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

Description

1 / 88 SYSTEM AND METHOD FOR A BATTERY POWER MANAGEMENT SYSTEM FOR AN ELECTRIC AIRCRAFT. CROSS-REFERENCE TO RELATED APPLICATIONS.

[001] This application claims priority to U.S. Patent Application No. 18 / 129,366, filed March 31, 2023, entitled SYSTEM AND METHOD FOR FLIGHT CONTROL IN ELECTRIC AIRCRAFT, which is a continuation in part of U.S. Application No. 17 / 515,124, filed October 29, 2021, issued as U.S. Patent No. 11,679,867 on June 20, 2023, entitled SYSTEM AND METHOD FOR FLIGHT CONTROL IN ELECTRIC AIRCRAFT (Application '124), and U.S. Application No. 18 / 114,478, filed February 27, 2023, entitled SYSTEM AND METHOD FOR THE PRIORITIZATION OF FLIGHT CONTROLS IN AN ELECTRIC AIRCRAFT (Application '478), the entirety of which is incorporated herein disclosure. In its entirety, for reference purposes. Application '124 is a continuation of Application No. U.S. 17 / 349,631, filed on June 16, 2021, entitled SYSTEM AND METHOD FOR FLIGHT CONTROL IN ELECTRIC AIRCRAFT, which is a continuation in part of Provisional Application No. U.S. 17 / 197.Application No. 427, filed March 10, 2021, issued October 12, 2021 as U.S. Patent No. 11,142,333, and entitled SYSTEM AND METHOD FOR FLIGHT CONTROL IN AN ELECTRIC START, the entirety of each of which is incorporated herein by reference. Application No. 478 is a continuation of Application No. 17 / 524,901, filed November 12, 2021, issued April 11, 2023 as U.S. Patent No. 11,623,738 and entitled SYSTEM AND METHOD FOR PRIORITIZING FLIGHT CONTROLS IN AN ELECTRIC START, the entirety of which is incorporated herein by reference. FIELD OF THE INVENTION

[002] The present invention generally relates to the field of battery management systems. In particular, the present invention is directed to a system and a method for a battery power management system for an electric aircraft. Petition 870250087341, dated 09 / 26 / 2025, p. 7 / 277 2 / 88 BACKGROUND

[003] Electric aircraft batteries can suffer from thermal runaway and / or electrical insulation breakdown when the batteries become excessively heated. It is crucial to prevent the batteries from becoming excessively heated. Existing solutions to this problem are not sufficient. SUMMARY OF REVELATION

[004] In one aspect, a system for a battery power management system for an electric aircraft is disclosed. The system includes at least one flight component of an electric aircraft, at least one battery, wherein at least one battery is configured to power at least one flight component of the electric aircraft, at least one sensor communicatively connected to at least one battery, and a controller communicatively connected to at least one sensor. The controller is configured to receive data from at least one sensor, identify a battery state based on the sensor data and a battery limit, and control the power from at least one battery to at least one flight component of the electric aircraft based on the battery state.

[005] In another aspect, a method for a battery power management system for an electric aircraft is disclosed. The method includes receiving, using a controller, sensor data from at least one sensor communicatively connected to at least one battery configured to supply power to at least one flight component of an electric aircraft. The method includes identifying, using the controller, a battery state as a function of the sensor data and a battery limit. The method includes controlling, using the controller, the power from at least one battery to at least one flight component of the electric aircraft as a function of the battery state.

[006] These and other aspects and features of the non-limiting embodiments of the present invention will become apparent to those skilled in the art after reviewing the following description of specific non-limiting embodiments of the Petition 870250087341, dated 09 / 26 / 2025, page 8 / 277 3 / 88 invention together with the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[007] In order to illustrate the invention, the drawings show aspects of one or more embodiments of the invention. However, it should be understood that the present invention is not limited to the precise arrangements and instruments shown in the drawings, wherein: Figure I is a block diagram of an exemplary embodiment of a battery power management system for an electric aircraft; Figure 2 schematically illustrates an exemplary battery module; Figure 3 is a perspective drawing illustrating a battery pack, according to its type; Figure 4 is a diagram of an exemplary battery pack to prevent the progression of thermal runaway between modules; Figure 5 is a block diagram of one embodiment of the battery management system; Figure 6 is an illustration of a sensor array in partial cross-sectional view; Figure 7 is a block diagram illustrating a data collection system; Figure 8 is an illustration of one type of electric aircraft; Figure 9 is a flowchart of a method for a battery power management system for an electric aircraft; and Figure 10 is a block diagram of a computing system that can be used to implement any one or more of the methodologies disclosed in this document and any one or more of its portions.

[008] The drawings are not necessarily to scale and may be illustrated by ghost lines, diagrammatic representations and fragmentary views. In certain cases, details that are not necessary for understanding the modalities or that hinder the perception of other details may have been omitted. DETAILED DESCRIPTION

[009] At a high level, aspects of the present revelation are directed to a Petition 870250087341, dated 09 / 26 / 2025, page 9 / 277 4 / 88 Battery power management system for an electric aircraft. The system includes at least one flight component of an electric aircraft, at least one battery, wherein at least one battery is configured to power at least one flight component of the electric aircraft, at least one sensor communicatively connected to at least one battery, and a controller communicatively connected to at least one sensor. The controller is configured to receive data from at least one sensor, identify a battery state based on sensor data and a battery limit, and control the power from at least one battery to at least one flight component of the electric aircraft based on the battery state.

[010] Aspects of the present disclosure can be used to prevent thermal runaway and / or electrical insulation breakdown. This is so, at least in part, because a system for a battery power management system can reduce the power of at least one battery when at least one battery becomes excessively heated.

[011] Aspects of the present disclosure make it possible to reduce the power of at least one battery for a flight component of an electric aircraft. Exemplary embodiments illustrating aspects of the present disclosure are described below in the context of several specific examples.

[012] With reference now to Figure 1, an exemplary embodiment of system 100 for a battery management system for an electric aircraft is illustrated. For the purposes of this disclosure, an electric aircraft is an aircraft powered by electricity. The electric aircraft 104 may be capable of rotor-based cruise flight, rotor-based takeoff, rotor-based landing, fixed-wing cruise flight, airplane-style takeoff, airplane-style landing, and / or any combination thereof. Rotor-based flight, as described in this disclosure, is where the aircraft has generated lift and propulsion by means of one or more powered rotors coupled to a motor, such as a quadcopter, multirotor helicopter, or other vehicle that maintains its Petition 870250087341, dated 09 / 26 / 2025, page 10 / 277 5 / 88 lift is primarily achieved through the use of downward thrust propellers. The term fixed-wing flight, as described in this disclosure, refers to an aircraft capable of flight using wings and / or blades that generate lift caused by the speed of the aircraft's forward airspeed and the shape of the wings and / or blades, similar to airplane flight. In one embodiment, the electric aircraft 104 may include an electric vertical takeoff and landing (eVTOL) aircraft. A vertical takeoff and landing aircraft, as used in this disclosure, is an aircraft that can hover, take off, and land vertically. In another embodiment, the electric aircraft 104 may include an electric conventional takeoff and landing (eCTOL) aircraft. For the purposes of this disclosure, a conventional takeoff and landing aircraft is an aircraft that takes off and lands horizontally from a runway of conventional length at a distance.In another embodiment, the electric aircraft may include an electric short takeoff and landing (eSTOL) aircraft. For the purposes of this disclosure, an electric short takeoff and landing aircraft is an aircraft that requires a shorter minimum horizontal distance to accelerate in order to climb into the air than typical types of fixed-wing aircraft. Furthermore, the electric aircraft disclosed herein is described in detail in Figure 8.

[013] With continued reference to Figure 1, system 100 includes at least one flight component 108. For the purposes of this disclosure, a flight component is a device in an electric aircraft that is used to affect the flight of the electric aircraft through the air. The at least one flight component 108 may include power sources, power sources, propulsion components, lift components, thrust components, control linkages for one or more elements, fuses, and / or mechanical couplings used to actuate and / or control any other flight component. The at least one flight component 108 may include an electric motor that operates to move one or more flight control components, to actuate one or more propellers, or something similar. An electric motor, for the purposes of this disclosure, is a device that converts electrical energy into mechanical energy. The electric motor may be Petition 870250087341, dated 09 / 26 / 2025, page 11 / 277 6 / 88 driven by direct current (DC) electrical power; for example, a motor may include a brushed DC motor or something similar. The electric motor may be driven by electrical power having varying or reverse voltage levels, such as alternating current (AC) power produced by an alternating current generator and / or inverter, or otherwise variable power, such as that produced by a switched-mode power supply. The electric motor may include, without limitation, a brushless DC electric motor, a permanent magnet synchronous motor, a switched reluctance motor, and / or an induction motor; persons skilled in the art, upon reviewing the entirety of this disclosure, will be aware of various alternative or additional forms and / or configurations that a motor may assume or exemplify as consistent with this disclosure.In addition to an inverter and / or switching power supply, a circuit that drives the propulsion machine may include electronic speed controllers (not shown) or other components to regulate the propulsion machine's speed, direction of rotation, torque, and the like. Furthermore, without limitation, at least one flight component 108 disclosed herein may be consistent with a flight component found in Patent Application No. 17 / 526,399, filed November 15, 2021, and entitled SYSTEMS AND METHODS FOR CONTROLLING A FLIGHT BOUNDARY OF AN AIRCRAFT, with attorney dossier number 1024-295USU1, the entirety of which is incorporated herein by reference.

[014] With continued reference to Figure 1, an electric motor may include a stator. For the purposes of this disclosure, a stator is a stationary part of an electric motor. The electric motor may include a rotor. A rotor, for the purposes of this disclosure, is the rotating part of an electric motor. As a non-limiting example, the electric motor may convert electrical energy into mechanical energy by rotating the rotor. In some embodiments, the rotor may include a circular cross-section. In some embodiments, the rotor may include a hollow central portion.

[015] With continued reference to Figure 1, in some embodiments, a motor Petition 870250087341, dated 09 / 26 / 2025, page 12 / 277 7 / 88 electric motors may include a plurality of electric motors. In some embodiments, the electric motor may include two electric motors. As a non-limiting example, the electric motor may include a first electric motor and a second electric motor. In some embodiments, the first electric motor may be consistent with the electric motor as described throughout this disclosure. In some embodiments, the second electric motor may be consistent with the electric motor as described throughout this disclosure. The first electric motor may include a stator consistent with the stator of the electric motor. The second electric motor may include a stator consistent with the stator of the electric motor. In some embodiments, the first electric motor and the second electric motor may include a rotor. The rotor of the first electric motor and the second electric motor may be consistent with the rotor of the electric motor.In some embodiments, the first electric motor and the second electric motor may include a shared rotor. The shared rotor may be compatible with the rotor of the electric motor. In some embodiments, the rotor of the first electric motor may be a first rotor and / or the rotor of the second electric motor may be a second rotor. In some embodiments, the first electric motor and the second electric motor may include a sprag-type clutch. The sprag-type clutch may allow the first electric motor to rotate the shaft even if the second electric motor is not running, or vice versa. As non-limiting examples, a sprag-type clutch may be located between the first rotor and the shaft and / or the second rotor and the shaft. In some embodiments, the electric motor may be consistent with the motor disclosure in U.S. Patent Application Serial No. 17 / 563.498 (Attorney's File No. 1024-341USU1), filed on December 28, 2021, and entitled AN ELECTRIC AIRCRAFT LIFT MOTOR WITH AIR COOLING, which is incorporated herein in its entirety by reference.

[016] With continued reference to Figure 1, in some embodiments, at least one flight component 108 may include a power source. The power source may include, for example, a generator, a device Petition 870250087341, dated 09 / 26 / 2025, p. 13 / 277 8 / 88 photovoltaic, a fuel cell, such as a hydrogen fuel cell, direct methanol fuel cell and / or solid oxide fuel cell, an electrical energy storage device (e.g., a capacitor, an inductor and / or a battery). The power supply may also include a battery, a battery cell or a plurality of battery cells connected in series in a module and each module connected in series or in parallel with other modules. The power supply configuration containing connected modules may be designed to meet a power or wattage requirement and may be designed to fit within a designated coverage area on an electric aircraft 104.

[017] Referring again to Figure 1, in one embodiment, at least one flight component 108 can be mechanically coupled to an electric aircraft 104. As used in this document, a person of ordinary skill in the art would understand that mechanically coupled means that at least a portion of a device, component or circuit is connected to at least a portion of the aircraft through a mechanical coupling.Said mechanical coupling may include, for example, rigid couplings such as beam couplings, bellows couplings, pin and bushing couplings, constant velocity couplings, split bearing couplings, diaphragm couplings, disc couplings, threaded couplings, elastic couplings, flexible couplings, fluid couplings, gear couplings, grid couplings, hirth couplings, hydrodynamic couplings, jaw couplings, magnetic couplings, Oldham couplings, sleeve couplings, tapered shaft locks, double spring couplings, rag joint couplings, universal joints, or any combination thereof. In one embodiment, the mechanical coupling may be used to connect the ends of adjacent parts and / or objects of an aircraft. Furthermore, in another embodiment, the mechanical coupling may be used to join two parts of rotating aircraft components. Petition 870250087341, dated 09 / 26 / 2025, page 14 / 277 9 / 88

[018] Referring again to Figure 1, in some embodiments, at least one flight component 108 may include at least one lift component and at least one thrust component. For the purposes of this disclosure, a thrust component is a component that propels and / or produces thrust in an aircraft through a medium. The thrust component may include a propeller, a blade, a motor, a rotor, a rotating element, an aileron, a rudder, arrangements thereof, combinations thereof, and the like. As a non-limiting example, the thrust component may include a thruster propeller, a blade wheel, a thruster motor, a thruster propeller, and the like. Furthermore, or alternatively, the thruster flight component may include a plurality of thruster flight components.Each component of the thruster, when a plurality is present, of the plurality of flight components 108 can be configured to produce, in one embodiment, substantially forward thrust and / or horizontal thrust so that the aircraft moves forward. The thruster component can be configured to produce forward thrust. As a non-limiting example, forward thrust may include a force to propel the aircraft in the horizontal direction along the longitudinal geometric axis. As another non-limiting example, the thruster component may twist and / or rotate to pull air behind it and, at the same time, propel an electric aircraft 104 forward with the same amount of force. In one embodiment, and without limitation, the more air forced behind the electric aircraft 104, the greater the thrust force with which the electric aircraft 104 can be propelled horizontally.In another embodiment, and without limitation, forward thrust may force the electric aircraft 104 through the relative air medium. Furthermore, or alternatively, at least one flight component 108 may include one or more extractor components. As used in this disclosure, a traction component is a component that pulls and / or tows an aircraft through a medium. As a non-limiting example, the extractor component may include a flight component 108, such as an extractor propeller. Petition 870250087341, dated 09 / 26 / 2025, page 15 / 277 10 / 88 an extractor motor, a tractor propeller, an extractor thruster and the like. In addition, or alternatively, the extractor component may include a plurality of extractor flight components.

[019] With continued reference to Figure 1, in some embodiments, at least one flight component 108 may include a lift component. As used in this disclosure, a lift component is a component and / or device used to propel a craft upward so as to exert downward force on a fluid medium, which may include a gaseous medium, such as air, or a liquid medium, such as water.

[020] The lift component may include any device or component that consumes electrical power on demand to propel an electric aircraft 104 in a direction or another vehicle while on the ground or in flight. The lift component may include a propeller, a propeller, a blade, a motor, a rotor, a rotating element, an aileron, a rudder, arrangements thereof, combinations thereof, and the like. Each lift component, when a plurality is present, of the plurality of flight components 108 may be configured to produce, in one embodiment, substantially upward thrust and / or vertical thrust so that the aircraft moves upward. For example, and without limitation, the lift component may include a rotor, propeller, paddle wheel, and the like, wherein a rotor is a component that produces torque along the longitudinal geometric axis and a propeller produces torque along the vertical geometric axis.In one embodiment, the lift component may include a plurality of blades. As used in this disclosure, a blade is a propeller that converts the rotary motion of an engine or other power source into a circular vortex. In one embodiment, the blade may convert the rotary motion to propel the propeller forward or backward. In one embodiment, the lift component may include a power-driven rotating hub to which multiple radial airfoil-section blades may be attached, such that the entire assembly rotates about a longitudinal geometric axis. Petition 870250087341, dated 09 / 26 / 2025, page 16 / 277 11 / 88

[021] With continued reference to Figure 1, in some embodiments, a lift component may be configured to produce lift. As used in this disclosure, lift is a force perpendicular to the direction of flow approaching the fluid around the surface. For example, and without limitation, the relative airspeed may be horizontal to the aircraft, wherein the lift force may be a force exerted in the vertical direction, which directs the aircraft upward. In one embodiment, and without limitation, the lift component may produce lift as a function of the application of a torque to the lift component. As used in this disclosure, torque is a measure of force that causes an object to rotate about a geometric axis in a direction. For example, and without limitation, torque may rotate an aileron and / or rudder to generate a force that may adjust and / or affect altitude, airspeed, ground speed, direction during flight, and / or thrust.For example, a flight component 108, such as a power supply, can apply torque to the lift component to produce lift.

