for battery pack cooling including a battery pack. The battery pack includes a plurality of pouch cells and a separation element, where the separation separates at least a first pouch cell of the plurality pouch cells from a second pouch cell of the plurality of pouch cells. The separation element contains a fluid. The system also includes a cooling plate, where the cooling plate is adjacent to the lower side of the battery pack. The cooling plate comprises at least a cooling fin, where the at least a cooling fin extends towards the separation element.

Systems and methods for a double-sided battery pack cooling assembly

An apparatus for active battery pack cooling including a battery pack with a plurality of battery modules. The apparatus further including an active cooling system with a coolant channel, wherein the coolant channel includes a coolant fluid. The active cooling system is in thermal communication with more than one of the plurality of battery modules. The apparatus also including a plurality of passive heat transfer elements, wherein each of the plurality of passive heat transfer elements is connected to the active cooling system, extends to a battery module of the plurality of battery modules, and extends away from the coolant channel.

Growing community of inventors

Essex, VT, United States of America

Stuart Denson Schreiber