[022] With continued reference to Figure 1, in some embodiments, at least one flight component 108 may include any related components and devices, as disclosed in Nonprovisional Application Serial No. U.S. 16 / 427,298, filed May 30, 2019, entitled SELECTIBLY DEPLOYABLE HEATED PROPULSOR SYSTEM (Attorney File No. 1024-003USU1), Nonprovisional Application Serial No. U.S. 16 / 703,225, filed December 4, 2019, entitled AN

[023] INTEGRATED ELECTRIC PROPULSION ASSEMBLY, (Attorney File No. 1024-009USU1), Non-Provisional Application Serial No. U.S. 16 / 910,255, filed June 24, 2020, entitled AN INTEGRATED ELECTRIC PROPULSION ASSEMBLY, (Attorney File No. 1024-009USC1), Non-Provisional Application Serial No. 17 / 319,155, filed May 13, 2021, entitled AIRCRAFT HAVING REVERSE THRUST CAPABILITIES, (Attorney File No. 1024-028USU1), Non-Provisional Application Serial No. U.S. 16 / 929,206, Petition 870250087341, dated 09 / 26 / 2025, page 17 / 277 12 / 88 filed on July 15, 2020, entitled A HOVER AND THRUST CONTROL ASSEMBLY FOR DUAL-MODE AIRCRAFT (Attorney File No. 1024-034USU1), Non-Provisional Application Serial No. US 17 / 001.845, filed on August 25, 2020, entitled A HOVER AND THRUST CONTROL ASSEMBLY FOR DUAL-MODE AIRCRAFT (Attorney File No. 1024-034USC1), Non-Provisional Application Serial No. US 17 / 186.079, filed on February 26, 2021, entitled METHODS AND SYSTEM FOR ESTIMATING PERCENTAGE TORQUE PRODUCED BY A PROPULSOR CONFIGURED FOR USE IN AN ELECTRIC AIRCRAFT (Attorney File No. 1024-079USU1), and Non-Provisional Application Serial No. US 17 / 321,662, filed May 17, 2021, entitled AIRCRAFT FOR FIXED PITCH LIFT (Attorney File No. 1024-103USU1), the entirety of which is incorporated herein by reference.

[024] With continued reference to Figure 1, the system 100 includes at least one battery 112. For the purposes of this disclosure, a battery is an electrical device and / or component used to store and supply electrical power to an electric vehicle and its electrical subsystems. At least one battery 112 is configured to power at least one flight component 108 of an electric aircraft 104. As a non-limiting example, at least one battery 112 may power a lift component. As another non-limiting example, at least one battery may power a thruster component. As yet another non-limiting example, at least one battery 112 may power a thruster of the electric aircraft 104. In some embodiments, at least one battery 112 may include one or more battery cells, one or more battery modules, and / or one or more batteries. A battery, as used in this disclosure, is an assembly of battery modules.The battery may be consistent with a battery in Figure 3. A battery module, as used in this disclosure, is an assembly of battery cells. The battery module may be consistent with a battery module in Figure 2. A battery cell, as used in this disclosure, is a single separate anode and cathode. Petition 870250087341, dated 09 / 26 / 2025, page 18 / 277 13 / 88 by electrolyte, wherein the cell produces voltage and current. The battery cell may be consistent with a battery cell in Figure 4. In some embodiments, at least one battery 112 may be one or more different types of batteries, such as a bag cell battery, stack batteries, prismatic battery, lithium-ion cells, or the like. In some embodiments, at least one battery 112 may include a battery, flywheel, rechargeable battery, flow battery, glass battery, lithium-ion battery, ultrabattery, and the like. Furthermore, without limitation, at least one battery 112 disclosed herein may be consistent with a power supply found in U.S. Patent Application No. 17 / 574.978, filed on January 13, 2022, and entitled APPARATUSES AND METHODS FOR PRECONDITIONING A POWER SOURCE OF AN ELECTRIC AIRCRAFT, which has attorney registration number 1024-204USU1, is incorporated herein in its entirety by reference.

[025] With continuous reference to Figure 1, system 100 includes at least one sensor 116. For the purposes of this disclosure, a sensor is a device that produces an output signal for the purpose of detecting a physical phenomenon. For example, and without limitation, at least one sensor 116 may transduce a detected phenomenon, such as, without limitation, temperature, voltage, current, pressure, speed, motion, light, humidity, and the like, into a detected signal. At least one sensor 116 may output the detected signal. At least one sensor 116 may include any computing device as described in the entirety of this disclosure and configured to convert and / or translate a plurality of detected signals into electrical signals for further analysis and / or manipulation. As a non-limiting example, at least one sensor 116 may detect the temperature of at least one battery 112 and output sensor 116 data of the temperature of at least one battery 112 to a controller 120.The data from sensor 116 and controller 120 disclosed in this document are described in more detail below. Electrical signals may include analog signals, digital signals, periodic or aperiodic signals. Petition 870250087341, dated 09 / 26 / 2025, page 19 / 277 14 / 88 step signals, unit impulse signal, unit ramp signal, unit parabolic signal, signum function, exponential signal, rectangular signal, triangular signal, sinusoidal signal, sine function, or pulse width modulated signal. Any data captured by at least one sensor 116 may include a circuit set, computing devices, electronic components, or a combination thereof that translates into at least one electronic signal configured to be transmitted to another electronic component. In a non-limiting embodiment, at least one sensor 116 may include a plurality of sensors included in a sensor set. In one or more embodiments, and without limitation, at least one sensor 116 may include a plurality of sensors. At least one sensor 116 disclosed herein may be consistent with a sensor described in relation to Figure 6.

[026] With continuous reference to Figure 1, at least one sensor 116 is communicatively connected to at least one battery 112. In some embodiments, at least one sensor 116 is communicatively connected to a controller 120. For the purposes of this disclosure, communicatively connected means connected by means of a connection, attachment or link between two or more related elements that allows the reception and / or transmission of information between them. For example, and without limitation, this connection may be wired or wireless, direct or indirect, and between two or more components, circuits, devices, systems and the like, which allows the reception and / or transmission of data and / or signal(s) between them. The data and / or signals between them may include, without limitation, electrical, electromagnetic, magnetic, video, audio, radio and microwave data and / or signals, combinations thereof and the like, among others.A communicative connection can be achieved, for example and without limitation, by means of wired or wireless electronic communication, digital or analog, directly or through one or more intervening devices or components. Furthermore, the communicative connection may include electrical coupling or the connection of at least one output of a device, component or circuit to at least one input. Petition 870250087341, dated 09 / 26 / 2025, page 20 / 277 15 / 88 from another device, component, or circuit. For example, and without limitation, by means of a bus or other means for intercommunication between elements of a computing device. Communicative connection may also include indirect connections via, for example, and without limitation, wireless connection, radio communication, low-power long-distance network, optical communication, magnetic, capacitive, or optical coupling, and the like. In some cases, the terminology communicatively coupled may be used instead of communicatively connected in this disclosure.

[027] With continuous reference to Figure 1, in one or more embodiments, at least one sensor 116 may include a sensor set that may include a plurality of sensors that can detect similar or unique phenomena. For example, in a non-limiting embodiment, the sensor set may include a plurality of voltmeters or a mixture of voltmeters and thermocouples. The system 100 may include a plurality of sensors in the form of individual sensors or a set of sensors that operate together or individually. A sensor set may include a plurality of independent sensors, as described in this disclosure, wherein any number of the sensors described may be used to detect any number of physical or electrical quantities associated with an aircraft.Independent sensors may include separate sensors that measure physical or electrical quantities that may be powered by and / or communicate with circuits independently, wherein each may signal the sensor output to a control circuit, such as the controller 120. In one or more embodiments, at least one sensor may include a sensor board, such as a sensor plate. A sensing board may have at least a part of a circuit board that includes one or more sensors configured to, for example, measure the temperature of at least one battery 112. In one or more embodiments, a sensing board may be connected to battery modules and / or cells of at least one battery 112. In one or more embodiments, a sensing board may include one or more circuits and / or circuit elements. Petition 870250087341, dated 09 / 26 / 2025, p. 21 / 277 16 / 88, which includes, for example, a printed circuit board component. A detection board may include, without limitation, a control circuit configured to execute and / or direct any actions performed by the detection board and / or any other component and / or element described in this disclosure. The control circuit may include any analog or digital control circuit, including, without limitation, a combinational and / or synchronous logic circuit, a processor, microprocessor, microcontroller, or similar.

[028] With continuous reference to Figure 1, at least one sensor 116 may include sensors configured to measure physical and / or electrical parameters. As a non-limiting example, the temperature and / or voltage of at least one battery 112 may be measured. For example, and without limitation, at least one sensor may monitor voltage and / or temperature of battery modules and / or cells of at least one battery 112. At least one sensor 116 may be configured to detect faults in each battery module, for example and without limitation, based on and / or using detected physical and / or electrical parameters.In one or more exemplary embodiments, battery cell failure may be characterized by a temperature spike, and at least one sensor may be configured to detect this temperature increase and generate signals, which are discussed further below, to notify users, support personnel, security personnel, flight crew, maintenance personnel, operators, emergency personnel, aircraft computers, or a combination thereof. Detection may be performed using any component, set of components, and / or mechanism suitable for direct or indirect measurement and / or detection of voltage levels, including, without limitation, comparators, analog-to-digital converters, any form of voltmeter, or similar.

[029] With continued reference to Figure 1, in some embodiments, at least one sensor 116 may include an electrical sensor. As described in this disclosure, an electrical sensor is a device configured to detect a Petition 870250087341, dated 09 / 26 / 2025, page 22 / 277 17 / 88 electrical parameter associated with an electrical phenomenon. Exemplary non-limiting electrical sensors include voltmeters, ammeters, ohmmeters, multimeters, oscilloscopes, and the like. As a non-limiting example, the electrical sensor may detect a voltage from at least one 112V battery and transmit voltage sensor data from at least one 112V battery to a 120V controller. As another non-limiting example, the electrical sensor may detect a current from at least one 112V battery and transmit current sensor data from at least one 112V battery to the 120V controller.

[030] With continued reference to Figure 1, in some embodiments, at least one sensor 116 may include a temperature sensor 124. For the purposes of this disclosure, a temperature sensor is a device that detects thermal energy and emits an electrical signal as a function of the detection of thermal energy. As a non-limiting example, the temperature sensor 124 may include thermocouples, thermistors, thermometers, passive infrared sensors, resistance temperature detectors (RTDs), semiconductor-based integrated circuits (ICs), a combination thereof, or another type of sensor not disclosed, alone or in combination. For the purposes of this disclosure, and as would be observed by one of ordinary skill in the art, temperature is a measure of the heat energy of a system. Temperature, measured by any number or combination of sensors, may be measured in Fahrenheit (°F), Celsius (°C), Kelvin (°K), or another scale alone or in combination.The temperature measured by sensors may comprise electrical signals that are transmitted to their appropriate destination wirelessly or via a wired connection. As a non-limiting example, temperature sensor 124 may detect a temperature of at least one battery 112 and transmit temperature sensor data from at least one battery 112 to a controller 120.

[031] With continued reference to Figure 1, system 100 includes a controller 120. The controller 120 may include any computing device as described in this disclosure, including, without limitation, a microcontroller, microprocessor, digital signal processor (DSP) and / or. Petition 870250087341, dated 09 / 26 / 2025, page 23 / 277 18 / 88 system-on-a-chip (SoC) as described in this disclosure. The computing device may include, be included with, and / or communicate with a mobile device, such as a cell phone or smartphone. The controller 120 may include a single computing device that operates independently, or it may include two or more computing devices that operate together, in parallel, sequentially, or similarly; two or more computing devices may be included together in a single computing device or in two or more computing devices. The controller 120 may interact with or communicate with one or more additional devices, as described in more detail below, through a network interface device. The network interface device may be used to connect the controller 120 to one or more of a variety of networks and one or more devices.Examples of a network interface device include, but are not limited to, a network interface card (e.g., a mobile network interface card, a LAN card), a modem, and any combination thereof. Examples of a network include, but are not limited to, a wide area network (e.g., the Internet, a corporate network), a local area network (e.g., a network associated with an office, a building, a campus, or other relatively small geographic space), a telephone network, a data network associated with a telephone / voice provider (e.g., a data and / or voice network of a mobile communications provider), a direct connection between two computing devices, and any combination thereof. A network may employ a wired and / or wireless communication mode. In general, any network topology can be used. The information (e.g., data, software, etc.)Data can be communicated to and / or from a computer and / or computing device. Controller 120 may include, but is not limited to, for example, a computing device or group of computing devices at a first location and a second computing device or group of computing devices at a second location. Controller 120 may include one or more computing devices. Petition 870250087341, dated 09 / 26 / 2025, page 24 / 277 19 / 88 dedicated to data storage, security, traffic distribution for load balancing, and similar purposes. The 120 controller can distribute one or more computing tasks, as described below, across a plurality of computing devices, which can operate in parallel, serially, redundantly, or in any other manner used for task or memory distribution among computing devices. The 120 controller can be implemented using a non-sharing architecture in which data is cached on the worker; in one mode, this can allow for scalability of the 100 system and / or the computing device.

[032] With continuous reference to Figure 1, a controller 120 can be designed and / or configured to execute any method, method step, or sequence of method steps in any embodiment described in this disclosure, in any order and with any degree of repetition. For example, the controller 120 can be configured to execute a single step or sequence repeatedly until a desired or commanded result is achieved; the repetition of a step or sequence of steps can be performed iteratively and / or recursively using the results of previous repetitions as inputs for subsequent repetitions, so as to aggregate inputs and / or outputs of repetitions to produce an aggregate result, reduction or decrease of one or more variables, such as global variables, and / or division of a larger processing task into a set of smaller processing tasks addressed iteratively.Controller 120 can execute any step or sequence of steps as described in this disclosure in parallel, such as simultaneously and / or substantially simultaneously executing a step two or more times using two or more parallel threads, processor cores, or the like; the division of tasks between threads and / or parallel processes can be performed according to any protocol suitable for dividing tasks between iterations. Persons skilled in the art, upon reviewing the entirety of this disclosure, will be... Petition 870250087341, dated 09 / 26 / 2025, page 25 / 277 20 / 88 aware of the various ways in which steps, sequences of steps, processing tasks and / or data can be subdivided, shared or otherwise handled using iteration, recursion and / or parallel processing.

[033] With continued reference to Figure 1, a controller 120 is configured to receive sensor data 116 from at least one sensor 116 communicatively connected to at least one battery 112. For the purposes of this disclosure, sensor data is data transmitted from at least one sensor 116. As a non-limiting example, sensor data 116 may include a temperature from at least one battery 112 of a temperature sensor 124. As another non-limiting example, sensor data 116 may include a current from at least one battery 112 of an electrical sensor. As yet another non-limiting example, sensor data 116 may include a voltage from at least one battery 112 of an electrical sensor.

[034] With continuous reference to Figure 1, a controller 120 is configured to identify a battery state 128 based on sensor data 116 and a battery limit 132. For the purposes of this disclosure, a battery limit is a limit for sensor data from at least one sensor communicatively connected to at least one battery of an electric aircraft. In one embodiment, a battery limit may include a temperature limit 136. For the purposes of this disclosure, a temperature limit is a limit for the temperature of at least one battery of an electric aircraft. In another embodiment, a battery limit may include a current limit. For the purposes of this disclosure, a current limit is a desirable limit for the current of at least one battery of an electric aircraft. In some embodiments, the battery limit may include a voltage limit.For the purposes of this disclosure, a voltage limit is a limit for the voltage of at least one battery in an electric aircraft. In some embodiments, a user may manually enter the battery limit 132 into the controller 120. For the purposes of this disclosure, a user is any person. Petition 870250087341, dated 09 / 26 / 2025, page 26 / 277 21 / 88 or group using a system 100. As a non-limiting example, a user may include a pilot, a person, a group, or something similar interacting with a remote device in communication with an electric aircraft 104, and similar. In some modes, the battery limit 132 may be retrieved from a database.

[035] With continued reference to Figure 1, the database may be implemented, without limitation, as a relational database, a key-value retrieval database, as a NoSQL database, or any other format or structure for use as a database that a person skilled in the art would recognize as suitable after reviewing the entirety of this disclosure. The database may be implemented, alternatively or additionally, with the use of a distributed data storage protocol and / or data structure, such as a distributed hash table or similar. The database may include a plurality of data entries and / or records, as described above. Data entries in a database may be flagged or linked to one or more additional elements of information, which may be reflected in data entry cells and / or in linked tables, such as tables related by one or more indexes in a relational database.Those skilled in the art, upon reviewing this disclosure in its entirety, will be aware of the various ways in which data entries in a database can store, retrieve, organize, and / or reflect data and / or records as used herein, as well as categories and / or populations of data consistent with this disclosure.

[036] With continued reference to Figure 1, in some embodiments, sensor 116 data outside a battery 132 boundary may indicate damage or an increased likelihood of future damage to an electric aircraft 104 and / or at least one battery 112. As a non-limiting example, the damage may include a thermal runaway. For the purposes of this disclosure, a thermal runaway is a phenomenon in which at least one battery enters an uncontrollable state of Petition 870250087341, dated 09 / 26 / 2025, page 27 / 277 22 / 88 Self-heating. Thermal runaway can occur when at least one 112 battery develops lower resistances or lower trigger voltages as the internal temperature increases. As current flow increases significantly, the increased power dissipation can further raise the temperature. A positive feedback effect from thermal runaway can cause failures such as inefficient use of battery power, lack of battery power, electrical explosion, or fire. In some cases, ejected debris may include, but is not limited to, gas, shrapnel, particles from at least one 112 battery, and the like. In some cases, ejected debris may include lithium-based compounds. Alternatively or additionally, ejected debris may include carbon-based compounds such as, without limitation, carbonate esters.The ejected debris may include matter in any phase or form, including solid, liquid, gas, vapor, and the like. In some cases, the ejected debris may undergo a phase change; for example, the ejected debris may be vaporous while initially ejected and then cool and may condense into a solid or liquid after ejection. As another, non-limiting example, the damage may include the breakdown of electrical insulation. For the purposes of this disclosure, breakdown of electrical insulation refers to a process that occurs when an electrically insulating material, subjected to a sufficiently high voltage, suddenly becomes a conductor and current flows through it. Breakdown of electrical insulation may cause failure of at least one battery 112 and / or an electrical aircraft 104, and fire hazards.

[037] With continuous reference to Figure I, for the purposes of this disclosure, a battery state is the state of at least one electric aircraft battery. In one embodiment, battery state 128 may include an O state. For the purposes of this disclosure, O state indicates that sensor data 116 from at least one sensor is within a battery limit. As a non-limiting example, when a temperature limit 136 is 60 °C (140 °F) and a temperature detected from a temperature sensor 124 connected in a manner Petition 870250087341, dated 09 / 26 / 2025, p. 28 / 277 23 / 88 communicative to at least one 112 battery is 26.7 °C (80 °F), the state of battery 128 may be state 0. As another non-limiting example, when a voltage limit is 2200 V and a voltage detected by an electrical sensor communicatively connected to at least one 112 battery is 150 V, the state of battery 128 may be state 0. Several names may be used to indicate state O and state 1. As another non-limiting example, when a voltage limit is 200 V and a voltage detected from an electrical sensor communicatively connected to at least one 112 battery is 150 V, the state of battery 128 may be state O. In another embodiment, the state of battery 128 may include a state 1. For the purposes of this disclosure, state I indicates that the sensor 116 data from at least one sensor is outside a battery limit.As a non-limiting example, when a temperature limit 136 is 60 °C (140 °F) and a temperature detected by a temperature sensor 124 communicatively connected to at least one battery 112 is 65.6 °C (150 °F), the state of battery 128 may be state 1. As another non-limiting example, when a voltage limit is 200 V and a voltage detected by an electrical sensor communicatively connected to at least one battery 112 is 220 V, the state of battery 128 may be state 1. Persons skilled in the art, upon reviewing the entirety of this disclosure, would appreciate, after reading the entirety of this disclosure, various names that may be used to indicate state 0 and state 1.

[038] With continued reference to Figure 1, in some embodiments, a battery state 128 can be calculated by subtracting the sensor data 116 from a battery threshold 132. In one embodiment, when a value of the subtraction is a positive value, then the battery state 128 can be state 0. As a non-limiting example, when a temperature threshold 136 is 60 °C (140 °F) and a detected temperature from a communicatively connected temperature sensor 124 to at least one battery 112 is 26.8 °C (80 °F), a controller 120 can subtract 26.8 °C (80 °F) from 60 °C (140 °F), resulting in a positive value of 33.2 (60), the battery state 128 can be state 0. Petition 870250087341, dated 09 / 26 / 2025, p. 29 / 277 24 / 88

[039] In another embodiment, when a subtraction value is zero, then the state of battery 128 may be state 1. As a non-limiting example, when a temperature limit 136 is 60 °C (140 °F) and a detected temperature from a communicatively connected temperature sensor 124 to at least one battery 112 is 60 °C (140 °F), a controller 120 may subtract 60 °C (140 °F) from 60 °C (140 °F), which gives 0, the state of battery 128 may be state 1. This occurs when the sensor 116 data includes a temperature of at least one battery 112 and a battery limit 132 includes a temperature limit 136, a zero from the subtraction of sensor 116 data from a battery limit 132 may indicate that there is a problem in at least one battery 112. Thus, this may indicate that a power of at least one 112 battery for at least one 108 flight component may need to be controlled.As another non-limiting example, when a voltage limit is 30 V and a detected voltage from an electrical sensor communicatively connected to at least one battery 112 is 30 V, a controller 120 can subtract 30 V from 30 V, resulting in zero, the state of battery 128 can be state 1. This occurs when sensor 116 data includes a voltage from at least one battery 112 and a battery 132 limit includes a voltage limit; a zero from the subtraction of sensor 116 data from a battery 132 limit may indicate that there is a problem with at least one battery 112. Thus, this may indicate that power from at least one battery 112 to at least one flight component 108 may need to be controlled.As another non-limiting example, when a current limit is 230 mAh and a current detected by an electrical sensor communicatively connected to at least one 112 battery is 230 mAh, a 120 controller can subtract 230 mAh from 230 mAh, which gives zero, the state of battery 128 can be state 1. This occurs when the data from sensor 116 includes a current from at least one 112 battery and a limit from battery 132 includes a current limit, a zero from the subtraction of sensor 116 data from a limit from battery 132 may indicate that there is a problem in at least one 112 battery. Thus, this may indicate that a... Petition 870250087341, dated 09 / 26 / 2025, page 30 / 277 25 / 88 power from at least one battery 112 to at least one flight component 108 may need to be controlled. In another embodiment, when a subtraction value is zero, then the state of battery 128 may be state 0, where the sensor data 116 may be from an electrical sensor and a battery limit 132 may include a resistance limit. As a non-limiting example, when the resistance limit is 400 mOhms and a detected resistance from an electrical sensor communicatively connected to at least one battery 112 is 400 mOhms, a controller 120 may subtract 400 mOhms from 400 mOhms, resulting in zero, the state of battery 128 may be state 0.

[040] With continued reference to Figure 1, in another embodiment, when a subtraction value is a negative value, then the state of battery 128 can be state 1. As a non-limiting example, when a temperature threshold 136 is 60 °C (140 °F) and a detected temperature from a temperature sensor 124 communicatively connected to at least one battery 112 is 71.1 °C (160 °F), a controller 120 can subtract 71.1 °C (160 °F) from 60 °C (140 °F), resulting in a negative value, -11.1 (-20), the state of battery 128 can be state 1. This occurs when the sensor data 116 includes a temperature from at least one battery 112 and a battery threshold 132 includes a temperature threshold 136, a negative value from a subtraction of the sensor data 116 from a A battery limit of 132 may indicate that there is a problem with at least one 112 battery.Thus, this may indicate that a power output of at least one 112 battery for at least one 108 flight component may need to be controlled.

[041] As another non-limiting example, when a voltage limit is 30 V and a detected voltage from an electrical sensor communicatively connected to at least one battery 112 is 35 V, a controller 120 can subtract 35 V from 30 V, resulting in a negative value, -5, the state of battery 128 can be state 1. This occurs when the sensor 116 data includes a voltage from at least one battery 112 and a battery 132 limit includes a voltage limit, Petition 870250087341, dated 09 / 26 / 2025, page 31 / 277 26 / 88 A negative value from subtracting sensor data 116 from a battery limit 132 may indicate that there is a problem with at least one battery 112. Thus, this may indicate that power from at least one battery 112 to at least one flight component 108 may need to be controlled. As another non-limiting example, when a current limit is 230 mAh and a current detected from an electrical sensor communicatively connected to at least one battery 112 is 250 mAh, a controller 120 can subtract 250 mAh from 230 mAh, resulting in a negative value, -20, the state of battery 128 may be state 1. This occurs when sensor 116 data includes a current from at least one battery 112 and a battery 132 limit includes a current limit; a negative value from a subtraction of sensor 116 data from a battery 132 limit may indicate that there is a problem in at least one battery 112.Thus, this may indicate that a power supply of at least one battery 112 to at least one flight component 108 may need to be controlled. In another embodiment, when a subtraction value is a negative value, the state of battery 128 may be state 0, where the sensor data 116 may be from an electrical sensor and a battery limit 132 may include a resistance limit. As a non-limiting example, when the resistance limit is 400 mOhms and a detected resistance from an electrical sensor communicatively connected to at least one battery 112 is 500 mOhms, a controller 120 may subtract 400 mOhms from 500 mOhms, resulting in a negative value, -100, the state of battery 128 may be state 0.

[042] With continued reference to Figure 1, in some embodiments, a controller 120 is configured to control the power of at least one battery 112 to at least one flight component 108 of an electric aircraft 104 as a function of a battery state 128. In some embodiments, the controller 120 can be configured to control the power of at least one battery to at least one flight component 108 by controlling one or more inverters that are communicatively connected to a motor. Petition 870250087341, dated 09 / 26 / 2025, page 32 / 277 27 / 88 electrical. An inverter, as used in this disclosure, is a power electronic device or circuit that changes direct current (DC) to alternating current (AC). An inverter (also called a power inverter) may be entirely electronic or may include at least one mechanism (such as a rotating apparatus) and electronic circuitry. In some embodiments, static inverters may not use moving parts in the conversion process. Inverters may not produce power themselves; instead, inverters may convert power produced by a DC power source. Inverters may often be used in electrical power applications where high currents and voltages are present; circuits that perform a similar function as inverters for electronic signals, with relatively low currents and potentials, may be called oscillators.In some cases, circuits that perform the opposite function to an inverter, converting AC to DC, may be called rectifiers. Further descriptions related to inverters and their use with electric motors are disclosed in Patent Application No. US 17 / 144,304 entitled METHODS AND SYSTEMS FOR A FRACTIONAL CONCENTRATED STATOR CONFIGURED FOR USE IN ELECTRIC AIRCRAFT MOTOR, filed January 8, 2021, by C. Lin et al., the contents of which are incorporated herein by reference. Additional descriptions related to inverters and electric motors are disclosed in Patent Application No. US 17 / 197,427 entitled SYSTEM AND METHOD FOR FLIGHT CONTROL IN ELECTRIC AIRCRAFT by T. Richter et al., filed March 10, 2021, the contents of which are incorporated herein by reference. Additional descriptions relating to an inverter can be found in US Patent Application No. 17 / 852.905, filed on June 29, 2022, and entitled AN APPARATUS AND METHOD FOR OPTIMIZING MOTOR PERFORMANCE IN AN ELECTRIC AIRCRAFT, with attorney registration number 1024-443USU1, the contents of which are incorporated herein in their entirety as such. Petition 870250087341, dated 09 / 26 / 2025, p. 33 / 277 Reference 28 / 88. The electric motor disclosed in this document is described above. In one embodiment, when the state of battery 128 is state 0, controller 120 can be configured to not control the power of at least one battery 112 to flight component 108. In another embodiment, when the state of battery 128 is state 1, controller 120 can be configured to reduce the power of at least one battery 112 to flight components 108. As a non-limiting example, when the state of battery 128 is state 1, controller 120 can reduce the power of at least one battery 112, and this can be a reduction in the current of at least one battery 112. As another non-limiting example, when the state of battery 128 is state 1, controller 120 can reduce the power of at least one battery 112, and this can be a reduction in the voltage of at least one battery 112.As a non-limiting example, when battery 128 is in state 1, controller 120 can reduce the power of at least one battery 112, and this can reduce the revolutions per minute (RPM) of a propeller. As another non-limiting example, when battery 128 is in state 1, controller 120 can reduce the power of at least one battery 112, and this can reduce the torque of a propeller.

[043] With continued reference to Figure 1, in some embodiments, a controller 120 can be configured to control the power of at least one battery 112 as a function of a state weight 140. For the purposes of this disclosure, a state weight is a difference between sensor data and a battery limit. As a non-limiting example, when the subtraction of a sensor data 116 from a battery limit 132 is a positive value of 60, then the state weight 140 is 60. As a non-limiting example, when the subtraction of a sensor data 116 from a battery limit 132 is a negative value, 20, then the state weight 140 is 20. As a non-limiting example, when the subtraction of a sensor data 116 from a battery limit 132 is zero, then the state weight 140 is zero. In some modes, the lower the state weight (140), the more power from at least one battery (112) may need to be reduced. Petition 870250087341, dated 09 / 26 / 2025, page 34 / 277 29 / 88 As a non-limiting example, in the case where a battery state 128 is state 1 and a state weight 140 is 30, where a subtraction of a temperature of at least one battery 112 from a temperature limit 136 is -30, the controller 120 can be configured to reduce more power than in a case where the battery state is state 1 and a state weight 140 is 20, where the subtraction of the temperature of at least one battery 112 from the temperature limit 136 is -20. As another non-limiting example, in the case of a battery state 128 being state 1 and a state weight 140 being 30, where subtracting the voltage of at least one battery 112 from a voltage limit is -30, the controller 120 can be configured to reduce more power than in a case where the battery state is state 1 and a state weight 140 is 20, where subtracting the voltage of at least one battery 112 from the voltage limit is -20.

[044] With continued reference to Figure 1, in some embodiments, a controller 120 can be configured to generate a battery alert 144 based on a battery status 128, status weight 140, and an alert interval 148. For the purposes of this disclosure, a battery alert is an alert to indicate to a user the status of a battery. As a non-limiting example, the battery alert 144 may include battery is overheating, reduce battery power, battery temperature is about to reach a limit, battery status is good and / or battery temperature is within a limit, there is no need to reduce battery power, and the like. As another non-limiting example, the battery alert 144 may include various formats, for example, without limitation, a video, an image, text, audio, vibration, and the like. For the purposes of this disclosure, an “alert interval” is a range of battery weight values.In some modes, a user can manually enter the 148 alert interval into the 120 controller. In some modes, the 148 alert range can be preset.

[045] With continued reference to Figure 1, in one embodiment, a controller Petition 870250087341, dated 09 / 26 / 2025, p. 35 / 277 30 / 88 Controller 120 can be configured to generate a battery alert 144 when a battery state 128 is state 1. As a non-limiting example, when the battery state is state 1, controller 120 can generate battery alert 144 as the battery is overheating and / or reducing a battery's power. In another embodiment, controller 120 can generate battery alert 144 when the battery state is state 0 and the weight of state 140 is outside an alert range 148. As a non-limiting example, when the battery state is state 0, the battery weight is 20, and an alert range 148 is 10, controller 120 can generate battery alert 144 as 'a battery's state is good' and / or 'a battery's temperature is within a limit'. In another mode, controller 120 can generate battery alert 144 when the battery status is state 0 and the weight of state 140 is within the alert range 148.As another non-limiting example, when the battery state is 1 and the battery weight is 5, and the alert interval 148 is 10, the controller 120 can generate battery alert 144 as 'the temperature of a battery is about to reach a limit'. As another non-limiting example, when the battery state is 0 and the battery weight is 10, and the alert interval 148 is 10, the controller 120 can generate battery alert 144 as 'the temperature of a battery is about to reach a limit'.

[046] With continued reference to Figure 1, in some embodiments, a system 100 may include a display device 152. For the purposes of the present disclosure, a display device is a device that transmits information. As a non-limiting example, the display device 152 may include a smartphone, tablet computers, laptop computers, monitors, headphones, and the like. In one embodiment, the display device 152 may transmit information in text format. In some embodiments, the display device 152 may transmit information in video format. In some embodiments, the display device 152 may transmit information in audio format. In some embodiments, the display device 152 may transmit information in animation. In Petition 870250087341, dated 09 / 26 / 2025, page 36 / 277 31 / 88 In some embodiments, a controller 120 can be communicatively connected to the display device 152. In some embodiments, a controller 120 can be configured to display sensor data 116 to a user on the display device. As a non-limiting example, the controller 120 can display the temperature of at least one battery 112. As another non-limiting example, the controller 120 can display the current of at least one battery 112. As another non-limiting example, the controller 120 can display the voltage of at least one battery 112. In some embodiments, the controller 120 can be configured to display a battery alert 144 to a user. As a non-limiting example, the controller 120 can display 'reduce battery power' in text form. As another non-limiting example, the controller 120 can display 'battery is overheating' in audio form.The battery alert 144 disclosed in this document is described in more detail above. In some embodiments, the display may include a screen, a phone, a tablet computer, a laptop computer, a desktop computer, and the like. In some embodiments, the flight controller 120 may display a query to a user. For the purposes of this disclosure, a query is a question. As a non-limiting example, a query may include yes or no. As another non-limiting example, the query may include a question asking what to do to reduce the power of at least one battery 112. For example, the query may ask if a user wants to reduce torque to a propeller, reduce propeller RPM, reduce the voltage of at least one battery 112, and so forth.

[047] With continued reference to Figure 1, in some embodiments, a system may include a user input device 156. For the purposes of this disclosure, a user input device is a device onto which a user can enter user input. For the purposes of this disclosure, user input is any input that a user can enter into a user input device. In one embodiment, the user input device 156 may include a touchscreen. As an example not Petition 870250087341, dated 09 / 26 / 2025, page 37 / 277 32 / 88 limiting, a user can touch a screen to enter user input. In some embodiments, the user input device 156 may include a switch. For the purposes of this disclosure, a switch is an electrical component that can disconnect or connect the conductive path in an electrical circuit. As a non-limiting example, the switch may include a selector switch, rotary switch, mercury switch, push-button switch, reversing switch, relay, circuit breaker, and the like. In some embodiments, the user input device 156 may be communicatively connected to a flight controller 120. In some embodiments, the user input device 156 may be configured to transmit user input to a flight controller 120. In some embodiments, a flight controller 120 may be configured to receive user input from a user input device 156.As a non-limiting example, a user can control a switch to generate user input. In some embodiments, flight controller 120 can then be configured to control the power of at least one battery 112 as a function of user input from user input device 156. For example, with limitation, flight controller 120 can display the query asking a user if the user wants to reduce the power of at least one battery 112. When the user enters 'yes', then flight controller 120 can control the power of at least one battery 112. When the user enters 'no', flight controller 120 can not reduce the power of at least one battery 112. In some embodiments, flight controller 120 can be configured to control the power of at least one battery 112 only after obtaining user input from a user.In some embodiments, flight controller 120 can be configured to control the power of at least one battery 112 without obtaining user input from a user. In some embodiments, the user can respond to a battery alert 144 using the user input device 156. As a non-limiting example, when flight controller 120 displays a battery alert 144 to a user. Petition 870250087341, dated 09 / 26 / 2025, page 38 / 277 33 / 88 on a display device 152 such as 'heated battery', a user can touch a screen to click to reduce the power of at least one battery 112. The flight controller 120 can then control the power of at least one battery 112. In some modes, the user can be a pilot of the electric aircraft.

[048] With continued reference to Figure 1, additionally, without limitation, further description relating to system 100 may be found in U.S. Patent Application No. 17 / 515,433, filed October 30, 2021, and entitled SYSTEMS AND METHODS FOR BATTERY MANAGEMENT FOR A VEHICLE, with attorney registration number 1024-150USU1, the contents of which are incorporated herein in their entirety by reference.

[049] With reference now to Figure 2, battery module 200 with multiple battery units 216 is illustrated, according to the embodiments. Battery module 200 may include a battery cell 204, cell retainer 208, cell guide 212, protective housing, backplate 220, end cap 224 and side panel 228. Battery module 200 may include a plurality of battery cells, one individual of which is labeled 204. In the embodiments, the battery cells 204 may be arranged and / or organized within a respective battery unit 216 in groupings of any number of columns and rows. For example, in the illustrative embodiment of Figure 2, the battery cells 204 are arranged in each respective battery unit 216 with 18 cells in two columns.It should be noted that, although the illustration may be interpreted as containing rows and columns, which represent the groupings of battery cells in a battery unit, the rows are present only as a consequence of the repetitive nature of the staggered pattern of battery cells and battery cell holes in the cell retainer that are aligned in a series. Although in the illustrative embodiment of Figure 2, 204 battery cells are arranged 18 to the 216 battery unit with a plurality of 216 battery units comprising the battery module. Petition 870250087341, dated 09 / 26 / 2025, page 39 / 277 34 / 88 200, a person skilled in the art will understand that the 204 battery cells can be arranged in any number for a row and in any number of columns, and furthermore, any number of battery units can be present in the 200 battery module. According to the embodiments, the 204 battery cells within a first column can be arranged and / or arranged so that they are staggered relative to the 204 battery cells within a second column. In this way, any two adjacent rows of 204 battery cells may not be laterally adjacent, but may be respectively offset by a predetermined distance. In embodiments, any two adjacent rows of 204 battery cells may be offset by a distance equal to the radius of a battery cell. This arrangement of 204 battery cells is only a non-limiting example and in no way excludes other arrangements of battery cells.

[050] Referring again to Figure 2, in some embodiments, the battery cells 204 can be fixed in position by the cell retainer 208. For illustrative purposes within Figure 2, the cell retainer 208 is represented as the negative space between the circles representing the battery cells 204. The cell retainer 208 comprises a sheet comprising circular openings corresponding to the cross-sectional area of ​​an individual battery cell 204. The cell retainer 208 comprises an arrangement of openings indicating the arrangement of the battery cells 204. In embodiments, the cell retainer 208 can be configured to mechanically couple, in a non-permanent manner, to a first end of the battery cell 204.

[051] Referring again to Figure 2, according to the embodiments, the battery module 200 may also comprise a plurality of cell guides 212 corresponding to each battery unit 216. The cell guide 212 may comprise a solid extrusion with cutouts (e.g., cutouts) corresponding to the radius of the cylindrical battery cell 204. The cell guide 212 may be positioned between the two columns of a battery unit 216 of Petition 870250087341, dated 09 / 26 / 2025, page 40 / 277 35 / 88 in such a way as to form a surface (e.g., side surface) of battery unit 216. In embodiments, the number of cell guides 212 may therefore correspond in quantity to the number of battery units 216. The cell guide 212 may comprise a material suitable for heat conduction.

[052] Referring again to Figure 2, battery module 200 may also include a protective enclosure woven between the plurality of battery cells 204. The protective enclosure may provide fire protection, thermal containment and thermal runaway protection during a battery cell malfunction or within the normal operating limits of one or more battery cells 204 and / or potentially the battery module 200 as a whole. Battery module 200 may also include a backplate 220. The backplate 220 is configured to provide structure and encapsulate at least a portion of the battery cells 204, cell retainers 208, cell guides 212 and protective enclosures.The end cap 224 may be configured to encapsulate at least a portion of the battery cells 204, cell retainers 208, cell guides 212, and battery units 216, as will be discussed further below; the end cap may include a protruding ridge that fits into the receivers at both ends of the back plate 220, as well as a similar ridge at a second end that fits into the sensing plate. The side panel 228 may provide another structural element with two opposing and opposite faces and further configured to encapsulate at least a portion of the battery cells 204, cell retainers 208, cell guides 212, and battery units 216.

[053] Referring again to Figure 2, in embodiments, the battery module 200 may include one or more battery cells 204. In another embodiment, the battery module 200 comprises a plurality of individual battery cells 204. The battery cells 204 may each comprise a cell configured to include an electrochemical reaction that produces sufficient electrical energy to power at least part of an electric aircraft. The battery cell 204 may include electrochemical cells, galvanic cells, Petition 870250087341, dated 09 / 26 / 2025, page 41 / 277 36 / 88 electrolytic cells, fuel cells, flow cells, voltaic cells, or any combination thereof—to name a few. In certain configurations, 204 battery cells may be electrically connected in series, in parallel, or in a combination of series and parallel. Series connection, as used in this document, comprises wiring from a first terminal of a first cell to a second terminal of a second cell and is further configured to comprise a single conductive path for electricity to flow while maintaining the same current (measured in Amperes) through any component of the circuit. 204 battery cells may use the term wired, but one with common skill in the art would realize that this term is synonymous with electrically connected and that there are many ways to couple electrical elements such as 204 battery cells.For example, 204 battery cells can be coupled by means of pre-made terminals of a first kind that fit with a second terminal of a second kind. Parallel connection, as used in this document, comprises wiring a first and second terminal of a first battery cell to a first and second terminal of a second battery cell and further configured to comprise more than one conductive path for electricity to flow while maintaining the same voltage (measured in Volts) in any component of the circuit. 204 battery cells can be connected in a series parallel circuit that combines characteristics of the constituent circuit types to that combined circuit. 204 battery cells can be electrically connected in any arrangement which can confer to the system the electrical advantages associated with that arrangement, such as high voltage applications, high current applications or the like.As used in this document, an electrochemical cell is a device capable of generating electrical energy from chemical reactions or of using electrical energy to cause chemical reactions. Furthermore, voltaic or galvanic cells are electrochemical cells that generate electric current from chemical reactions, while electrolytic cells... Petition 870250087341, dated 09 / 26 / 2025, page 42 / 277 37 / 88 generate chemical reactions through electrolysis. As used in this document, the term battery refers to a collection of cells connected in series or parallel to each other.

[054] Referring again to Figure 2, according to the embodiments and as discussed above, any two rows of battery cells 204 and therefore the openings of the cell retainer 208 are offset half a length so that two battery cells 204 are not directly next to each other along the length of the battery module 200; this is the staggered arrangement shown in the illustrated embodiment of Figure 2. The cell retainer 208 may employ this staggered arrangement to allow more cells to be arranged closer to each other than in square columns and rows, as in a grid pattern. The staggered arrangement may also be configured to allow better thermodynamic dissipation, methods of which may be revealed later. The cell retainer 208 may include staggered openings that align with the battery cells 204 and are still configured to hold the battery cells 204 in fixed positions.Cell retainer 208 may comprise an injection-molded component. The injection-molded component may comprise a component manufactured by injecting a liquid into a mold and allowing it to solidify so as to take the shape of the mold in its hardened form. Cell retainer 208 may include liquid crystal polymer, polypropylene, polycarbonate, acrylonitrile butadiene styrene, polyethylene, nylon, polystyrene, polyether ether ketone, to name a few. Cell retainer 208 may include a second cell retainer attached to the second end of battery cells 204 and configured to hold battery cells 204 in place at both ends. The second cell retainer may include similar or exactly the same features and functions as the first cell retainer 208. Battery module 200 may also include cell guide 212. Cell guide 212 includes material disposed between two rows of battery cells 204.In certain modes, the 212 cell guide can be configured to distribute heat. Petition 870250087341, dated 09 / 26 / 2025, page 43 / 277 38 / 88 which can be generated by the cells of battery 204.

[055] Still referring to Figure 2, battery module 200 may also include backplate 220. Backplate 220 is configured to provide a base structure for battery module 200 and may encapsulate at least a portion thereof. Backplate 220 may have any shape and includes opposite and opposing sides with a thickness between them. In embodiments, backplate 220 may comprise an effectively flat rectangular prism-shaped sheet. For example, backplate 220 may comprise one side of a larger rectangular prism that characterizes the shape of battery module 200 as a whole. Backplate 220 also comprises openings correlated to each battery cell 204 of the plurality of battery cells 204. Backplate 220 may comprise a multi-layer lamination.The layers that are laminated together may comprise FR-2, a glass fiber reinforced epoxy laminate material, and a thermal barrier of a similar or exactly the same type as disclosed above. The backplate 220 may be configured to provide structural support and containment of at least a portion of the battery module 200, as well as provide fire and thermal protection.

[056] Referring again to Figure 2, the battery module 200 may also comprise the first end cap 224 configured to encapsulate at least part of the battery module 200. The end cap 224 may provide structural support for the battery module 200 and hold the back plate 220 in a fixed relative position compared to the overall battery module 200. The end cap 224 may comprise a projecting ridge at a first end that engages and locks into a receiving feature at a first end of the back plate 220. The end cap 224 may include a second projecting ridge at a second end that engages and locks into a receiving feature on the sensing plate.

[057] Referring again to Figure 2, battery module 200 may also comprise at least one side panel 228 which may encapsulate two sides Petition 870250087341, dated 09 / 26 / 2025, page 44 / 277 39 / 88 of battery module 200. Side panel 228 may comprise opposing and contrary faces comprising a metal or composite material. In the illustrative embodiment of Figure 2, a second side panel 228 is present but not illustrated so that the interior of battery module 200 may be shown. Side panel(s) 228 may provide structural support for battery module 200 and provide a barrier to separate battery module 200 from external components within the aircraft or environment.

[058] Referring now to Figure 3, a perspective drawing of an embodiment of a battery pack with a plurality of battery modules arranged therein 300. The configuration of the battery pack 300 is merely exemplary and should in no way be considered limiting. The battery pack 300 is configured to facilitate the flow of medium through each battery module of the plurality of battery modules to cool the battery pack. The battery pack 300 may include one or more 304A-N battery modules. The battery pack 300 is configured to house and / or enclose one or more 304A-N battery modules. Each battery module of the plurality of 304A-N battery modules may include any battery module as described in more detail in the entirety of this disclosure.As an exemplary embodiment, Figure 3 illustrates 7 304A-N battery modules forming the 300 battery pack; however, a person with ordinary skill in the field would understand that any number of 304A-N battery modules can be housed within the 300 battery pack. In one embodiment, each battery module of the plurality of 304A-N battery modules may include one or more 308A-N battery cells. Each 304A-N battery module is configured to house and / or enclose one or more 308A-N battery cells. Each battery cell of the plurality of 308A-N battery cells may include any battery cell, as described in more detail in the entirety of this disclosure. The 308A-N battery cells may be configured to be contained within each 304A-N battery module, wherein each 308A-N battery cell is arranged in any configuration without... Petition 870250087341, dated 09 / 26 / 2025, page 45 / 277 40 / 88 limitation. As an exemplary embodiment, Figure 3 illustrates 240 308A-N battery cells housed within each 304A-N battery module; however, a person with ordinary skill in the field would understand that any number of 308A-N battery units can be housed within each 304A-N battery module of the 300 battery pack. Furthermore, each battery module of the plurality of 304A-N battery modules of the 300 battery pack includes circuit 312. Circuit 312 may include any circuit as described in greater detail throughout this disclosure. Each battery module of the plurality of 304A-N battery modules further includes the second circuit 316. The second circuit 316 may include any circuit as described in greater detail throughout this disclosure.Those skilled in the art, upon reviewing this entire disclosure, will be aware of various configurations of the plurality of battery modules that can be used for the battery pack in a manner consistent with this disclosure.

[059] Referring again to Figure 3, in some embodiments, a battery unit may be configured to couple to one or more other battery units, wherein the combination of two or more battery units forms at least part of the vehicle battery and / or charging battery. The battery unit may be configured to include a plurality of battery cells. The plurality of battery cells may include any battery cell, as described in the entirety of this disclosure. In the instant embodiment, for example and without limitation, the battery unit includes a first row of battery cells, wherein the first row of battery cells is in contact with the first side of the thermal conduit, as described in more detail below. As a non-limiting example, the row of battery cells is configured to contain ten columns of battery cells.Furthermore, in the instantaneous mode, for example and without limitation, the battery unit includes a second row of battery cells, wherein the second row of battery cells is in contact with the second side of the thermal conduit, as described in more detail below. As an example, no. Petition 870250087341, dated 09 / 26 / 2025, page 46 / 277 41 / 88 limiting, the second row of battery cells is configured to contain ten columns of battery cells. In some embodiments, the battery unit may be configured to contain twenty battery cells in the first and second rows. The battery cells of the battery unit may be arranged in any configuration, so that the battery unit may contain any number of rows of battery cells and any number of columns of battery cells. In embodiments, the battery unit may contain any offset distance between the first row of battery cells and the second row of battery cells, wherein the battery cells of the first row and the battery cells of the second row are not centered on each other.In instantaneous mode, for example and without limitation, the battery unit includes the first row and the adjacent second row, each containing ten battery cells, each battery cell in the first row and each battery cell in the second row being offset by a length corresponding to the radius of a battery cell, wherein the center of each battery cell in the first row and each battery cell in the second row being separated from the center of the battery cell in the adjacent column by a length equal to the radius of the battery cell.As a further example and without limitation, each battery cell in the first row and each battery cell in the second row are offset by a length equivalent to one-quarter of the diameter of each battery cell, wherein the center of each battery cell in the first row and each battery cell in the second row are separated from the center of a battery cell in the adjacent column by a length equal to one-quarter of the diameter of the battery cell. The first row of battery cells and the second row of battery cells of the plurality of battery units may be configured to be fixed in one position using a cell retainer, as described in full in this disclosure. Each battery cell may be connected using any means of connection, as described in full in this disclosure. In some embodiments, the battery unit may include thermal conduit, wherein the thermal conduit has a... Petition 870250087341, dated 09 / 26 / 2025, page 47 / 277 42 / 88 first surface and a second opposite and contrary surface. In some cases, the height of the thermal conduit may not exceed the height of the battery cells, as described in the entirety of this disclosure. For example, and without limitation, the thermal conduit may be at a height that is equal to the height of each battery cell in the first and second rows. The thermal conduit is configured to include a recess in the component for each battery cell coupled to the first surface and / or the second surface of the thermal conduit. Persons skilled in the art, upon reviewing this entire disclosure, will be aware of components that may be used as thermal conduits in a manner consistent with this disclosure.

[060] Referring again to Figure 3, in some embodiments, the thermal conduit may include at least one passage, wherein the plurality of passages comprises an opening that begins at the first end of the thermal conduit and terminates at a second opposite end of the thermal conduit. The passage, as described in this document, is a horizontal channel with openings at each end of the thermal conduit. The plurality of passages may be configured to have a hollow form comprising one or more sides, at least two ends (e.g., a top and a bottom) and a length, wherein the hollow form comprises a void having a shape equal to or different from the shape of the plurality of passages and terminates at an opposite end, opposite the second end of the form. For example and without limitation, in some embodiments, the plurality of passages comprises a tubular form in the shape of a rectangle.In the embodiments, the tubular component effectively travels perpendicular to each battery cell. In the embodiments, the plurality of passages may be arranged in such a way as to form a void that originates on one side of the battery module and terminates on the second, opposite side of the battery module. According to the embodiments, the plurality of passages and / or thermal conduits may be composed of any suitable material. For example, and without limitation, the thermal conduit and / or the plurality of passages. Petition 870250087341, dated 09 / 26 / 2025, p. 48 / 277 43 / 88 may be composed of polypropylene, polycarbonate, acrylonitrile butadiene styrene, polyethylene, nylon, polystyrene, polyether ether ketone and the like.

[061] Referring again to Figure 3, in some embodiments, the plurality of passage may be arranged in the thermal conduit such that the plurality of passage is configured to allow the displacement of a medium from a first end of the thermal conduit to the second, opposite end of the thermal conduit. For example, the plurality of passage may be arranged to allow the passage of media through the hollow opening / void of the plurality of passage. The media may include any media, as described in the entirety of this disclosure. The hollow opening of the thermal conduit and / or the plurality of passage may be configured to be of any size and / or diameter. For example, and without limitation, the hollow opening of the plurality of passage may be configured to have a diameter equal to or less than the radius of each battery cell.The thermal conduit and / or multiple passage may have a length equal to or less than the length of a row of battery cells, such that the thermal conduit and / or multiple passage is configured not to exceed the length of the first row and / or second row of battery cells. The opening of the multiple passage may be configured to be disposed at each end of the thermal conduit, wherein the multiple passage may be in contact with each battery cell in a respective battery unit located at the end of each column and / or row of the battery unit. For example, and without limitation, in some embodiments, a battery unit may contain two rows with ten columns of battery cells and the opening of the multiple passage at each end of the thermal conduit that is in contact with a respective battery cell at the end of each of the two columns.Those versed in the technique, upon reviewing this entire revelation, will be aware of several components that can be used as at least one passage in a manner consistent with this revelation.

[062] Still referring to Figure 3, in some modalities, the circuit and / or Petition 870250087341, dated 09 / 26 / 2025, p. 49 / 277 44 / 88 thermal conduit can be configured to facilitate the flow of media through each battery module of the plurality of battery modules to cool the battery pack. The media may include any media described in more detail throughout this disclosure. The circuit may include any circuit as described above in more detail. In this embodiment, the circuit may be configured to couple to a first end of the thermal conduit, wherein the coupling is configured to facilitate the flow of the circuit medium to the first end of the thermal conduit through the plurality of passages. The coupling may include any coupling as described in more detail throughout this disclosure. The circuit may include any component configured to facilitate the flow of media to the battery pack using an electrical current.For example, and without limitation, the circuit may include a printed circuit board, wherein the printed circuit board mechanically supports the electrical connection, which facilitates the flow of media to the battery pack. The circuit may be configured to include a first end and a second end, wherein the second end is opposite the first end of the circuit. In some embodiments, the first end of the circuit is in a plane perpendicular to the longitudinal geometric axis of the thermal conduit. The first end of the circuit is configured to include the media power supply component. The circuit embodiment illustrates the media power supply component arranged only on the first side of the circuit; however, this is not limiting, and the circuit may include the media power supply component arranged at the second end of the circuit.The circuit's media power supply component can be configured to allow media to power the circuit, battery module, and / or battery pack, wherein the media flow can be initiated by coupling the circuit's media power supply component to the thermal management device's media feeder. The media power supply component can include any media power supply component as described in more detail above. In some embodiments, the component... Petition 870250087341, dated 09 / 26 / 2025, page 50 / 277 45 / 88 media feed is a threaded hole, where the media feeder of the thermal management device is configured to engage with the threaded hole of the media feed component, however, this is not limiting and the media feed component may include, without limitation, a magnetic component, a locking mechanism, a pressure-adjusting piping mechanism, a nozzle mechanism, an orifice, a flap and the like.

[063] Referring again to Figure 3, in some embodiments, the thermal conduit may include any thermal conduit, as described in more detail above. The height of the thermal conduit may not exceed the height of each battery cell of the plurality of battery cells, in some cases, as described in full in this disclosure. The thermal conduit may be composed of any suitable material, as described in more detail above. The thermal conduit may be configured to include any curvature of the first and / or second side of the thermal conduit. For example, and without limitation, the curvature of the first and / or second side of the thermal conduit correlates at least a portion of a battery cell of the plurality of battery cells.As a further example and without limitation, in one embodiment, the thermal conduit may be configured to include ten bends on the first surface of the thermal conduit, wherein each bend is configured to contain the plurality of portions of each battery cell from the plurality of battery cells adjacent to the first surface of the thermal conduit. As a further example and without limitation, in some embodiments, the thermal conduit may be configured to include ten bends on the second surface of the thermal conduit, wherein each bend may be configured to contain the plurality of portions of each battery cell from the plurality of battery cells adjacent to the second surface of the thermal conduit. The thermal conduit embodiment illustrates ten bends on each surface of the thermal conduit; however, this is not limiting, and the thermal conduit may include any number of bends on each surface of the thermal conduit, wherein each bend corresponds to the plurality of. Petition 870250087341, dated 09 / 26 / 2025, page 51 / 277 46 / 88 portions of a battery cell from a plurality of battery cells.

[064] Referring again to Figure 3, in some embodiments, the thermal conduit may include any thermal conduit, as described in more detail above. As described in more detail above, the thermal conduit may be composed of any suitable material. Furthermore, the thermal conduit may be configured to include any curvature of the first and / or second side of the thermal conduit, as described in more detail above. The thermal conduit may be configured for at least one passage. The plurality of passage may include at least one passage, as described in more detail above.The passage plurality is configured to have a hollow form comprising one or more sides, at least two ends (e.g., an upper and a lower one), and a length, wherein the hollow form comprises a void with a shape equal to or different from the form of the passage plurality and terminates at an opposite end, opposite the second end of the form, as described above in more detail. For example and without limitation, in the illustrative embodiment, the passage plurality comprises a tubular form in the shape of a rectangle. In the embodiments, the tubular component is effectively disposed perpendicular to each battery cell and / or to the curvature of the thermal conduit configured to house each battery cell.In the embodiments, the passage plurality can be arranged so as to form a void that originates on one side of the battery module and terminates on the other, opposite side of the battery module, as described in more detail in the entirety of this disclosure. According to the embodiments, the passage plurality and / or thermal conduit can be composed of any suitable material, as described in more detail above. In the embodiments, the passage plurality can be arranged in the thermal conduit such that the passage plurality can be configured to allow the displacement of a medium from one end of the thermal conduit to the other, opposite end of the thermal conduit, as described in more detail. Petition 870250087341, dated 09 / 26 / 2025, page 52 / 277 47 / 88 details in full of this revelation.

[065] Referring now to Figure 4, Figure 4 illustrates a block diagram of an exemplary 400 battery pack to prevent the progression of thermal runaway between modules. The 400 battery pack may include a 404A-B bag cell. As used in this disclosure, a bag cell is a battery cell or module that includes a bag. In some cases, a bag cell may include or be called a prismatic bag cell, for example, when a general bag shape is prismatic. In some cases, a bag cell may include a bag that is substantially flexible. Alternatively or additionally, in some cases, the bag may be substantially rigid. The 404A-B bag cell may include at least one 408A-B electrode pair. At least one 408A-B electrode pair may include a positive electrode and a negative electrode. Each electrode of at least one 408A-B electrode pair may include an electrically conductive element.Exemplary but not limiting electrically conductive elements include stranded wire, solid wire, metal foil, circuits such as printed circuit boards and the like. At least one pair of 408A-B electrodes may be in electrical communication and / or electrically connected to at least one pair of 412A-B aluminum tabs. At least one pair of 408A-B electrodes may be connected in electrical communication and / or electrically connected to at least one pair of 412A-B foil tabs by any known method, including, without limitation, welding, brazing, soldering, adhesion, engineering adjustments, electrical connectors and the like. In some cases, at least one pair of foil tabs may include a cathode and an anode. In some cases, an exemplary cathode may include a lithium-based substance, such as lithium-metal oxide, connected to an aluminum foil tab. In some cases, an exemplary anode may include a carbon-based substance, such as graphite, connected to a copper tab.A 404A-B pocket cell may include a 416A-B insulating layer. As used in this disclosure, an insulating layer is an electrically insulating material that is substantially permeable to battery ions, such as, without limitation, lithium ions. Petition 870250087341, dated 09 / 26 / 2025, page 53 / 277 48 / 88 In some cases, the insulating layer may be called a separating layer or simply a separator. In some cases, the 416A-B insulating layer is configured to prevent direct electrical communication between at least one pair of 412A-B foil tabs (e.g., cathode and anode). In some cases, the 416A-B insulating layer may be configured to allow ion flow through it. The 416A-B insulating layer may consist of a polymer, such as, without limitation, polyolifin (PO). The 416A-B insulating layer may include leaks that are configured to allow the passage of ions, for example, lithium ions. In some cases, leaks in a 416A-B PO insulating layer may have a width not exceeding 100 µm, 10 µm, 1 µm, or 0.1 µm. In some cases, a PO 41 6A-B insulating layer may have a thickness within a range of 1-100 µm or 10-50 µm.

[066] Referring again to Figure 4, the 404A-B bag cell may include a 420A-B bag. The 420A-B bag may be configured to substantially cover at least one pair of 412A-B foil flaps and at least part of the 416A-B insulating layer. In some cases, the 420A-B bag may include a polymer, such as, without limitation, polyethylene, acrylic, polyester, and the like. In some cases, the 420A-B bag may be coated with one or more coatings. For example, in some cases, the bag may have an outer surface coated with a metallizing coating, such as a coating containing aluminum or nickel. In some cases, the bag coating may be configured to ground and / or electrically insulate the bag, increase the impermeability of the bags, increase the resistance of the bags to high temperatures, increase the thermal resistance of the bags (insulation), and the like. An electrolyte 424A-B is located inside the bag.In some cases, the 424A-B electrolyte may comprise a liquid, a solid, a gel, a paste, and / or a polymer. The electrolyte may wet or come into contact with one or both of at least one pair of 412A-B aluminum pellets.

[067] Still referring to Figure 4, battery 400 may additionally include an ejected material barrier 428. The ejected material barrier may be Petition 870250087341, dated 09 / 26 / 2025, p. 54 / 277 49 / 88 located substantially between a first 404A bag cell and a second 404B bag cell. As used in this disclosure, an ejected material barrier is any material or structure configured to substantially block, contain, or impede the passage of ejected material. As used in this disclosure, ejected material is any material that has been ejected, for example, from a battery cell. In some cases, the ejected material may be ejected during thermal runaway from a battery cell. Alternatively or additionally, in some cases, the ejected material may be ejected without thermal runaway from a battery cell. In some cases, the ejected material may include lithium-based compounds. Alternatively or additionally, the ejected material may include carbon-based compounds, such as, without limitation, carbonate esters.The ejected material may include matter in any phase or form, including solid, liquid, gas, vapor, and the like. In some cases, the ejected material may undergo a phase change; for example, the ejected material may be vaporous while initially ejected and then cool and condense into a solid or liquid after ejection. In some cases, the ejected material barrier may be configured to prevent ejected materials from a first 404A bag cell from coming into contact with a second 404B bag cell. For example, in some cases, the 428 ejected material barrier is substantially impermeable to ejected material from the 404A-B battery bag cell. In some embodiments, the 428 ejected material barrier may include titanium. In some embodiments, the 428 ejected material barrier may include carbon fiber.In some cases, the ejected material barrier 428 may include at least one layer of a lithophilic or lithiophobic material or layer, configured to absorb and / or repel lithium-based compounds. In some cases, the ejected material barrier 428 may include a lithophilic metal coating, such as silver or gold. In some cases, the ejected material barrier 428 may be flexible and / or rigid. In some cases, the ejected material barrier 428 may include a sheet, a film, a foil, or something similar. For example, in some... Petition 870250087341, dated 09 / 26 / 2025, page 55 / 277 In cases 50 / 88, the ejected material barrier may have a thickness between 25 and 5000 micrometers. In some cases, an ejected material barrier may have a nominal thickness of about 2 mm. Alternatively or additionally, in some cases, an ejected material barrier may include rigid and / or structural elements, for example, which are solid. Rigid ejected material barriers 428 may include metals, composites, and the like. In some cases, the ejected material barrier 428 may be further configured to structurally support at least one bag cell 428. For example, in some cases, at least one bag cell 428 may be mounted on a rigid ejected material barrier 428.

[068] Referring again to Figure 4, the battery pack 400 may additionally include at least one vent 432A-B. In some cases, at least one vent 432A may be configured to vent the ejected material from the first bag cell 404A. In some cases, at least one vent 404A may be configured to vent the ejected material along a flow path 436A. A flow path 436A may substantially exclude the second bag cell 404B, for example, fluids such as gases, liquids or any material acting as a gas or liquid, flowing along the flow path 436A may be isolated from contact with the second bag cell 404B. For example, the flow path 436A may be configured so as not to intersect with any surface of the second bag cell 404B.The 436A-B flow path may include any channel, tube, hose, conduit, or similar suitable for facilitating fluid communication, for example with a 404A-B battery bag cell. In some cases, the 436A-B flow path may include a check valve. As used in this disclosure, a check valve is a valve that allows fluid flow only in a certain direction, for example, one direction. In some cases, the check valve may be configured to allow fluid flow substantially only away from the 404A-B battery bag cell, while preventing backflow of vented fluid into the battery bag cell. Petition 870250087341, dated 09 / 26 / 2025, page 56 / 277 51 / 88 404A-B. In some cases, the check valve may include a duckbill check valve. In some cases, a duckbill check valve may have lips that are substantially in the shape of a duckbill. The lips may be configured to open to allow forward flow (out of the lips), while remaining normally closed to prevent backflow (into the lips). In some cases, the duckbill lips may be configured to close automatically (remain normally closed), for example, with the use of a compatible element such as, without limitation, an elastomeric material, a spring, and the like. In some embodiments, the vent may include a poppet-type mushroom valve. In some cases, a mushroom trigger valve may include a mushroom-shaped trigger. The mushroom-shaped trigger may seal against a sealing element, for example, a ring around the bottom of a mushroom-shaped trigger cap.In some cases, the mushroom-type shutter valve may be loaded against the sealing element, for example, by means of a flexible element such as a spring. According to some embodiments, the 432A-B vent may have a vacuum applied to assist in venting the ejected material. The vacuum pressure differential may vary from 0.34 kPa (0.1 Hg) to 121.91 kPa (36 Hg).

[069] Referring again to Figure 4, battery 400 may include a first battery bag cell 404A and a second battery bag cell 404B. The first bag cell 404A may include at least one first pair of electrodes 408A, at least one first pair of foil tabs 412A in electrical communication with the first electrodes 408A, at least one first insulating layer 416A located substantially between the plurality of the first pair of foil tabs 412A, a first bag 420A encompassing substantially the plurality of the first pair of foil tabs 412A and at least a portion of the plurality of the first separating layer 416A, and a first electrolyte 424A within the first bag 420A. The second bag cell 404B may include at least one second pair of electrodes 408B, at least Petition 870250087341, dated 09 / 26 / 2025, page 57 / 277 52 / 88 a second pair of foil tabs 412B in electrical communication with the first electrodes 408B, at least one second insulator 416B located substantially between the plurality of the first pair of foil tabs 412B, a second bag 420B encompassing substantially the plurality of the second pair of foil tabs 412B and at least a portion of the plurality of the second insulator 416B, and a second electrolyte 424B within the second bag 420B. The battery 400 may include an ejected material barrier 428 located substantially between the first cell of bag 404A and the second cell of bag 404B. The ejected material barrier 428 may be substantially impermeable to ejected material, for example, ejected material from the first cell of bag 404A. In some cases, the 400 battery pack may include a vent configured to vent ejected materials, for example from the first 404A bag cell.In some embodiments, the ejected material barrier 428 may substantially encapsulate at least a portion of the bag cell 404A-B. For example, the ejected material barrier 428 may substantially encapsulate the first bag cell 404A. In some cases, the vent may be configured to provide fluidic communication through at least one of the ejected material barriers 428 and bag 420A-B. In some cases, the vent may include a seam. The seam may be a bag seam 420A-B. Alternatively or additionally, the seam may be an ejected material barrier 428 seam.

[070] Referring again to Figure 4, in some embodiments the 400 battery pack may additionally include a third pouch cell. The third pouch cell may include at least a third pair of electrodes, at least a third pair of foil tabs welded to the third electrodes, at least a third insulating layer situated substantially between the plurality of the third pair of foil tabs, a third pouch that substantially encloses the plurality of the third pair of foil tabs and the plurality of the third separating layer, and a third electrolyte within the third pouch. The battery pack may include a plurality that includes any number of Petition 870250087341, dated 09 / 26 / 2025, p. 58 / 277 53 / 88 bag cells. In some cases, each bag cell of the bag cell plurality is separated from adjacent bag cells with at least one ejected material barrier 428. Any bag cell of a bag cell plurality in a battery pack may include any component described in this disclosure, for example, without limitation, vents, valves and the like.

[071] Referring again to Figure 4, in some embodiments, 404A-B pocket cells may include lithium-ion batteries which may include NCA, NMC, lithium iron phosphate (LiFePO4) and lithium manganese oxide (LMO) batteries, which may be mixed with other cathode chemistry to provide more specific power if the application requires lithium metal batteries, which have a lithium metal anode that provides high power on demand, lithium-ion batteries which have a silicon anode, tin nanocrystals, graphite, graphene or titanate, or the like.Batteries and / or battery modules may include, without limitation, batteries using nickel-based chemistries such as nickel-cadmium or nickel-metal hydride, batteries using lithium-ion battery chemistries such as nickel-cobalt-aluminum (NCA), nickel-manganese-cobalt (NMC), lithium iron phosphate (LiFePO4), lithium cobalt oxide (LCO) and / or lithium manganese oxide (LMO), batteries using lithium polymer technology, metal-air batteries. 404A-B pocket cells may include lead-based batteries such as, without limitation, lead-acid batteries and lead-carbon batteries. 404A-B pocket cells may include lithium-sulfur batteries, magnesium-ion batteries and / or sodium-ion batteries. Batteries may include solid-state batteries or supercapacitors or other suitable power source. Batteries may be primary or secondary or a combination of both.Further disclosures relating to batteries and battery modules can be found in the U.S. Patent Applications entitled SYSTEM AND METHOD FOR HIGH ENERGY DENSITY BATTERY MODULE and SYSTEMS AND METHODS FOR RESTRICTING POWER TO A LOAD TO PREVENT ENGAGING CIRCUIT. Petition 870250087341, dated 09 / 26 / 2025, page 59 / 277 54 / 88 PROTECTION DEVICE FOR AN AIRCRAFT, which have Patent Applications No. 16 / 948,140 and No. 16 / 590,496, respectively; the entirety of both applications is incorporated herein by reference. Those skilled in the art, upon a complete review of this disclosure, will be aware of various component devices that can be used as a battery module. In some cases, the 400 battery pack is constructed in such a way as to vent the ejected material while preventing the ejected material from one bag cell from interacting with another bag cell.

[072] Referring again to Figure 4, the battery pack 400 may include at least one sensor 440. At least one sensor 440 may include a set of sensors, for example, as described above. In some cases, at least one sensor 440 may be configured to detect battery data and transmit battery data to a data storage system, for example, as described above.

[073] Referring now to Figure 5, one embodiment of the battery management system 500 is presented. The battery management system 500 is integrated into a battery pack configured for use in an electric aircraft. The battery management system 500 is integrated into a part of the battery pack or subassembly thereof, which will be revealed in more detail with reference to Figures 4-6. The battery management system 500 includes the first battery management component 504 disposed at a first end of the battery pack. A person of ordinary skill in the art will understand that there are various areas in and on a battery pack and / or subassemblies thereof that may include the first battery management component 504. The first battery management component 504 may assume any suitable form.In a non-limiting embodiment, the first 504 battery management component may include a circuit board, such as a printed circuit board and / or integrated circuit board, a subassembly mechanically coupled to at least part of the battery pack, or stand-alone components. Petition 870250087341, dated 09 / 26 / 2025, page 60 / 277 55 / 88 coupled in a communicative manner with each other or other undisclosed arrangement of components; for example, and without limitation, several components of the first battery management component 504 may be soldered or otherwise electrically connected to a circuit board. The first battery management component may be arranged directly on, adjacent to, facing and / or near a battery module and, specifically, at least a part of a battery cell. The first battery management component 504 includes the first set of sensors 508. The first set of sensors 508 is configured to measure, detect, capture and transmit the first plurality of data from the battery pack 528 to the data storage system 520, which will be disclosed in more detail with reference to Figure 9.

[074] Referring again to Figure 5, the battery management system 500 includes the second battery management component 512. The second battery management component 512 is disposed at or on a second end of the battery pack 524. The second battery management component 512 includes the second sensor set 516. The second sensor set 516 may be consistent with the description of any sensor set disclosed herein. The second sensor set 516 is configured to measure the second data plurality of the battery pack 532. The second data plurality of the battery pack 532 may be consistent with the description of any battery pack data disclosed herein. The second data plurality of the battery pack 532 may additionally or alternatively include data not measured or recorded in another section of the battery management system 500.The second set of data from battery pack 532 can be communicated to additional or alternative systems to which it is coupled in a communicative manner. The second set of sensors 516 includes a humidity sensor consistent with any humidity sensor disclosed herein, namely, humidity sensor 804. Petition 870250087341, dated 09 / 26 / 2025, page 61 / 277 56 / 88

[075] Referring again to Figure 5, the first battery management component 504 disposed on or over the battery pack 524 can be physically isolated from the second battery management component 512 also disposed on or over battery pack 524. Physical isolation, for the purposes of this disclosure, refers to the components of a first system, communicative coupling and any other constituent parts, whether software or hardware, being separated from the components of a second system, communicative coupling and any other constituent parts, whether software or hardware, respectively. The first battery management component 504 and the second battery management component 508 may perform the same functions or different functions in the battery management system 500. In a non-limiting embodiment, the first and second battery management components perform the same functions and are therefore redundant.If, for example, the first battery management component 504 malfunctions, in whole or in part, the second battery management component 508 may still function correctly, and therefore the battery management system 500 may still operate and function correctly for electric aircraft in which it is installed. Furthermore, or alternatively, the second battery management component 508 may power on while the first battery management component 504 is faulty. Anyone with average technical skill would understand that the terms "first" and "second" do not refer to battery management components as primary or secondary.In non-limiting embodiments, the first battery management component 504 and the second battery management component 508 may be connected and operate through the same ground operations of an electric aircraft and through the same flight envelope of an electric aircraft. This does not prevent one battery management component, the first battery management component 504, from replacing the second battery management component 508 if it malfunctions. Petition 870250087341, dated 09 / 26 / 2025, page 62 / 277 In non-limiting embodiments, the first and second battery management components, due to their physical isolation, may be configured to withstand malfunctions or failures in the other system and survive and operate. Provisions may be made to protect the first battery management component 504 from the second battery management component 508, except for physical location, such as circuit structures and fuses. In non-limiting embodiments, the first battery management component 504, the second battery management component 508, or their subcomponents may be arranged in an internal component or set of components within the battery pack 524, such as on the battery module detection board.

[076] Referring again to Figure 5, the first battery management component 504 can be electrically isolated from the second battery management component 508. Electrical isolation, for the purposes of this disclosure, refers to the separation of components of a first system that carry electrical signals or electrical energy from the components of a second system. The first battery management component 504 may suffer an electrical catastrophe, which renders it inoperable, and, due to the electrical isolation, the second battery management component 508 can still continue to operate and function normally, so as to manage the battery pack of an electric aircraft. Shielding, such as structural components, material selection, a combination thereof, or another undisclosed method of electrical isolation and insulation, may be used, in non-limiting embodiments.For example, a rubber component or other electrically insulating material may be placed between the electrical components of the first and second battery management components, so as to prevent electrical energy from being conducted through it, thus isolating the first and second battery management components from each other.

[077] Still referring to Figure 5, the battery management system 500 includes a data storage system 520. The storage system Petition 870250087341, dated 09 / 26 / 2025, page 63 / 277 Data storage system 520 is configured to store the first battery pack data plurality 528 and the second battery pack data plurality 532. Data storage system 520 may include a database. Data storage system 520 may include a solid-state memory or tape hard disk. Data storage system 520 may be communicatively coupled to the first battery management component 504 and the second battery management component 512 and may be configured to receive electrical signals related to measured physical or electrical phenomena and store these electrical signals as first battery pack data 528 and second battery pack data 532, respectively. Alternatively, data storage system 520 may include more than one discrete data storage system that are physically and electrically isolated from each other.In this non-limiting embodiment, each of the first battery management components 504 and the second battery management component 512 can separately store the data of the first battery pack 528 and the data of the second battery pack 532. A person with ordinary skill in the art would understand the virtually unlimited arrangements of data storage with which the battery management system 500 could employ to store the first and second plurality of battery pack data.

[078] Referring again to Figure 5, the data storage system 520 stores the first plurality of battery pack data 528 and the second plurality of battery pack data 532. The first plurality of battery pack data 528 and the second plurality of battery pack data 532 may include the total flight hours that the battery pack 524 and / or the electric aircraft have operated.The first and second plurality of data from the battery pack may include the total energy that flowed through the battery pack 524. The data storage system 520 may be communicatively coupled to sensors that detect, measure, and store energy in a plurality of measurements that may include current, voltage, resistance, etc. Petition 870250087341, dated 09 / 26 / 2025, page 64 / 277 59 / 88 impedance, coulombs, watts, temperature, or a combination thereof. Furthermore, or alternatively, the data storage system 520 can be communicatively coupled to a set of sensors consistent with this disclosure to measure physical and / or electrical characteristics. The data storage system 520 can be configured to store data from the first battery pack 528 and data from the second battery pack 532, with at least some of the data including the battery pack maintenance history. The battery maintenance history may include mechanical failures and technicians' resolutions of those failures, electrical failures and technicians' resolutions of those failures. Additionally, the battery pack maintenance history may include component failures such that the overall system still functions.The 520 data storage system can store data from the first and second battery packs, including an upper voltage limit and a lower voltage limit consistent with this disclosure. The data from the first battery pack 528 and the data from the second battery pack 532 can include a humidity level limit. The humidity level limit can include an absolute, relative, and / or specific humidity level limit. The 500 battery management system can be designed to the Federal Aviation Administration (FAA) Design Assurance Level A (DAL-A), using redundant DAL-B subsystems.

[079] Referring now to Figure 6, one embodiment of the sensor array 600 is presented. The system and method disclosed herein may comprise a plurality of sensors in the form of individual sensors or an array of sensors that operate together or individually. A sensor array may include a plurality of independent sensors, as described herein, wherein any number of the sensors described may be used to detect any number of physical or electrical quantities associated with an aircraft power system or an electrical energy storage system. Sensors Petition 870250087341, dated 09 / 26 / 2025, page 65 / 277 Independent 60 / 88 systems may include separate sensors that measure physical or electrical quantities that may be powered by and / or communicate with circuits independently, wherein each may signal the sensor output to a control circuit, such as a graphical user interface. In a non-limiting example, there may be four independent sensors housed in and / or on the battery pack, measuring temperature, electrical characteristics such as voltage, amperage, resistance or impedance, or any other parameters and / or quantities as described in this disclosure.In one embodiment, the use of a plurality of independent sensors may result in redundancy configured to employ more than one sensor measuring the same phenomenon, these sensors being of the same type, a combination of, or another undisclosed sensor type, so that in the event of failure of one sensor, the ability of the battery management system 500 and / or the user to detect the phenomenon is maintained and, in a non-limiting example, a user alters the use of the aircraft according to the sensor readings.

[080] Referring again to Figure 6, in some embodiments, the sensor set 600 may be suitable for use as the first sensor set 504 and / or the second sensor set 516. The sensor set 600 includes a humidity sensor 604. The term “humidification,” as used in this disclosure, refers to the presence of water, which may include water vapor in the air, condensation on the surfaces of objects, or concentrations of liquid water. Humidification may include moisture. The term “humidity,” as used in this disclosure, refers to the property of a gaseous medium (almost always air) to retain water in the form of vapor. The amount of water vapor contained in a parcel of air can vary significantly. Water vapor is generally invisible to the human eye and can damage electrical components. There are three primary measures of humidity: absolute, relative, and specific.Absolute humidity, for the purposes of this disclosure, describes the water content of the air and is expressed in grams per cubic meter or grams per kilogram. The humidity... Petition 870250087341, dated 09 / 26 / 2025, p. 66 / 277 61 / 88 relative humidity, for the purposes of this disclosure, is expressed as a percentage, indicating a current state of absolute humidity relative to a given maximum humidity at the same temperature. The term specific humidity, for the purposes of this disclosure, is the ratio of the mass of water vapor to the total mass of the humid air packet, the packet being a given portion of a gaseous medium. The 604 humidity sensor may be a psychrometer. The 604 humidity sensor may be a hygrometer. The 604 humidity sensor may be configured to act as or include a humidistat. A humidistat, for the purposes of this disclosure, is a humidity-activated switch, often used to control another electronic device. The 604 humidity sensor may use capacitance to measure relative humidity and include within itself, or as an external component, a device to convert relative humidity measurements into absolute humidity measurements.Capacitance, for the purposes of this disclosure, is the ability of a system to store an electrical charge; in this case, the system is a parcel of air that may be near, adjacent to, or above a battery cell.

[081] Referring again to Figure 6, in some embodiments, the sensor set 600 may include electrical sensors 608. Electrical sensors 608 may be configured to measure the voltage across a component, the electrical current through a component, and the resistance of a component. Electrical sensors 608 may include separate sensors to measure each of the electrical characteristics disclosed above, such as voltmeter, ammeter, and ohmmeter, respectively.

[082] Referring again to Figure 6, alternatively or additionally, the sensor set 600 includes a sensor or plurality thereof that can detect voltage and direct the charging of individual battery cells according to the charge level; the detection can be carried out using any component, set of components and / or mechanism suitable for direct or indirect measurement and / or detection of voltage levels, including, without limitation, comparators, analog-to-digital converters, any Petition 870250087341, dated 09 / 26 / 2025, p. 67 / 277 62 / 88 voltmeter form or similar. The 600 sensor set and / or a control circuit incorporated in it and / or communicatively connected to it can be configured to adjust the charge of one or more battery cells as a function of a detected charge level and / or parameter. For example, and without limitation, the 600 sensor set can be configured to determine that a battery cell charge level is high based on a detected voltage level of that battery cell or part of the battery pack.The 600 sensor array can detect, alternatively or additionally, a load reduction event, defined for the purposes of this disclosure as any temporary or permanent state of a battery cell that requires a reduction or cessation of charging; a load reduction event may include a fully charged cell and / or a cell undergoing a physical and / or electrical process that makes continuous charging at the current voltage and / or current inadvisable due to the risk of the cell being damaged, overheating, or something similar. Detection of a load reduction event may include detection of a cell temperature above a threshold level, detection of a voltage and / or resistance level above or below a threshold, or something similar. The 600 sensor array may include digital sensors, analog sensors, or a combination thereof.The 600 sensor array may include digital-to-analog converters (DACs), analog-to-digital converters (ADCs, AIDs, A-to-D), a combination of these, or other signal conditioning components used in transmitting a first plurality of data from the 128 battery pack to a destination via wireless or wired connection.

[083] Referring again to Figure 6, in some embodiments, the sensor array 600 may include a sensor configured to detect gas that may be emitted during or after a cell failure. Cell failure, for the purposes of this disclosure, refers to a failure of a battery cell, which may be an electrochemical cell, that renders the cell inoperable for its designed function, namely, to provide electrical power to at least part of an aircraft. Petition 870250087341, dated 09 / 26 / 2025, page 68 / 277 63 / 88 electrical. The byproducts of cell failure 612 may include gaseous discharge, which may include oxygen, hydrogen, carbon dioxide, methane, carbon monoxide, a combination thereof, or other undisclosed gas, alone or in combination. Furthermore, the sensor configured to detect electrochemical cell vent gas may include a gas detector. For the purposes of this disclosure, a gas detector is a device used to detect whether a gas is present in an area. Gas detectors, and more specifically the gas sensor that may be used in the sensor array 600, may be configured to detect combustible, flammable, toxic, oxygen-deficient gases, a combination thereof, or other types of gas alone or in combination.The gas sensor that may be present in the sensor suite 600 may include a combustible gas, photoionization detectors, electrochemical gas sensors, ultrasonic sensors, metal-oxide-semiconductor (MOS) sensors, infrared imaging sensors, a combination thereof, or other undisclosed type of gas sensor, alone or in combination. The sensor suite 600 may include sensors configured to detect non-gaseous byproducts of cell failure 612, including, but not limited to, liquid chemical leaks, including aqueous alkaline solution, ionomer, molten phosphoric acid, liquid electrolytes with redox and ionomer shuttle, and saltwater, among others. The sensor suite 600 may include sensors configured to detect non-gaseous byproducts of cell failure 612, including, but not limited to, electrical anomalies detected by any of the sensors or components disclosed above.

[084] Referring again to Figure 6, in some embodiments, the sensor array 600 can be configured to detect events where the voltage approaches an upper or lower voltage limit. The upper voltage limit can be stored in the data storage system 520 for comparison with an instantaneous measurement made by any combination of sensors present in the sensor array 600. The upper voltage limit Petition 870250087341, dated 09 / 26 / 2025, p. 69 / 277 The 64 / 88 can be calculated and calibrated based on factors related to battery cell integrity, maintenance history, location within the battery pack, intended application and type, among others. The 600 sensor array can measure voltage instantly, over a period of time, or periodically. The 600 sensor array can be configured to operate in any of these detection modes, switch between modes, or measure simultaneously in more than one mode. First, the 504 battery management component can detect, via the 600 sensor array, events where the voltage approaches the lower voltage limit. The lower voltage limit may indicate power loss to or from an individual battery cell or part of the battery pack. The first 504 battery management component can detect, via the 600 sensor array, events where the voltage exceeds both the upper and lower voltage limits.Events in which the voltage exceeds the upper and lower voltage limits may indicate battery cell failure or electrical anomalies that could lead to potentially dangerous situations for aircraft and personnel who may be present in or near the aircraft's operation.

[085] Referring now to Figure 7, a block diagram of a data collection system 700 is presented. The data collection system 700 includes the sensor set 600, which can be used for the first sensor set 508 in the first battery management component 504 or for the second sensor set 516 in the second battery management component 512 or consistent with any sensor set disclosed above. The data collection system 700 includes the data storage system 520. The sensor set 600 is configured to measure physical and / or electrical phenomena and characteristics of the battery pack 524, in whole or in part. The sensor set 600 transmits electrical signals to the data storage system 520 to be saved. These electrical signals are representative of the first battery data 528 and the second battery data 532. The electrical signals communicated by the sensor set 600 and, Petition 870250087341, dated 09 / 26 / 2025, p. 70 / 277 65 / 88 In addition, the first or second battery management component to which it belongs may be transformed or conditioned in accordance with any signal conditioning present in this disclosure. The data collection system 700, and more specifically the first battery management component 504, may be configured to save the data from the first battery pack 528 and the data from the second battery pack 532 periodically at regular intervals in the data storage system 520. Regular intervals, for the purposes of this disclosure, refers to an event that occurs repeatedly after a certain period of time has elapsed. The data collection system 700 may include the first battery management component 504, which may include the timer 704. The timer 704 may include a timing circuit, internal clock, or other circuit, component, or part configured to track elapsed time and / or time of day.For example, in non-limiting embodiments, the data storage system 520 can save the first and second battery data every 30 seconds, every minute, every 30 minutes, or another time period according to the timer 704. Furthermore, or alternatively, the data storage system 520 can save the data from the first and second battery packs after the occurrence of certain events, for example, in non-limiting embodiments, at each power cycle, electric aircraft landing, when the battery pack is charging or discharging, or during scheduled maintenance periods. In non-limiting embodiments, the phenomena of the battery pack 524 can be continuously measured and stored in an intermediate storage location and then permanently saved by the data storage system 520 at a later time, such as at a regular interval or after the occurrence of an event, as disclosed above.Additionally, or alternatively, the data storage system can be configured to save the first data from battery 528 and the second data from battery 532 at a predetermined time. Predetermined time, for the... Petition 870250087341, dated 09 / 26 / 2025, page 71 / 277 66 / 88, for the purposes of this disclosure, refers to an internal clock within the battery management system 500 that commands the data storage system 520 to save the data for the first and second battery packs at that time. For example, the data storage system 520 can be configured to save the first and second battery data at 0600 hours, 51 PM EDT, or another time, or several times a day.

[086] Referring now to Figure 8, an exemplary embodiment of an 800 aircraft is illustrated. The 800 aircraft may include an electrically powered aircraft (i.e., electric aircraft). In some embodiments, the electrically powered aircraft may be an electric vertical takeoff and landing (eVTOL) aircraft. In some embodiments, the 800 aircraft may include an 804 fuselage. The 804 fuselage may include structural elements that physically support the shape and structure of an aircraft. The structural elements may take a plurality of forms, either individually or in combination with other types. The structural elements may vary depending on the type of aircraft construction and, specifically, the fuselage. The 804 fuselage may include a truss structure. A truss structure may be used with a light aircraft and may include welded steel tube trusses.A truss, as used in this document, is an assembly of beams that create a rigid structure, often in combinations of triangles to create three-dimensional shapes. A truss structure may alternatively include titanium construction in place of steel tubes, or a combination thereof. In some embodiments, the structural elements may include aluminum tubes and / or titanium beams. In one embodiment, and without limitation, the structural elements may include an aircraft skin. The aircraft skin may be layered over the truss-constructed body shape. The aircraft skin may include a plurality of materials, such as aluminum, fiberglass, and / or carbon fiber, the latter of which will be discussed in more detail later in this document.

[087] Referring again to Figure 8, the 800 aircraft may include a plurality. Petition 870250087341, dated 09 / 26 / 2025, page 72 / 277 67 / 88 of actuators 808. The actuator 808 may include any motor and / or propeller described in this disclosure. In one embodiment, the actuator 808 may be mechanically coupled to an aircraft. As used herein, a person of ordinary skill in the art would understand that mechanically coupled means that at least a portion of a device, component, or circuit is connected to at least a portion of the aircraft through a mechanical coupling.Said mechanical coupling may include, for example, rigid couplings such as beam couplings, bellows couplings, pin and bushing couplings, constant velocity couplings, split sleeve couplings, diaphragm couplings, disc couplings, donut couplings, elastic couplings, flexible couplings, fluid couplings, gear couplings, grid couplings, Hirth joints, hydrodynamic couplings, claw couplings, magnetic couplings, Oldham couplings, sleeve couplings, tapered shaft locks, double spring couplings, cloth joint couplings, universal joints, or any combination thereof. As a non-limiting example, aircraft may include airplanes, helicopters, aerostats, airships, gliders, paramotors, and the like. In one embodiment, the mechanical coupling may be used to connect the ends of adjacent parts and / or objects of an electric aircraft.Furthermore, in one embodiment, mechanical coupling can be used to join two pieces of rotating components of electric aircraft.

[088] With continued reference to Figure 8, a plurality of 808 actuators may be configured to produce a torque. As used in this disclosure, a torque is a measure of force that causes an object to rotate about a geometric axis in a direction. For example, and without limitation, torque may rotate an aileron and / or rudder to generate a force that may adjust and / or affect altitude, airspeed, ground speed, direction during flight, and / or thrust. For example, the plurality of 808 actuators may include a component used to produce a torque that affects the Petition 870250087341, dated 09 / 26 / 2025, page 73 / 277 68 / 88 roll and pitch of aircraft, such as, without limitation, one or more ailerons. An aileron, as used in this disclosure, is a hinged surface that forms part of the trailing edge of a wing on a fixed-wing aircraft, and which may be moved by mechanical means, such as, without limitation, servomotors, mechanical linkages, or the like. As another example, the plurality of actuators 808 may include a rudder, which may include, without limitation, a segmented rudder that produces a torque about a vertical geometric axis. In addition, or alternatively, the plurality of actuators 808 may include other flight control surfaces, such as thrusters, rotary flight controls, or any other structural features that may adjust the movement of the aircraft 800.A plurality of 808 actuators may include one or more rotors, turbines, duct fans, paddle wheels and / or other components configured to propel a vehicle through a fluid medium, including, but not limited to, air.

[089] Referring again to Figure 8, a plurality of actuators 808 may include at least one propulsion component. As used in this disclosure, a propulsion component or propeller is a component and / or device used to propel a vessel by exerting force on a fluid medium, which may include a gaseous medium, such as air, or a liquid medium, such as water. In one embodiment, when a propeller rotates and pulls air behind it, it can simultaneously propel an aircraft forward with a quantity of force and / or thrust. More air pulled behind an aircraft results in greater thrust with which the aircraft is propelled forward. The propulsion component may include any device or component that consumes electrical power on demand to propel an aircraft in a direction or another vehicle while on the ground or in flight.As a non-limiting example, the extractor component may include a flight component, such as an extractor propeller, an extractor motor, an extractor thruster, and the like. Furthermore, or alternatively, the extractor component may include a plurality of extractor flight components. In another embodiment, the... Petition 870250087341, dated 09 / 26 / 2025, page 74 / 277 69 / 88 The propulsion component may include an impeller component. As a non-limiting example, the impeller component may include an impeller component such as an impeller propeller, an impeller motor, an impeller thruster, and the like. In addition, or alternatively, the impeller flight component may include a plurality of impeller flight components.

[090] Referring again to Figure 8, in another embodiment, the propeller may include a propeller, a blade, or any combination of the two. A propeller may function to convert the rotary motion of an engine or other power source into a vortex that can propel the propeller forward or backward. The propeller may include a power-driven rotating hub to which several radial airfoil-section blades may be attached, so that the whole assembly rotates about a longitudinal geometric axis. As a non-limiting example, the pitch of the propeller blades may be fixed at a fixed angle, manually variable to some defined positions, automatically variable (e.g., a constant speed type), and / or any combination thereof, as described further in this disclosure. As used in this disclosure, a fixed angle is an angle that is fixed and / or substantially immobile from the point of attachment.For example, and without limitation, a fixed angle may be an angle of 2.2° inward and / or 1.7° forward. As another non-limiting example, a fixed angle may be an angle of 3.6° outward and / or 2.7° backward. In one embodiment, the propellers of an aircraft are designed to be fixed to the hub at an angle similar to the thread of a screw that makes an angle with the shaft; this angle may be termed as a pitch or pitch angle which will determine a forward speed of movement as the blade rotates. Furthermore, or alternatively, the propeller component may be configured with a variable pitch angle. As used in this disclosure, a variable pitch angle is an angle that can be moved and / or rotated. For example, and without limitation, the propeller component may be pitched at a first angle of 3.3° inward, wherein the component... Petition 870250087341, dated 09 / 26 / 2025, page 75 / 277 The 70 / 88 propeller can be rotated and / or offset by a second angle of 1.7° outwards.

[091] Referring again to Figure 8, the propeller may include a thrust element that may be integrated into the propeller. The thrust element may include, without limitation, a device using movable or rotating blades, such as one or more rotors, a spiral or propeller, a set of spirals or propellers, such as counter-rotating propellers, a moving or flapping wing or the like. In addition, a thrust element may, for example, include, without limitation, a marine propeller or screw, an impeller, a turbine, a pump jet, a blade or paddle-based device or the like.

[092] Referring again to Figure 8, the plurality of actuators 808 may include power sources, control links for one or more elements, fuses and / or mechanical couplings used to actuate and / or control any other flight component. The plurality of actuators 808 may include a motor that operates to move one or more flight control components and / or one or more control surfaces, to actuate one or more thrusters or similar. A motor may be driven by direct current (DC) electrical power and may include, without limitation, brushless DC electric motors, switched reluctance motors, induction motors or any combination thereof. Alternatively or additionally, a motor may be driven by an inverter. A driving machine may also include electronic speed controllers, inverters or other components for regulating the speed of the driving machine, direction of rotation and / or dynamic braking.

[093] Referring again to Figure 8, the plurality of actuators 808 may include a power source. A power source may include, for example, a generator, a photovoltaic device, a fuel cell, such as a hydrogen fuel cell, a direct methanol fuel cell and / or a solid oxide fuel cell, an electrical energy storage device (e.g., a capacitor, an inductor and / or a battery). A power source may also include a battery cell or a Petition 870250087341, dated 09 / 26 / 2025, page 76 / 277 71 / 88 A plurality of battery cells connected in series in a module, and each module connected in series or in parallel with other modules. The configuration of a power supply containing connected modules may be designed to meet a power or wattage requirement and may be designed to fit within a designated footprint on an electric aircraft in which the system may be incorporated.

[094] Referring again to Figure 8, in another embodiment, a power supply may be used to provide a constant supply of electrical power to a load during a flight by an 800 electric aircraft. For example, the power supply may be able to provide sufficient power for cruise and other relatively low-power flight phases. A power supply may also be able to provide electrical power for some higher-power flight phases, particularly when the power supply is at a high SOC, as may be the case, for example, during takeoff. In one embodiment, the power supply may include an emergency power unit that may be able to provide sufficient electrical power for auxiliary loads, including, without limitation, lighting, navigation, communications, de-icing, steering, or other systems that require power or energy.Furthermore, the power supply may be capable of providing sufficient power for controlled descent and landing protocols, including, without limitation, hovering descent or runway landing. As used in this document, the power supply may have high power density, where the electrical power that a power supply can usefully produce per unit volume and / or mass is relatively high. As used in this disclosure, electrical power is a rate of electrical energy per unit time. A power supply may include a device for which the power that can be produced per unit volume and / or mass has been optimized, for example, at the expense of maximum specific total energy density or power capacity. Non-limiting examples of items that may be used as at least one power supply are listed. Petition 870250087341, dated 09 / 26 / 2025, page 77 / 277 72 / 88 power supplies include batteries used for starting applications, including lithium-ion batteries, which may include NCA, NMC, lithium iron phosphate (LiFePO4) and lithium manganese oxide (LMO) batteries, which may be mixed with other cathode chemistry to provide more specific power if the application requires it; lithium metal batteries, which have a lithium metal anode that provides high power on demand; lithium-ion batteries which have a silicon or titanite anode; the power supply may be used, in one embodiment, to provide electrical power to an electric aircraft or drone, such as an electric aircraft vehicle, during times requiring high power rates, including, without limitation, takeoff, landing, thermal de-icing and situations requiring higher power for stability reasons, such as high turbulence situations, as described in more detail below.A battery may include, without limitation, a battery using nickel-based chemistries such as nickel-cadmium or nickel-metal hydride, a battery using lithium-ion battery chemistries such as nickel-cobalt-aluminum (NCA), nickel-manganese-cobalt (NMC), lithium-ferrophosphate (LiFePO4), lithium-cobalt oxide (LCO) and / or lithium-manganese oxide (LMO), a battery using lithium polymer technology, lead-based batteries such as, without limitation, lead-acid batteries, metal-air batteries or any other suitable battery. Persons skilled in the art, upon reviewing the entirety of this disclosure, will be aware of various component devices that may be used as a power source.

[095] Referring again to Figure 8, a power supply may include a plurality of power sources, referred to in this document as a power source module. The module may include batteries connected in parallel or in series, or a plurality of modules connected in series or in parallel designed to meet power and energy requirements. Connecting batteries in series can increase the potential of at least one power source, which can provide more power on demand. High-potential batteries may require cell matching when charging is needed. Petition 870250087341, dated 09 / 26 / 2025, page 78 / 277 73 / 88 peak high. As more cells are connected in series, there may be a possibility of a cell failing, which can increase the resistance in the module and reduce the overall power, as the module voltage may decrease as a result of that failed cell. Connecting batteries in parallel can increase the total current capacity by decreasing the total resistance and can also increase the overall ampere-hour capacity. The overall energy and power output of at least one power supply can be based on the individual performance of the battery cell or on an extrapolation based on the measurement of at least one electrical parameter. In an embodiment where the power supply includes a plurality of battery cells, the overall power output capacity may depend on the electrical parameters of each individual cell.If a cell exhibits high self-discharge during demand, the energy drawn from at least one power source may be reduced to prevent damage to a weaker cell. The power source may include, without limitation, wiring, conduit, housing, cooling system, and battery management system. Those skilled in the art will be aware, after reviewing the entirety of this disclosure, of many different components of a power source. Exemplary power sources are disclosed in detail in Patent Applications No. 16 / 948,157 and No. 16 / 048,140, ​​both entitled SYSTEM AND METHOD FOR HIGH ENERGY DENSITY BATTERY MODULE by S. Donovan et al., which are incorporated herein in their entirety by reference.

[096] Referring again to Figure 8, according to some embodiments, a power supply may include an emergency power unit (EPU) (i.e., auxiliary power unit). As used in this disclosure, an emergency power unit is a power supply as described herein that is configured to power a system essential to a critical function in an emergency, for example, without limitation, when another power supply has failed, is depleted, or is unavailable. Non-limiting exemplary essential systems include systems Petition 870250087341, dated 09 / 26 / 2025, page 79 / 277 74 / 88 navigation equipment, such as MFD, GPS, VOR receiver or directional gyroscope, and other essential flight components, such as thrusters.

[097] Referring again to Figure 8, another exemplary actuator may include the landing gear. The landing gear may be used for takeoff and / or landing. The landing gear may be used to make contact with the ground while the aircraft 800 is not in flight. The exemplary landing gear is disclosed in detail in U.S. Patent Application No. 17 / 196,719 entitled SYSTEM FOR ROLLING LANDING GEAR by R. Griffin et al., which is incorporated herein in its entirety by reference.

[098] Still referring to Figure 8, the aircraft 800 may include a pilot control 812, which includes, without limitation, a hover control, a thrust control, an inceptor stick, a cyclic and / or a collective control. As used in this disclosure, a collective or collective control is a mechanical control of an aircraft that allows the pilot to adjust and / or control the pitch angle of the plurality of actuators 808. For example and without limitation, the collective control may alter and / or adjust the pitch angle of all the main rotor blades collectively. For example and without limitation, the pilot control 812 may include a pitch control. As used in this disclosure, a throttle control is a mechanical control of an aircraft for controlling pitch and / or roll. For example and without limitation, the stick control may alter and / or adjust the roll angle of the aircraft 800 as a function of the control and / or maneuver of the ailerons.In one embodiment, the 812 pilot control may include one or more foot brakes, control stick, pedals, throttle levels, and the like. In another embodiment, and without limitation, the 812 pilot control may be configured to control a principal geometric axis of the aircraft. As used in this disclosure, a principal geometric axis is a geometric axis on a body that represents a three-dimensional orientation. For example, and without limitation, a principal geometric axis or more yaw, pitch, and / or roll geometric axes. The principal geometric axis may include a yaw geometric axis. As used in this disclosure, a geometric axis. Petition 870250087341, dated 09 / 26 / 2025, page 80 / 277 The yaw axis (75 / 88) is a geometric axis directed toward the underside of the aircraft, perpendicular to the wings. For example, and without limitation, a positive yaw motion may include adjusting and / or shifting the nose of the aircraft 800 degrees to the right. The principal geometric axis may include a pitch geometric axis. As used in this disclosure, a pitch geometric axis is a geometric axis directed toward the right wing that extends laterally from the aircraft. For example, and without limitation, a positive pitch motion may include adjusting and / or shifting the nose of the aircraft 800 degrees upward. The principal geometric axis may include a roll geometric axis. As used in this disclosure, a roll geometric axis is a geometric axis directed longitudinally toward the nose of the aircraft, parallel to the fuselage.For example, and without limitation, a positive rolling motion may include raising the left wing and lowering the right wing simultaneously.

[099] Still referring to Figure 8, the pilot control 812 may be configured to modify a variable pitch angle. For example, and without limitation, the pilot control 812 may adjust one or more angles of attack of a propeller. As used in this disclosure, an angle of attack is an angle between the propeller chord and the relative wind. For example, and without limitation, the angle of attack may include a propeller blade pitched at 3.2°. In one embodiment, the pilot control 812 may modify the variable pitch angle from a first angle of 2.71° to a second angle of 3.52°. Furthermore, or alternatively, the pilot control 812 may be configured to translate a desired torque from the pilot to the flight component 808. For example, and without limitation, the pilot control 812 may translate that a desired torque from a pilot to a propeller is 160 lb. ft. of torque.As another non-limiting example, the 812 pilot control can introduce the pilot's desired torque so that a propeller has 290 lb. ft. of torque. Further disclosure relating to the 812 pilot control can be found in U.S. Patent Applications No. 17 / 001,545 and U.S. 16 / 929,206, both titled A HOVER AND THRUST CONTROL ASSEMBLY FOR DUAL-MODE AIRCRAFT by C. Petition 870250087341, dated 09 / 26 / 2025, page 81 / 277 76 / 88 Spiegel et al., which are incorporated into this document in their entirety by way of reference.

[100] Referring again to Figure 8, the 800 aircraft may include a loading system. A loading system may include a system configured to load an aircraft with cargo or personnel. For example, some exemplary loading systems may include a swing nose, which is configured to swing the nose of the 800 aircraft out of the way, thus allowing direct access to a cargo compartment located behind the nose. A notable exemplary swing nose aircraft is the Boeing 747. Further disclosure relating to loading systems may be found in U.S. Patent Application No. 17 / 87,594 entitled SYSTEM AND METHOD FOR LOADING AND SECURING PAYLOAD IN AN AIRCRAFT by R. Griffin et al., which is incorporated herein in its entirety by reference.

[101] Referring again to Figure 8, aircraft 800 may include a sensor 816. Sensor 816 may include any noise monitoring sensor or circuit described in this disclosure. 816 may be configured to detect a characteristic of pilot control 812. The sensor may be a device, module and / or subsystem, which uses any hardware, software and / or any combination thereof to detect a characteristic and / or changes thereof, in an instantaneous environment, for example, without limitation, a pilot control 812, to which the sensor is near or otherwise in a detected communication and transmit information associated with the characteristic, for example, without limitation, digitized data. Sensor 816 may be mechanically and / or communicatively coupled to aircraft 800, including, for example, at least one pilot control 812. Sensor 816 may be configured to detect a characteristic associated with at least one pilot control 812.An environmental sensor may include, without limitation, one or more sensors used to detect ambient temperature, barometric pressure and / or air velocity, and one or more motion sensors which may include, without limitation. Petition 870250087341, dated 09 / 26 / 2025, page 82 / 277 77 / 88 limitation, gyroscopes, accelerometers, inertial measurement unit (IMU) and / or magnetic sensors, one or more humidity sensors, one or more oxygen sensors or similar. In addition, or alternatively, sensor 816 may include at least one geospatial sensor. Sensor 816 may be located inside an aircraft; and / or be included and / or attached to at least a portion of the aircraft. The sensor may include one or more proximity sensors, displacement sensors, vibration sensors and the like. The sensor may be used to monitor the aircraft's status 800 for critical and non-critical functions. The sensor may be incorporated into the vehicle or aircraft or be remote.

[102] Referring again to Figure 8, in some embodiments, sensor 816 can be configured to detect a feature associated with any pilot control described in this disclosure. Non-limiting examples of a sensor 816 may include an inertial measurement unit (IMU), an accelerometer, a gyroscope, a proximity sensor, a pressure sensor, a light sensor, a pitot tube, an airspeed sensor, a position sensor, a speed sensor, a switch, a thermometer, a voltage meter, an acoustic sensor, and an electrical sensor. In some cases, sensor 816 may detect a feature as an analog measurement, for example, so as to render a continuously varying electrical potential indicative of the detected feature. In such cases, sensor 816 may additionally include an analog-to-digital converter (ADC), as well as any additional circuitry such as, without limitation, a Wheatstone bridge, an amplifier, a filter, and the like.For example, in some cases, the 816 sensor may include a strain indicator configured to determine the loading of one or more flight components, for example, landing gear. The strain indicator may be included in a circuit comprising a Whetstone bridge, an amplified filter, and a bandpass filter to provide an analog strain measurement signal with a high signal-to-noise ratio, which characterizes the strain in a landing gear member. An ADC can then digitize the analog signal and produce a digital signal that can... Petition 870250087341, dated 09 / 26 / 2025, page 83 / 277 78 / 88 be transmitted to other systems within the aircraft 800, for example, without limitation, a computing system, a pilot display and a memory component. Alternatively or additionally, the sensor 816 may detect a characteristic of a pilot control 812 digitally. For example, in some embodiments, the sensor 816 may detect a characteristic by means of digital means or digitize a natively detected signal. In some cases, for example, the sensor 816 may include a rotational encoder and be configured to detect a rotational position of a pilot control; in this case, the rotational encoder may digitally detect rotational clicks by any known method, such as, without limitation, magnetically, optically and the like.

[103] Referring again to Figure 8, the electric aircraft 800 may include at least one motor 824, which may be mounted on a structural feature of the aircraft. The design of the motor 824 may allow it to be installed externally to the structural member (such as a boom, nacelle, or fuselage) to facilitate maintenance access and minimize accessibility requirements for the structure; this may improve structural efficiency, requiring fewer large holes in the mounting area. In some embodiments, the motor 824 may include two main holes at the top and bottom of the mounting area to access the bearing cartridge. Furthermore, a structural feature may include an electric aircraft 800 component. For example, and without limitation, the structural feature may be any part of a vehicle incorporating the motor 824, which includes any vehicle as described in this disclosure.As another non-limiting example, a structural feature may include, without limitation, a wing, a spar, a stabilizer, a fuselage, or any part thereof; persons skilled in the art, upon reviewing the entirety of this disclosure, will be aware of many possible features that may function as at least one structural feature. At least one structural feature may be constructed of any suitable material or combination of materials, including, without limitation, metal. Petition 870250087341, dated 09 / 26 / 2025, page 84 / 277 79 / 88 such as aluminum, titanium, steel or similar materials, polymeric or composite materials, fiberglass, carbon fiber, wood or any other suitable material. As a non-limiting example, at least one structural feature may be constructed from additively manufactured polymeric material with a carbon fiber exterior; aluminum parts or other elements may be enclosed for structural strength or for support purposes, for example, vibration, torque or shear stresses imposed by at least the 808 propellant. Persons skilled in the art, upon reviewing the entirety of this disclosure, will be aware of various materials, combinations of materials and / or construction techniques.

[104] Referring again to Figure 8, several aerodynamic forces can act on the electric aircraft 800 during flight. The forces acting on the electric aircraft 800 during flight may include, without limitation, thrust, the forward force produced by the rotating element of the electric aircraft 800 and acting parallel to the longitudinal geometric axis. Another force acting on the electric aircraft 800 may be, without limitation, drag, which can be defined as a retarding force caused by the interruption of airflow by any protruding surface of the electric aircraft 800, such as, without limitation, the wing, rotor and fuselage. Drag may oppose thrust and acts rearward parallel to the relative wind. An additional force acting on the electric aircraft 800 may include, without limitation, weight, which may include a combined load of the electric aircraft 800 itself, crew, baggage and / or fuel.Weight can pull electric aircraft 800 downwards due to the force of gravity. An additional force acting on electric aircraft 800 may include, without limitation, lift, which may act to oppose the downward force of weight and may be produced by the dynamic effect of air acting on the airfoil and / or downward thrust of the electric aircraft's propeller 808. The lift generated by the airfoil may depend on the airflow velocity, air density, total area of ​​an airfoil and / or segment thereof, and / or angle of attack between the air and the airfoil. For example, and without limitation, the... Petition 870250087341, dated 09 / 26 / 2025, page 85 / 277 80 / 88 electric 800 aircraft are designed to be as light as possible. Reducing aircraft weight and designing to reduce the number of components is essential to optimizing weight. To save energy, it can be useful to reduce the weight of 800 electric aircraft components, which includes, but is not limited to, propellers and / or propulsion assemblies. In one embodiment, the 824 motor can eliminate the need for many external structural features that might otherwise be required to join one component to another. The 824 motor can also increase energy efficiency by allowing a lower physical propulsion profile, which reduces drag and / or wind resistance. This can also increase durability by decreasing the extent to which drag and / or wind resistance increases the forces acting on 800 electric aircraft and / or propellers.

[105] Referring now to Figure 9, a flow diagram of a method 900 for a battery power management system for an electric aircraft. The method 900 includes a step 905 of receiving, using a controller, sensor data from at least one sensor communicatively connected to at least one battery configured to supply power to at least one flight component of an electric aircraft. The method 900 includes a step 910 of identifying, using the controller, a battery state based on sensor data and a battery threshold. In some embodiments, the battery state identification step 910 may further include subtracting the temperature sensor data from at least one battery from the temperature threshold. In some embodiments, the battery state identification step 910 may further include subtracting the temperature sensor data from at least one battery from the temperature threshold.Method 900 includes a step 915 of controlling, using the controller, the power of at least one battery to at least one flight component of the electric aircraft as a function of the battery state. In some embodiments, step 915 of controlling the power of at least one battery to at least one flight component may also include reduction. Petition 870250087341, dated 09 / 26 / 2025, page 86 / 277 81 / 88 using the controller, of the revolutions per minute (RPM) of the propeller. In some modes, step 915 of controlling the power from at least one battery to at least one flight component may also include reducing, using the controller, the current from at least one battery.

[106] With continued reference to Figure 9, in some embodiments, at least one sensor may include a temperature sensor, and method 900 may further include detecting, using at least one sensor, sensor data, wherein the sensor data comprises a temperature of at least one battery and transmitting, using at least one sensor, the temperature of at least one battery to the controller. In some embodiments, the battery limit may include a temperature limit of at least one battery. In some embodiments, at least one flight component may include at least one propeller.

[107] With continued reference to Figure 9, in some embodiments, the battery state may include a state 0, where the sensor data may be within the battery limit, and a state 1, where the sensor data may be outside the battery limit. In some embodiments, method 900 may further include identifying, using the controller, a state weight and controlling, using the controller, the power of at least one battery as a function of the state weight. In some embodiments, the flight controller may be communicatively connected to a display device and method 900 may further include displaying, using the controller, a battery alert to a user on the display device, receiving, using the controller, user input in response to the battery alert, and controlling, using the controller, the power of at least one battery as a function of user input.They can be implemented as revealed with reference to Figures 1-8.

[108] It should be noted that any one or more of the aspects and modalities described in this document may be conveniently implemented using one or more machines (for example, one or more devices of Petition 870250087341, dated 09 / 26 / 2025, p. 87 / 277 82 / 88 computing devices that are used as a user computing device for an electronic document, one or more server devices, such as a document server, etc.) programmed in accordance with the teachings of this specification, as will be apparent to those of common skill in computing techniques. Appropriate software coding can be readily prepared by skilled programmers based on the teachings of this disclosure, as will be apparent to those of common skill in software techniques. The aspects and implementations discussed above that employ software and / or software modules may also include appropriate hardware to assist in implementing the executable machine instructions of the software and / or software module.

[109] This software may be a computer program product that employs a machine-readable storage medium. A machine-readable storage medium may be any medium capable of storing and / or encoding a sequence of instructions for execution by a machine (e.g., a computing device) and that causes the machine to execute any of the methodologies and / or modalities described in this document. Examples of a machine-readable storage medium include, but are not limited to, a magnetic disk, an optical disk (e.g., CD, CD-R, DVD, DVD-R, etc.), a magneto-optical disk, a read-only memory device (ROM), a random-access memory device (RAM), a magnetic card, an optical card, a solid-state memory device, an EPROM, an EEPROM, and any combinations thereof.A machine-readable medium, as used in this document, is intended to include a single medium as well as a collection of physically separate media, such as, for example, a collection of compact discs or one or more hard disk drives in combination with computer memory. As used in this document, a machine-readable storage medium does not include transient forms of signal transmission. Petition 870250087341, dated 09 / 26 / 2025, page 88 / 277 83 / 88

[110] This software may also include information (e.g., data) carried as a data signal on a data carrier, such as a carrier wave. For example, machine-executable information may be included as a data carrier signal embedded in a data carrier in which the signal encodes a sequence of instructions, or part thereof, for execution by a machine (e.g., a computing device) and any related information (e.g., data structures and data) that causes the machine to execute any of the methodologies and / or modalities described in this document.

[111] Examples of a computing device include, but are not limited to, an electronic book reader, a computer workstation, a terminal computer, a server computer, a portable device (e.g., a tablet-type switch, a smartphone, etc.), a web device, a network router, a network switch, a network bridge, any machine capable of executing a sequence of instructions specifying an action to be performed by that machine, and any combinations thereof. In one example, a computing device may include and / or be included in a kiosk.

[112] Figure 10 shows a diagrammatic representation of an embodiment of a computing device in the exemplary form of a computer system 1000 within which a set of instructions for causing a control system to execute any or more of the aspects and / or methodologies of the present disclosure can be executed. It is also contemplated that several computing devices can be used to implement a specially configured set of instructions for causing one or more of the devices to execute any or more of the aspects and / or methodologies of the present disclosure. The computer system 1000 includes a processor 1004 and a memory 1008 that communicate with each other and with other components by means of a bus 1012. The bus 1012 can include any of several types of bus structures, Petition 870250087341, dated 09 / 26 / 2025, page 89 / 277 84 / 88, which includes, but is not limited to, a memory bus, a memory controller, a peripheral bus, a local bus, and any combination thereof, using any of the various bus architectures.

[113] The 1004 processor may include any suitable processor, such as, without limitation, a processor incorporating logic circuits to perform arithmetic and logical operations, such as an arithmetic and logic unit (ALU), which may be regulated with a state machine and driven by operational memory inputs and / or sensors; the 1004 processor may be organized according to the Von Neumann and / or Harvard architecture as a non-limiting example. The 1004 processor may include, incorporate and / or be incorporated, without limitation, into a microcontroller, microprocessor, digital signal processor (DSP), FPGA (Field Programmable Gate Array), CPLD (Complex Programmable Logic Device), GPU (Graphics Processing Unit), general-purpose GPU, TPU (Tensor Processing Unit), analog or mixed signal processor, TPM (Trusted Platform Module), FPU (Floating Point Unit) and / or SoC (system on a chip).

[114] Memory 1008 may include various components (e.g., machine-readable media), including, but not limited to, a random-access memory component, a read-only component, and any combination thereof. In one example, a basic input / output system 1016 (BIOS), including basic routines that help transfer information between elements within the computer system 1000, such as during initialization, may be stored in memory 1008. Memory 1008 may also include (e.g., stored on one or more machine-readable media) instructions (e.g., software) 1020 that incorporate any one or more of the aspects and / or methodologies of the present disclosure. In another example, memory 1008 may include any number of program modules, including, but not limited to, a system Petition 870250087341, dated 09 / 26 / 2025, page 90 / 277 85 / 88 operational, one or more application programs, other program modules, program data and any combination thereof.

[115] The 1000 computer system may also include a 1024 storage device. Examples of a storage device (e.g., 1024 storage device) include, but are not limited to, a hard disk drive, a magnetic disk drive, an optical disk drive in combination with an optical medium, a solid-state memory device, and any combinations thereof. The 1024 storage device may be connected to the 1012 bus by an appropriate interface (not shown). Examples of interfaces include, but are not limited to, SCSI, Advanced Technology Connection (ATA), Serial ATA, Universal Serial Bus (USB), IEEE 1394 (FIREWIRE), and any combinations thereof. In one example, the 1024 storage device (or one or more components thereof) may be removablely connected to the 1000 computer system (e.g., by means of an external port connector (not shown)).Specifically, storage device 1024 and associated machine-readable media 1028 can provide non-volatile and / or volatile storage of machine-readable instructions, data structures, program modules, and / or other data for computer system 1000. In one example, software 1020 may reside, wholly or partially, on machine-readable media 1028. In another example, software 1020 may reside, wholly or partially, on processor 1004.

[116] Computer system 1000 may also include an input device 1032. In one example, a user of computer system 1000 may enter commands and / or other information into computer system 1000 by means of input device 1032. Examples of an input device 1032 include, but are not limited to, an alphanumeric input device (e.g., a keyboard), a pointing device, a steering lever, a game controller, an audio input device (e.g., a microphone, a voice response system, etc.), a control device for Petition 870250087341, dated 09 / 26 / 2025, page 91 / 277 86 / 88 cursor (e.g., a mouse), a touch-sensitive device, an optical scanner, a video capture device (e.g., a still camera, a video camera), a touch screen, and any combination thereof. The 1032 input device can be connected to the 1012 bus via any of several interfaces (not shown), including, but not limited to, a serial interface, a parallel interface, a game port, a USB interface, a FIREWIRE interface, a direct interface to the 1012 bus, and any combination thereof. The 1032 input device may include a touch screen interface that may be part of or separate from the 1036 screen, discussed later. The 1032 input device can be used as a user selection device to select one or more graphical representations in a graphical interface, as described above.

[117] A user may also enter commands and / or other information into the computer system 1000 by means of the storage device 1024 (e.g., a removable disk drive, a flash drive, etc.) and / or network interface device 1040. A network interface device, such as network interface device 1040, may be used to connect the computer system 1000 to one or more of a variety of networks, such as network 1044, and one or more remote devices 1048 connected to it. Examples of a network interface device include, but are not limited to, a network interface card (e.g., a mobile network interface card, a LAN card), a modem, and any combination thereof.Examples of a network include, but are not limited to, a wide area network (e.g., the Internet, a corporate network), a local area network (e.g., a network associated with an office, building, campus, or other relatively small geographic area), a telephone network, a data network associated with a telephone / voice provider (e.g., a data and / or voice network of a mobile communications provider), a direct connection between two computing devices, and any combination thereof. Petition 870250087341, dated 09 / 26 / 2025, page 92 / 277 87 / 88 A network, such as the 1044 network, can employ a wired and / or wireless communication mode. In general, any network topology can be used. Information (e.g., data, 1020 software, etc.) can be communicated to and / or from a 1000 computer system via a 1040 network interface device.

[118] The computer system 1000 may further include a video adapter 1052 for communicating a displayable image to a display device, such as the display device 1036. Examples of a display device include, but are not limited to, a liquid crystal display (LCD), a cathode ray tube (CRT), a plasma display, a light-emitting diode (LED) display, and any combination thereof. The video adapter 1052 and the display device 1036 may be used in combination with the processor 1004 to provide graphical representations of aspects of the present disclosure. In addition to a display device, the computer system 1000 may include one or more other peripheral output devices, including, but not limited to, an audio speaker, a printer, and any combination thereof. These peripheral output devices may be connected to the bus 1012 via a peripheral interface 1056.Examples of a peripheral interface include, but are not limited to, a serial port, a USB connection, a FireWire connection, a parallel connection, and any combination thereof.

[119] The foregoing was a detailed description of illustrative embodiments of the invention. Various modifications and additions may be made without departing from the spirit and scope of this invention. The features of each of the various embodiments described above may be combined with features of other embodiments described, as appropriate, in order to provide a multiplicity of combinations of features in new associated embodiments. Furthermore, although the foregoing describes a number of separate embodiments, what has been described in the present document is merely illustrative of the application of the principles of the present invention. In addition, although Petition 870250087341, dated 09 / 26 / 2025, page 93 / 277 88 / 88 specific methods in the present document may be illustrated and / or described as being performed in a specific order; the ordering is highly variable within the common ability to obtain methods and systems according to the present disclosure. Consequently, this description should be taken only as an example, and not to limit the scope of this invention.

[120] Exemplary embodiments have been disclosed above and illustrated in the accompanying drawings. It will be understood by those skilled in the art that various alterations, omissions and additions may be made to what is specifically disclosed in the present document without departing from the spirit and scope of the present invention. Petition 870250087341, dated 09 / 26 / 2025, p. 94 / 277

Claims

1 / 3 CLAIMS 1. A SYSTEM characterized by comprising: a flight component of an electric aircraft; a battery configured to power the flight component of the electric aircraft; a sensor communicatively connected to the battery; and one or more controllers communicatively connected to the sensor, wherein one or more controllers are configured to: receive sensor data from the sensor; identify the battery status based on sensor data and a battery limit; and control the power consumed by the flight component of the electric aircraft from the battery based on the battery status.

2. SYSTEM, according to claim 1, characterized in that one or more controllers are additionally configured to display, on a pilot display, a battery alert based, at least in part, on the battery status.

3. SYSTEM, according to claim 1 or 2, characterized in that one or more controllers are additionally configured to display, on a pilot display, the battery limit.

4. SYSTEM, according to any one of claims 1-3, characterized in that one or more controllers comprise: a flight control component configured to control the energy consumed by the aircraft's electric flight component from the battery; and a battery management component configured to identify the battery status as a function of sensor data and battery limit.

5. SYSTEM, according to claim 4, characterized by the flight control component limiting one or more flight component control parameters according to the battery limit.

6. SYSTEM, according to claim 5, characterized in that one or more flight component control parameters comprise at least one of revolutions per minute (RPM), torque, or power; and wherein the flight control component determines a flight component control parameter for each of a plurality of flight components to maintain an aggregate power demand by the plurality of flight components that is below the battery limit.

7. SYSTEM, according to any one of claims 1-6, characterized in that one or more controllers are configured to control the energy consumed by the flight component of the battery-electric aircraft by reducing a flight control parameter.

8. SYSTEM, according to any one of claims 1-7, characterized in that one or more controllers are configured to control the power consumed by the flight component of the battery-electric aircraft by reducing torque, revolutions per minute (RPM), or the power of the flight component.

9. A SYSTEM characterized by comprising: a flight component of an electric aircraft; a battery configured to power the flight component of the electric aircraft; a sensor communicatively connected to the battery; and at least one controller communicatively connected to the sensor, wherein at least one controller is configured to: receive sensor data from the sensor; identify the battery state based on the sensor data; and control the amount of energy consumed by the flight component of the electric aircraft from the battery based on the battery state by reducing the torque of the flight component.

10. SYSTEM, according to claim 9, characterized in that the sensor comprises a temperature sensor configured to: detect sensor data, wherein the sensor data comprises a battery temperature; and transmit the battery temperature to at least one controller.

11. SYSTEM, according to claim 9 or 10, characterized in that the battery state comprises a battery temperature.

12. SYSTEM, according to claim 11, characterized by identifying the battery state comprising subtracting the battery temperature from a temperature limit.

13. SYSTEM, according to any one of claims 9-12, characterized in that the flight component comprises a propeller.

14. SYSTEM, according to claim 13, characterized by controlling the amount of power consumed by the flight component of the battery-electric aircraft, further comprising a reduction of one revolution per minute (RPM) of the propeller.

15. SYSTEM, according to any one of claims 9-14, characterized by controlling the amount of energy consumed by the flight component of the electric aircraft from the battery, comprising reducing a current from the battery. Petition 870250087341, dated 09 / 26 / 2025, pp. 97 / 277

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